Trajectory Optimization of Launch Vehicles Using Steepest Descent Method – A Novel Approach

Dileep, M V and Nair, Vishnu G and Prahlad, K R and Kamath, Surekha (2014) Trajectory Optimization of Launch Vehicles Using Steepest Descent Method – A Novel Approach. International Journal of Engineering Research and Applications, 4 (1). pp. 116-121. ISSN 2248-9622

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Abstract

Trajectory optimization of a generic launch vehicle is considered in this paper. The direct application of a nonlinear programming method is used in recent literature, which transforms the original problem into a nonlinear optimization problem.To study the rocket motion under the influence of gravitational field, 2-D simulator is developed. The rocket motion is analyzed for a gravity turn trajectory. The objective is to ensure desired terminal conditions as well as minimum control effort in the low dynamic pressure region. Design of optimal trajectory for a single stage rocket is a two point boundary problem. Trajectory is designed for a single stage liquid rocket.Trajectory is computed for a given initial and final condition using equations of motion of rocket in 2-D plane. Hamiltonian is formulated for the given constraints. The non-linear equations are solved using steepest descent method.It is assumed that the launch vehicle is not experiencing any perturbations. Results are compared for Runge-kutta and Euler‟s integration methods,which clearly brings out the potential advantages of the proposed approach.

Item Type: Article
Uncontrolled Keywords: Trajectory optimization, Steepest descent method, Euler‟s method, Runge-Kutta method
Subjects: Engineering > MIT Manipal > Aeronautical and Automobile
Engineering > MIT Manipal > Instrumentation and Control
Depositing User: MIT Library
Date Deposited: 14 May 2016 09:11
Last Modified: 14 May 2016 09:11
URI: http://eprints.manipal.edu/id/eprint/146049

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