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Articles 1 - 9 of 9
Full-Text Articles in Astrodynamics
Investigation Of Interplanetary Trajectories To Sedna, John W. Sarappo Iii, Samuel Brickley, Iliane Domenech, Lorenzo Franceschetti, James E. Lyne
Investigation Of Interplanetary Trajectories To Sedna, John W. Sarappo Iii, Samuel Brickley, Iliane Domenech, Lorenzo Franceschetti, James E. Lyne
Chancellor’s Honors Program Projects
No abstract provided.
Titan Aerogravity Assist For Saturn Orbital Insertion And Study Of Enceladus, Hannah Hajdik, Samantha Ramsey, Richard Andrew Wright, Nathan Stover, Jason Patel, Jonathan Spitznas, Nishant Lokanathan, James Evans Lyne
Titan Aerogravity Assist For Saturn Orbital Insertion And Study Of Enceladus, Hannah Hajdik, Samantha Ramsey, Richard Andrew Wright, Nathan Stover, Jason Patel, Jonathan Spitznas, Nishant Lokanathan, James Evans Lyne
Chancellor’s Honors Program Projects
No abstract provided.
System Architecture Design And Development For A Reusable Lunar Lander, Chad Batten, Camille E. Bergin, Aaron Crigger, Darryl Harris, Gillian Suzanne Mcglothin
System Architecture Design And Development For A Reusable Lunar Lander, Chad Batten, Camille E. Bergin, Aaron Crigger, Darryl Harris, Gillian Suzanne Mcglothin
Chancellor’s Honors Program Projects
No abstract provided.
Enceladus Sample Return Mission, Braxton Brakefield, Rekesh Ali, Andrew Bishop, Shelby Honaker, David Taylor
Enceladus Sample Return Mission, Braxton Brakefield, Rekesh Ali, Andrew Bishop, Shelby Honaker, David Taylor
Chancellor’s Honors Program Projects
No abstract provided.
Improved Modeling Of Atmospheric Entry For Meteors With Nose Radii Between 5cm And 10m, Jakob Dale Brisby
Improved Modeling Of Atmospheric Entry For Meteors With Nose Radii Between 5cm And 10m, Jakob Dale Brisby
Masters Theses
Atmospheric entry studies typically look closely at the peak heating rate that a body encounters during its trajectory. This is an extremely important phenomenon to study because it allows engineers to determine if a trajectory is possible with given materials and craft design specifications. It also allows designers to choose what type of method will be used for mitigating the enormous heat fluxes during entry. In general, it is accepted that during the super-sonic flight regime the body will continue to be heated and an ablative heat shield often is used to deal with these heating processes. The theory outlined …
Development Of A Database For Rapid Approximation Of Spacecraft Radiation Dose During Jupiter Flyby, Sarah Gilbert Stewart
Development Of A Database For Rapid Approximation Of Spacecraft Radiation Dose During Jupiter Flyby, Sarah Gilbert Stewart
Masters Theses
Interplanetary and deep space missions greatly benefit from the utilization of gravitational assists to reach their final destinations. By closely “swinging by” a planet, a spacecraft can gain or lose velocity or change directions without requiring any expenditure of propulsion. In today’s budget-driven design environment, gravity assist flybys reduce the need for on-board fuel and propulsion systems, thereby reducing overall cost, increasing payload and mission capacity, increasing mission life, and decreasing travel time. It is expected that many future missions will also be designed to swing by Jupiter in order to utilize a gravity assist. However, there is a risk …
Design Of Economical Upper Stage Hybrid Rocket Engine, Christopher R. Potter
Design Of Economical Upper Stage Hybrid Rocket Engine, Christopher R. Potter
Chancellor’s Honors Program Projects
No abstract provided.
Optimization And Design For Heavy Lift Launch Vehicles, Paul Andreas Ritter
Optimization And Design For Heavy Lift Launch Vehicles, Paul Andreas Ritter
Masters Theses
The simulation and evaluation of an orbital launch vehicle requires consideration of numerous factors. These factors include, but are not limited to the propulsion system, aerodynamic effects, rotation of the earth, oblateness, and gravity. A trajectory simulation that considers these different factors is generated by a code developed for this thesis titled Trajectories for Heavy-lift Evaluation and Optimization (THEO). THEO is a validated trajectory simulation code with the ability to model numerous launch configurations. THEO also has the capability to provide the means for an optimization objective. Optimization of a launch vehicle can be specified in terms of many different …
Development And Analysis Of Onboard Translunar Injection Targeting Algorithms, Phillippe Lyles Winters Reed
Development And Analysis Of Onboard Translunar Injection Targeting Algorithms, Phillippe Lyles Winters Reed
Masters Theses
Several targeting algorithms are developed and analyzed for possible future use onboard a spacecraft. Each targeter is designed to determine the appropriate propulsive burn for translunar injection to obtain desired orbital parameters upon arrival at the moon. Primary design objectives are to minimize the computational requirements for each algorithm but also to ensure reasonable accuracy, so that the algorithm’s errors do not force the craft to conduct large mid-course corrections. Several levels of accuracy for dynamical models are explored, the convergence range and speed of each algorithm are compared, and the possible benefits of the Broyden and trust-region targeters are …