Development and Validation of Reentry Simulation Using MATLAB
Master's thesis, Sep 2004-Mar 2006
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
Pagination or Media Count:
This research effort develops a program using MATLAB to solve the equations of motion for atmospheric reentry and analyzes the validity of the program for use as a tool to expeditiously predict reentry profiles. The reentry vehicle is modeled as a point mass with constant aerodynamic properties as defined by the user. The equations of motion for reentry are based on the two-body problem. The atmosphere is modeled as a single layer exponentially decreasing in density. The MATLAB program has the ability to derive the initial trajectory conditions from the position and velocity relative to the rotating surface of the Earth, the Earth-centered inertial position and velocity, or the classic orbital elements. The program is compared to previously established programs in order to validate its accuracy and numerical stability when predicting various reentry profiles to include sub-orbital, super-circular and hyperbolic trajectories as well as wide ranges of aerodynamic properties.
- Theoretical Mathematics
- Guided Missile Trajectories, Accuracy and Ballistics
- Guided Missile Reentry Vehicles