Optimization of the 3 rd Stage Rocket Trajectory Using Genetic Algorithm
Main Article Content
Abstract
To optimize the third stage of a space launch vehicle, powered by Liquid Rocket Engine (LRE) and also to optimize the fuel efficiency by varying injection pressure and gravity turn. The space launch vehicle trajectory is designed analytically by using the general governing equations of the rocket. These trajectories are solved with the implementation of the genetic algorithm. The trajectories are designed and simulated with the commercial software MATLAB, furthermore the relation between parameters and generate MATLAB Coding to simulate the trajectory of the vehicle at 3rd stage. The governing equations are solved using Chebyshev polynomials subroutine and Lagrange polynomial equation available in MATLAB software. The variation of velocity, specific impulse, time is plotted for different parameter (injection pressure) values of the spacecraft
Article Details
This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License.
IJCERT Policy:
The published work presented in this paper is licensed under the Creative Commons Attribution 4.0 International (CC BY 4.0) license. This means that the content of this paper can be shared, copied, and redistributed in any medium or format, as long as the original author is properly attributed. Additionally, any derivative works based on this paper must also be licensed under the same terms. This licensing agreement allows for broad dissemination and use of the work while maintaining the author's rights and recognition.
By submitting this paper to IJCERT, the author(s) agree to these licensing terms and confirm that the work is original and does not infringe on any third-party copyright or intellectual property rights.
References
Rockets and space craft propulsion by Martin J.L.Turner, states the information about the above parameters.
Trajectory Optimization for Target Localization,Sameera S. Ponda A simplified ascent trajectory optimization procedure has been developed with application of Ares I launch vehicle
Direct Trajectory Optimization by a ChebyshevPseudospectral Method, journal ofguidance, control, and dynamics Vol. 25, No. 1, January–February 2002.
Fahroo, F., and Ross, I. M., “Costate Estimation by a Legendre Pseudospectral Method,” Journal of Guidance, Control, and Dynamics, Vol. 24,No. 2, 2001, pp. 270–277. Survey of Numerical Methods for Trajectory Optimizationby John T. Betts journal of guidance, control, and dynamics, Vol. 21, No. 2, March–April 1998. A chebyshev polynomial method for optimal control with state constraints,jacquesvlassenbroeckt,automatic a, vol. 24, no. 4, pp. 499-506, 1988.
Space trajectory optimization and l1-optimalcontrol problems, michael ross, modern astrodynamics, pp. 155-188,elsevierastrodynamics series, 2006.
A genetic algorithm approach to solving optimal control problems with linearly appearingcontrolsh. Seywaldr.r.kumarts.m. deshpande,aiaa
Books:-
Development of trajectory simulation capabilities for the planetary entry systems synthesis tool By Devin Matthew Kipp, 2005.
Orbit selection and ekv guidance for spacebased ICBM intercept By AhmetTarikAydin
Programming with M-Files: A Rocket Trajectory Analysis Using For Loops By Darryl Morrell.
Rapid Trajectory Optimization for the ARES I Launch Vehicle By Greg A. Dukeman
Advanced control of Aircraft, Spacecraft and Rockets by AshishTewari, A John Wiley & Sons Publication, 2011.
Rocket and Spacecraft Propulsion, by Martin J. L. Turner, 2nd Edition, Springer2005.
Numerical Methods by using MATLAB by john H.Mathews,KurtisD.Fink.
Matlab and Simulink (Intro to aapplications) byPartha S Mallick.
Engineering Optimization: Theory and Practice, Fourth Edition Singiresu S. Rao.
Introduction to space dynamics by William tryell thomson.guidance, navigation and control conference