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Dept: Aerospace Engineering

You searched for subject:(Trajectory). Showing records 1 – 30 of 82 total matches.

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Georgia Tech

1. Chen, Gene Lamar. MACHINE LEARNING REGRESSION FOR ESTIMATING CHARACTERISTICS OF LOW-THRUST TRANSFERS.

Degree: MS, Aerospace Engineering, 2019, Georgia Tech

 In this thesis, a methodology for training machine learning algorithms to predict the fuel and time costs of low-thrust trajectories between two objects is developed.… (more)

Subjects/Keywords: Low-thrust; Continuous thrust; Trajectory; Trajectory design; Astrodynamics; Orbit; Orbital transfer; Optimization; Machine learning; Regression; Design of experiments; Trajectory optimization

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Chen, G. L. (2019). MACHINE LEARNING REGRESSION FOR ESTIMATING CHARACTERISTICS OF LOW-THRUST TRANSFERS. (Masters Thesis). Georgia Tech. Retrieved from http://hdl.handle.net/1853/61316

Chicago Manual of Style (16th Edition):

Chen, Gene Lamar. “MACHINE LEARNING REGRESSION FOR ESTIMATING CHARACTERISTICS OF LOW-THRUST TRANSFERS.” 2019. Masters Thesis, Georgia Tech. Accessed July 17, 2019. http://hdl.handle.net/1853/61316.

MLA Handbook (7th Edition):

Chen, Gene Lamar. “MACHINE LEARNING REGRESSION FOR ESTIMATING CHARACTERISTICS OF LOW-THRUST TRANSFERS.” 2019. Web. 17 Jul 2019.

Vancouver:

Chen GL. MACHINE LEARNING REGRESSION FOR ESTIMATING CHARACTERISTICS OF LOW-THRUST TRANSFERS. [Internet] [Masters thesis]. Georgia Tech; 2019. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/1853/61316.

Council of Science Editors:

Chen GL. MACHINE LEARNING REGRESSION FOR ESTIMATING CHARACTERISTICS OF LOW-THRUST TRANSFERS. [Masters Thesis]. Georgia Tech; 2019. Available from: http://hdl.handle.net/1853/61316


Penn State University

2. Tu, Chenmeng. Application of a Homotopy Method to Low-Thrust Trajectory Optimization.

Degree: MS, Aerospace Engineering, 2008, Penn State University

 Continuous optimization methods, historically classified into direct and indirect method categories, have demonstrated notable success in continuous-thrust trajectory optimization. An optimization problem is transformed into… (more)

Subjects/Keywords: Trajectory Optimization; Low-Thrust; Homotopy Method

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APA (6th Edition):

Tu, C. (2008). Application of a Homotopy Method to Low-Thrust Trajectory Optimization. (Masters Thesis). Penn State University. Retrieved from https://etda.libraries.psu.edu/catalog/8862

Chicago Manual of Style (16th Edition):

Tu, Chenmeng. “Application of a Homotopy Method to Low-Thrust Trajectory Optimization.” 2008. Masters Thesis, Penn State University. Accessed July 17, 2019. https://etda.libraries.psu.edu/catalog/8862.

MLA Handbook (7th Edition):

Tu, Chenmeng. “Application of a Homotopy Method to Low-Thrust Trajectory Optimization.” 2008. Web. 17 Jul 2019.

Vancouver:

Tu C. Application of a Homotopy Method to Low-Thrust Trajectory Optimization. [Internet] [Masters thesis]. Penn State University; 2008. [cited 2019 Jul 17]. Available from: https://etda.libraries.psu.edu/catalog/8862.

Council of Science Editors:

Tu C. Application of a Homotopy Method to Low-Thrust Trajectory Optimization. [Masters Thesis]. Penn State University; 2008. Available from: https://etda.libraries.psu.edu/catalog/8862


University of Texas – Austin

3. -9883-5836. Patched periodic orbits : a systematic strategy for low-energy trajectory and moon tour design.

Degree: Aerospace Engineering, 2018, University of Texas – Austin

 The implementation of low-energy trajectories has opened a new paradigm in trajectory design, where, at the cost of long transfer times, low-fuel consumption missions opened… (more)

Subjects/Keywords: Low-energy trajectory; Astrodynamics; Celestial mechanics; Circular restricted three-body problem; Periodic orbits; Mission design; Trajectory optimization; Galilean moon tours

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APA (6th Edition):

-9883-5836. (2018). Patched periodic orbits : a systematic strategy for low-energy trajectory and moon tour design. (Thesis). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/68679

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16th Edition):

-9883-5836. “Patched periodic orbits : a systematic strategy for low-energy trajectory and moon tour design.” 2018. Thesis, University of Texas – Austin. Accessed July 17, 2019. http://hdl.handle.net/2152/68679.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

-9883-5836. “Patched periodic orbits : a systematic strategy for low-energy trajectory and moon tour design.” 2018. Web. 17 Jul 2019.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Vancouver:

-9883-5836. Patched periodic orbits : a systematic strategy for low-energy trajectory and moon tour design. [Internet] [Thesis]. University of Texas – Austin; 2018. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/2152/68679.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

-9883-5836. Patched periodic orbits : a systematic strategy for low-energy trajectory and moon tour design. [Thesis]. University of Texas – Austin; 2018. Available from: http://hdl.handle.net/2152/68679

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete
Not specified: Masters Thesis or Doctoral Dissertation


University of Michigan

4. Patel, Prashant R. Automating Interplanetary Trajectory Generation for Electric Propulsion Trade Studies.

Degree: PhD, Aerospace Engineering, 2008, University of Michigan

 The goal of this work is to provide methods which can be used to auto-generate feasible electric propulsion interplanetary trajectories for use with Hall and… (more)

Subjects/Keywords: Automate; Feasible Trajectory; Trajectory Optimization; Aerospace Engineering; Engineering

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APA (6th Edition):

Patel, P. R. (2008). Automating Interplanetary Trajectory Generation for Electric Propulsion Trade Studies. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/61553

Chicago Manual of Style (16th Edition):

Patel, Prashant R. “Automating Interplanetary Trajectory Generation for Electric Propulsion Trade Studies.” 2008. Doctoral Dissertation, University of Michigan. Accessed July 17, 2019. http://hdl.handle.net/2027.42/61553.

MLA Handbook (7th Edition):

Patel, Prashant R. “Automating Interplanetary Trajectory Generation for Electric Propulsion Trade Studies.” 2008. Web. 17 Jul 2019.

Vancouver:

Patel PR. Automating Interplanetary Trajectory Generation for Electric Propulsion Trade Studies. [Internet] [Doctoral dissertation]. University of Michigan; 2008. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/2027.42/61553.

Council of Science Editors:

Patel PR. Automating Interplanetary Trajectory Generation for Electric Propulsion Trade Studies. [Doctoral Dissertation]. University of Michigan; 2008. Available from: http://hdl.handle.net/2027.42/61553


Georgia Tech

5. Steffens, Michael J. A combined global and local methodology for launch vehicle trajectory design-space exploration and optimization.

Degree: MS, Aerospace Engineering, 2014, Georgia Tech

Trajectory optimization is an important part of launch vehicle design and operation. With the high costs of launching payload into orbit, every pound that can… (more)

Subjects/Keywords: Launch vehicle; Trajectory optimization; Launch vehicles (Astronautics); Trajectories (Mechanics); Mathematical optimization

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APA (6th Edition):

Steffens, M. J. (2014). A combined global and local methodology for launch vehicle trajectory design-space exploration and optimization. (Masters Thesis). Georgia Tech. Retrieved from http://hdl.handle.net/1853/51884

Chicago Manual of Style (16th Edition):

Steffens, Michael J. “A combined global and local methodology for launch vehicle trajectory design-space exploration and optimization.” 2014. Masters Thesis, Georgia Tech. Accessed July 17, 2019. http://hdl.handle.net/1853/51884.

MLA Handbook (7th Edition):

Steffens, Michael J. “A combined global and local methodology for launch vehicle trajectory design-space exploration and optimization.” 2014. Web. 17 Jul 2019.

Vancouver:

Steffens MJ. A combined global and local methodology for launch vehicle trajectory design-space exploration and optimization. [Internet] [Masters thesis]. Georgia Tech; 2014. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/1853/51884.

Council of Science Editors:

Steffens MJ. A combined global and local methodology for launch vehicle trajectory design-space exploration and optimization. [Masters Thesis]. Georgia Tech; 2014. Available from: http://hdl.handle.net/1853/51884


Georgia Tech

6. De La Torre, Gerardo. Autonomous suspended load operations via trajectory optimization and variational integrators.

Degree: PhD, Aerospace Engineering, 2015, Georgia Tech

 Advances in machine autonomy hold great promise in advancing technology, economic markets, and general societal well-being. For example, the progression of unmanned air systems (UAS)… (more)

Subjects/Keywords: Trajectory optimization; Variational integrator; Suspended load; Stochastic control; Polynomial chaos

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APA (6th Edition):

De La Torre, G. (2015). Autonomous suspended load operations via trajectory optimization and variational integrators. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/53932

Chicago Manual of Style (16th Edition):

De La Torre, Gerardo. “Autonomous suspended load operations via trajectory optimization and variational integrators.” 2015. Doctoral Dissertation, Georgia Tech. Accessed July 17, 2019. http://hdl.handle.net/1853/53932.

MLA Handbook (7th Edition):

De La Torre, Gerardo. “Autonomous suspended load operations via trajectory optimization and variational integrators.” 2015. Web. 17 Jul 2019.

Vancouver:

De La Torre G. Autonomous suspended load operations via trajectory optimization and variational integrators. [Internet] [Doctoral dissertation]. Georgia Tech; 2015. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/1853/53932.

Council of Science Editors:

De La Torre G. Autonomous suspended load operations via trajectory optimization and variational integrators. [Doctoral Dissertation]. Georgia Tech; 2015. Available from: http://hdl.handle.net/1853/53932


Penn State University

7. Davis, Elizabeth. SOLAR SAIL TRAJECTORY OPTIMIZATION USING.

Degree: MS, Aerospace Engineering, 2008, Penn State University

 Solar sail spacecraft rely solely on solar radiation pressure for propulsion. Since the acceleration received by radiation pressure increases as the spacecraft nears the Sun,… (more)

Subjects/Keywords: solar sail; collocation; evolutionary algorithm; trajectory optimization; NAGA II

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APA (6th Edition):

Davis, E. (2008). SOLAR SAIL TRAJECTORY OPTIMIZATION USING. (Masters Thesis). Penn State University. Retrieved from https://etda.libraries.psu.edu/catalog/8407

Chicago Manual of Style (16th Edition):

Davis, Elizabeth. “SOLAR SAIL TRAJECTORY OPTIMIZATION USING.” 2008. Masters Thesis, Penn State University. Accessed July 17, 2019. https://etda.libraries.psu.edu/catalog/8407.

MLA Handbook (7th Edition):

Davis, Elizabeth. “SOLAR SAIL TRAJECTORY OPTIMIZATION USING.” 2008. Web. 17 Jul 2019.

Vancouver:

Davis E. SOLAR SAIL TRAJECTORY OPTIMIZATION USING. [Internet] [Masters thesis]. Penn State University; 2008. [cited 2019 Jul 17]. Available from: https://etda.libraries.psu.edu/catalog/8407.

Council of Science Editors:

Davis E. SOLAR SAIL TRAJECTORY OPTIMIZATION USING. [Masters Thesis]. Penn State University; 2008. Available from: https://etda.libraries.psu.edu/catalog/8407


Penn State University

8. Shin, Bong Gun. PREDICTION OF SAND PARTICLE TRAJECTORIES AND SAND EROSION DAMAGE ON HELICOPTER ROTOR BLADES.

Degree: PhD, Aerospace Engineering, 2010, Penn State University

 Erosion damage on a helicopter rotor blade by the impact of solid particle causes serious material removal from the surface of the rotor blade. The… (more)

Subjects/Keywords: Rotorcraft; Aerodynamics; Particle Trajectory; Sand Erosion; Helicopter rotor blade

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APA (6th Edition):

Shin, B. G. (2010). PREDICTION OF SAND PARTICLE TRAJECTORIES AND SAND EROSION DAMAGE ON HELICOPTER ROTOR BLADES. (Doctoral Dissertation). Penn State University. Retrieved from https://etda.libraries.psu.edu/catalog/10860

Chicago Manual of Style (16th Edition):

Shin, Bong Gun. “PREDICTION OF SAND PARTICLE TRAJECTORIES AND SAND EROSION DAMAGE ON HELICOPTER ROTOR BLADES.” 2010. Doctoral Dissertation, Penn State University. Accessed July 17, 2019. https://etda.libraries.psu.edu/catalog/10860.

MLA Handbook (7th Edition):

Shin, Bong Gun. “PREDICTION OF SAND PARTICLE TRAJECTORIES AND SAND EROSION DAMAGE ON HELICOPTER ROTOR BLADES.” 2010. Web. 17 Jul 2019.

Vancouver:

Shin BG. PREDICTION OF SAND PARTICLE TRAJECTORIES AND SAND EROSION DAMAGE ON HELICOPTER ROTOR BLADES. [Internet] [Doctoral dissertation]. Penn State University; 2010. [cited 2019 Jul 17]. Available from: https://etda.libraries.psu.edu/catalog/10860.

Council of Science Editors:

Shin BG. PREDICTION OF SAND PARTICLE TRAJECTORIES AND SAND EROSION DAMAGE ON HELICOPTER ROTOR BLADES. [Doctoral Dissertation]. Penn State University; 2010. Available from: https://etda.libraries.psu.edu/catalog/10860


Penn State University

9. Reiter, Jason A. Numerical And Analytical Solutions To Rapid Collision Avoidance Maneuvers Constrained By Mission Performance Requirements.

Degree: MS, Aerospace Engineering, 2016, Penn State University

 Collision avoidance maneuvers to prevent orbital collisions between two catalogued objects are typically planned multiple days in advance. If the warning time is decreased to… (more)

Subjects/Keywords: astrodynamics; collision avoidance; debris; trade studies; optimization; trajectory; mission design

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APA (6th Edition):

Reiter, J. A. (2016). Numerical And Analytical Solutions To Rapid Collision Avoidance Maneuvers Constrained By Mission Performance Requirements. (Masters Thesis). Penn State University. Retrieved from https://etda.libraries.psu.edu/catalog/29469

Chicago Manual of Style (16th Edition):

Reiter, Jason A. “Numerical And Analytical Solutions To Rapid Collision Avoidance Maneuvers Constrained By Mission Performance Requirements.” 2016. Masters Thesis, Penn State University. Accessed July 17, 2019. https://etda.libraries.psu.edu/catalog/29469.

MLA Handbook (7th Edition):

Reiter, Jason A. “Numerical And Analytical Solutions To Rapid Collision Avoidance Maneuvers Constrained By Mission Performance Requirements.” 2016. Web. 17 Jul 2019.

Vancouver:

Reiter JA. Numerical And Analytical Solutions To Rapid Collision Avoidance Maneuvers Constrained By Mission Performance Requirements. [Internet] [Masters thesis]. Penn State University; 2016. [cited 2019 Jul 17]. Available from: https://etda.libraries.psu.edu/catalog/29469.

Council of Science Editors:

Reiter JA. Numerical And Analytical Solutions To Rapid Collision Avoidance Maneuvers Constrained By Mission Performance Requirements. [Masters Thesis]. Penn State University; 2016. Available from: https://etda.libraries.psu.edu/catalog/29469


Penn State University

10. Sottile, Bradley Joseph. Evolutionary Computation for Spacecraft Trajectory Optimization.

Degree: MS, Aerospace Engineering, 2013, Penn State University

 Evolutionary Computation has exploded in use in engineering and the applied sciences. For this thesis, three algorithms – Particle Swarm Optimization (PSO), Bacteria Foraging Optimization… (more)

Subjects/Keywords: Astrodynamics; Evolutionary Algorithms; Evolutionary Computation; Evolutionary Strategies; Optimization; Spacecraft Trajectory

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APA (6th Edition):

Sottile, B. J. (2013). Evolutionary Computation for Spacecraft Trajectory Optimization. (Masters Thesis). Penn State University. Retrieved from https://etda.libraries.psu.edu/catalog/19135

Chicago Manual of Style (16th Edition):

Sottile, Bradley Joseph. “Evolutionary Computation for Spacecraft Trajectory Optimization.” 2013. Masters Thesis, Penn State University. Accessed July 17, 2019. https://etda.libraries.psu.edu/catalog/19135.

MLA Handbook (7th Edition):

Sottile, Bradley Joseph. “Evolutionary Computation for Spacecraft Trajectory Optimization.” 2013. Web. 17 Jul 2019.

Vancouver:

Sottile BJ. Evolutionary Computation for Spacecraft Trajectory Optimization. [Internet] [Masters thesis]. Penn State University; 2013. [cited 2019 Jul 17]. Available from: https://etda.libraries.psu.edu/catalog/19135.

Council of Science Editors:

Sottile BJ. Evolutionary Computation for Spacecraft Trajectory Optimization. [Masters Thesis]. Penn State University; 2013. Available from: https://etda.libraries.psu.edu/catalog/19135


Penn State University

11. Corbets, Jeffrey. Real-Time Trajectory Generation for Target Localization Using Micro Air Vehicles.

Degree: MS, Aerospace Engineering, 2008, Penn State University

 This thesis presents an approach to near-optimal target localization for small and micro unmanned aerial vehicles using a family of pre-computed parameterized trajectories. These trajectories… (more)

Subjects/Keywords: uav; mav; localization; planning; path; trajectory; real time; micro; target; tracking

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APA (6th Edition):

Corbets, J. (2008). Real-Time Trajectory Generation for Target Localization Using Micro Air Vehicles. (Masters Thesis). Penn State University. Retrieved from https://etda.libraries.psu.edu/catalog/8672

Chicago Manual of Style (16th Edition):

Corbets, Jeffrey. “Real-Time Trajectory Generation for Target Localization Using Micro Air Vehicles.” 2008. Masters Thesis, Penn State University. Accessed July 17, 2019. https://etda.libraries.psu.edu/catalog/8672.

MLA Handbook (7th Edition):

Corbets, Jeffrey. “Real-Time Trajectory Generation for Target Localization Using Micro Air Vehicles.” 2008. Web. 17 Jul 2019.

Vancouver:

Corbets J. Real-Time Trajectory Generation for Target Localization Using Micro Air Vehicles. [Internet] [Masters thesis]. Penn State University; 2008. [cited 2019 Jul 17]. Available from: https://etda.libraries.psu.edu/catalog/8672.

Council of Science Editors:

Corbets J. Real-Time Trajectory Generation for Target Localization Using Micro Air Vehicles. [Masters Thesis]. Penn State University; 2008. Available from: https://etda.libraries.psu.edu/catalog/8672


Penn State University

12. Goodyear, Andrew. Optimal low-thrust geostationary transfer orbit using a hybrid pseudospectral collocation method.

Degree: MS, Aerospace Engineering, 2015, Penn State University

 The focus of this thesis is a two-phase method for the solution of trajectory op- timization problems where a low-thrust ion engine is used for… (more)

Subjects/Keywords: low-thrust; pseudospectral; trajectory optimization; geostationary; modified equinoctial elements

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APA (6th Edition):

Goodyear, A. (2015). Optimal low-thrust geostationary transfer orbit using a hybrid pseudospectral collocation method. (Masters Thesis). Penn State University. Retrieved from https://etda.libraries.psu.edu/catalog/29467

Chicago Manual of Style (16th Edition):

Goodyear, Andrew. “Optimal low-thrust geostationary transfer orbit using a hybrid pseudospectral collocation method.” 2015. Masters Thesis, Penn State University. Accessed July 17, 2019. https://etda.libraries.psu.edu/catalog/29467.

MLA Handbook (7th Edition):

Goodyear, Andrew. “Optimal low-thrust geostationary transfer orbit using a hybrid pseudospectral collocation method.” 2015. Web. 17 Jul 2019.

Vancouver:

Goodyear A. Optimal low-thrust geostationary transfer orbit using a hybrid pseudospectral collocation method. [Internet] [Masters thesis]. Penn State University; 2015. [cited 2019 Jul 17]. Available from: https://etda.libraries.psu.edu/catalog/29467.

Council of Science Editors:

Goodyear A. Optimal low-thrust geostationary transfer orbit using a hybrid pseudospectral collocation method. [Masters Thesis]. Penn State University; 2015. Available from: https://etda.libraries.psu.edu/catalog/29467


Mississippi State University

13. Yake, Bronson Thomas. Self-Smoothing Functional Estimation.

Degree: MS, Aerospace Engineering, 2002, Mississippi State University

 Analysis of measured data is often required when there is no deep understanding of the mathematics that accurately describes the process being measured. Additionally, realistic… (more)

Subjects/Keywords: trajectory; estimation; filter; curve fit

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APA (6th Edition):

Yake, B. T. (2002). Self-Smoothing Functional Estimation. (Masters Thesis). Mississippi State University. Retrieved from http://sun.library.msstate.edu/ETD-db/theses/available/etd-09032002-090546/ ;

Chicago Manual of Style (16th Edition):

Yake, Bronson Thomas. “Self-Smoothing Functional Estimation.” 2002. Masters Thesis, Mississippi State University. Accessed July 17, 2019. http://sun.library.msstate.edu/ETD-db/theses/available/etd-09032002-090546/ ;.

MLA Handbook (7th Edition):

Yake, Bronson Thomas. “Self-Smoothing Functional Estimation.” 2002. Web. 17 Jul 2019.

Vancouver:

Yake BT. Self-Smoothing Functional Estimation. [Internet] [Masters thesis]. Mississippi State University; 2002. [cited 2019 Jul 17]. Available from: http://sun.library.msstate.edu/ETD-db/theses/available/etd-09032002-090546/ ;.

Council of Science Editors:

Yake BT. Self-Smoothing Functional Estimation. [Masters Thesis]. Mississippi State University; 2002. Available from: http://sun.library.msstate.edu/ETD-db/theses/available/etd-09032002-090546/ ;

14. Brennan, Martin James. Preliminary interplanetary trajectory design tools using ballistic and powered gravity assists.

Degree: Aerospace Engineering, 2015, University of Texas – Austin

 Preliminary interplanetary trajectory designs frequently use simplified two-body orbital mechanics and linked conics methodology to model the complex trajectories in multi-body systems. Incorporating gravity assists… (more)

Subjects/Keywords: Interplanetary; Trajectory design; Preliminary trajectory; Spacecraft; Mission design; Flyby; Swingby; Gravity assist; Powered flyby; Powered gravity assist; Powered swingby; Optimal flyby, Optimal; Powered; Optimal gravity assist; Impulsive; Ballistic; Trajectory optimization; Ballistic flyby; Ballistic gravity assist; Ballistic swingby; Optimization; Design tool; Orbit; Hyperbolic; Transfer; Trajectory

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APA (6th Edition):

Brennan, M. J. (2015). Preliminary interplanetary trajectory design tools using ballistic and powered gravity assists. (Thesis). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/31342

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):

Brennan, Martin James. “Preliminary interplanetary trajectory design tools using ballistic and powered gravity assists.” 2015. Thesis, University of Texas – Austin. Accessed July 17, 2019. http://hdl.handle.net/2152/31342.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Brennan, Martin James. “Preliminary interplanetary trajectory design tools using ballistic and powered gravity assists.” 2015. Web. 17 Jul 2019.

Vancouver:

Brennan MJ. Preliminary interplanetary trajectory design tools using ballistic and powered gravity assists. [Internet] [Thesis]. University of Texas – Austin; 2015. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/2152/31342.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Brennan MJ. Preliminary interplanetary trajectory design tools using ballistic and powered gravity assists. [Thesis]. University of Texas – Austin; 2015. Available from: http://hdl.handle.net/2152/31342

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation


University of Texas – Austin

15. -5205-5968. Multiple-shooting differential dynamic programming with applications to spacecraft trajectory optimization.

Degree: Aerospace Engineering, 2017, University of Texas – Austin

 The optimization of spacecraft trajectories has been, and continues to be, critical for the development of modern space missions. Longer flight times, continuous low-thrust propulsion,… (more)

Subjects/Keywords: Optimal control; Differential dynamic programming; Multiple-shooting; Spacecraft trajectory optimization

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APA (6th Edition):

-5205-5968. (2017). Multiple-shooting differential dynamic programming with applications to spacecraft trajectory optimization. (Thesis). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/61764

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16th Edition):

-5205-5968. “Multiple-shooting differential dynamic programming with applications to spacecraft trajectory optimization.” 2017. Thesis, University of Texas – Austin. Accessed July 17, 2019. http://hdl.handle.net/2152/61764.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

-5205-5968. “Multiple-shooting differential dynamic programming with applications to spacecraft trajectory optimization.” 2017. Web. 17 Jul 2019.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Vancouver:

-5205-5968. Multiple-shooting differential dynamic programming with applications to spacecraft trajectory optimization. [Internet] [Thesis]. University of Texas – Austin; 2017. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/2152/61764.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

-5205-5968. Multiple-shooting differential dynamic programming with applications to spacecraft trajectory optimization. [Thesis]. University of Texas – Austin; 2017. Available from: http://hdl.handle.net/2152/61764

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete
Not specified: Masters Thesis or Doctoral Dissertation


Georgia Tech

16. Barlow, Sarah. A Multi-UAV Trajectory Optimization Methodology for Complex Enclosed Environments.

Degree: MS, Aerospace Engineering, 2019, Georgia Tech

 Unmanned Aerial Systems (UAS) have become remarkably more popular over the past decade and demonstrate a continuous upward market trend. As UAS become more accessible… (more)

Subjects/Keywords: UAV trajectory optimization; Vehicle routing problem; Traveling salesmen problem

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APA (6th Edition):

Barlow, S. (2019). A Multi-UAV Trajectory Optimization Methodology for Complex Enclosed Environments. (Masters Thesis). Georgia Tech. Retrieved from http://hdl.handle.net/1853/61304

Chicago Manual of Style (16th Edition):

Barlow, Sarah. “A Multi-UAV Trajectory Optimization Methodology for Complex Enclosed Environments.” 2019. Masters Thesis, Georgia Tech. Accessed July 17, 2019. http://hdl.handle.net/1853/61304.

MLA Handbook (7th Edition):

Barlow, Sarah. “A Multi-UAV Trajectory Optimization Methodology for Complex Enclosed Environments.” 2019. Web. 17 Jul 2019.

Vancouver:

Barlow S. A Multi-UAV Trajectory Optimization Methodology for Complex Enclosed Environments. [Internet] [Masters thesis]. Georgia Tech; 2019. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/1853/61304.

Council of Science Editors:

Barlow S. A Multi-UAV Trajectory Optimization Methodology for Complex Enclosed Environments. [Masters Thesis]. Georgia Tech; 2019. Available from: http://hdl.handle.net/1853/61304


University of Illinois – Urbana-Champaign

17. Shah, Vishwa Jayesh. Automated global optimization of low-energy trajectories using a hybrid optimal control framework.

Degree: MS, Aerospace Engineering, 2017, University of Illinois – Urbana-Champaign

 Leveraging dynamical structures found in the three-body problem provides opportunities to explore transfers that utilize considerably less fuel, thus gaining the moniker of low-energy transfers.… (more)

Subjects/Keywords: Aerospace; Spacecraft trajectory optimization; Low-energy mission design

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APA (6th Edition):

Shah, V. J. (2017). Automated global optimization of low-energy trajectories using a hybrid optimal control framework. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/97392

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):

Shah, Vishwa Jayesh. “Automated global optimization of low-energy trajectories using a hybrid optimal control framework.” 2017. Thesis, University of Illinois – Urbana-Champaign. Accessed July 17, 2019. http://hdl.handle.net/2142/97392.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Shah, Vishwa Jayesh. “Automated global optimization of low-energy trajectories using a hybrid optimal control framework.” 2017. Web. 17 Jul 2019.

Vancouver:

Shah VJ. Automated global optimization of low-energy trajectories using a hybrid optimal control framework. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2017. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/2142/97392.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Shah VJ. Automated global optimization of low-energy trajectories using a hybrid optimal control framework. [Thesis]. University of Illinois – Urbana-Champaign; 2017. Available from: http://hdl.handle.net/2142/97392

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation


Cal Poly

18. Smiroldo, Jordan. Investigation into the Mitigation of the Effects of Uncertain Optical Degradation on an Interplanetary Solar Sail Mission Using a Single Model Update.

Degree: MS, Aerospace Engineering, 2013, Cal Poly

  The renewed academic interest in using solar sails as a source of spacecraft propulsion has been accompanied by a recent fervor of investigations into… (more)

Subjects/Keywords: Solar; Sail; Trajectory; Collocation; Non-ideal; Performance; Astrodynamics

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APA (6th Edition):

Smiroldo, J. (2013). Investigation into the Mitigation of the Effects of Uncertain Optical Degradation on an Interplanetary Solar Sail Mission Using a Single Model Update. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/1135 ; 10.15368/theses.2013.215

Chicago Manual of Style (16th Edition):

Smiroldo, Jordan. “Investigation into the Mitigation of the Effects of Uncertain Optical Degradation on an Interplanetary Solar Sail Mission Using a Single Model Update.” 2013. Masters Thesis, Cal Poly. Accessed July 17, 2019. https://digitalcommons.calpoly.edu/theses/1135 ; 10.15368/theses.2013.215.

MLA Handbook (7th Edition):

Smiroldo, Jordan. “Investigation into the Mitigation of the Effects of Uncertain Optical Degradation on an Interplanetary Solar Sail Mission Using a Single Model Update.” 2013. Web. 17 Jul 2019.

Vancouver:

Smiroldo J. Investigation into the Mitigation of the Effects of Uncertain Optical Degradation on an Interplanetary Solar Sail Mission Using a Single Model Update. [Internet] [Masters thesis]. Cal Poly; 2013. [cited 2019 Jul 17]. Available from: https://digitalcommons.calpoly.edu/theses/1135 ; 10.15368/theses.2013.215.

Council of Science Editors:

Smiroldo J. Investigation into the Mitigation of the Effects of Uncertain Optical Degradation on an Interplanetary Solar Sail Mission Using a Single Model Update. [Masters Thesis]. Cal Poly; 2013. Available from: https://digitalcommons.calpoly.edu/theses/1135 ; 10.15368/theses.2013.215


Cal Poly

19. Morrison, Oliver K. Use of Manifolds in the Insertion of Ballistic Cycler Trajectories.

Degree: MS, Aerospace Engineering, 2018, Cal Poly

  Today, Mars is one of the most interesting and important destinations for humankind and copious methods have been proposed to accomplish these future missions.… (more)

Subjects/Keywords: cycler; trajectory; manifold; orbit; transfer; mars; Aerospace Engineering; Astrodynamics; Space Vehicles

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Morrison, O. K. (2018). Use of Manifolds in the Insertion of Ballistic Cycler Trajectories. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/1937

Chicago Manual of Style (16th Edition):

Morrison, Oliver K. “Use of Manifolds in the Insertion of Ballistic Cycler Trajectories.” 2018. Masters Thesis, Cal Poly. Accessed July 17, 2019. https://digitalcommons.calpoly.edu/theses/1937.

MLA Handbook (7th Edition):

Morrison, Oliver K. “Use of Manifolds in the Insertion of Ballistic Cycler Trajectories.” 2018. Web. 17 Jul 2019.

Vancouver:

Morrison OK. Use of Manifolds in the Insertion of Ballistic Cycler Trajectories. [Internet] [Masters thesis]. Cal Poly; 2018. [cited 2019 Jul 17]. Available from: https://digitalcommons.calpoly.edu/theses/1937.

Council of Science Editors:

Morrison OK. Use of Manifolds in the Insertion of Ballistic Cycler Trajectories. [Masters Thesis]. Cal Poly; 2018. Available from: https://digitalcommons.calpoly.edu/theses/1937


University of Illinois – Urbana-Champaign

20. Aurich, Joshua Daniel. Automated detection of invariant manifold intersections using grid based approach.

Degree: MS, Aerospace Engineering, 2017, University of Illinois – Urbana-Champaign

 When designing spacecraft trajectories, there exist cases where a trade-off between time-of-flight and fuel become crucial to the mission design scenario, especially for unmanned missions… (more)

Subjects/Keywords: Low energy; Trajectory; Poincare surface of section; Poincare; Compute unified device architecture (CUDA); Automated detection; Spacecraft trajectory; Periodic orbit; Invariant manifold; Manifold intersection

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APA (6th Edition):

Aurich, J. D. (2017). Automated detection of invariant manifold intersections using grid based approach. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/97385

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):

Aurich, Joshua Daniel. “Automated detection of invariant manifold intersections using grid based approach.” 2017. Thesis, University of Illinois – Urbana-Champaign. Accessed July 17, 2019. http://hdl.handle.net/2142/97385.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Aurich, Joshua Daniel. “Automated detection of invariant manifold intersections using grid based approach.” 2017. Web. 17 Jul 2019.

Vancouver:

Aurich JD. Automated detection of invariant manifold intersections using grid based approach. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2017. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/2142/97385.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Aurich JD. Automated detection of invariant manifold intersections using grid based approach. [Thesis]. University of Illinois – Urbana-Champaign; 2017. Available from: http://hdl.handle.net/2142/97385

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

21. Fuller, John D. Methods to Alleviate Processing Requirements of High-Fidelity Multibody Parachute Simulations Involving a Confluence Mass.

Degree: MS, Aerospace Engineering, 2009, North Carolina State University

 Methods designed to reduce the numerical stiffness and processing requirements of high fidelity entry trajectory models involving parachutes are explored. Parachute deployment systems have often… (more)

Subjects/Keywords: confluence mass; singular perturbation; parachutes; trajectory; trajectory simulation

…a parachute system in the latter phases of entry, descent, and landing. Trajectory… …requires a small time step to integrate the equations of motion. Some trajectory analysis… …greatly reduce the turn-around time of trajectory simulations involving parachute deployment… …mass Trajectory analysts are more concerned with the behavior of the parachute and attached… …models are analyzed using POSTII, a trajectory analysis program used to simulate entry, descent… 

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APA (6th Edition):

Fuller, J. D. (2009). Methods to Alleviate Processing Requirements of High-Fidelity Multibody Parachute Simulations Involving a Confluence Mass. (Thesis). North Carolina State University. Retrieved from http://www.lib.ncsu.edu/resolver/1840.16/2296

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):

Fuller, John D. “Methods to Alleviate Processing Requirements of High-Fidelity Multibody Parachute Simulations Involving a Confluence Mass.” 2009. Thesis, North Carolina State University. Accessed July 17, 2019. http://www.lib.ncsu.edu/resolver/1840.16/2296.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Fuller, John D. “Methods to Alleviate Processing Requirements of High-Fidelity Multibody Parachute Simulations Involving a Confluence Mass.” 2009. Web. 17 Jul 2019.

Vancouver:

Fuller JD. Methods to Alleviate Processing Requirements of High-Fidelity Multibody Parachute Simulations Involving a Confluence Mass. [Internet] [Thesis]. North Carolina State University; 2009. [cited 2019 Jul 17]. Available from: http://www.lib.ncsu.edu/resolver/1840.16/2296.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Fuller JD. Methods to Alleviate Processing Requirements of High-Fidelity Multibody Parachute Simulations Involving a Confluence Mass. [Thesis]. North Carolina State University; 2009. Available from: http://www.lib.ncsu.edu/resolver/1840.16/2296

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation


Georgia Tech

22. Kutty, Prasad M. Reconstruction and uncertainty quantification of entry, descent and landing trajectories using vehicle aerodynamics.

Degree: MS, Aerospace Engineering, 2014, Georgia Tech

 The reconstruction of entry, descent and landing (EDL) trajectories is significantly affected by the knowledge of the atmospheric conditions during flight. Away from Earth, this… (more)

Subjects/Keywords: Trajectory reconstruction; Entry, descent and landing; Space vehicles; Space trajectories; Space vehicles Atmospheric entry; Algorithms

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APA (6th Edition):

Kutty, P. M. (2014). Reconstruction and uncertainty quantification of entry, descent and landing trajectories using vehicle aerodynamics. (Masters Thesis). Georgia Tech. Retrieved from http://hdl.handle.net/1853/51893

Chicago Manual of Style (16th Edition):

Kutty, Prasad M. “Reconstruction and uncertainty quantification of entry, descent and landing trajectories using vehicle aerodynamics.” 2014. Masters Thesis, Georgia Tech. Accessed July 17, 2019. http://hdl.handle.net/1853/51893.

MLA Handbook (7th Edition):

Kutty, Prasad M. “Reconstruction and uncertainty quantification of entry, descent and landing trajectories using vehicle aerodynamics.” 2014. Web. 17 Jul 2019.

Vancouver:

Kutty PM. Reconstruction and uncertainty quantification of entry, descent and landing trajectories using vehicle aerodynamics. [Internet] [Masters thesis]. Georgia Tech; 2014. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/1853/51893.

Council of Science Editors:

Kutty PM. Reconstruction and uncertainty quantification of entry, descent and landing trajectories using vehicle aerodynamics. [Masters Thesis]. Georgia Tech; 2014. Available from: http://hdl.handle.net/1853/51893


Georgia Tech

23. Park, Sang Gyun. Optimal control based method for design and analysis of continuous descent arrivals.

Degree: PhD, Aerospace Engineering, 2014, Georgia Tech

 Continuous Descent Arrival (CDA) is a procedure where aircraft descend, at or near idle thrust, from their cruise altitude to their Final Approach Fix without… (more)

Subjects/Keywords: Continuous descent arrival; Optimal control; Hybrid system; Trajectory optimization; Flight management system

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APA (6th Edition):

Park, S. G. (2014). Optimal control based method for design and analysis of continuous descent arrivals. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/53005

Chicago Manual of Style (16th Edition):

Park, Sang Gyun. “Optimal control based method for design and analysis of continuous descent arrivals.” 2014. Doctoral Dissertation, Georgia Tech. Accessed July 17, 2019. http://hdl.handle.net/1853/53005.

MLA Handbook (7th Edition):

Park, Sang Gyun. “Optimal control based method for design and analysis of continuous descent arrivals.” 2014. Web. 17 Jul 2019.

Vancouver:

Park SG. Optimal control based method for design and analysis of continuous descent arrivals. [Internet] [Doctoral dissertation]. Georgia Tech; 2014. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/1853/53005.

Council of Science Editors:

Park SG. Optimal control based method for design and analysis of continuous descent arrivals. [Doctoral Dissertation]. Georgia Tech; 2014. Available from: http://hdl.handle.net/1853/53005


Georgia Tech

24. Steffens, Michael. Trajectory-based launch vehicle performance analysis for design-space exploration in conceptual design.

Degree: PhD, Aerospace Engineering, 2016, Georgia Tech

Trajectory optimization is an important part of launch vehicle conceptual design. Current methods for trajectory optimization involve numerical analysis, are computationally expensive and require trajectory(more)

Subjects/Keywords: Trajectory optimization; Launch vehicle design; Launch vehicle performance analysis; Extreme value theory

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APA (6th Edition):

Steffens, M. (2016). Trajectory-based launch vehicle performance analysis for design-space exploration in conceptual design. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/55649

Chicago Manual of Style (16th Edition):

Steffens, Michael. “Trajectory-based launch vehicle performance analysis for design-space exploration in conceptual design.” 2016. Doctoral Dissertation, Georgia Tech. Accessed July 17, 2019. http://hdl.handle.net/1853/55649.

MLA Handbook (7th Edition):

Steffens, Michael. “Trajectory-based launch vehicle performance analysis for design-space exploration in conceptual design.” 2016. Web. 17 Jul 2019.

Vancouver:

Steffens M. Trajectory-based launch vehicle performance analysis for design-space exploration in conceptual design. [Internet] [Doctoral dissertation]. Georgia Tech; 2016. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/1853/55649.

Council of Science Editors:

Steffens M. Trajectory-based launch vehicle performance analysis for design-space exploration in conceptual design. [Doctoral Dissertation]. Georgia Tech; 2016. Available from: http://hdl.handle.net/1853/55649


Virginia Tech

25. Shankar, Uday J. Singular-perturbation analysis of climb-cruise-dash optimization.

Degree: MS, Aerospace Engineering, 1985, Virginia Tech

Subjects/Keywords: Trajectory optimization.; LD5655.V855 1985.S527

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APA (6th Edition):

Shankar, U. J. (1985). Singular-perturbation analysis of climb-cruise-dash optimization. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/45736

Chicago Manual of Style (16th Edition):

Shankar, Uday J. “Singular-perturbation analysis of climb-cruise-dash optimization.” 1985. Masters Thesis, Virginia Tech. Accessed July 17, 2019. http://hdl.handle.net/10919/45736.

MLA Handbook (7th Edition):

Shankar, Uday J. “Singular-perturbation analysis of climb-cruise-dash optimization.” 1985. Web. 17 Jul 2019.

Vancouver:

Shankar UJ. Singular-perturbation analysis of climb-cruise-dash optimization. [Internet] [Masters thesis]. Virginia Tech; 1985. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/10919/45736.

Council of Science Editors:

Shankar UJ. Singular-perturbation analysis of climb-cruise-dash optimization. [Masters Thesis]. Virginia Tech; 1985. Available from: http://hdl.handle.net/10919/45736


Virginia Tech

26. Munro, Bruce C. Airplane trajectory expansion for dynamics inversion.

Degree: MS, Aerospace Engineering, 1992, Virginia Tech

Subjects/Keywords: Trajectory optimization.; LD5655.V855 1992.M867

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APA (6th Edition):

Munro, B. C. (1992). Airplane trajectory expansion for dynamics inversion. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/43640

Chicago Manual of Style (16th Edition):

Munro, Bruce C. “Airplane trajectory expansion for dynamics inversion.” 1992. Masters Thesis, Virginia Tech. Accessed July 17, 2019. http://hdl.handle.net/10919/43640.

MLA Handbook (7th Edition):

Munro, Bruce C. “Airplane trajectory expansion for dynamics inversion.” 1992. Web. 17 Jul 2019.

Vancouver:

Munro BC. Airplane trajectory expansion for dynamics inversion. [Internet] [Masters thesis]. Virginia Tech; 1992. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/10919/43640.

Council of Science Editors:

Munro BC. Airplane trajectory expansion for dynamics inversion. [Masters Thesis]. Virginia Tech; 1992. Available from: http://hdl.handle.net/10919/43640


Virginia Tech

27. Sankaranarayanan, S. Topology optimization with simultaneous analysis and design.

Degree: PhD, Aerospace Engineering, 1992, Virginia Tech

Subjects/Keywords: Trajectory optimization.; LD5655.V856 1992.S272

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APA (6th Edition):

Sankaranarayanan, S. (1992). Topology optimization with simultaneous analysis and design. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/37690

Chicago Manual of Style (16th Edition):

Sankaranarayanan, S. “Topology optimization with simultaneous analysis and design.” 1992. Doctoral Dissertation, Virginia Tech. Accessed July 17, 2019. http://hdl.handle.net/10919/37690.

MLA Handbook (7th Edition):

Sankaranarayanan, S. “Topology optimization with simultaneous analysis and design.” 1992. Web. 17 Jul 2019.

Vancouver:

Sankaranarayanan S. Topology optimization with simultaneous analysis and design. [Internet] [Doctoral dissertation]. Virginia Tech; 1992. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/10919/37690.

Council of Science Editors:

Sankaranarayanan S. Topology optimization with simultaneous analysis and design. [Doctoral Dissertation]. Virginia Tech; 1992. Available from: http://hdl.handle.net/10919/37690


Virginia Tech

28. Kumar, Renjith R. Singular optimal atmospheric rocket trajectories.

Degree: MS, Aerospace Engineering, 1986, Virginia Tech

  Singular subarcs arise in quite a few problems of flight dynamics. The present study is devoted to the specific problem of ascent and acceleration… (more)

Subjects/Keywords: Trajectory optimization; LD5655.V855 1986.K763

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APA (6th Edition):

Kumar, R. R. (1986). Singular optimal atmospheric rocket trajectories. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/43577

Chicago Manual of Style (16th Edition):

Kumar, Renjith R. “Singular optimal atmospheric rocket trajectories.” 1986. Masters Thesis, Virginia Tech. Accessed July 17, 2019. http://hdl.handle.net/10919/43577.

MLA Handbook (7th Edition):

Kumar, Renjith R. “Singular optimal atmospheric rocket trajectories.” 1986. Web. 17 Jul 2019.

Vancouver:

Kumar RR. Singular optimal atmospheric rocket trajectories. [Internet] [Masters thesis]. Virginia Tech; 1986. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/10919/43577.

Council of Science Editors:

Kumar RR. Singular optimal atmospheric rocket trajectories. [Masters Thesis]. Virginia Tech; 1986. Available from: http://hdl.handle.net/10919/43577


University of Texas – Austin

29. Jesick, Mark Christopher. Optimal lunar orbit insertion from a free return trajectory.

Degree: Aerospace Engineering, 2012, University of Texas – Austin

 With the discovery of water ice at the moon's south pole, future human lunar exploration will likely occur at polar sites and, therefore, require high… (more)

Subjects/Keywords: Free return; Trajectory optimization; Lunar orbit insertion; Mission design; Parameter optimization; Optimal control theory

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APA (6th Edition):

Jesick, M. C. (2012). Optimal lunar orbit insertion from a free return trajectory. (Thesis). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/32893

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):

Jesick, Mark Christopher. “Optimal lunar orbit insertion from a free return trajectory.” 2012. Thesis, University of Texas – Austin. Accessed July 17, 2019. http://hdl.handle.net/2152/32893.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Jesick, Mark Christopher. “Optimal lunar orbit insertion from a free return trajectory.” 2012. Web. 17 Jul 2019.

Vancouver:

Jesick MC. Optimal lunar orbit insertion from a free return trajectory. [Internet] [Thesis]. University of Texas – Austin; 2012. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/2152/32893.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Jesick MC. Optimal lunar orbit insertion from a free return trajectory. [Thesis]. University of Texas – Austin; 2012. Available from: http://hdl.handle.net/2152/32893

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation


University of Texas – Austin

30. Campbell, Alan Robert. Numerical analysis of complex-step differentiation in spacecraft trajectory optimization problems.

Degree: Aerospace Engineering, 2011, University of Texas – Austin

 An analysis of the use of complex-step differentiation (CSD) in optimization problems is presented. Complex-step differentiation is a numerical approximation of the derivative of a… (more)

Subjects/Keywords: Trajectory optimization; Numerical differentiation; Complex step differentiation; Optimization; Lunar ascent problem; Optimal orbit transfer problem

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APA (6th Edition):

Campbell, A. R. (2011). Numerical analysis of complex-step differentiation in spacecraft trajectory optimization problems. (Thesis). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/ETD-UT-2011-05-3440

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):

Campbell, Alan Robert. “Numerical analysis of complex-step differentiation in spacecraft trajectory optimization problems.” 2011. Thesis, University of Texas – Austin. Accessed July 17, 2019. http://hdl.handle.net/2152/ETD-UT-2011-05-3440.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Campbell, Alan Robert. “Numerical analysis of complex-step differentiation in spacecraft trajectory optimization problems.” 2011. Web. 17 Jul 2019.

Vancouver:

Campbell AR. Numerical analysis of complex-step differentiation in spacecraft trajectory optimization problems. [Internet] [Thesis]. University of Texas – Austin; 2011. [cited 2019 Jul 17]. Available from: http://hdl.handle.net/2152/ETD-UT-2011-05-3440.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Campbell AR. Numerical analysis of complex-step differentiation in spacecraft trajectory optimization problems. [Thesis]. University of Texas – Austin; 2011. Available from: http://hdl.handle.net/2152/ETD-UT-2011-05-3440

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

[1] [2] [3]

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