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Delft University of Technology
1.
Stolk, Rob (author).
Minimum drag control allocation for the Innovative Control Effector aircraft: Optimal use of control redundancy on modern fighters.
Degree: 2017, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:43ce35bc-eb94-4c7b-a826-80a80e24a6d6 
► The Innovative Control Effector model is a tailless delta-wing aircraft concept equipped with 11 control surfaces with overlapping functionality and two-directional thrust vectoring. The high…
(more)
▼ The Innovative Control Effector model is a tailless delta-wing aircraft concept equipped with 11 control surfaces with overlapping functionality and two-directional thrust vectoring. The high level of redundancy makes it an interesting object for research on mission-specific control allocation. A (spline-based) incremental control allocation approach is proposed to deal with nonlinear input functions and aerodynamic interaction between multiple control surfaces. Two control allocation modes to minimize drag are proposed and assessed in a general flight scenario. With both modes the average drag is reduced by about 6.5% relative to a standard control allocation scheme. Sensitivity analysis points out that one mode is vulnerable to the choice of initial parameters, whereas the other is primarily sensitive to the accuracy of the onboard model. Improvement of the ICE aerodynamic model is necessary to substantiate the true potential of mission-specific control allocation for next generation aircraft.
Control & Simulation
Advisors/Committee Members: de Visser, Coen (mentor), Delft University of Technology (degree granting institution).
Subjects/Keywords: Control Allocation; Innovative Control Effectors; ICE; Incremental Control; Tailless Aircraft; Drag
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APA (6th Edition):
Stolk, R. (. (2017). Minimum drag control allocation for the Innovative Control Effector aircraft: Optimal use of control redundancy on modern fighters. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:43ce35bc-eb94-4c7b-a826-80a80e24a6d6
Chicago Manual of Style (16th Edition):
Stolk, Rob (author). “Minimum drag control allocation for the Innovative Control Effector aircraft: Optimal use of control redundancy on modern fighters.” 2017. Masters Thesis, Delft University of Technology. Accessed January 25, 2021.
http://resolver.tudelft.nl/uuid:43ce35bc-eb94-4c7b-a826-80a80e24a6d6.
MLA Handbook (7th Edition):
Stolk, Rob (author). “Minimum drag control allocation for the Innovative Control Effector aircraft: Optimal use of control redundancy on modern fighters.” 2017. Web. 25 Jan 2021.
Vancouver:
Stolk R(. Minimum drag control allocation for the Innovative Control Effector aircraft: Optimal use of control redundancy on modern fighters. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Jan 25].
Available from: http://resolver.tudelft.nl/uuid:43ce35bc-eb94-4c7b-a826-80a80e24a6d6.
Council of Science Editors:
Stolk R(. Minimum drag control allocation for the Innovative Control Effector aircraft: Optimal use of control redundancy on modern fighters. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:43ce35bc-eb94-4c7b-a826-80a80e24a6d6
University of Missouri – Kansas City
2.
Kraft, Tyler E.
Extended Range Tactical Resupply Using Tailless UAV.
Degree: 2017, University of Missouri – Kansas City
URL: http://hdl.handle.net/10355/62665
► An alternative approach for precision aerial delivery utilizing a flying wing for controllable forward glide is presented. Although effective, current delivery methods either display a…
(more)
▼ An alternative approach for precision aerial delivery utilizing a flying wing for
controllable forward glide is presented. Although effective, current delivery methods
either display a lack of control, or require close standoff distances, potentially endangering
aircraft personnel as well as bystanders. Hardware-in-the-loop simulations provide
an efficient method for evaluating various wing designs and actuation configurations.
Four control surface configurations are presented and evaluated, encompassing traditional
aircraft and ram-air parafoil control approaches. Fixed-wing and multirotor unmanned
aircraft-basedflight tests were conducted to evaluate the controllability and handling performance of the various configurations of both a fixed wing model and a model with collapsing wings. A manufacturing process was developed to allow repeatable results in the
field using cheap, mostly disposable materials. A powered flying wing model was used to
maximize data collection in later stages of software development. Data collected during
flight tests was used to create a model of the system and develop a Nonlinear Dynamic
Inversion controller for autonomous flight. The NDI controller was able to provide stable
flight in pitch, but will need more development to control yaw, instead an intentional bias
was built in to show proof of concept for direct yaw control. The results demonstrate the
feasibility of the flying wing-based aerial delivery; however, significant challenges remain
regarding the stability and scalability of the system.
Advisors/Committee Members: Fields, Travis (advisor).
Subjects/Keywords: Thesis – University of Missouri – Kansas City – Engineering; Delivery of goods; Drone aircraft; Airplanes, Tailless
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APA (6th Edition):
Kraft, T. E. (2017). Extended Range Tactical Resupply Using Tailless UAV. (Thesis). University of Missouri – Kansas City. Retrieved from http://hdl.handle.net/10355/62665
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):
Kraft, Tyler E. “Extended Range Tactical Resupply Using Tailless UAV.” 2017. Thesis, University of Missouri – Kansas City. Accessed January 25, 2021.
http://hdl.handle.net/10355/62665.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Kraft, Tyler E. “Extended Range Tactical Resupply Using Tailless UAV.” 2017. Web. 25 Jan 2021.
Vancouver:
Kraft TE. Extended Range Tactical Resupply Using Tailless UAV. [Internet] [Thesis]. University of Missouri – Kansas City; 2017. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/10355/62665.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Kraft TE. Extended Range Tactical Resupply Using Tailless UAV. [Thesis]. University of Missouri – Kansas City; 2017. Available from: http://hdl.handle.net/10355/62665
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Cranfield University
3.
de Castro, Helena V.
Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft.
Degree: PhD, School of Engineering, 2003, Cranfield University
URL: http://hdl.handle.net/1826/119
► The blended-wing-body (BWB) configuration appears as a promising contender for the next generation of large transport aircraft. The idea of blending the wing with the…
(more)
▼ The blended-wing-body (BWB) configuration appears as a promising contender for the next generation of large transport aircraft. The idea of blending the wing with the fuselage and eliminating the tail is not new, it has long been known that tailless aircraft can suffer from stability and control problems that must be addressed early in the design. This thesis is concerned with identifying and then evaluating the flight dynamics, stability, flight controls and handling qualities of a generic BWB large transport aircraft concept.
Longitudinal and lateral-directional static and dynamic stability analysis using aerodynamic data representative of different BWB configurations enabled a better understanding of the BWB aircraft characteristics and identification of the mechanisms that influence its behaviour. The static stability studies revealed that there is limited control power both for the longitudinal and lateral-directional motion. The solution for the longitudinal problem is to limit the static margins to small values around the neutral point, and even to use negative static margins. However, for the directional control problem the solution is to investigate alternative ways of generating directional control power. Additional investigation uncovered dynamic instability due to the low and negative longitudinal and directional static stability. Furthermore, adverse roll and yaw responses were found to aileron inputs.
The implementation of a pitch rate command/attitude hold flight control system (FCS) improved the longitudinal basic BWB characteristics to satisfactory levels, or Level 1, flying and handling qualities (FHQ). Although the lateral-directional command and stability FCS also improved the BWB flying and handling qualities it was demonstrated that Level 1 was not achieved for all flight conditions due to limited directional control power.
The possibility to use the conventional FHQs criteria and requirements for FCS design and FHQs assessment on BWB configurations was also investigated. Hence, a limited set of simulation trials were undertaken using an augmented BWB configuration. The longitudinal Bandwidth/Phase delay/Gibson dropback criteria, as suggested by the military standards, together with the Generic Control Anticipation Parameter (GCAP) proved possible to use to assess flying and handling qualities of BWB aircraft. For the lateral-directional motion the MIL-F-8785C criteria were used. Although it is possible to assess the FHQ of BWB configuartions using these criteria, more research is recommended specifically on the lateral-directional FHQs criteria and requirements of highly augmented large transport aircraft.
Subjects/Keywords: Tailless aircraft; Aircraft handling; Blended wing body; Fly by wire; Aircraft stability
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APA (6th Edition):
de Castro, H. V. (2003). Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft. (Doctoral Dissertation). Cranfield University. Retrieved from http://hdl.handle.net/1826/119
Chicago Manual of Style (16th Edition):
de Castro, Helena V. “Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft.” 2003. Doctoral Dissertation, Cranfield University. Accessed January 25, 2021.
http://hdl.handle.net/1826/119.
MLA Handbook (7th Edition):
de Castro, Helena V. “Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft.” 2003. Web. 25 Jan 2021.
Vancouver:
de Castro HV. Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft. [Internet] [Doctoral dissertation]. Cranfield University; 2003. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/1826/119.
Council of Science Editors:
de Castro HV. Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft. [Doctoral Dissertation]. Cranfield University; 2003. Available from: http://hdl.handle.net/1826/119
Cranfield University
4.
de Castro, Helena V.
Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft.
Degree: PhD, 2003, Cranfield University
URL: http://dspace.lib.cranfield.ac.uk/handle/1826/119
;
http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.484641
► The blended-wing-body (BWB) configuration appears as a promising contender for the next generation of large transport aircraft. The idea of blending the wing with the…
(more)
▼ The blended-wing-body (BWB) configuration appears as a promising contender for the next generation of large transport aircraft. The idea of blending the wing with the fuselage and eliminating the tail is not new, it has long been known that tailless aircraft can suffer from stability and control problems that must be addressed early in the design. This thesis is concerned with identifying and then evaluating the flight dynamics, stability, flight controls and handling qualities of a generic BWB large transport aircraft concept. Longitudinal and lateral-directional static and dynamic stability analysis using aerodynamic data representative of different BWB configurations enabled a better understanding of the BWB aircraft characteristics and identification of the mechanisms that influence its behaviour. The static stability studies revealed that there is limited control power both for the longitudinal and lateral-directional motion. The solution for the longitudinal problem is to limit the static margins to small values around the neutral point, and even to use negative static margins. However, for the directional control problem the solution is to investigate alternative ways of generating directional control power. Additional investigation uncovered dynamic instability due to the low and negative longitudinal and directional static stability. Furthermore, adverse roll and yaw responses were found to aileron inputs. The implementation of a pitch rate command/attitude hold flight control system (FCS) improved the longitudinal basic BWB characteristics to satisfactory levels, or Level 1, flying and handling qualities (FHQ). Although the lateral-directional command and stability FCS also improved the BWB flying and handling qualities it was demonstrated that Level 1 was not achieved for all flight conditions due to limited directional control power. The possibility to use the conventional FHQs criteria and requirements for FCS design and FHQs assessment on BWB configurations was also investigated. Hence, a limited set of simulation trials were undertaken using an augmented BWB configuration. The longitudinal Bandwidth/Phase delay/Gibson dropback criteria, as suggested by the military standards, together with the Generic Control Anticipation Parameter (GCAP) proved possible to use to assess flying and handling qualities of BWB aircraft. For the lateral-directional motion the MIL-F-8785C criteria were used. Although it is possible to assess the FHQ of BWB configuartions using these criteria, more research is recommended specifically on the lateral-directional FHQs criteria and requirements of highly augmented large transport aircraft.
Subjects/Keywords: 629.133340423; Tailless aircraft; Aircraft handling; Blended wing body; Fly by wire; Aircraft stability
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Manager
APA (6th Edition):
de Castro, H. V. (2003). Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft. (Doctoral Dissertation). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/119 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.484641
Chicago Manual of Style (16th Edition):
de Castro, Helena V. “Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft.” 2003. Doctoral Dissertation, Cranfield University. Accessed January 25, 2021.
http://dspace.lib.cranfield.ac.uk/handle/1826/119 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.484641.
MLA Handbook (7th Edition):
de Castro, Helena V. “Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft.” 2003. Web. 25 Jan 2021.
Vancouver:
de Castro HV. Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft. [Internet] [Doctoral dissertation]. Cranfield University; 2003. [cited 2021 Jan 25].
Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/119 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.484641.
Council of Science Editors:
de Castro HV. Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft. [Doctoral Dissertation]. Cranfield University; 2003. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/119 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.484641
North Carolina State University
5.
Cusher, Aaron Anthony.
Ideal Lift Distributions and Flap Settings for Adaptive Tailless Aircraft.
Degree: MS, Aerospace Engineering, 2006, North Carolina State University
URL: http://www.lib.ncsu.edu/resolver/1840.16/1803
► With ever increasing maturity in the field of subsonic aircraft design, there exists the desire to tailor the performance of an aircraft to suit specific…
(more)
▼ With ever increasing maturity in the field of subsonic
aircraft design, there exists the desire to tailor the performance of an
aircraft to suit specific flight conditions. This has led to several adaptive-wing approaches which seek to improve
aircraft performance by changing the wing shape in flight, resulting in drag reduction. One such adaptive-wing approach that has gained considerable popularity is the use of multiple spanwise trailing-edge flaps which are used to optimally distribute the lift of the wing such that drag is minimized. Recent research has been conducted utilizing such a technique applied to an
aircraft with a wing-tail configuration and discussed the need to extend these methods to
tailless, or all-wing,
aircraft, thereby improving design possibilities to include unconventional configurations. The current work explores
tailless aircraft configurations which utilize multiple trailing-edge flaps for the purpose of wing adaptation and drag reduction.
As with all
tailless aircraft design, the trailing-edge flap settings, and thus wing lift distribution, must be solved while satisfying a longitudinal-pitching-moment constraint in order to ensure longitudinal stability and trim. This is due to the lack of a secondary horizontal surface, such as a tail or canard, which is typically used for stability and trim purposes. The current work implements a numerical approach which was developed to solve for the optimal flap scheduling of a wing with multiple trailing-edge flaps for various flight conditions. Theory presented by R.T. Jones was used as a starting point to solve for the target lift distribution resulting in minimized induced drag with a pitching moment constraint. Also utilized were the ideas of basic and additional lift, as well as thin airfoil theory relations in order to reduce both induced and profile drag by the redistribution of wing lift along its span. The cases were solved with longitudinal trim and lift constraints. The results were presented for planar, tapered wings with multiple quarter-chord sweep angles as well as multiple airfoil sections in order to verify the theory and gain insight into design capabilities and trends. It has been shown by these results that such adaptive wing methods are applicable and beneficial to
tailless aircraft configurations, as reductions in both induced and profile drag have been achieved. In addition, the method is successful for achieving longitudinal trim, and was explored successfully for multiple static margins in order to test the consequence of different longitudinal stability considerations.
Advisors/Committee Members: Dr. Ashok Gopalarathnam, Committee Chair (advisor), Dr. Robert T. Nagel, Committee Member (advisor), Dr. Larry M. Silverberg, Committee Member (advisor).
Subjects/Keywords: Adaptive; Flap Settings; Lift Distributions; Ideal; Tailless Aircraft
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APA (6th Edition):
Cusher, A. A. (2006). Ideal Lift Distributions and Flap Settings for Adaptive Tailless Aircraft. (Thesis). North Carolina State University. Retrieved from http://www.lib.ncsu.edu/resolver/1840.16/1803
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):
Cusher, Aaron Anthony. “Ideal Lift Distributions and Flap Settings for Adaptive Tailless Aircraft.” 2006. Thesis, North Carolina State University. Accessed January 25, 2021.
http://www.lib.ncsu.edu/resolver/1840.16/1803.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Cusher, Aaron Anthony. “Ideal Lift Distributions and Flap Settings for Adaptive Tailless Aircraft.” 2006. Web. 25 Jan 2021.
Vancouver:
Cusher AA. Ideal Lift Distributions and Flap Settings for Adaptive Tailless Aircraft. [Internet] [Thesis]. North Carolina State University; 2006. [cited 2021 Jan 25].
Available from: http://www.lib.ncsu.edu/resolver/1840.16/1803.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Cusher AA. Ideal Lift Distributions and Flap Settings for Adaptive Tailless Aircraft. [Thesis]. North Carolina State University; 2006. Available from: http://www.lib.ncsu.edu/resolver/1840.16/1803
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Brno University of Technology
6.
Prokop, Vít.
Vývoj a vlastnosti bezocasých letadel: Evolution and Characteristics of Tailess Aircraft.
Degree: 2018, Brno University of Technology
URL: http://hdl.handle.net/11012/1703
► This bachelor work is about Evolution and Characteristics of Tailless Aircraft divided into two sections. The first section will cover the questions about stability and…
(more)
▼ This bachelor work is about Evolution and Characteristics of
Tailless Aircraft divided into two sections. The first section will cover the questions about stability and maneuverability of the aircrafts.The second section will cover a type overview of these aircrafts and a comparison of their flying characteristics.
Advisors/Committee Members: Daněk, Vladimír (advisor), Vaněk, František (referee).
Subjects/Keywords: Horten; Fauvel; Lippisch; Marske; SWIFT; samokřídlo; bezocasé letadlo; závěsný kluzák; profil; zkroucení křídla; stabilita; Horten; Fauvel; Lippisch; Marske; SWIFT; allwing aircraft; tailless aircraft; hangglider; airfoil; twisted wing; stability
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Manager
APA (6th Edition):
Prokop, V. (2018). Vývoj a vlastnosti bezocasých letadel: Evolution and Characteristics of Tailess Aircraft. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/1703
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):
Prokop, Vít. “Vývoj a vlastnosti bezocasých letadel: Evolution and Characteristics of Tailess Aircraft.” 2018. Thesis, Brno University of Technology. Accessed January 25, 2021.
http://hdl.handle.net/11012/1703.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Prokop, Vít. “Vývoj a vlastnosti bezocasých letadel: Evolution and Characteristics of Tailess Aircraft.” 2018. Web. 25 Jan 2021.
Vancouver:
Prokop V. Vývoj a vlastnosti bezocasých letadel: Evolution and Characteristics of Tailess Aircraft. [Internet] [Thesis]. Brno University of Technology; 2018. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/11012/1703.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Prokop V. Vývoj a vlastnosti bezocasých letadel: Evolution and Characteristics of Tailess Aircraft. [Thesis]. Brno University of Technology; 2018. Available from: http://hdl.handle.net/11012/1703
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
7.
Langston, Sarah.
Low-Speed Stability and Control of Exploratory Tailless Long-Range Supersonic Configurations.
Degree: 2015, University of Washington
URL: http://hdl.handle.net/1773/33542
► This thesis presents studies of the low-speed stability and control of a representative long-range supersonic flight vehicle. The aircraft of interest is a research uninhabited…
(more)
▼ This thesis presents studies of the low-speed stability and control of a representative long-range supersonic flight vehicle. The
aircraft of interest is a research uninhabited aerial vehicle (R-UAV), a 1/16th scaled model of a concept supersonic business jet. Evaluation of stability and control characteristics is based on a linear time-invariant state-space small-perturbations approach. Low-speed wind tunnel results together with unsteady aerodynamic panel method analysis are the basis for the aerodynamic stability derivatives used. The main goal of this work is to study the effects on stability and controllability of reduction in size or complete elimination of tail surfaces, with particular emphasis on the vertical tail.
Advisors/Committee Members: Livne, Eli (advisor).
Subjects/Keywords: Aircraft; Supersonic; Tailless; Aerospace engineering; aeronautics and astronautics
…8.3 Root Locus Plot of the Lat-Dir Tailless R-UAV Poles at Various Yaw
and Roll Damper Gains… …8.4 Time History of Damper Augmented Tailless R-UAV to a 1 Degree
Sideslip Angle… …8.5 Root Locus Plot of the Lat-Dir Tailless R-UAV Poles at Various Yaw
and Roll Damper Gains… …8.6 Time History of Damper Augmented Tailless R-UAV to a 1 Degree
Sideslip Angle… …8.9 Control Surface Responses Required to Stabilize Tailless R-UAV from
the above State…
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Manager
APA (6th Edition):
Langston, S. (2015). Low-Speed Stability and Control of Exploratory Tailless Long-Range Supersonic Configurations. (Thesis). University of Washington. Retrieved from http://hdl.handle.net/1773/33542
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):
Langston, Sarah. “Low-Speed Stability and Control of Exploratory Tailless Long-Range Supersonic Configurations.” 2015. Thesis, University of Washington. Accessed January 25, 2021.
http://hdl.handle.net/1773/33542.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Langston, Sarah. “Low-Speed Stability and Control of Exploratory Tailless Long-Range Supersonic Configurations.” 2015. Web. 25 Jan 2021.
Vancouver:
Langston S. Low-Speed Stability and Control of Exploratory Tailless Long-Range Supersonic Configurations. [Internet] [Thesis]. University of Washington; 2015. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/1773/33542.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Langston S. Low-Speed Stability and Control of Exploratory Tailless Long-Range Supersonic Configurations. [Thesis]. University of Washington; 2015. Available from: http://hdl.handle.net/1773/33542
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Pretoria
8.
[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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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 25, 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. 25 Jan 2021.
Vancouver:
author] [. Longitudinal handling characteristics of a tailless
gull-wing aircraft
. [Internet] [Masters thesis]. University of Pretoria; 2008. [cited 2021 Jan 25].
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
9.
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
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):
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 25, 2021.
http://hdl.handle.net/2263/28011.
MLA Handbook (7th Edition):
Agenbag, Daniel. “Longitudinal
handling characteristics of a tailless gull-wing
aircraft.” 2008. Web. 25 Jan 2021.
Vancouver:
Agenbag D. Longitudinal
handling characteristics of a tailless gull-wing
aircraft. [Internet] [Masters thesis]. University of Pretoria; 2008. [cited 2021 Jan 25].
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
10.
Mardanpour, Pezhman.
Effects of engine placement and morphing on nonlinear aeroelastic behavior of flying wing aircraft.
Degree: PhD, Aerospace Engineering, 2013, Georgia Tech
URL: http://hdl.handle.net/1853/50268
► Effects of engine placement on flutter characteristics of a very flexible high-aspect-ratio wing are investigated using the code NATASHA (Nonlinear Aeroelastic Trim And Stability of…
(more)
▼ Effects of engine placement on flutter characteristics of a very flexible high-aspect-ratio wing are investigated using the code NATASHA (Nonlinear Aeroelastic Trim And Stability of HALE
Aircraft). The analysis was validated against published results for divergence and flutter of swept wings and found to be in excellent agreement with the experimental results of the classical wing of Goland. Moreover, modal frequencies and damping obtained for the Goland wing were found in excellent agreement with published results based on a new continuum-based unsteady aerodynamic formulation. Gravity for this class of wings plays an important role in flutter characteristics. In the absence of aerodynamic and gravitational forces and without an engine, the kinetic energy of the first two modes are calculated. Maximum and minimum flutter speed locations coincide with the area of minimum and maximum kinetic energy of the second bending and torsion modes. Time-dependent dynamic behavior of a turboshaft engine (JetCat SP5) is simulated with a transient engine model and the nonlinear aeroelastic response of the wing to the engine's time-dependent thrust and dynamic excitation is presented. Below the flutter speed, at the wing tip and behind the elastic axis, the impulse engine excitation leads to a stable limit cycle oscillation; and for the ramp kind of excitation, beyond the flutter speed, at 75% span, behind the elastic axis, it produces chaotic oscillation of the wing. Both the excitations above the flutter speed are stabilized, on the inboard portion of the wing.
Effects of engine placement and sweep on flutter characteristics of a backswept flying wing resembling the Horten IV are explored using NATASHA. This
aircraft exhibits a non-oscillatory yawing instability, expected in
aircraft with neither a vertical tail nor yaw control. More important, however, is the presence of a low frequency “body-freedom flutter” mode. The
aircraft center of gravity was held fixed during the study, which allowed
aircraft controls to trim similarly for each engine location, and minimized flutter speed variations along the inboard span. Maximum flutter speed occurred for engine placement just outboard of 60% span with engine center of gravity forward of the elastic axis. The body-freedom flutter mode was largely unaffected by the engine placement except for cases in which the engine is placed at the wing tip and near the elastic axis. In the absence of engines, aerodynamics, and gravity, a region of minimum kinetic energy density for the first symmetric free-free bending mode is also near the 60% span. A possible relationship between the favorable flutter characteristics obtained by placing the engines at that point and the region of minimum kinetic energy is briefly explored.
Effects of multiple engine placement on a similar type of
aircraft are studied. The results showed that multiple engine placement increases flutter speed particularly when the engines are placed in the outboard portion of the wing (60% to 70% span), forward of the elastic…
Advisors/Committee Members: Hodges, Dewey H. (advisor), Kardomateas, George A. (committee member), Yavari, Arash (committee member), Rimoli, Julian J. (committee member), Kiessling, Fritz (committee member).
Subjects/Keywords: Nonlinear aeroelasticity; Follower force; Effects of engine placement; HALE aircraft; Flying wing aircraft; Area of minimum kinetic energy; Passive morphing; Solar powered flying wing; Airplanes, Tailless; Aeroelasticity; Solar airplanes; Airplanes
…INTRODUCTION
1.1
Flying wing aircraft
A flying wing is a tailless fixed-wing aircraft with no… …73
98
Aircraft mass balance… …74
99
Effect of engine placement and aircraft center of gravity with zero offset from the… …75
100 Contour of normalized flutter speed at η = 0.65, keeping aircraft c.g. constant… …75
101 Contour of normalized flutter frequency at η = 0.65, keeping aircraft c.g. constant…
Record Details
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Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Mardanpour, P. (2013). Effects of engine placement and morphing on nonlinear aeroelastic behavior of flying wing aircraft. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/50268
Chicago Manual of Style (16th Edition):
Mardanpour, Pezhman. “Effects of engine placement and morphing on nonlinear aeroelastic behavior of flying wing aircraft.” 2013. Doctoral Dissertation, Georgia Tech. Accessed January 25, 2021.
http://hdl.handle.net/1853/50268.
MLA Handbook (7th Edition):
Mardanpour, Pezhman. “Effects of engine placement and morphing on nonlinear aeroelastic behavior of flying wing aircraft.” 2013. Web. 25 Jan 2021.
Vancouver:
Mardanpour P. Effects of engine placement and morphing on nonlinear aeroelastic behavior of flying wing aircraft. [Internet] [Doctoral dissertation]. Georgia Tech; 2013. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/1853/50268.
Council of Science Editors:
Mardanpour P. Effects of engine placement and morphing on nonlinear aeroelastic behavior of flying wing aircraft. [Doctoral Dissertation]. Georgia Tech; 2013. Available from: http://hdl.handle.net/1853/50268
. 
Open Access Theses and Dissertations
