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Abstract
The objective for this project was to give one the opportunity to apply the concepts of modern control systems in a realistic design scenario. The project also provided a chance to gain a better understanding of how closed loop systems and forward loop systems model the dynamics of a space vehicle re-entering the earth’s atmosphere. These are the tools that can be utilized in real world engineering projects. The system modeling the space vehicle dynamics was successfully used with specific gain values to produce a stable system built to design specifications.
Introduction
The design of a winged space vehicle is one that has occupied the National Aeronautics Space Administration throughout the 1950’s and 1960’s. It was not until the 1970’s that NASA put into use the first winged space orbiter. Set to this backdrop of history, we began our modest endeavor to model the wing dynamics of our spacecraft design. The goal for the final design of the vehicle dynamics system is to modify the system to be stable in a specific range. For this project we were able to find a range of stability for the design problem.
One of the objectives was to first model the system with the integral gain K1 equal to 1 and the proportional gain K2 equal to 0. The next objective of this project is to model the vehicle system for specified output parameters. The requirements for this project were to obtain the Bode diagram, gain margin, and phase margin. It is then possible to determine the stability, rise time, peak time, settling time, and percent overshoot of the system by examining the graphs. The second requirement was to stabilize the system by selecting two values of the gain (K1 and K2), which will result in a gain crossover frequency of 1rad/sec with a phase margin of at least 40 degrees and a gain margin of at least 45 db.
Design
The project first involved examining the control system with the integral gain K1 = 1 and the proportional gain K2 = 0. The second stage of the project involved selecting the values of the integral gain K1 and the proportional gain K2 that will give the phase margin of at least 40° and the gain margin of at least 45 db. The control diagram that models the space vehicle can be examined at the beginning of the appendix.
4. Fourth Stage[t3-t4](Fig.10) : At time t3, CM finished energy get transfer at that instant the diode D1 is blocked. The energy transfer to output maintain till t4 till power switch is turn on.
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