Longitudinal Control System Design Using Gradient Method for a Suborbital Launcher

Abstract:

The aim of this paper is to present a design method for the guidance navigation and control system (GNC) of a suborbital launcher. In order to achieve a symmetric evolution in the vertical plane we start with the decoupled form of the equation of motion. Afterwards these equations are linearized and the extended stability and command matrices are constructed by adding some auxiliary equations. The linear control law is obtained and the control matrix containing the unknown coefficients is presented. The design of the control system is based on a modified gradient method. To illustrate the proposed method the synthesis of the control system in the specific case of the SLT ("Suborbital Launcher for Testing - SLT" financed thru „Programme for Research-Development-Innovation on Space Technology and Advanced Research – STAR”) is presented.

• Periodical: Applied Mechanics and Materials (Volume 555)
• Pages: 113-120
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.555.113
• Online since: June 2014
• Authors: Teodor Viorel Chelaru, Valentin Pana*, Adrian Chelaru

References

[1] Berbente C., Mitran S., Zancu S. Metode Numerice , Ed. Tehnică 1997, ISBN 973-31-1135-X.

[2] Bryson A.E., and Ho, Y.C., Applied Optimal Control, Hemisphere , New York, 1975, Chap. 3, 5, 9.

[3] CHELARU T.V. Dinamica Zborului–Racheta dirijată, Ediţia a-II-a revizuită şi adaugită (Dynamic flight – guided missile – 2-nd edition). , Ed. Printech, Bucureşti, ISBN 973-718-013-5 , mai (2004).

[4] CHELARU T.V., BARBU C., CHELARU A., Mathematical model and technical solution for small multistage suborbital launchers, Proceedings of the 4th International Conference on Recent Advances in Space Technologies-RAST2009, ISBN: 978-1-4244-3626-2, Istambul, Turkey, 11-13 Jun (2009).

DOI: 10.1109/rast.2009.5158194

[5] Chelaru T.V., Barbu C. Mathematical model for sounding rockets, using attitude and rotation angles, International Journal of Applied Mathematics and Informatics, ISSN 2074-1278, Issue 1, Volume 3, pp.35-44.

[6] Chelaru T.V., Barbu C., Chelaru A., Dynamic Flight and Control for Suborbital Launcher for Testing , Proceedings of 1st International Conference New Challenges in Aerospace Sciences, ISSN 2344-4762, NCAS 2013, pp.98-102, Bucharest, Romania 7-8 November (2013).

DOI: 10.1109/rast.2013.6581330

[7] Kazakov, I.E., Mişakov, A.F., Aviaţionnîe upravliaemîe raketî , Ed. VVIA N.E. Jukovski, (1985).

[8] Moraru, F., Manual de balistică exterioară , Editura Militară, Bucureşti, (1976).

[9] Stoia-Djeska M, Chelaru T.V. A Sensitivity Analysis Approach in the Design of the Attitude Control System of Small Satellites, Proceedings of the 63rd International Astronautical Congress, (CD) , ISSN 1995-6258, Naples, Italy- October (2012).

[10] xxx, STANAG 4355 - The modified point mass and five degrees of freedom trajectory models.