rajectory Optimization of the Internally Carried Air Launch

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Seraj, Javad | 2015

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 47378 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Asadian, Nima; Fathi, Mohsen
Abstract:
One of the most interesting and at the same time the newest methods to launch a satellite into space is Air Launch or Launch throw the mother aircraft. The placement of the satellite into space by a rocket in specific altitude and speed is separated from the mother aircraft, takes place. The most problems in multi stage rocket launching is trajectory optimization to reaching the maximum height. The survey was conducted using classical optimization methods, which is derived the equations for the gradient based on the calculus of variations. that can be used or modified for emissions control wings and changing the direction of thrust exhaust. It should be noted that in the model of rigid body model (three degrees of freedom) is attended by aerodynamic forces. At the end of the third stage ignition, by launching a satellite in a circular orbit. The effect of the initial conditions on Rocket flying free after release from the mother plane and the mother plane is examined on the final orbit and final range
Keywords:
Trajectory Optimization ; Air Launching ; Steepest Descent Method ; Multistage Rocket

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