Based on the finite time theory, the finite time convergence terminal guidance law and Pulse Width Pulse Frequency (PWPF) modulator are proposed for intercepting near space high-speed maneuvering targets. First, the mathematical model and working principle of terminal guidance with PWPF modulator are introduced. Second, the finite time convergent guidance law is designed. The convergence conditions and properties are proved based on the finite time theory, and areextended to the condition considering the thrust constraint. Finally, considering the fast convergence of Line of Sight (LOS) angular rate and the minimum working time of the engine, the parameters of the PWPF modulator are designed. The simulation results show that the LOS angular rate converges to zero in finite time before the end of terminal guidance. The guidance law, robust to the maneuvering target, has higher guidance precision. and can avoid frequent on-off of the engine to save fuel.
DUAN Meijun
,
ZHOU Di
,
CHENG Dalin
. Development of terminal guidance law and PWPF modulator for near space interceptor based on finite time theory[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018
, 39(1)
: 321481
-321481
.
DOI: 10.7527/S1000-6893.2017.321481
[1] GUO G, LIU H, ZHANG B. Aero-optical effects of an optical seeker with a supersonic jet for hypersonic vehicles in near space[J]. Applied optics, 2016, 55(17):4741-4751.[2] LIU X, LIU W, ZHAO Y. Navier-Stokes predictions of dynamic stability derivatives for air-breathing hypersonic vehicle[J]. Acta Astronautica, 2016, 118:262-285.[3] BORG M P, SCHNEIDER S P. Effect of freestream noise on roughness-induced transition for the X-51A forebody[J]. Journal of Spacecraft and Rockets, 2008, 45(6):1106-1116.[4] 周伟. 美国导弹防御拦截系统的发展趋势分析[J]. 现代军事, 2015(10):60-66. ZHOU W. Analysis of the development trend of American missile defense interception system[J]. Modern Military, 2015(10):60-66(in Chinese).[5] 王肖, 郭杰, 唐胜景, 等. 吸气式高超声速飞行器鲁棒非奇异Terminal滑模反步控制[J]. 航空学报, 2017, 38(3):320287. WANG X, GUO J, TANG S J, et al. Robust nonsingular Terminal sliding mode backstepping control for air-breathing hypersonic vehicles[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(3):320287(in Chinese).[6] KUMAR S R, RAO S, GHOSE D. Nonsingular terminal sliding mode guidance with impact angle constraints[J]. Journal of Guidance, Control, and Dynamics, 2014, 37(4):1114-1130.[7] SONG J, NIU Y, ZOU Y. Finite-time stabilization via sliding mode control[J]. IEEE Transactions on Automatic Control, 2017, 62(3):1478-1483.[8] LI G, JI H. A three-dimensional robust nonlinear terminal guidance law with ISS finite-time convergence[J]. International Journal of Control, 2016, 89(5):938-949.[9] ZHANG Z, MAN C, LI S, et al. Finite-time guidance laws for three-dimensional missile-target interception[J]. Proceedings of the Institution of Mechanical Engineers, Part G:Journal of Aerospace Engineering, 2016, 230(2):392-403.[10] LI G L, YAN H, JI H B. A guidance law with finite time convergence considering autopilot dynamics and uncertainties[J]. International Journal of Control, Automation and Systems, 2014, 12(5):1011-1017.[11] QU P, SHAO C, ZHOU D. Finite time convergence guidance law accounting for missile autopilot[J]. Journal of Dynamic Systems, Measurement, and Control, 2015, 137(5):051014.[12] GUO Y, HU X, HE F, et al. Triangle interception scenario:A finite-time guidance approach[J]. International Journal of Aerospace Engineering, 2016(3):1-12.[13] 周红建, 赵拥军. PWPF调节器在空间拦截器侧力控制中的应用[J]. 系统工程与电子技术, 1997, 19(4):9-12. ZHOU H J, ZHAO Y J. Application of PWPF modulator in space interceptor side force control[J]. System Engineering and Electronics, 1997, 19(4):9-12(in Chinese).[14] 王清, 杨宝庆, 马克茂. 一种优化PWPF调节器在动能拦截器末制导中的应用研究[J]. 宇航学报, 2005, 26(5):576-580. WANG Q, YANG B Q, MA K M. PWPF optimizing design and its application research to terminal guidance of kenetic killing vehicle[J]. Journal of Astronautics, 2005, 26(5):576-580(in Chinese).[15] GUO J, ZHANG T, ZHOU J, et al. The three dimensional guidance system design of terminal attack phase for exo-atmospheric kill vehicle[J]. Optic-International Journal for Light and Electron Optics, 2017, 130:1158-1167.[16] KHOSRAVI A, SARHADI P. Tuning of pulse-width pulse-frequency modulator using PSO:An engineering approach to spacecraft attitude controller design[J]. Automatica, 2016, 57(1):212-220.[17] BELLAR A, FELLAH M K, MOHAMMED M A S. A cold gas thruster microsatellite attitude control[J]. Revue Roumaine des Science Techniques-Series Electro Technique et Energetique, 2013, 58(4):395-404.[18] LI P, ZHU Z H, MEGUID S A. State dependent model predictive control for orbital rendezvous using pulse-width pulse-frequency modulated thrusters[J]. Advances in Space Research, 2016, 58(1):64-73.[19] SHIRAZI A, MAZINAN A H. Mathematical modeling of spacecraft guidance and control system in 3D space orbit transfer mission[J]. Computational and Applied Mathematics, 2016, 35(3):865-879.[20] MAZINAN A H. A lyapunov-based three-axis attitude intelligent control approach for unmanned aerial vehicle[J]. Journal of Central South University, 2015, 22(12):4669-4678.[21] ZHOU D, SUN S, TEO K L. Guidance laws with finite time convergence[J]. Journal of Guidance, Control, and Dynamics, 2009, 32(6):1838-1846.[22] 孙胜, 周荻. 有限时间收敛变结构导引律[J]. 宇航学报, 2008, 29(4):1258-1262. SUN S, ZHOU D. A finite time convergent variable structure guidance law[J]. Journal of Astronautics, 2008, 29(4):1258-1262(in Chinese).
CJA