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Penn State University
1.
Conti, Angelina Maria.
Incorporating Handling Qualities Assessment into the Design of Compound Rotorcraft.
Degree: 2018, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/15143aic5390
► The next fleet of rotorcraft will need to achieve higher forward flight speeds to meet the demanding requirements of military operation. One potential solution is…
(more)
▼ The next fleet of rotorcraft will need to achieve higher forward flight speeds to meet the demanding requirements of military operation. One potential solution is to offload the main rotor by compounding with a lifting wing and auxiliary propulsion system. Compound rotorcraft also feature additional control effectors (flaperons, elevators, propeller thrust, etc.), which can be used to augment control response of the aircraft. To leverage the benefits of fly-by-wire flight controls and meet flight
handling qualities requirements, it is essential that controller design be incorporated early in the development process.
Modern
handling qualities design standards, such as ADS-33E-PRF, provide specifications that can be implemented in early design phases. Predictive strategies relate signal response characteristics to desired flight
handling qualities specifications, and piloted simulation verifies the results for various maneuvers called Mission Task Elements. This thesis incorporates predictive and experimental
handling qualities analysis into the design of a future high-speed compound rotorcraft and its fly-by-wire flight control system. The simulated rotorcraft features a compounded wing and pusher propeller to offload the main rotor, various drag clean-ups and larger installed power to reach high forward flight speeds, and a full-authority dynamic inversion controller to optimize
handling qualities.
This study focuses on the combined effect of controller and design parameter variations on
handling qualities. Initial results revealed that the controller command filter parameter impacts the bandwidth of the aircraft, where increasing this parameter generally improved
handling qualities for all cyclic pitch deflections. The addition of redundant controls improved
handling qualities by relieving control saturation, and trends from variation of flapping hinge offset and wing/tail size were generally unclear. Future research studies should apply alternative predictive and piloted simulation methods in order to identify and verify trends.
Advisors/Committee Members: Dr. Joseph F. Horn, Thesis Advisor/Co-Advisor.
Subjects/Keywords: Flight Controls; Helicopters; Rotorcraft; ADS-33; Flight Handling Qualities
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APA (6th Edition):
Conti, A. M. (2018). Incorporating Handling Qualities Assessment into the Design of Compound Rotorcraft. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/15143aic5390
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Conti, Angelina Maria. “Incorporating Handling Qualities Assessment into the Design of Compound Rotorcraft.” 2018. Thesis, Penn State University. Accessed January 24, 2021.
https://submit-etda.libraries.psu.edu/catalog/15143aic5390.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Conti, Angelina Maria. “Incorporating Handling Qualities Assessment into the Design of Compound Rotorcraft.” 2018. Web. 24 Jan 2021.
Vancouver:
Conti AM. Incorporating Handling Qualities Assessment into the Design of Compound Rotorcraft. [Internet] [Thesis]. Penn State University; 2018. [cited 2021 Jan 24].
Available from: https://submit-etda.libraries.psu.edu/catalog/15143aic5390.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Conti AM. Incorporating Handling Qualities Assessment into the Design of Compound Rotorcraft. [Thesis]. Penn State University; 2018. Available from: https://submit-etda.libraries.psu.edu/catalog/15143aic5390
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Penn State University
2.
Berger, Tom.
Handling Qualities Requirements and Control Design for High-Speed Rotorcraft.
Degree: 2019, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/17211tub246
► The U.S. Department of Defense has established the Future Vertical Lift initiative to develop a family of next-generation vertical lift aircraft that will fly farther,…
(more)
▼ The U.S. Department of Defense has established the Future Vertical Lift initiative to develop a family of next-generation vertical lift aircraft that will fly farther, faster, and more efficiently than the current fleet of rotorcraft. To accomplish these goals, advanced rotorcraft configurations beyond the single main rotor/tail rotor design must be considered. Two advanced configurations currently being flight tested in a technology demonstrator program are a lift offset coaxial rotorcraft with a pusher propeller and a tiltrotor. The U.S. Army Aviation Development Directorate has developed generic, high-fidelity flight-dynamics models of these two configurations to provide the government with independent control-system design,
handling-
qualities analysis, and simulation research capabilities for these types of aircraft in support of the Future Vertical Lift initiative.
In an effort to begin defining high-speed
handling qualities requirements for these types of advanced rotorcraft configurations, full flight envelope inner-loop explicit model following control systems were designed for both configurations using a multi-objective optimization approach to meet a comprehensive set of stability,
handling qualities, and performance requirements. The requirements were chosen from both helicopter and fixed-wing criteria. The control laws for both aircraft were evaluated in a piloted simulation experiment at the NASA Ames Vertical Motion Simulator using a series of high-speed
handling qualities demonstration maneuvers. The results from the simulation experiment show overall assigned Level 1
handling qualities for both aircraft which correlates well with the predicted Level 1
handling qualities they were designed to, thus supporting the choice of
handling qualities requirements selected during the design process.
In addition, outer-loop control laws were also developed for both aircraft in an effort to improve
handling qualities and reduce pilot workload. A dynamic inversion control law architecture was used for the outer loops, and again a comprehensive set of stability,
handling qualities, and performance requirements was used to optimize the parameters of the control laws. The outer-loop control laws for both aircraft were evaluated in a piloted simulation experiment at the Pennsylvania State University Flight Simulator facility using a subset of the high-speed
handling qualities demonstration maneuvers used in the first evaluation. Overall, the outer-loop control laws provided Level 1
handling qualities for the Break Turn and High-Speed Acceleration/Deceleration maneuvers, with improvements seen over the inner-loop control laws. In addition, the outer-loop control laws improved performance and reduced workload during a formation flying task that was developed for this project. However, for pitch attitude capture and tracking tasks, the outer-loop control laws degraded
handling qualities as compared to the inner-loop control laws. This was due to the pitch attitude dropback behavior of the outer-loops, even though they…
Advisors/Committee Members: Joseph Francis Horn, Dissertation Advisor/Co-Advisor, Joseph Francis Horn, Committee Chair/Co-Chair, Eric Norman Johnson, Committee Member, Edward Smith, Committee Member, Christopher D. Rahn, Outside Member, Mark B. Tischler, Special Member, Amy Ruth Pritchett, Program Head/Chair.
Subjects/Keywords: Rotorcraft; Handling Qualities; Flight Control System; Control Laws; Tiltrotor; Compound Helicopter
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
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APA (6th Edition):
Berger, T. (2019). Handling Qualities Requirements and Control Design for High-Speed Rotorcraft. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/17211tub246
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Berger, Tom. “Handling Qualities Requirements and Control Design for High-Speed Rotorcraft.” 2019. Thesis, Penn State University. Accessed January 24, 2021.
https://submit-etda.libraries.psu.edu/catalog/17211tub246.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Berger, Tom. “Handling Qualities Requirements and Control Design for High-Speed Rotorcraft.” 2019. Web. 24 Jan 2021.
Vancouver:
Berger T. Handling Qualities Requirements and Control Design for High-Speed Rotorcraft. [Internet] [Thesis]. Penn State University; 2019. [cited 2021 Jan 24].
Available from: https://submit-etda.libraries.psu.edu/catalog/17211tub246.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Berger T. Handling Qualities Requirements and Control Design for High-Speed Rotorcraft. [Thesis]. Penn State University; 2019. Available from: https://submit-etda.libraries.psu.edu/catalog/17211tub246
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Penn State University
3.
ONeill, Eric Paul.
MODELING AND CONTROL OF TRAILING EDGE FLAPS FOR GUST ALLEVIATION AND HANDLING QUALITIES
.
Degree: 2011, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/12646
► Operating a helicopter in a turbulent wind environment is a difficult challenge for a pilot. Tasks that would be simple in a calm environment become…
(more)
▼ Operating a helicopter in a turbulent wind environment is a difficult challenge for a pilot. Tasks that would be simple in a calm environment become a unique challenge when wind gusts begin changing the behavior of the rotorcraft. The requirements of constantly correcting the attitude of the aircraft can increase the pilot workload to unacceptable levels. Recently research has been focused on using automated control designs to compensate for wind disturbances, relieving some of the workload from the pilot. Control designs using swashplate actuation have run into trade-off issues between stability margin constraints and disturbance rejection considerations. The topic of this thesis is the modeling and design of an alternative control mechanism, on-blade control devices called trailing edge flaps, to improve
handling qualities and disturbance rejection capabilities over those of the swashplate.
A primary objective of this thesis is to establish an accurate model of the aerodynamic effects and dynamics of trailing edge flaps. A study of the dynamics of the rotor shows that a flap on the UH-60 would behave as a moment flap, working to twist the blade to change the distributed lift as opposed to creating only a local lift increment. The Genhel-PSU model is modified with a torsion degree of freedom to accurately model the effects of a flap on a UH-60 helicopter.
To verify the accuracy of this implementation, the Genhel-PSU model is configured for the SH-2G Helicopter, since significant flight data and identified model is available for this aircraft. The identified model from previous research is compared with a linear model produced by the converted Genhel-PSU model. Significant differences are noticed in roll-flap and pitch-flap modes causing changes in the frequency responses. Model structure analysis reveals that the rotor time constant is significantly different from the value in the identified model. The identified value was substituted into the linear model, which corrected the discrepancies. Flap damping was added to the non-linear model, and the resulting linear model had a much closer frequency response match, as well the rotor time constant value matched the identified model much more closely. The rotor Lock number was varied in an attempt increase the predicted flap damping. A significant decrease in flapping inertia (~40%) created a model with a rotor time constant that matched the identified model, however the response for the modified model did not match the identified model. The cause of this discrepancy could not be identified.
Actuation methods are an important consideration when using on-blade trailing edge flaps. Piezo-electric tube actuators are experimental designs that are both extremely fast, compact, and can be made to achieve the desired deflection. These actuators are still experimental and are just being used as a theoretical design. A model of a Piezo-electric actuator implementation for trailing edge flaps is developed. This model is then simplified and converted to work…
Advisors/Committee Members: Joseph Francis Horn, Thesis Advisor/Co-Advisor, Joseph Francis Horn, Thesis Advisor/Co-Advisor.
Subjects/Keywords: SH-2G; UH-60; Trailing Edge Flaps; Handling Qualities
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
ONeill, E. P. (2011). MODELING AND CONTROL OF TRAILING EDGE FLAPS FOR GUST ALLEVIATION AND HANDLING QUALITIES
. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/12646
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
ONeill, Eric Paul. “MODELING AND CONTROL OF TRAILING EDGE FLAPS FOR GUST ALLEVIATION AND HANDLING QUALITIES
.” 2011. Thesis, Penn State University. Accessed January 24, 2021.
https://submit-etda.libraries.psu.edu/catalog/12646.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
ONeill, Eric Paul. “MODELING AND CONTROL OF TRAILING EDGE FLAPS FOR GUST ALLEVIATION AND HANDLING QUALITIES
.” 2011. Web. 24 Jan 2021.
Vancouver:
ONeill EP. MODELING AND CONTROL OF TRAILING EDGE FLAPS FOR GUST ALLEVIATION AND HANDLING QUALITIES
. [Internet] [Thesis]. Penn State University; 2011. [cited 2021 Jan 24].
Available from: https://submit-etda.libraries.psu.edu/catalog/12646.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
ONeill EP. MODELING AND CONTROL OF TRAILING EDGE FLAPS FOR GUST ALLEVIATION AND HANDLING QUALITIES
. [Thesis]. Penn State University; 2011. Available from: https://submit-etda.libraries.psu.edu/catalog/12646
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Toronto
4.
Peterson, Timothy Shaw.
Handling Qualities of a Blended Wing Body Aircraft.
Degree: 2011, University of Toronto
URL: http://hdl.handle.net/1807/31384
► The blended wing body (BWB) is a tailless aircraft with the potential to use 27% less fuel than a conventional aircraft with the same passenger…
(more)
▼ The blended wing body (BWB) is a tailless aircraft with the potential to use 27% less fuel than a conventional aircraft with the same passenger capacity and range. The primary purpose of the current study was to determine the handling qualities of the BWB, using piloted-handling trials in a moving-base simulator. The secondary purpose was to determine the effect of simulator motion on handling-quality ratings. De Castro conducted piloted-handling trials in a fixed-base simulator. De Castro's tasks and flight model were modified in the current study. In the current study, three subjects rated the handling qualities as Level 1 or 2, depending on the task. Simulator motion did not have a significant effect on the results.
MAST
Advisors/Committee Members: Grant, Peter R., Aerospace Science and Engineering.
Subjects/Keywords: flight simulation; handling qualities; blended wing body; 0538
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
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APA (6th Edition):
Peterson, T. S. (2011). Handling Qualities of a Blended Wing Body Aircraft. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/31384
Chicago Manual of Style (16th Edition):
Peterson, Timothy Shaw. “Handling Qualities of a Blended Wing Body Aircraft.” 2011. Masters Thesis, University of Toronto. Accessed January 24, 2021.
http://hdl.handle.net/1807/31384.
MLA Handbook (7th Edition):
Peterson, Timothy Shaw. “Handling Qualities of a Blended Wing Body Aircraft.” 2011. Web. 24 Jan 2021.
Vancouver:
Peterson TS. Handling Qualities of a Blended Wing Body Aircraft. [Internet] [Masters thesis]. University of Toronto; 2011. [cited 2021 Jan 24].
Available from: http://hdl.handle.net/1807/31384.
Council of Science Editors:
Peterson TS. Handling Qualities of a Blended Wing Body Aircraft. [Masters Thesis]. University of Toronto; 2011. Available from: http://hdl.handle.net/1807/31384

Delft University of Technology
5.
Damveld, H.J.
A Cybernetic Approach to Assess the Longitudinal Handling Qualities of Aeroelastic Aircraft.
Degree: 2009, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:3869d074-4e3c-4738-b445-15dbdfd51cab
;
urn:NBN:nl:ui:24-uuid:3869d074-4e3c-4738-b445-15dbdfd51cab
;
urn:NBN:nl:ui:24-uuid:3869d074-4e3c-4738-b445-15dbdfd51cab
;
http://resolver.tudelft.nl/uuid:3869d074-4e3c-4738-b445-15dbdfd51cab
► The future demand for larger and lighter civil transport aircraft leads to more flexible aircraft, which bring their own controlling and handling problems. A review…
(more)
▼ The future demand for larger and lighter civil transport aircraft leads to more flexible aircraft, which bring their own controlling and
handling problems. A review of established
handling qualities methods showed that they were either unsuitable for aeroelastic aircraft, or had significant disadvantages. After consideration of the basic principles behind a number of
handling qualities methods, a new
handling qualities method was developed, the Experimental Behavior Measurement Method (EBMM). This new method is based on the principle that a satisfactory match between the aircraft characteristics and the human operator's behavioral characteristics is required to acquire proper vehicle
handling qualities. The EBMM requires pilots to perform a number of pitch tracking tasks with a pursuit display, in the aircraft or a moving-base simulator. During these tasks the tracking signal bandwidth is increased, while the pilot's control behavior is determined using system identification techniques. A sudden decrease of the crossover frequency in the pilot's control behavior can be observed when the tracking signal bandwidth exceeds the pilot-vehicle capabilities. This phenomenon is called crossover regression, and the bandwidth at which crossover regression occurs is defined as the crossover-regression frequency. Since the crossover-regression frequency is dependent on the pilot-vehicle capabilities, it can be considered to be a measure of the
handling qualities. The validity and applicability of the EBMM were investigated by conducting an experiment in the TU Delft SIMONA flight-simulator. Three aircraft models with varying levels of aeroelasticity were evaluated, using both the new EBMM as well as the well-established Cooper-Harper rating method, which assesses flying
qualities as a surrogate for
handling qualities. When the effects of the amount of aeroelasticity on the flying and
handling qualities were compared, both a quantitative and qualitative correlation was seen between the results of the Cooper-Harper rating method and the new EBMM. In conclusion, the results suggest that the new EBMM method can contribute to the development of improved
handling qualities of large and flexible future aircraft aircraft.
Advisors/Committee Members: Mulder, J.A..
Subjects/Keywords: Handling Qualities; Aeroelasticity; Cybernetics
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Damveld, H. J. (2009). A Cybernetic Approach to Assess the Longitudinal Handling Qualities of Aeroelastic Aircraft. (Doctoral Dissertation). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:3869d074-4e3c-4738-b445-15dbdfd51cab ; urn:NBN:nl:ui:24-uuid:3869d074-4e3c-4738-b445-15dbdfd51cab ; urn:NBN:nl:ui:24-uuid:3869d074-4e3c-4738-b445-15dbdfd51cab ; http://resolver.tudelft.nl/uuid:3869d074-4e3c-4738-b445-15dbdfd51cab
Chicago Manual of Style (16th Edition):
Damveld, H J. “A Cybernetic Approach to Assess the Longitudinal Handling Qualities of Aeroelastic Aircraft.” 2009. Doctoral Dissertation, Delft University of Technology. Accessed January 24, 2021.
http://resolver.tudelft.nl/uuid:3869d074-4e3c-4738-b445-15dbdfd51cab ; urn:NBN:nl:ui:24-uuid:3869d074-4e3c-4738-b445-15dbdfd51cab ; urn:NBN:nl:ui:24-uuid:3869d074-4e3c-4738-b445-15dbdfd51cab ; http://resolver.tudelft.nl/uuid:3869d074-4e3c-4738-b445-15dbdfd51cab.
MLA Handbook (7th Edition):
Damveld, H J. “A Cybernetic Approach to Assess the Longitudinal Handling Qualities of Aeroelastic Aircraft.” 2009. Web. 24 Jan 2021.
Vancouver:
Damveld HJ. A Cybernetic Approach to Assess the Longitudinal Handling Qualities of Aeroelastic Aircraft. [Internet] [Doctoral dissertation]. Delft University of Technology; 2009. [cited 2021 Jan 24].
Available from: http://resolver.tudelft.nl/uuid:3869d074-4e3c-4738-b445-15dbdfd51cab ; urn:NBN:nl:ui:24-uuid:3869d074-4e3c-4738-b445-15dbdfd51cab ; urn:NBN:nl:ui:24-uuid:3869d074-4e3c-4738-b445-15dbdfd51cab ; http://resolver.tudelft.nl/uuid:3869d074-4e3c-4738-b445-15dbdfd51cab.
Council of Science Editors:
Damveld HJ. A Cybernetic Approach to Assess the Longitudinal Handling Qualities of Aeroelastic Aircraft. [Doctoral Dissertation]. Delft University of Technology; 2009. Available from: http://resolver.tudelft.nl/uuid:3869d074-4e3c-4738-b445-15dbdfd51cab ; urn:NBN:nl:ui:24-uuid:3869d074-4e3c-4738-b445-15dbdfd51cab ; urn:NBN:nl:ui:24-uuid:3869d074-4e3c-4738-b445-15dbdfd51cab ; http://resolver.tudelft.nl/uuid:3869d074-4e3c-4738-b445-15dbdfd51cab

Delft University of Technology
6.
van Bruchem, Barend-Jan (author).
Helicopter drive train modelling for manoeuvre load alleviation.
Degree: 2017, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:433d35fd-0475-4863-90dc-4ed2a6d34b70
► Helicopters are complex and expensive aircraft with a level of technology that is immature compared to fixed- wing counterparts. Helicopters suffer from vibratory loads stemming…
(more)
▼ Helicopters are complex and expensive aircraft with a level of technology that is immature compared to fixed- wing counterparts. Helicopters suffer from vibratory loads stemming from the main rotor and exhibit control and stability problems in the low-speed flight regime. Operating a helicopter near the limits of its flight envelope may result in unacceptable high structural loads which adversely affects wear and tear of drive train components. Conservative safety regulations lead to high operating cost where a significant part can be attributed to maintenance. Manufacturers and operators therefore strive to make helicopters more capable and reliable in an effort to reduce operating cost. Structural load alleviation offers an attractive option to achieve this goal by reducing component damage accumulation and subsequent required maintenance. This thesis investigates structural load alleviation in the tail rotor drive train of the UH-60 Black Hawk. The Black Hawk provides a compelling case for load alleviation research because of its ever growing operational weight and resulting increase of drive train load levels. Furthermore, the lifetime of the UH-60 is to be extended so that it will fly for many years to come. Current research and applications of rotorcraft structural load alleviation focus on the main rotor but less attention is given to tail rotor drive train components. This project seeks to address this knowledge gap by investigating manoeuvres that result in critical dynamic loads in the UH-60 tail rotor drive train. A survey of pertinent literature and interviews with helicopter pilots indicate that pedal inputs for left-hand turns in hover lead to high dynamic loads in the UH-60 tail rotor drive train. A flight simulation model is constructed that offers the novel capability to predict dynamic loads in tail rotor drive shafts. This model consists of an available high fidelity engine model and existing rotor models coupled by a multi body dynamics tail rotor drive train model with properties that are based on component measurements and CAD drawings. Experiments are conducted to determine the relation between manoeuvre aggressiveness and dynamic loads in tail rotor drive shafts. Based on the results a manoeuvre load alleviation control strategy is devised to reduce dynamic loads while ensuring applicable Level 1
handling quality requirements. Application of this control strategy will decrease dynamic loads during left-hand yaw manoeuvres in hover. Furthermore, the results highlight what reduction in loads can be achieved for varying levels of manoeuvre aggressiveness. These findings may aid in the design of flight control systems that incorporate tail rotor drive train load alleviation objectives.
Advisors/Committee Members: Voskuijl, Mark (mentor), Delft University of Technology (degree granting institution).
Subjects/Keywords: UH-60; TRDT; Handling Qualities; Structural Load Alleviation; Modelling
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
van Bruchem, B. (. (2017). Helicopter drive train modelling for manoeuvre load alleviation. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:433d35fd-0475-4863-90dc-4ed2a6d34b70
Chicago Manual of Style (16th Edition):
van Bruchem, Barend-Jan (author). “Helicopter drive train modelling for manoeuvre load alleviation.” 2017. Masters Thesis, Delft University of Technology. Accessed January 24, 2021.
http://resolver.tudelft.nl/uuid:433d35fd-0475-4863-90dc-4ed2a6d34b70.
MLA Handbook (7th Edition):
van Bruchem, Barend-Jan (author). “Helicopter drive train modelling for manoeuvre load alleviation.” 2017. Web. 24 Jan 2021.
Vancouver:
van Bruchem B(. Helicopter drive train modelling for manoeuvre load alleviation. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Jan 24].
Available from: http://resolver.tudelft.nl/uuid:433d35fd-0475-4863-90dc-4ed2a6d34b70.
Council of Science Editors:
van Bruchem B(. Helicopter drive train modelling for manoeuvre load alleviation. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:433d35fd-0475-4863-90dc-4ed2a6d34b70

Penn State University
7.
Soneson, Gregory Lorentz.
Development and Piloted Simulation Testing of Advanced Response Types for Ship-based Rotorcraft.
Degree: 2014, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/22764
► Piloted simulation tests were conducted to develop and evaluate advanced control laws and optimal response types for ship-based rotorcraft. Simulations used the GENHEL-PSU non-linear flight…
(more)
▼ Piloted simulation tests were conducted to develop and evaluate advanced control laws and optimal response types for ship-based rotorcraft. Simulations used the GENHEL-PSU non-linear flight model of the H-60 integrated with the Penn State rotorcraft flight simulator. The simulation includes ship motion, a visual model of a FFG-7 frigate, and the Control Equivalent
Turbulence Input (CETI) model for airwake turbulence. The controller uses a Non-Linear Dynamic Inversion (NLDI) scheme to accurately track a variety of response types. An Attitude
Command / Attitude Hold (ACAH) control mode was used as the baseline control law. Di�fferent
variants of Acceleration Command / Velocity Hold (ACVH) and Translational Rate Command
/ Position Hold (TRC/PH) response types were designed to make use of ship deck motion measurements. Filtered deck states are fed into the control laws to command velocity and position relative to the landing spot. Piloted simulation tests were performed for a variety of control con�figurations with and without ship motion and airwake turbulence e�ffects using a maritime Mission Task Element (MTE). Pilot comments and
handling qualities ratings indicated that the best performance was
achieved using an ACVH response type for the pitch axis on approach, which then automatically
transitions to TRC/PH over the ship deck. Level 1
Handling Qualities were achieved in all test
cases when using the optimized ship-relative ACVH/TRC Automatic Transition control mode.
Simulation results indicated that it is best to �filter out most of the dynamic ship deck motion
(primarily ship roll) and to maximize the lateral axis TRC bandwidth.
Advisors/Committee Members: Joseph Francis Horn, Thesis Advisor/Co-Advisor, Jack W Langelaan, Thesis Advisor/Co-Advisor, George A Lesieutre, Thesis Advisor/Co-Advisor.
Subjects/Keywords: Helicopter; Rotorcraft; Controls; Simulation; Handling Qualities; Shipboard; Response Types; Non-Linear Dynamic Inversion
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APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Soneson, G. L. (2014). Development and Piloted Simulation Testing of Advanced Response Types for Ship-based Rotorcraft. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/22764
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Soneson, Gregory Lorentz. “Development and Piloted Simulation Testing of Advanced Response Types for Ship-based Rotorcraft.” 2014. Thesis, Penn State University. Accessed January 24, 2021.
https://submit-etda.libraries.psu.edu/catalog/22764.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Soneson, Gregory Lorentz. “Development and Piloted Simulation Testing of Advanced Response Types for Ship-based Rotorcraft.” 2014. Web. 24 Jan 2021.
Vancouver:
Soneson GL. Development and Piloted Simulation Testing of Advanced Response Types for Ship-based Rotorcraft. [Internet] [Thesis]. Penn State University; 2014. [cited 2021 Jan 24].
Available from: https://submit-etda.libraries.psu.edu/catalog/22764.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Soneson GL. Development and Piloted Simulation Testing of Advanced Response Types for Ship-based Rotorcraft. [Thesis]. Penn State University; 2014. Available from: https://submit-etda.libraries.psu.edu/catalog/22764
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Penn State University
8.
Zheng, Albert.
Investigation of Bandwidth and Disturbance Rejection Properties of a Dynamic Inversion Control Law for Ship-Based Rotorcraft.
Degree: 2015, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/27468
► This thesis is an investigation to better understand the bandwidth and the disturbance rejection requirements of a non-linear dynamic inversion (NLDI) controller (and for rotorcraft…
(more)
▼ This thesis is an investigation to better understand the bandwidth and the disturbance rejection requirements of a non-linear dynamic inversion (NLDI) controller (and for rotorcraft control characteristics in general), when operating in a range of sea states and airwake conditions. The US Army's rotorcraft
handling qualities specification, ADS-33E-PRF, provides no specific design guidance on bandwidth or disturbance rejection properties for maritime operations. A family of controllers was developed to test varying levels of bandwidth and disturbance rejection properties of Attitude Command / Attitude Hold (ACAH) and TRC control modes. The controllers' gain sets for bandwidth were baselined at the minimum Level 1 ADS-33 requirements for response to pilot inputs. Two gain sets for disturbance rejection were developed with the first set of gains baselined at the 45
∘ / 6-dB stability margins recommended by standard flight control design specifications. The second gain set was baselined at the proposed disturbance rejection criteria developed by the Aeroflightdynamics Directorate (AFDD).
Piloted simulation tests were conducted to evaluate the
handling qualities of the family of controllers in the midst of high sea states and a turbulent airwake. A Computational Fluid Dynamics (CFD) airwake model was used for testing the disturbance rejection gain set baselined at the standard stability margins. The second gain set using the AFDD baseline was assessed with a Control Equivalent Turbulence Equivalent (CETI) model. Simulations used the GENHEL-PSU UH-60 model integrated with the Penn State rotorcraft flight simulator. A maritime mission task element (MTE) was flown to evaluate
handling qualities ratings (HQR) using the various response types and gain parameters. Time-frequency metrics were used to supplement the pilot ratings in order to assess the impact of pilot workload and strategy on the
handling qualities in the shipboard environment.
Results indicate that ACAH can improve HQRs over the conventional rate command mechanical control system of the UH-60A. HQRs with ACAH were still Level 2, and the required bandwidth in order to improve HQRs is significantly higher than that currently specified in ADS-33E-PRF. Results also demonstrated that HQRs can be improved by increasing the disturbance rejection bandwidth (DRB) in ACAH in mild sea states or without ship motion. Pilot ratings indicated ACAH can achieve Level 1 HQRs in sea state 3, but the required DRB is much greater than the proposed minimum criteria recommended by the AFDD. The HQRs also show that sea state 4 diminishes the benefit of DRB where the ratings become strictly Level 2.
Results indicated that a Level 1 HQR could be achieved with ship-relative TRC in sea state 5, but that
handling qualities were sensitive to rise time, with the required rise time at the low end of the range recommended by ADS-33E-PRF. Initial results also show that HQRs can be improved by increasing the DRB in ship-relative TRC in sea state 4. Pilot ratings indicated…
Advisors/Committee Members: Joseph Francis Horn, Thesis Advisor/Co-Advisor.
Subjects/Keywords: Helicopter; Rotorcraft; Flight Controls; Simulation; Handling Qualities; Shipboard; Bandwidth; Disturbance Rejection; Pilot
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Zheng, A. (2015). Investigation of Bandwidth and Disturbance Rejection Properties of a Dynamic Inversion Control Law for Ship-Based Rotorcraft. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/27468
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Zheng, Albert. “Investigation of Bandwidth and Disturbance Rejection Properties of a Dynamic Inversion Control Law for Ship-Based Rotorcraft.” 2015. Thesis, Penn State University. Accessed January 24, 2021.
https://submit-etda.libraries.psu.edu/catalog/27468.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Zheng, Albert. “Investigation of Bandwidth and Disturbance Rejection Properties of a Dynamic Inversion Control Law for Ship-Based Rotorcraft.” 2015. Web. 24 Jan 2021.
Vancouver:
Zheng A. Investigation of Bandwidth and Disturbance Rejection Properties of a Dynamic Inversion Control Law for Ship-Based Rotorcraft. [Internet] [Thesis]. Penn State University; 2015. [cited 2021 Jan 24].
Available from: https://submit-etda.libraries.psu.edu/catalog/27468.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Zheng A. Investigation of Bandwidth and Disturbance Rejection Properties of a Dynamic Inversion Control Law for Ship-Based Rotorcraft. [Thesis]. Penn State University; 2015. Available from: https://submit-etda.libraries.psu.edu/catalog/27468
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Delft University of Technology
9.
van Lierop, Bas (author).
Handling Qualities Criteria for Training Effectiveness Assessment of the BS115 Aircraft.
Degree: 2017, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:33534a03-6d57-4175-9c3e-116b9e8fe3ea
► With the introduction of the BS115, an ultra-light two-seater general aviation aircraft, a new opportunity for military pilot training is presented. To increase the training…
(more)
▼ With the introduction of the BS115, an ultra-light two-seater general aviation aircraft, a new opportunity for military pilot training is presented. To increase the training potential of this aircraft, the training effectiveness has been investigated. Previous research on training effectiveness assessment has failed to address the influence of
handling qualities, even though it is identified as one of the most important criteria. To assess the influence of
handling qualities on training effectiveness, a set of evaluation criteria has been established. These evaluation criteria have been assessed using a series of CS-VLA certification flight tests, supplemented with a DATCOM analysis. The evaluation showed that the BS115 performed adequate in terms of stability and roll performance. However, control forces were found to be unsatisfactory for both the elevator and ailerons. To maximize the training effectiveness of the BS115, the flight control system should be adapted to increase these control forces.
Advisors/Committee Members: Melkert, Joris (mentor), Delft University of Technology (degree granting institution).
Subjects/Keywords: General Aviation; Handling Qualities; Training Effectiveness; Military; Pilot training; flight testing; DATCOM
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APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
van Lierop, B. (. (2017). Handling Qualities Criteria for Training Effectiveness Assessment of the BS115 Aircraft. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:33534a03-6d57-4175-9c3e-116b9e8fe3ea
Chicago Manual of Style (16th Edition):
van Lierop, Bas (author). “Handling Qualities Criteria for Training Effectiveness Assessment of the BS115 Aircraft.” 2017. Masters Thesis, Delft University of Technology. Accessed January 24, 2021.
http://resolver.tudelft.nl/uuid:33534a03-6d57-4175-9c3e-116b9e8fe3ea.
MLA Handbook (7th Edition):
van Lierop, Bas (author). “Handling Qualities Criteria for Training Effectiveness Assessment of the BS115 Aircraft.” 2017. Web. 24 Jan 2021.
Vancouver:
van Lierop B(. Handling Qualities Criteria for Training Effectiveness Assessment of the BS115 Aircraft. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Jan 24].
Available from: http://resolver.tudelft.nl/uuid:33534a03-6d57-4175-9c3e-116b9e8fe3ea.
Council of Science Editors:
van Lierop B(. Handling Qualities Criteria for Training Effectiveness Assessment of the BS115 Aircraft. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:33534a03-6d57-4175-9c3e-116b9e8fe3ea

Penn State University
10.
Yomchinda, Thanan.
Integrated Flight Control Design and Handling Qualities Analysis for a Tiltrotor Aircraft.
Degree: 2009, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/9130
► Tiltrotor aircraft present a challenge for flight control designers and handling qualities engineers. Achieving consistent handling qualities throughout an operational flight envelope is difficult since…
(more)
▼ Tiltrotor aircraft present a challenge for flight control designers and
handling qualities engineers. Achieving consistent
handling qualities throughout an operational flight envelope is difficult since the aircraft’s flight dynamics change significantly at different operating conditions (e.g. speed, attitudes, etc.) and configurations (e.g. helicopter mode, conversion mode or airplane mode). The requirement to meet both helicopter and fixed-wing flying
qualities specifications always results in substantial cost and time. Development of integrated methods for flight control design and
handling qualities analysis could greatly enhance the future of tiltrotor aircraft.
In 2008, the University of Liverpool conducted a competition on flight control design for tiltrotor aircraft. The goal is to deliver level one
handling qualities across the flight envelope for a predefined search and rescue (SAR) mission for the XV-15 tiltrotor aircraft. The competitors were provided linear models of XV-15 simulation model and specifications together with the following tasks to submit:
• The predicted bare-airframe
handling qualities
• A flight control system achieving predicted level one
handling qualities
• A full report of the flight control design and
handling qualities results
This thesis will present the integrated methodology of model following based flight control design and
handling qualities analysis developed at the Penn State University and the test pilot evaluation conducted at the University of Liverpool. In this research, a linear model analysis was developed in MATLAB to evaluate predicted
handling qualities based on assigned specifications and the dynamic model. A controller was designed to meet level one
handling qualities and also have maneuvering stability. The results of predicted
handling qualities were determined and showed the control concept was effective. A few criteria showed degraded
handling qualities below level one. These criteria were investigated and discussed. The pilot evaluation showed that the model following / inversion controller with airspeed-scheduled inversion model was effective in delivering level one
handling qualities to the tiltrotor aircraft in helicopter configuration.
Advisors/Committee Members: Joseph Francis Horn, Thesis Advisor/Co-Advisor, Joseph Francis Horn, Thesis Advisor/Co-Advisor.
Subjects/Keywords: Model Inversion Control Law; Flight Control; Aircraft Handling Qualities
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Yomchinda, T. (2009). Integrated Flight Control Design and Handling Qualities Analysis for a Tiltrotor Aircraft. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/9130
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Yomchinda, Thanan. “Integrated Flight Control Design and Handling Qualities Analysis for a Tiltrotor Aircraft.” 2009. Thesis, Penn State University. Accessed January 24, 2021.
https://submit-etda.libraries.psu.edu/catalog/9130.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Yomchinda, Thanan. “Integrated Flight Control Design and Handling Qualities Analysis for a Tiltrotor Aircraft.” 2009. Web. 24 Jan 2021.
Vancouver:
Yomchinda T. Integrated Flight Control Design and Handling Qualities Analysis for a Tiltrotor Aircraft. [Internet] [Thesis]. Penn State University; 2009. [cited 2021 Jan 24].
Available from: https://submit-etda.libraries.psu.edu/catalog/9130.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Yomchinda T. Integrated Flight Control Design and Handling Qualities Analysis for a Tiltrotor Aircraft. [Thesis]. Penn State University; 2009. Available from: https://submit-etda.libraries.psu.edu/catalog/9130
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Delft University of Technology
11.
Sluiter, Carlijn (author).
Bicycle Handling Qualities: finding objective measures for subjective handling qualities.
Degree: 2018, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:d8f74cbd-0326-4908-8e84-0b85d9d80a0b
Subjects/Keywords: Bicycle; Handling Qualities; Subjective; Objective measure; Correlations
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Sluiter, C. (. (2018). Bicycle Handling Qualities: finding objective measures for subjective handling qualities. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:d8f74cbd-0326-4908-8e84-0b85d9d80a0b
Chicago Manual of Style (16th Edition):
Sluiter, Carlijn (author). “Bicycle Handling Qualities: finding objective measures for subjective handling qualities.” 2018. Masters Thesis, Delft University of Technology. Accessed January 24, 2021.
http://resolver.tudelft.nl/uuid:d8f74cbd-0326-4908-8e84-0b85d9d80a0b.
MLA Handbook (7th Edition):
Sluiter, Carlijn (author). “Bicycle Handling Qualities: finding objective measures for subjective handling qualities.” 2018. Web. 24 Jan 2021.
Vancouver:
Sluiter C(. Bicycle Handling Qualities: finding objective measures for subjective handling qualities. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Jan 24].
Available from: http://resolver.tudelft.nl/uuid:d8f74cbd-0326-4908-8e84-0b85d9d80a0b.
Council of Science Editors:
Sluiter C(. Bicycle Handling Qualities: finding objective measures for subjective handling qualities. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:d8f74cbd-0326-4908-8e84-0b85d9d80a0b

Cranfield University
12.
Guo, Wei.
Gain scheduling for a passenger aircraft control system to satisfy handling qualities.
Degree: MSc by Research, 2010, Cranfield University
URL: http://dspace.lib.cranfield.ac.uk/handle/1826/6701
► This thesis considers the problem of designing gain scheduled flight control system (FCS) for large transport aircraft that satisfy handling qualities criteria. The goal is…
(more)
▼ This thesis considers the problem of designing gain scheduled flight control system
(FCS) for large transport aircraft that satisfy handling qualities criteria. The goal is
to design a set of local Linear Time Invariant (LTI) controllers to cover the wide non-
linear aircraft operation flight envelope from the viewpoint of the handling qualities
assessment. The global gain scheduler is then designed that interpolates between
the gains of the local controllers in order to transfer smoothly between different
equilibrium points, and more importantly to satisfy the handling qualities over the
entire flight envelope. The mathematical model of the Boeing 747-100/200 aircraft
is selected for the purpose of the flight controller design and handling qualities as-
sessment.
In order to achieve an attitude hold characteristic, and also improve the dynamic
tracking behavior of the aircraft, longitudinal pitch Rate Command-Attitude Hold
(RCAH) controllers are designed as the local flight controllers at the specific equilib-
rium points in the flight envelope by means of a state space pole placement design
procedure.
The handling qualities assessment of the aircraft is presented, based on which the
scheduler is designed. A number of existing criteria are employed to assess the han-
dling qualities of the aircraft, including the Control Anticipation Parameter (CAP),
Neal and Smith, and C∗ criteria. The gain scheduled flight controller is found to
have satisfactory handling qualities.
The global gain scheduler is designed by interpolating the gains of the local flight
controllers in order to transfer smoothly between different equilibrium points, and
more importantly to satisfy the handling qualities over the flight envelope.
The main contribution of this research is the combination of the gain scheduling
technique based on the local controller design approach and handling qualities as-
sessment. The controllers are designed based at a number of operating points and
the interpolation between them (scheduling) takes place through the scheduling
scheme functions. The aircraft augmented with gain-scheduled controller performs
satisfactorily and meets the requirement of handling qualities. Moreover, the per-
formance using the gain-scheduled controller is considerably improved compared to
the performance using the fixed one.
Subjects/Keywords: Gain Scheduling; Flight Control System; Handling Qualities; Rate Command-Attitude Hold; Passenger Aircraft; Flight Dynamics; Boeing 747
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Guo, W. (2010). Gain scheduling for a passenger aircraft control system to satisfy handling qualities. (Masters Thesis). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/6701
Chicago Manual of Style (16th Edition):
Guo, Wei. “Gain scheduling for a passenger aircraft control system to satisfy handling qualities.” 2010. Masters Thesis, Cranfield University. Accessed January 24, 2021.
http://dspace.lib.cranfield.ac.uk/handle/1826/6701.
MLA Handbook (7th Edition):
Guo, Wei. “Gain scheduling for a passenger aircraft control system to satisfy handling qualities.” 2010. Web. 24 Jan 2021.
Vancouver:
Guo W. Gain scheduling for a passenger aircraft control system to satisfy handling qualities. [Internet] [Masters thesis]. Cranfield University; 2010. [cited 2021 Jan 24].
Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/6701.
Council of Science Editors:
Guo W. Gain scheduling for a passenger aircraft control system to satisfy handling qualities. [Masters Thesis]. Cranfield University; 2010. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/6701

Cranfield University
13.
Andrews, Stuart P.
Modelling and simulation of flexible aircraft : handling qualities with active load control.
Degree: PhD, 2011, Cranfield University
URL: http://dspace.lib.cranfield.ac.uk/handle/1826/7705
► The study of the motion of manoeuvring aircraft has traditionally considered the aircraft to be rigid. This simplifying assumption has been shown to give quite…
(more)
▼ The study of the motion of manoeuvring aircraft has traditionally considered the aircraft
to be rigid. This simplifying assumption has been shown to give quite accurate results for
the flight dynamics of many aircraft types. As modern transport aircraft have developed
however, there has been a marked increase in the size and weight of these aircraft. This
trend is likely to continue with the development of future blended-wing-body and supersonic
transport aircraft. This increase in size and weight has brought about a unique set
of aeroelastic and handling quality issues.
The aerodynamic forces and moments acting on an aeroplane have traditionally been
represented using the aerodynamic derivative approach. It has been shown that this quasisteady
aerodynamic model inadequately predicts the aircraft’s stability characteristics,
and that the inclusion of unsteady aerodynamics “greatly improves the fidelity” of aircraft
models.
This thesis thus presents a novel numerical simulation of an aeroelastic aeroplane for
real-time analysis. The model is built around the standard six degree-of-freedom equations
of motion for a rigid aeroplane using the mean-axes system, and includes unsteady
aerodynamics and structural dynamics. This is suitable for pilot-in-the-loop simulation,
handling qualities and flight loads analysis, and control law development. The dynamics
of the structure are modelled as a set of normal modes, and the equations of motion are
realised in state-space form. The unsteady aerodynamic forces acting on the aeroplane
are described by an indicial state-space model, including unsteady tailplane downwash
and compressibility effects. An implementation of the model is presented in the MATLAB/
Simulink environment.
The interaction between the flight control system, the aeroelastic system and the rigidbody
motion of the aeroplane can result in degraded handling qualities, excessive actuator
control, and fatigue problems. The introduction of load alleviation systems for the management
of loads due to manoeuvres and gusts is also likely to result in the handling
qualities of the aeroplane being degraded.
This thesis presents a number of studies into the impact of structural dynamics, unsteady
aerodynamics, and load alleviation on the handling qualities of a flexible civil transport
aeroplane. The handling qualities of the aeroplane are assessed against a number of
different handling qualities criteria and flying specifications, including the Neal-Smith,
Bandwidth, and CAP criterion. It is shown that aeroelastic effects alter the longitudinal
and lateral-directional characteristics of the aeroplane, resulting in degraded handling
qualities. Manoeuvre and gust load alleviation are similarly found to degrade handling
qualities, while active mode control is shown to offer the possibility of improved handling
qualities.
Subjects/Keywords: Flexible; Elastic; Civil Transport; Aeroplane; Flight Dynamics; Handling Qualities; Aeroelasticity; Aeroservoelasticity; Structural Dynamics; Unsteady Aerodynamics; Load Alleviation
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Andrews, S. P. (2011). Modelling and simulation of flexible aircraft : handling qualities with active load control. (Doctoral Dissertation). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/7705
Chicago Manual of Style (16th Edition):
Andrews, Stuart P. “Modelling and simulation of flexible aircraft : handling qualities with active load control.” 2011. Doctoral Dissertation, Cranfield University. Accessed January 24, 2021.
http://dspace.lib.cranfield.ac.uk/handle/1826/7705.
MLA Handbook (7th Edition):
Andrews, Stuart P. “Modelling and simulation of flexible aircraft : handling qualities with active load control.” 2011. Web. 24 Jan 2021.
Vancouver:
Andrews SP. Modelling and simulation of flexible aircraft : handling qualities with active load control. [Internet] [Doctoral dissertation]. Cranfield University; 2011. [cited 2021 Jan 24].
Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/7705.
Council of Science Editors:
Andrews SP. Modelling and simulation of flexible aircraft : handling qualities with active load control. [Doctoral Dissertation]. Cranfield University; 2011. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/7705

Cranfield University
14.
Andrews, Stuart P.
Modelling and simulation of flexible aircraft : handling qualities with active load control.
Degree: PhD, 2011, Cranfield University
URL: http://dspace.lib.cranfield.ac.uk/handle/1826/7705
;
http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.566018
► The study of the motion of manoeuvring aircraft has traditionally considered the aircraft to be rigid. This simplifying assumption has been shown to give quite…
(more)
▼ The study of the motion of manoeuvring aircraft has traditionally considered the aircraft to be rigid. This simplifying assumption has been shown to give quite accurate results for the flight dynamics of many aircraft types. As modern transport aircraft have developed however, there has been a marked increase in the size and weight of these aircraft. This trend is likely to continue with the development of future blended-wing-body and supersonic transport aircraft. This increase in size and weight has brought about a unique set of aeroelastic and handling quality issues. The aerodynamic forces and moments acting on an aeroplane have traditionally been represented using the aerodynamic derivative approach. It has been shown that this quasisteady aerodynamic model inadequately predicts the aircraft’s stability characteristics, and that the inclusion of unsteady aerodynamics “greatly improves the fidelity” of aircraft models. This thesis thus presents a novel numerical simulation of an aeroelastic aeroplane for real-time analysis. The model is built around the standard six degree-of-freedom equations of motion for a rigid aeroplane using the mean-axes system, and includes unsteady aerodynamics and structural dynamics. This is suitable for pilot-in-the-loop simulation, handling qualities and flight loads analysis, and control law development. The dynamics of the structure are modelled as a set of normal modes, and the equations of motion are realised in state-space form. The unsteady aerodynamic forces acting on the aeroplane are described by an indicial state-space model, including unsteady tailplane downwash and compressibility effects. An implementation of the model is presented in the MATLAB/ Simulink environment. The interaction between the flight control system, the aeroelastic system and the rigidbody motion of the aeroplane can result in degraded handling qualities, excessive actuator control, and fatigue problems. The introduction of load alleviation systems for the management of loads due to manoeuvres and gusts is also likely to result in the handling qualities of the aeroplane being degraded. This thesis presents a number of studies into the impact of structural dynamics, unsteady aerodynamics, and load alleviation on the handling qualities of a flexible civil transport aeroplane. The handling qualities of the aeroplane are assessed against a number of different handling qualities criteria and flying specifications, including the Neal-Smith, Bandwidth, and CAP criterion. It is shown that aeroelastic effects alter the longitudinal and lateral-directional characteristics of the aeroplane, resulting in degraded handling qualities. Manoeuvre and gust load alleviation are similarly found to degrade handling qualities, while active mode control is shown to offer the possibility of improved handling qualities.
Subjects/Keywords: Flexible; Elastic; Civil Transport; Aeroplane; Flight Dynamics; Handling Qualities; Aeroelasticity; Aeroservoelasticity; Structural Dynamics; Unsteady Aerodynamics; Load Alleviation
Record Details
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Record Details
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Andrews, S. P. (2011). Modelling and simulation of flexible aircraft : handling qualities with active load control. (Doctoral Dissertation). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/7705 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.566018
Chicago Manual of Style (16th Edition):
Andrews, Stuart P. “Modelling and simulation of flexible aircraft : handling qualities with active load control.” 2011. Doctoral Dissertation, Cranfield University. Accessed January 24, 2021.
http://dspace.lib.cranfield.ac.uk/handle/1826/7705 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.566018.
MLA Handbook (7th Edition):
Andrews, Stuart P. “Modelling and simulation of flexible aircraft : handling qualities with active load control.” 2011. Web. 24 Jan 2021.
Vancouver:
Andrews SP. Modelling and simulation of flexible aircraft : handling qualities with active load control. [Internet] [Doctoral dissertation]. Cranfield University; 2011. [cited 2021 Jan 24].
Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/7705 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.566018.
Council of Science Editors:
Andrews SP. Modelling and simulation of flexible aircraft : handling qualities with active load control. [Doctoral Dissertation]. Cranfield University; 2011. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/7705 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.566018

Penn State University
15.
Spires, James Michael.
MODEL FOLLOWING AND HIGH ORDER AUGMENTATION FOR ROTORCRAFT CONTROL, APPLIED VIA PARTIAL AUTHORITY.
Degree: 2017, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/13773jms1188
► This dissertation consists of two main studies, a few small studies, and design documentation, all aimed at improving rotorcraft control by employing multi-input multi-output (MIMO)…
(more)
▼ This dissertation consists of two main studies, a few small studies, and design documentation, all aimed at improving rotorcraft control by employing multi-input multi-output (MIMO) command-model-following control as a baseline, together with a selectable (and de-selectable) MIMO high order compensator that augments the baseline.
Two methods of MIMO command-model-following control design are compared for rotorcraft flight control. The first, Explicit Model Following (EMF), employs SISO inverse plants with a dynamic decoupling matrix, which is a purely feed-forward approach to inverting the plant. The second is Dynamic Inversion (DI), which involves both feed-forward and feedback path elements to invert the plant. The EMF design is purely linear, while the DI design has some nonlinear elements in vertical rate control. For each of these methods, an architecture is presented that provides angular rate model-following with selectable vertical rate model-following. Implementation challenges of both EMF and DI are covered, and methods of dealing with them are presented. These two MIMO model-following approaches are evaluated regarding (1) fidelity to the command model, and (2) turbulence rejection. Both are found to provide good tracking of commands and reduction of cross coupling.
Next, an architecture and design methodology for high order compensator (HOC) augmentation of a baseline controller for rotorcraft is presented. With this architecture, the HOC compensator is selectable and can easily be authority-limited, which might ease certification. Also, the plant for this augmentative MIMO compensator design is a stabilized helicopter system, so good flight test data could be safely gathered for more accurate plant identification. The design methodology is carried out twice on an example helicopter model, once with turbulence rejection as the objective, and once with the additional objective of closely following pilot commands. The turbulence rejection HOC is feedback only (HOC_FB), while the combined objective HOC has both feedback and feedforward elements (HOC_FBFF). The HOC_FB was found to be better at improving turbulence rejection but generally degrades the following of pilot commands. The HOC_FBFF improves turbulence rejection relative to the Baseline controller, but not by as much as HOC_FB. However, HOC_FBFF also generally improves the following of pilot commands.
Future work is suggested and facilitated in the areas of DI, MIMO EMF, and HOC augmentation. High frequency dynamics, neglected in the DI design, unexpectedly change the low frequency behavior of the DI-plant system, in addition to the expected change in high frequency dynamics. This dissertation shows why, and suggests a technique for designing a pseudo-command pre-filter that at least partially restores the intended DI-plant dynamics. For EMF, a procedure is presented that avoids use of a reduced-order model, and instead uses a full-order model or even frequency-domain flight test data. With HOC augmentation, future research might…
Advisors/Committee Members: Joseph Horn, Dissertation Advisor/Co-Advisor, Joseph Horn, Committee Chair/Co-Chair, Edward Smith, Committee Member, Jacob Langelaan, Committee Member, Chris Rahn, Outside Member.
Subjects/Keywords: rotorcraft control; model following control; dynamic decoupling; explicit model following; H2; Hinf; dynamic inversion; nonlinear dynamic inversion; handling qualities; partial authority control; feed forward; turbulence rejection; piggyback compensation
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APA ·
Chicago ·
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Export
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APA (6th Edition):
Spires, J. M. (2017). MODEL FOLLOWING AND HIGH ORDER AUGMENTATION FOR ROTORCRAFT CONTROL, APPLIED VIA PARTIAL AUTHORITY. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/13773jms1188
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Spires, James Michael. “MODEL FOLLOWING AND HIGH ORDER AUGMENTATION FOR ROTORCRAFT CONTROL, APPLIED VIA PARTIAL AUTHORITY.” 2017. Thesis, Penn State University. Accessed January 24, 2021.
https://submit-etda.libraries.psu.edu/catalog/13773jms1188.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Spires, James Michael. “MODEL FOLLOWING AND HIGH ORDER AUGMENTATION FOR ROTORCRAFT CONTROL, APPLIED VIA PARTIAL AUTHORITY.” 2017. Web. 24 Jan 2021.
Vancouver:
Spires JM. MODEL FOLLOWING AND HIGH ORDER AUGMENTATION FOR ROTORCRAFT CONTROL, APPLIED VIA PARTIAL AUTHORITY. [Internet] [Thesis]. Penn State University; 2017. [cited 2021 Jan 24].
Available from: https://submit-etda.libraries.psu.edu/catalog/13773jms1188.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Spires JM. MODEL FOLLOWING AND HIGH ORDER AUGMENTATION FOR ROTORCRAFT CONTROL, APPLIED VIA PARTIAL AUTHORITY. [Thesis]. Penn State University; 2017. Available from: https://submit-etda.libraries.psu.edu/catalog/13773jms1188
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
16.
Antonioli, Jean-Charles.
Spécification de lois de commande pour hélicoptères orientée Qualités de Vol : Designing helicopter control laws with Handling Qualities objectives.
Degree: Docteur es, Automatique, 2015, Aix Marseille Université
URL: http://www.theses.fr/2015AIXM4333
► Cette thèse s'inscrit dans le domaine de l’étude des lois de commandes de vol pour hélicoptères. Les automaticiens doivent régler les gains de ces lois…
(more)
▼ Cette thèse s'inscrit dans le domaine de l’étude des lois de commandes de vol pour hélicoptères. Les automaticiens doivent régler les gains de ces lois de manière à respecter au mieux les exigences de Qualités de Pilotage extraites de la norme ADS-33. La norme traduit ces exigences en termes de critères de Qualités de Vol. Ils évaluent la qualité de la stabilité, de l'agilité, et du suivi des consignes du pilote par la machine. Ils traduisent la pilotabilité de l'hélicoptère pour un pilote « moyen » de référence. A part une technique d’optimisation interactive développée à la NASA et l'US Army depuis 40 ans, il n’existe pas de méthode appropriée à ce problème. Les réglages sont effectués de manière empirique et itérative. L’ONERA propose une approche méthodologique structurée. L’objectif de la thèse consiste à développer cette méthodologie de manière à gérer deux contraintes supplémentaires par rapport aux capacités des méthodes de synthèse classiques en automatique : la capacité à prendre en compte la structure contrainte des lois de commande et les exigences spécifiques en terme de Qualités de Vol selon la norme ADS-33.Une technique d'amélioration des Qualités de Vol par analyse de sensibilités entre les gains et les critères est développée. Puis une méthodologie d’initialisation des gains est proposée, via la création et l’utilisation efficace de nouveaux abaques de Qualités de Vol pour modèles équivalents simplifiés. Afin d'améliorer l'efficacité de ce réglage initial, deux contraintes supplémentaires sont prises en compte (énergie et découplage). Enfin, un processus complet de réglage est proposé : initialisation, ajustement linéaire et ajustement non linéaire.
This study is in the field of designing helicopter control laws. Designers must tune the gains of these laws in order to meet as much as possible Handling Qualities requirements from ADS-33. This standard translates these requirements in terms of Flying Qualities requirements. Then, we can evaluate the quality of the stability, of the quickness, and of the ability of the machine to follow the inputs from the pilot. Apart from an interactive optimization technique developed at NASA and US Army over the last 40 years, no appropriate method exists to solve this problem. Then, empirical iterative tunings are led. ONERA addresses this issue through a structured methodological approach. The aim of the thesis is to develop this methodology, taking into account two additional constraints compared with the capabilities of usual synthesis methods used in automatics: the capability to deal with the constraints from the control law structures and with the Handling Qualities requirements from the ADS-33 standards. A technique is developed to improve the Flying Qualities using sensitivity studies between gains and criteria. Then, a methodology to initialize the gains is developed, through the creation and the efficient usage of new Flying Qualities-based charts for equivalent simplified models. In order to improve the efficiency of the initial tuning, two additional…
Advisors/Committee Members: Ouladsine, Mustapha (thesis director), Rakotomamonjy, Thomas (thesis director), Taghizad, Armin (thesis director).
Subjects/Keywords: Critères de Qualités de Vol; Norme ADS-33; Hélicoptère; Automatique classique; Commande; Pid; Handling Qualities requirements; ADS-33 standard; Helicopter; Automatics; Control; Pid
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Antonioli, J. (2015). Spécification de lois de commande pour hélicoptères orientée Qualités de Vol : Designing helicopter control laws with Handling Qualities objectives. (Doctoral Dissertation). Aix Marseille Université. Retrieved from http://www.theses.fr/2015AIXM4333
Chicago Manual of Style (16th Edition):
Antonioli, Jean-Charles. “Spécification de lois de commande pour hélicoptères orientée Qualités de Vol : Designing helicopter control laws with Handling Qualities objectives.” 2015. Doctoral Dissertation, Aix Marseille Université. Accessed January 24, 2021.
http://www.theses.fr/2015AIXM4333.
MLA Handbook (7th Edition):
Antonioli, Jean-Charles. “Spécification de lois de commande pour hélicoptères orientée Qualités de Vol : Designing helicopter control laws with Handling Qualities objectives.” 2015. Web. 24 Jan 2021.
Vancouver:
Antonioli J. Spécification de lois de commande pour hélicoptères orientée Qualités de Vol : Designing helicopter control laws with Handling Qualities objectives. [Internet] [Doctoral dissertation]. Aix Marseille Université 2015. [cited 2021 Jan 24].
Available from: http://www.theses.fr/2015AIXM4333.
Council of Science Editors:
Antonioli J. Spécification de lois de commande pour hélicoptères orientée Qualités de Vol : Designing helicopter control laws with Handling Qualities objectives. [Doctoral Dissertation]. Aix Marseille Université 2015. Available from: http://www.theses.fr/2015AIXM4333
17.
Denieul, Yann.
Conception préliminaire de surfaces de contrôle et lois de commande pour configurations d’avions non conventionnelles : Preliminary Design of Control Surfaces and Laws for Unconventional Aircraft Configurations.
Degree: Docteur es, Automatique, 2016, Toulouse, ISAE
URL: http://www.theses.fr/2016ESAE0033
► La prochaine génération d’avions civil sera probablement une révolution en termede configuration d’avion, différant largement de l’architecture désormais classique “fuselage- ailes- moteurs sous voilure”. Du…
(more)
▼ La prochaine génération d’avions civil sera probablement une révolution en termede configuration d’avion, différant largement de l’architecture désormais classique “fuselage- ailes- moteurs sous voilure”. Du point de vue des qualités de vol, la tendance actuelle est d’évoluer versdes avions de moins en moins stables, à la fois en longitudinal et latéral. Il est dès lors probableque les futurs avions ne seront pas directement contrôlables par un humain sans l’apport de lois decommande stabilisantes. Il devient alors nécessaire de considérer l’apport des systèmes de commandesde vol très tôt dans la conception de l’avion, notamment pour le dimensionnement desempennages, gouvernes et actionneurs, contrairement au processus actuel qui ne prend principalementen compte que des critères “boucle ouverte” d’équilibre en phase de conception préliminaire.Plutôt qu’un processus itératif de dimensionnement puis synthèse de lois de commande, nousproposons d’optimiser simultanément les tailles de gouvernes, actionneurs et commandes de volen tenant compte des instabilités longitudinales et latérales, ainsi que des contraintes industriellessur la structure de correcteurs, sur un cas d’application de type aile volante. Ce processus de“co-design” permet de dimensionner des paramètres physiques de l’avion en tenant compte desapports d’une boucle de retour pour contrer des perturbations externes telles que de la turbulenceatmosphérique, permettant un avion plus sûr et optimal.
Next generation of civil transport aircraft is likely to be a radical change in overallconfiguration compared to traditional tube-and-wing design. From a handling qualities perspective,current trend in modern airliners is to evolve towards more and more unstable aircraft, bothfrom longitudinal and lateral-directional point of view. As a consequence future aircraft may notbe controllable by human operator without stabilizing control laws. It then becomes necessaryto consider flight control systems contribution early in the design phase for control surfaces,empennages and actuators sizing, as opposed to traditional way of working dealing only withopen-loop criteria for preliminary sizing. Instead of an iterative process of sizing and controllaws synthesis, we propose to concurrently optimize control surfaces, actuators and flight controllaws taking into account longitudinal and lateral instability as well as industrial structure forcontrollers, for unstable configurations such as Blended Wing-Body (BWB). This “co-design”procedure enables sizing of physical aircraft parameters taking into account benefits from feedbackstabilization for counteracting external disturbance such as atmospheric turbulence, thus leadingto safer and more optimal aircraft configurations.
Advisors/Committee Members: Alazard, Daniel (thesis director), Bordeneuve-Guibé, Joël (thesis director).
Subjects/Keywords: Dimensionnement avion; Systèmes commandes de vol; Lois de commande; Optimisation; Qualités de vol; Aircraft Design; Flight Control Systems; Control Laws; Optimization; Handling Qualities; 629.8
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Denieul, Y. (2016). Conception préliminaire de surfaces de contrôle et lois de commande pour configurations d’avions non conventionnelles : Preliminary Design of Control Surfaces and Laws for Unconventional Aircraft Configurations. (Doctoral Dissertation). Toulouse, ISAE. Retrieved from http://www.theses.fr/2016ESAE0033
Chicago Manual of Style (16th Edition):
Denieul, Yann. “Conception préliminaire de surfaces de contrôle et lois de commande pour configurations d’avions non conventionnelles : Preliminary Design of Control Surfaces and Laws for Unconventional Aircraft Configurations.” 2016. Doctoral Dissertation, Toulouse, ISAE. Accessed January 24, 2021.
http://www.theses.fr/2016ESAE0033.
MLA Handbook (7th Edition):
Denieul, Yann. “Conception préliminaire de surfaces de contrôle et lois de commande pour configurations d’avions non conventionnelles : Preliminary Design of Control Surfaces and Laws for Unconventional Aircraft Configurations.” 2016. Web. 24 Jan 2021.
Vancouver:
Denieul Y. Conception préliminaire de surfaces de contrôle et lois de commande pour configurations d’avions non conventionnelles : Preliminary Design of Control Surfaces and Laws for Unconventional Aircraft Configurations. [Internet] [Doctoral dissertation]. Toulouse, ISAE; 2016. [cited 2021 Jan 24].
Available from: http://www.theses.fr/2016ESAE0033.
Council of Science Editors:
Denieul Y. Conception préliminaire de surfaces de contrôle et lois de commande pour configurations d’avions non conventionnelles : Preliminary Design of Control Surfaces and Laws for Unconventional Aircraft Configurations. [Doctoral Dissertation]. Toulouse, ISAE; 2016. Available from: http://www.theses.fr/2016ESAE0033
18.
Saucez, Manuel.
Résolution des qualités de vol de l'aile volante Airbus : Handling qualities resolution of the Airbus flying wing.
Degree: Docteur es, Mathématiques appliquées et Systèmes Embarqués, 2013, Toulouse, ISAE
URL: http://www.theses.fr/2013ESAE0026
► L'objectif de cette étude est de résoudre les qualités de vol d'une aile volante long courrier, au stade de la conception avion. Le concept d'aile…
(more)
▼ L'objectif de cette étude est de résoudre les qualités de vol d'une aile volante long courrier, au stade de la conception avion. Le concept d'aile volante promet un gain important en terme de performances et de niveau de finesse par rapport aux configurations classiques. Ce gain est obtenu par l'intégration des quatre fonctions principales de l'avion (portance, contrôle, propulsion, transport) dans un seul corps. Ces choix de configuration entraînent des challenges à relever, dont l'obtention de qualités de vol respectant la certification. La configuration initiale étudiée présente de fortes instabilités longitudinales et latérales, une faible autorité en roulis, et des difficultés à effectuer la manœuvre de rotation au décollage. Dans cette étude sont proposées des solutions, combinant des surfaces de contrôle innovantes et des degrés de libertés originaux, qui tirent profit des avantages de la configuration. Les qualités de vols sont résolues dans un processus de résolution avec aussi peu de boucles que possible, et l'impact sur les performances est minimisé. En sortie de ce processus se trouve l'architecture de surface de contrôle optimisée, qui minimise l'impact des qualités de vol sur le coût de la mission.
The aim of this study is to solve the handling qualities problems of a long range blended wing body, at the conceptual design phase. That concept, also named flying wing in this report, is an aircraft which integrates the four aircraft functions (lift, control, propulsion, passengers transportation) in one single body. That configuration presents a benefit in cruise lift-over-drag ratio, as well as in noise emissions, due to the shielding effect provided by the inner wing to mask the engine noise.That configuration choice leads also to challenges. One of them is the handling qualities. The baseline studied flying wing presents initially longitudinal and lateral instabilities, as well as lack of roll manoeuvrability and difficulty to do the rotation at takeoff. In this report are proposed solutions, combining innovative control surfaces and original drivers, which are adapted to the configuration advantages. The handling qualitiesare solved in a resolution process with as few loops as possible, and the impact on the performances is minimized. The output of that process is the best control surfaces architecture and airfoils design which minimizes the impact of the handling qualities resolution on the cost of the mission.
Advisors/Committee Members: Boiffier, Jean-Luc (thesis director).
Subjects/Keywords: Aile volante; Mécanique du vol; Conception avion; Optimisation; Handling qualities; Blended wing body; Control law; Conceptual design; Double split flaps; Thrust vectoring; Optimization; 621.39
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Saucez, M. (2013). Résolution des qualités de vol de l'aile volante Airbus : Handling qualities resolution of the Airbus flying wing. (Doctoral Dissertation). Toulouse, ISAE. Retrieved from http://www.theses.fr/2013ESAE0026
Chicago Manual of Style (16th Edition):
Saucez, Manuel. “Résolution des qualités de vol de l'aile volante Airbus : Handling qualities resolution of the Airbus flying wing.” 2013. Doctoral Dissertation, Toulouse, ISAE. Accessed January 24, 2021.
http://www.theses.fr/2013ESAE0026.
MLA Handbook (7th Edition):
Saucez, Manuel. “Résolution des qualités de vol de l'aile volante Airbus : Handling qualities resolution of the Airbus flying wing.” 2013. Web. 24 Jan 2021.
Vancouver:
Saucez M. Résolution des qualités de vol de l'aile volante Airbus : Handling qualities resolution of the Airbus flying wing. [Internet] [Doctoral dissertation]. Toulouse, ISAE; 2013. [cited 2021 Jan 24].
Available from: http://www.theses.fr/2013ESAE0026.
Council of Science Editors:
Saucez M. Résolution des qualités de vol de l'aile volante Airbus : Handling qualities resolution of the Airbus flying wing. [Doctoral Dissertation]. Toulouse, ISAE; 2013. Available from: http://www.theses.fr/2013ESAE0026

Delft University of Technology
19.
Scholten, Pepijn (author).
A Variable Stability In-Flight Simulation System using Incremental Non-Linear Dynamic Inversion.
Degree: 2019, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:fbdfb1fe-b5a9-46b4-841c-27e4268a2925
Subjects/Keywords: Variable; Stability; In-Flight; Simulation; Handling; Qualities; Incremental; Non-linear; Dynamic; Inversion
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Scholten, P. (. (2019). A Variable Stability In-Flight Simulation System using Incremental Non-Linear Dynamic Inversion. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:fbdfb1fe-b5a9-46b4-841c-27e4268a2925
Chicago Manual of Style (16th Edition):
Scholten, Pepijn (author). “A Variable Stability In-Flight Simulation System using Incremental Non-Linear Dynamic Inversion.” 2019. Masters Thesis, Delft University of Technology. Accessed January 24, 2021.
http://resolver.tudelft.nl/uuid:fbdfb1fe-b5a9-46b4-841c-27e4268a2925.
MLA Handbook (7th Edition):
Scholten, Pepijn (author). “A Variable Stability In-Flight Simulation System using Incremental Non-Linear Dynamic Inversion.” 2019. Web. 24 Jan 2021.
Vancouver:
Scholten P(. A Variable Stability In-Flight Simulation System using Incremental Non-Linear Dynamic Inversion. [Internet] [Masters thesis]. Delft University of Technology; 2019. [cited 2021 Jan 24].
Available from: http://resolver.tudelft.nl/uuid:fbdfb1fe-b5a9-46b4-841c-27e4268a2925.
Council of Science Editors:
Scholten P(. A Variable Stability In-Flight Simulation System using Incremental Non-Linear Dynamic Inversion. [Masters Thesis]. Delft University of Technology; 2019. Available from: http://resolver.tudelft.nl/uuid:fbdfb1fe-b5a9-46b4-841c-27e4268a2925

University of Maryland
20.
Brown, Daniel Richard.
EFFECTS OF CONTRAST AND SPATIAL FREQUENCY ON IDEALIZED COMPENSATORY TASKS.
Degree: Aerospace Engineering, 2014, University of Maryland
URL: http://hdl.handle.net/1903/15446
► The present analysis describes a series of experiments to quantify the effects of loss of contrast on highly-idealized, compensatory piloting tasks. The effects of spatial…
(more)
▼ The present analysis describes a series of experiments to quantify the effects of loss of contrast on highly-idealized, compensatory piloting tasks. The effects of spatial frequency are simultaneously studied via the Modulation Transfer Function (MTF). The MTF can quantify the contrast and spatial frequency (relative size) of the objects that provide visual cues necessary for closing pilot control loops. A brief analysis is also performed on different input devices and their effects on task performance. The results show compensatory task performance can be modeled with multiple MTFs, each representing a unique numeric characterization of the pilot response in a single task. The results also quantify the intuitively known fact that physiological limits of human vision directly correlate to piloting task performance. Therefore, the MTF may represent a key building block of quantitative, objective rotorcraft
Handling Qualities metrics for Degraded Visual Environments (DVE).
Advisors/Committee Members: Celi, Roberto (advisor).
Subjects/Keywords: Aerospace engineering; ADS-33; Degraded Visual Enviornments (DVE); Modulation Transfer Function (MTF); Rotorcraft Brownout; Rotorcraft Handling Qualities (HQ); Usable Cue Environment (UCE)
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Brown, D. R. (2014). EFFECTS OF CONTRAST AND SPATIAL FREQUENCY ON IDEALIZED COMPENSATORY TASKS. (Thesis). University of Maryland. Retrieved from http://hdl.handle.net/1903/15446
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Brown, Daniel Richard. “EFFECTS OF CONTRAST AND SPATIAL FREQUENCY ON IDEALIZED COMPENSATORY TASKS.” 2014. Thesis, University of Maryland. Accessed January 24, 2021.
http://hdl.handle.net/1903/15446.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Brown, Daniel Richard. “EFFECTS OF CONTRAST AND SPATIAL FREQUENCY ON IDEALIZED COMPENSATORY TASKS.” 2014. Web. 24 Jan 2021.
Vancouver:
Brown DR. EFFECTS OF CONTRAST AND SPATIAL FREQUENCY ON IDEALIZED COMPENSATORY TASKS. [Internet] [Thesis]. University of Maryland; 2014. [cited 2021 Jan 24].
Available from: http://hdl.handle.net/1903/15446.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Brown DR. EFFECTS OF CONTRAST AND SPATIAL FREQUENCY ON IDEALIZED COMPENSATORY TASKS. [Thesis]. University of Maryland; 2014. Available from: http://hdl.handle.net/1903/15446
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Pretoria
21.
[No author].
Longitudinal handling characteristics of a tailless
gull-wing aircraft
.
Degree: 2008, University of Pretoria
URL: http://upetd.up.ac.za/thesis/available/etd-09182008-132941/
► A handling quality investigation was performed on the swept gull-wing configuration. The swept gull-wing configuration is tailless and has a wing with a transition in…
(more)
▼ A
handling quality investigation was performed on
the swept gull-wing configuration. The swept gull-wing
configuration is tailless and has a wing with a transition in the
sweep and dihedral angle. An example of this type of aircraft is
the Exulans. This aircraft is currently under development at the
University of Pretoria. The
handling quality study was focussed on
pitch axis dynamics. The Exulans is a research testbed that will be
used to investigate the swept gull-wing configuration and its
special controls by means of full-scale flight testing. Variable
wing sweep, twisting elevons and winglets will be investigated as
means of control. These control devices are configured in such a
way as to have minimum impact on the performance of the aircraft.
The
handling qualities of the swept gull-wing configuration have to
be acceptable while using these different control strategies. The
study was launched to investigate whether a gull-wing configuration
aircraft will have satisfactory
handling qualities at CG positions
associated with the most favourable aerodynamic performance. There
is an aerodynamic performance gain in designing an aircraft so that
the CG falls on the so-called `E-point'. The E-point is the centre
of pressure for an elliptical circulation distribution. An
elliptical circulation distribution is associated with the highest
Oswald efficiency for an aircraft. Time domain simulation
techniques and frequency domain analysis techniques were used to
analyse the
handling qualities of the gull-wing configuration. The
C-star criterion was used to analyse
handling qualities with time
domain simulation data as input. Comparative time domain
simulations were performed between the Exulans and other aircraft
to compare
handling qualities. Eigenvalue analysis was used
together with the thumbprint criterion to investigate inherent
gull-wing airframe dynamics. The Shomber-Gertsen and Military
Specification 8785 criteria were also used for the same purpose.
The Neal-Smith method was used to investigate the effect of control
authority on
handling qualities and the effect of a pilot. The
Monnich and Dalldorff criterion was used to evaluate gust
handling
qualities. An analysis chart by Fremaux and Vairo was used to
evaluate the tumbling susceptibility of the gull-wing
configuration. The pitch
handling quality investigation shows
sufficient promise that the swept gull-wing configuration will have
acceptable
handling qualities with the CG placed at positions
associated with optimised aerodynamic performance. Analysis showed
that the swept gull-wing configuration is potentially prone to
tumbling. With low static margins, the configuration should exhibit
improved
handling qualities in gusty conditions when compared to
existing tailless aircraft. It is recommended that a lateral
handling quality study be performed before full scale flight
testing commences on the Exulans. In addition, the possibility of
wingtip stall must be investigated for the case of the swept
gull-wing configuration.
Advisors/Committee Members: Theron, Nicolaas J (advisor).
Subjects/Keywords: Flight simulation;
Tumbling;
Thumbprint criterion;
Neal-smith analysis;
C-star criterion;
Shomber-gertsen analysis;
Pilot induced oscillation;
Oswald efficiency;
Pilot mathematical model;
Variable sweep wing;
Exulans;
Variable static margin;
Swept gull-wing configuration;
O-point;
E-point;
Handling qualities;
Gust handling qualities;
Tailless aircraft;
Pecking;
Monnich and dalldorff criterion;
UCTD
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MLA ·
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Export
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APA (6th Edition):
author], [. (2008). Longitudinal handling characteristics of a tailless
gull-wing aircraft
. (Masters Thesis). University of Pretoria. Retrieved from http://upetd.up.ac.za/thesis/available/etd-09182008-132941/
Chicago Manual of Style (16th Edition):
author], [No. “Longitudinal handling characteristics of a tailless
gull-wing aircraft
.” 2008. Masters Thesis, University of Pretoria. Accessed January 24, 2021.
http://upetd.up.ac.za/thesis/available/etd-09182008-132941/.
MLA Handbook (7th Edition):
author], [No. “Longitudinal handling characteristics of a tailless
gull-wing aircraft
.” 2008. Web. 24 Jan 2021.
Vancouver:
author] [. Longitudinal handling characteristics of a tailless
gull-wing aircraft
. [Internet] [Masters thesis]. University of Pretoria; 2008. [cited 2021 Jan 24].
Available from: http://upetd.up.ac.za/thesis/available/etd-09182008-132941/.
Council of Science Editors:
author] [. Longitudinal handling characteristics of a tailless
gull-wing aircraft
. [Masters Thesis]. University of Pretoria; 2008. Available from: http://upetd.up.ac.za/thesis/available/etd-09182008-132941/

University of Pretoria
22.
Agenbag, Daniel
Sarel.
Longitudinal
handling characteristics of a tailless gull-wing
aircraft.
Degree: Mechanical and Aeronautical
Engineering, 2008, University of Pretoria
URL: http://hdl.handle.net/2263/28011
► A handling quality investigation was performed on the swept gull-wing configuration. The swept gull-wing configuration is tailless and has a wing with a transition in…
(more)
▼ A
handling quality investigation was performed on the
swept gull-wing configuration. The swept gull-wing configuration is
tailless and has a wing with a transition in the sweep and dihedral
angle. An example of this type of aircraft is the Exulans. This
aircraft is currently under development at the University of
Pretoria. The
handling quality study was focussed on pitch axis
dynamics. The Exulans is a research testbed that will be used to
investigate the swept gull-wing configuration and its special
controls by means of full-scale flight testing. Variable wing
sweep, twisting elevons and winglets will be investigated as means
of control. These control devices are configured in such a way as
to have minimum impact on the performance of the aircraft. The
handling qualities of the swept gull-wing configuration have to be
acceptable while using these different control strategies. The
study was launched to investigate whether a gull-wing configuration
aircraft will have satisfactory
handling qualities at CG positions
associated with the most favourable aerodynamic performance. There
is an aerodynamic performance gain in designing an aircraft so that
the CG falls on the so-called `E-point'. The E-point is the centre
of pressure for an elliptical circulation distribution. An
elliptical circulation distribution is associated with the highest
Oswald efficiency for an aircraft. Time domain simulation
techniques and frequency domain analysis techniques were used to
analyse the
handling qualities of the gull-wing configuration. The
C-star criterion was used to analyse
handling qualities with time
domain simulation data as input. Comparative time domain
simulations were performed between the Exulans and other aircraft
to compare
handling qualities. Eigenvalue analysis was used
together with the thumbprint criterion to investigate inherent
gull-wing airframe dynamics. The Shomber-Gertsen and Military
Specification 8785 criteria were also used for the same purpose.
The Neal-Smith method was used to investigate the effect of control
authority on
handling qualities and the effect of a pilot. The
Monnich and Dalldorff criterion was used to evaluate gust
handling
qualities. An analysis chart by Fremaux and Vairo was used to
evaluate the tumbling susceptibility of the gull-wing
configuration. The pitch
handling quality investigation shows
sufficient promise that the swept gull-wing configuration will have
acceptable
handling qualities with the CG placed at positions
associated with optimised aerodynamic performance. Analysis showed
that the swept gull-wing configuration is potentially prone to
tumbling. With low static margins, the configuration should exhibit
improved
handling qualities in gusty conditions when compared to
existing tailless aircraft. It is recommended that a lateral
handling quality study be performed before full scale flight
testing commences on the Exulans. In addition, the possibility of
wingtip stall must be investigated for the case of the swept
gull-wing configuration.
Advisors/Committee Members: Theron, Nicolaas J. (advisor).
Subjects/Keywords: Flight
simulation;
Tumbling; Thumbprint
criterion; Neal-smith
analysis; C-star
criterion;
Shomber-gertsen analysis; Pilot induced
oscillation; Oswald
efficiency; Pilot
mathematical model; Variable sweep
wing;
Exulans; Variable
static margin; Swept
gull-wing configuration;
O-point;
E-point; Handling
qualities; Gust handling
qualities; Tailless
aircraft;
Pecking; Monnich and
dalldorff criterion;
UCTD
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Agenbag, D. (2008). Longitudinal
handling characteristics of a tailless gull-wing
aircraft. (Masters Thesis). University of Pretoria. Retrieved from http://hdl.handle.net/2263/28011
Chicago Manual of Style (16th Edition):
Agenbag, Daniel. “Longitudinal
handling characteristics of a tailless gull-wing
aircraft.” 2008. Masters Thesis, University of Pretoria. Accessed January 24, 2021.
http://hdl.handle.net/2263/28011.
MLA Handbook (7th Edition):
Agenbag, Daniel. “Longitudinal
handling characteristics of a tailless gull-wing
aircraft.” 2008. Web. 24 Jan 2021.
Vancouver:
Agenbag D. Longitudinal
handling characteristics of a tailless gull-wing
aircraft. [Internet] [Masters thesis]. University of Pretoria; 2008. [cited 2021 Jan 24].
Available from: http://hdl.handle.net/2263/28011.
Council of Science Editors:
Agenbag D. Longitudinal
handling characteristics of a tailless gull-wing
aircraft. [Masters Thesis]. University of Pretoria; 2008. Available from: http://hdl.handle.net/2263/28011

Delft University of Technology
23.
Yilmaz, D.
Identification of manual control behaviour to assess rotorcraft handling qualities.
Degree: 2018, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:00fadafa-0e24-4176-b533-d4b908c91a73
;
urn:NBN:nl:ui:24-uuid:00fadafa-0e24-4176-b533-d4b908c91a73
;
00fadafa-0e24-4176-b533-d4b908c91a73
;
10.4233/uuid:00fadafa-0e24-4176-b533-d4b908c91a73
;
urn:isbn:978-94-6186-966-1
;
urn:NBN:nl:ui:24-uuid:00fadafa-0e24-4176-b533-d4b908c91a73
;
http://resolver.tudelft.nl/uuid:00fadafa-0e24-4176-b533-d4b908c91a73
► Flight safety has been a fundamental aspect of aircraft, and the future demand for wider usage of aerial operations leads to more focus on the…
(more)
▼ Flight safety has been a fundamental aspect of aircraft, and the future demand for wider usage of aerial operations leads to more focus on the flight safety. Particularly rotorcraft require high standards of flight safety due to their inherent features, such as complicated rotary mechanisms, close-to-ground operations, and complex aerodynamic environment. Consequently, rotorcraft pilots need to exert relatively high workload to safely operate these vehicles. An understanding of the interaction between the rotorcraft and the pilot is essential for improving flight safety. This interaction is elaborated by the
Handling Qualities (HQ) discipline, which aims to identify and, if possible predict any deficiency in HQ that could potentially jeopardize safe flight. A typical (and potentially catastrophic) example of a HQ deficiency are the Aircraft / Rotorcraft Pilot Couplings (A/RPC), formerly referred to as Pilot Induced Oscillations (PIO). A/RPC is defined as the involuntary and adverse interaction between the pilot and the vehicle under control. Generally for rotorcraft, the ‘vehicle’ part of this interaction is evaluated by objective HQ criteria and online Rotorcraft Pilot Coupling (RPC) detection tools, whereas the ‘pilot’ part is assessed with subjective pilot ratings. Using subjective ratings has several disadvantages, such as being used at very late stages of the design when a prototype vehicle is already built. Addressing a serious HQ deficiency after this late design stage then requires immerse effort to re-design the vehicle systems and repeat the flight tests...
Advisors/Committee Members: Mulder, M., Pavel, M.D., Pool, D.M., Delft University of Technology.
Subjects/Keywords: Rotorcraft; Handling Qualities; Adverse Rotorcraft Pilot Couplings; Manual Control Behaviour Identification; Pilot Modeling; Pilot Induced Oscillations
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Yilmaz, D. (2018). Identification of manual control behaviour to assess rotorcraft handling qualities. (Doctoral Dissertation). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; urn:NBN:nl:ui:24-uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; 00fadafa-0e24-4176-b533-d4b908c91a73 ; 10.4233/uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; urn:isbn:978-94-6186-966-1 ; urn:NBN:nl:ui:24-uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; http://resolver.tudelft.nl/uuid:00fadafa-0e24-4176-b533-d4b908c91a73
Chicago Manual of Style (16th Edition):
Yilmaz, D. “Identification of manual control behaviour to assess rotorcraft handling qualities.” 2018. Doctoral Dissertation, Delft University of Technology. Accessed January 24, 2021.
http://resolver.tudelft.nl/uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; urn:NBN:nl:ui:24-uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; 00fadafa-0e24-4176-b533-d4b908c91a73 ; 10.4233/uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; urn:isbn:978-94-6186-966-1 ; urn:NBN:nl:ui:24-uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; http://resolver.tudelft.nl/uuid:00fadafa-0e24-4176-b533-d4b908c91a73.
MLA Handbook (7th Edition):
Yilmaz, D. “Identification of manual control behaviour to assess rotorcraft handling qualities.” 2018. Web. 24 Jan 2021.
Vancouver:
Yilmaz D. Identification of manual control behaviour to assess rotorcraft handling qualities. [Internet] [Doctoral dissertation]. Delft University of Technology; 2018. [cited 2021 Jan 24].
Available from: http://resolver.tudelft.nl/uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; urn:NBN:nl:ui:24-uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; 00fadafa-0e24-4176-b533-d4b908c91a73 ; 10.4233/uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; urn:isbn:978-94-6186-966-1 ; urn:NBN:nl:ui:24-uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; http://resolver.tudelft.nl/uuid:00fadafa-0e24-4176-b533-d4b908c91a73.
Council of Science Editors:
Yilmaz D. Identification of manual control behaviour to assess rotorcraft handling qualities. [Doctoral Dissertation]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; urn:NBN:nl:ui:24-uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; 00fadafa-0e24-4176-b533-d4b908c91a73 ; 10.4233/uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; urn:isbn:978-94-6186-966-1 ; urn:NBN:nl:ui:24-uuid:00fadafa-0e24-4176-b533-d4b908c91a73 ; http://resolver.tudelft.nl/uuid:00fadafa-0e24-4176-b533-d4b908c91a73

Georgia Tech
24.
Potter, James Jackson.
Input-shaped manual control of helicopters with suspended loads.
Degree: PhD, Mechanical Engineering, 2013, Georgia Tech
URL: http://hdl.handle.net/1853/50342
► A helicopter can be used to transport a load hanging from a suspension cable. This technique is frequently used in construction, firefighting, and disaster relief…
(more)
▼ A helicopter can be used to transport a load hanging from a suspension cable. This technique is frequently used in construction, firefighting, and disaster relief operations, among other applications. Unfortunately, the suspended load swings, which makes load positioning difficult and can degrade control of the helicopter. This dissertation investigates the use of input shaping (a command-filtering technique for reducing vibration) to mitigate the load swing problem. The investigation is conducted using two different, but complementary, approaches. One approach studies manual tracking tasks, where a human attempts to make a cursor follow an unpredictably moving target. The second approach studies horizontal repositioning maneuvers on small-scale helicopter systems, including a novel testbed that limits the helicopter and suspended load to move in a vertical plane. Both approaches are used to study how input shaping affects control of a flexible element (the suspended load) and a driven base (the helicopter). In manual tracking experiments, conventional input shapers somewhat degraded control of the driven base but greatly improved control of the flexible element. New input shapers were designed to improve load control without negatively affecting base control. A method for adjusting the vibration-limiting aggressiveness of any input shaper between unshaped and fully shaped was also developed. Next, horizontal repositioning maneuvers were performed on the helicopter testbed using a human-pilot-like feedback controller from the literature, with parameter values scaled to match the fast dynamics of the model helicopter. It was found that some input shapers reduced settling time and peak load swing when applied to Attitude Command or Translational Rate Command response types. When the load was used as a position reference instead of the helicopter, the system was unstable without input shaping, and adding input shaping to a Translational Rate Command was able to stabilize the load-positioning system. These results show the potential to improve the safety and efficiency of helicopter suspended load operations.
Advisors/Committee Members: Singhose, William (advisor), Costello, Mark (committee member), Johnson, Eric (committee member), Pritchett, Amy (committee member), Whiteman, Wayne (committee member).
Subjects/Keywords: Helicopter; Input shaping; Command filter; Sling load; Flexible system; Manual control; Human-in-the-loop control; Operator study; Handling qualities; Experimental platform; Dynamic modeling; Helicopters; Flight control; Cranes, derricks, etc. Dynamics; Feedback control systems; Damping (Mechanics)
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Potter, J. J. (2013). Input-shaped manual control of helicopters with suspended loads. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/50342
Chicago Manual of Style (16th Edition):
Potter, James Jackson. “Input-shaped manual control of helicopters with suspended loads.” 2013. Doctoral Dissertation, Georgia Tech. Accessed January 24, 2021.
http://hdl.handle.net/1853/50342.
MLA Handbook (7th Edition):
Potter, James Jackson. “Input-shaped manual control of helicopters with suspended loads.” 2013. Web. 24 Jan 2021.
Vancouver:
Potter JJ. Input-shaped manual control of helicopters with suspended loads. [Internet] [Doctoral dissertation]. Georgia Tech; 2013. [cited 2021 Jan 24].
Available from: http://hdl.handle.net/1853/50342.
Council of Science Editors:
Potter JJ. Input-shaped manual control of helicopters with suspended loads. [Doctoral Dissertation]. Georgia Tech; 2013. Available from: http://hdl.handle.net/1853/50342

Brigham Young University
25.
Foster, Tyler Michael.
Dynamic Stability and Handling Qualities of Small Unmanned-Aerial-Vehicles UNMANNED-AERIAL-VEHICLES.
Degree: MS, 2004, Brigham Young University
URL: https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=1218&context=etd
► General aircraft dynamic stability theory was used to predict the natural frequencies, damping ratios and time constants of the dynamic modes for three specific…
(more)
▼ General aircraft dynamic stability theory was used to predict the natural frequencies, damping ratios and time constants of the dynamic modes for three specific small UAVs with wingspans on the scale from 0.6 meters to 1.2 meters. Using USAF DatCom methods, a spreadsheet program for predicting the dynamic stability and handling qualities of small UAVs was created for use in the design stage of new small UAV concept development. This program was verified by inputting data for a Cessna-182, and by then comparing the program output with that of a similar program developed by DAR Corporation. Predictions with acceptable errors were made for all of the dynamic modes except for the spiral mode. The design tool was also used to verify and develop dynamic stability and handling qualities design guidelines for small UAV designers. Using this design tool, it was observed that small UAVs tend to exhibit higher natural frequencies of oscillation for all of the dynamic modes. Comparing the program outputs with military handling qualities specifications, the small UAVs at standard configurations fell outside the range of acceptable handling qualities for short-period mode natural frequency, even though multiple test pilots rated the flying qualities as acceptable. Using dynamic scaling methods to adjust the current military standards for the short period mode, a new scale was proposed specifically for small UAVs. This scale was verified by conducting flight tests of three small UAVs at various configurations until poor handling qualities were observed. These transitions were observed to occur at approximately the boundary predicted by the new, adjusted scale.
Subjects/Keywords: Unmanned-Aerial-Vehicles; UAVs; UAV; Dynamic Stability; Static Stability; Handling Qualities; Flying Qualities; USAF DatCom; MIL-F-8785C; Dynamic Scaling; short period; phugoid; dutch-roll; spiral; roll; Mechanical Engineering
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Foster, T. M. (2004). Dynamic Stability and Handling Qualities of Small Unmanned-Aerial-Vehicles UNMANNED-AERIAL-VEHICLES. (Masters Thesis). Brigham Young University. Retrieved from https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=1218&context=etd
Chicago Manual of Style (16th Edition):
Foster, Tyler Michael. “Dynamic Stability and Handling Qualities of Small Unmanned-Aerial-Vehicles UNMANNED-AERIAL-VEHICLES.” 2004. Masters Thesis, Brigham Young University. Accessed January 24, 2021.
https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=1218&context=etd.
MLA Handbook (7th Edition):
Foster, Tyler Michael. “Dynamic Stability and Handling Qualities of Small Unmanned-Aerial-Vehicles UNMANNED-AERIAL-VEHICLES.” 2004. Web. 24 Jan 2021.
Vancouver:
Foster TM. Dynamic Stability and Handling Qualities of Small Unmanned-Aerial-Vehicles UNMANNED-AERIAL-VEHICLES. [Internet] [Masters thesis]. Brigham Young University; 2004. [cited 2021 Jan 24].
Available from: https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=1218&context=etd.
Council of Science Editors:
Foster TM. Dynamic Stability and Handling Qualities of Small Unmanned-Aerial-Vehicles UNMANNED-AERIAL-VEHICLES. [Masters Thesis]. Brigham Young University; 2004. Available from: https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=1218&context=etd
26.
Tritschler, John.
Contributions to the Characterization and Mitigation of Rotorcraft Brownout.
Degree: Aerospace Engineering, 2012, University of Maryland
URL: http://hdl.handle.net/1903/13061
► Rotorcraft brownout, the condition in which the flow field of a rotorcraft mobilizes sediment from the ground to generate a cloud that obscures the pilot's…
(more)
▼ Rotorcraft brownout, the condition in which the flow field of a rotorcraft mobilizes sediment from the ground to generate a cloud that obscures the pilot's field of view, continues to be a significant hazard to civil and military rotorcraft operations. This dissertation presents methodologies for: (i) the systematic mitigation of rotorcraft brownout through operational and design strategies and (ii) the quantitative characterization of the visual degradation caused by a brownout cloud.
In Part I of the dissertation, brownout mitigation strategies are developed through simulation-based brownout studies that are mathematically formulated within a numerical optimization framework. Two optimization studies are presented. The first study involves the determination of approach-to-landing maneuvers that result in reduced brownout severity. The second study presents a potential methodology for the design of helicopter rotors with improved brownout characteristics. The results of both studies indicate that the fundamental mechanisms underlying brownout mitigation are aerodynamic in nature, and the evolution of a ground vortex ahead of the rotor disk is seen to be a key element in the development of a brownout cloud.
In Part II of the dissertation, brownout cloud characterizations are based upon the Modulation Transfer Function (MTF), a metric commonly used in the optics community for the characterization of imaging systems. The use of the MTF in experimentation is examined first, and the application of MTF calculation and interpretation methods to actual flight test data is described. The potential for predicting the MTF from numerical simulations is examined second, and an initial methodology is presented for the prediction of the MTF of a brownout cloud. Results from the experimental and analytical studies rigorously quantify the intuitively-known facts that the visual degradation caused by brownout is a space and time-dependent phenomenon, and that high spatial frequency features, i.e., fine-grained detail, are obscured before low spatial frequency features, i.e., large objects. As such, the MTF is a metric that is amenable to
Handling Qualities (HQ) analyses.
Advisors/Committee Members: Celi, Roberto (advisor).
Subjects/Keywords: Aerospace engineering; Degraded Visual Environments (DVE); Handling Qualities (HQ); Modulation Transfer Function (MTF); Rotorcraft brownout; Trajectory optimization
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Tritschler, J. (2012). Contributions to the Characterization and Mitigation of Rotorcraft Brownout. (Thesis). University of Maryland. Retrieved from http://hdl.handle.net/1903/13061
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Tritschler, John. “Contributions to the Characterization and Mitigation of Rotorcraft Brownout.” 2012. Thesis, University of Maryland. Accessed January 24, 2021.
http://hdl.handle.net/1903/13061.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Tritschler, John. “Contributions to the Characterization and Mitigation of Rotorcraft Brownout.” 2012. Web. 24 Jan 2021.
Vancouver:
Tritschler J. Contributions to the Characterization and Mitigation of Rotorcraft Brownout. [Internet] [Thesis]. University of Maryland; 2012. [cited 2021 Jan 24].
Available from: http://hdl.handle.net/1903/13061.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Tritschler J. Contributions to the Characterization and Mitigation of Rotorcraft Brownout. [Thesis]. University of Maryland; 2012. Available from: http://hdl.handle.net/1903/13061
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
.