TECHNICAL MECHANICS
ISSN (Print): 1561-9184, ISSN (Online): 2616-6380

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UDC 621.002.56

Technical mechanics, 2019, 1, 38 - 52

ON THE CHOICE OF METHODS USED IN THE OPTIMIZATION OF ROCKET DESIGN PARAMETERS AND CONTROL PROGRAMS

DOI: https://doi.org/10.15407/itm2019.01.038

Senkin V. S., Syutkina-Doronina S. V.

Senkin V. S.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

Syutkina-Doronina S. V.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

      The aim of this work is to choose rational methods for solving the combined problem of the optimization of the design parameters, trajectory parameters, control programs, and basic characteristics of single-stage controlled rockets with solid-propellant sustainer engines at the initial design stage. The optimization parameters include rocket design parameters and trajectory parameters that allow one to form flight control programs in different flight segments. The parameters were optimized in such a way as to maximize the flight range objective function, i. e. the distance for which the rocket head is to be delivered with the required values of the kinematic parameters at the end of the flight. Algorithms and programs were developed to assess the efficiency of deterministic optimization methods, such as the Hooke–Jeeves zero-order pattern search, the Nelder–Mead zero-order polytope method, and first- and second-order coordinate gradient descent methods, in the solution of the combined problem. The use of the Hooke–Jeeves zero-order pattern search, which gives the optimization parameter vector closest to the global optimum of the objective function, was shown to be expedient. As shown by calculations, first- and second-order coordinate gradient descent methods and the zero-order polytope method require a comparatively larger number of iterations to find the optimal value of the optimization parameter vector. The flight range depends essentially on the values of the chosen optimization parameters. Because of this, the optimization of the chosen parameters (and, perhaps, other parameters too) in the solution of specific target problems seems to be an indispensable stage of controlled-rocket design. The optimization algorithms considered may be used without any significant modifications by design organizations at the initial design stage of space hardware of different purposes.
     

controlled object, solid-propellant sustainer rocket engine, initial design stage, design parameters, trajectory parameters, objective functional, deterministic optimization methods

1. Degtyarev A. V. Rocketry: Problems and Prospects. Selected science and technology publications. Dnipropetrovsk: ART-PRESS, 2014. 420 pp. (in Russian).

2. Aksenenko A. V., Baranov E. Yu., Gursky A. I., Klochkov A. S., Morozov A. S., Alpatov A. P., Senkin V. S., Syutkina-Doronina S. V. Methodology for the optimization of rocket design parameters, trajectory parameters, and flight control programs at the initial design stage. Kosmicheskaya Tekhnika. Raketnoye Vooruzheniye. 2018. No. 2 (116). Pp. 101-116. (in Russian).

3. Senkin V. S., Syutkina-Doronina S. V. Study of the objective functional sensitivity to variations in the design parameters of controlled rocket. Aviatsionno-Kosmicheskaya Tekhnika i Tekhnologiya. 2016. No. 3. Pp. 9-17. (in Russian).

4. Senkin V. S. On the choice of programs to control rocket motion along a ballistic trajectory. Teh. Meh. 2018. No. 1. Pp. 48-59. (in Russian).

5. Senkin V. S., Syutkina-Doronina S. V. Combined use of random search methods and gradient methods in the optimization of rocket design parameters and control programs. Teh. Meh. 2018. No. 2. Pp. 44-59. (in Russian).

6. Stuart R., Norvig P. Artificial Intelligence: A Modern Approach. 2nd Edition. Moscow: Williams Publishing House, 2007. 1408 pp. (in Russian).

7. Panteleev A. V., Letova T. A. Optimization Methods in Examples and Problems: Manual for Universities. 2nd Edition. Moscow: Vysshaya Shkola, 2005. 544 pp. (in Russian).

8. Tarasov E. V. Algorithm for the Optimal Design of a Flying Vehicle. Moscow: Mashinostroyeniye, 1970. 364 pp. (in Russian).

9. Krotov V. F., Gurman V. I. Optimal Control Methods and Problems. Moscow: Nauka, 1973. 446 pp. (in Russian).

10. Razumev V. F., Kovalev B. K. Basics of Solid-Propellant Ballistic Rocket Design. Moscow: Mashinostroyeniye, 1976. 356 pp. (in Russian).

11. Sinyukov A. M., Volkov L. I., L'vov A. I., Shishkevich A. M. Solid-Propellant Ballistic Missile. Moscow: Voenizdat, 1972. 511 pp. (in Russian).

12. Erokhin B. T. Theoretical Foundations of Solid-Propellant Rocket Engine Design. Moscow: Mashinostroyeniye, 1982. 206 pp. (in Russian).

13. Abugov D. I., Bobylev V. M. Solid-Propellant Rocket Engine Theory and Design. Moscow: Mashinostroyeniye, 1987. 272 pp. (in Russian).

14. Shishkov A. A. Solid-Propellant Rocket Engine Gas Dynamics. Moscow: Mashinostroyeniye, 1974. 156 pp. (in Russian).

15. E. L. Fleeman. Tactical Missile Design. Second Edition. Liburn, Georgia: AIAA Education Series, 2006. 469 pp.

DOI: https://doi.org/10.15407/itm2019.01.038

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