导弹制导与控制一体化三通道解耦设计方法

doi:10.7527/S1000-6893.2014.0078

Abstract

Abstract:

Based on extended state observer (ESO) and backstepping-sliding mode design method, a novel integrated guidance and control three-channel decoupling design approach is proposed for the problem that a homing missile attacks ground target during diving phase. The fully integrated guidance and control model is established by combining guidance and control system in addition to considering interaction between three channels in control system. ESOs are adopted to estimate and compensate dynamic coupling terms and uncertainties currently in six degrees of freedom (6DOF) system, which realizes the active decoupling between each channel in the system, thereby generating three-channel decoupling control law for integrated missile guidance and control based on ESO. Meanwhile, in order to solve the problem that high order nonlinear system can cause "computation explosion" according to using ESO to measure state values, the adaptive control law is employed to afford redress for observation error in ESO. It is demonstrated that all states in the closed loop system are ultimately bounded on account of Lyapunov stability theorem. Compared with three-channel independent design method for integrated system and traditional guidance and control system design method, the simulation results verify the advantages and practicalities of the integrated guidance and control decoupling design algorithm based on ESO.

Key words: integrated guidance and control, backstepping, sliding mode control, three channels, decoupling design, extended state observer

CLC Number:

ZHANG Yao, GUO Jie, TANG Shengjing, MA Yueyue. Integrated Missile Guidance and Control Three-channel Decoupling Design Method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(12): 3438-3450.

References

[1] Hou M Z. Integrated guidance and control for homing missiles[D]. Harbin: Harbin Institute of Technology, 2011. (in Chinese) 侯明哲. 寻的导弹导引与控制一体化设计[D]. 哈尔滨: 哈尔滨工业大学, 2011.

[2] Williams D E, Richman J, Friedland B. Design of an integrated strapdown guidance and control system for a tactical missile, AIAA-1983-2169[R]. Reston: AIAA, 1983.

[3] Tournes C, Paschal N, Wilkerson P. Integrated terminal guidance and automatic pilot subspace-stabilization, AIAA-2001-4275[R]. Reston: AIAA, 2001.

[4] Shima T, Idan M, Golan O M. Sliding mode control for integrated missile autopilot guidance[J]. Journal of Guidance, Control, and Dynamics, 2006, 29(2): 250-260.

[5] Hwang T W, Tahk M J. Integrated backstepping design of missile guidance and control with robust disturbance observer[C]//International Joint Conference SICE-ICASE. 2006: 4911-4915.

[6] Yan H, Ji H B. Integrated guidance and control for dual-control missiles based on small-gain theorem[J]. Automatica, 2012, 48(10): 2686-2692.

[7] Dong F Y, Lei H M, Zhou C J, et al. Research of integrated robust high order sliding mode guidance and control for missiles[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(9): 2212-2218. (in Chinese) 董飞垚, 雷虎民, 周池军, 等. 导弹鲁棒高阶滑模制导控制一体化方法研究[J]. 航空学报, 2013, 34(9): 2212-2218.

[8] Ge L Z, Shen Y, Yuan L H. Three-dimensional guidance model and guidance law design for head pursuit interception[J]. Systems Engineering and Electronics, 2008, 30(6): 1118-1121. (in Chinese) 葛连正, 沈毅, 院老虎. 前向拦截的三维制导模型及制导律设计[J]. 系统工程与电子技术, 2013, 30(6): 1118-1121.

[9] Zhu K, Qi N M. Research on vertical impact terminal guidance law based on sliding mode disturbance observer[J]. Acta Armamentrii, 2011, 32(12): 1462-1467. (in Chinese) 朱凯, 齐乃明. 基于滑模干扰观测器的垂直攻击末制导律研究[J]. 兵工学报, 2011, 32(12): 1462-1467.

[10] Zhang J P, Yan J J, Li S H, et al. A guidance law design based on disturbance observer and backstepping[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(12): 2291-2300. (in Chinese) 张金鹏, 燕洁静, 李世华, 等. 基于Backstepping和扰动观测器的导引律[J]. 航空学报, 2012, 33(12): 2291-2300.

[11] Ma K M, Ma J. Design and implementation of variable structure guidance law for maneuvering target interception[J]. Journal of Astronautics, 2010, 31(6): 1589-1594. (in Chinese) 马克茂, 马杰. 机动目标拦截的变结构制导律设计与实现[J]. 宇航学报, 2010, 31(6): 1589-1594.

[12] Shu Y J, Tang S. Integrated guidance and control backstepping design for blended control missile based on NDO[J]. Journal of Astronautics, 2013, 34(1): 79-85. (in Chinese) 舒燕军, 唐硕. 轨控式复合控制导弹制导与控制一体化反步设计[J]. 宇航学报, 2013, 34(1): 79-85.

[13] Hou M Z, Liang X L, Duan G R. Adaptive block dynamic surface control for integrated missile guidance and autopilot[J]. Chinese Journal of Aeronautics, 2013, 26(3): 741-750.

[14] Ma Y Y, Tang S J, Guo J, et al. High angle of attack control system design based on ADRC and fuzzy logic[J]. Systems Engineering and Electronics, 2013, 35(8): 1711-1716. (in Chinese) 马悦悦, 唐胜景, 郭杰, 等. 基于自抗扰与模糊逻辑的大攻角控制系统设计[J]. 系统工程与电子技术, 2013, 35(8): 1711-1716.

[15] Guo B Z, Zhao Z L. On the convergence of an extended state observer for nonlinear systems with uncertainty[J]. System and Control Letters, 2011, 60(6): 420-430.

[16] Zhu Z, Xu D, Liu J M, et al. Missile guidance law based on extended state observer[J]. IEEE Transactions on Industrial Electronics, 2013, 60(12): 5882-5891.

[17] Han J Q. Active disturbance rejection control technique-the technique for estimating and compensating the uncertainties[M]. Beijing: National Defense Industry Press, 2008: 221-237. (in Chinese) 韩京清. 自抗扰控制技术——估计补偿不确定因素的控制技术[M]. 北京:国防工业出版社, 2008: 221-237.

[18] Vaddi S S, Menon P K, Ohlmeyer E J. Numerical SDRE approach for missile integrated guidance and control[J]. Journal of Guidance, Control, and Dynamics, 2009, 32(2): 699-703.

[19] Khalil H. Nonlinear systems[M]. Upper Saddle River: Prentice Hall, 1996: 66-68.

[20] 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.

Integrated Missile Guidance and Control Three-channel Decoupling Design Method

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Hongyan ZHANG, Wei WANG, Shiwei CHEN, Yi JI, Jiaqi LIU. Integrated guidance and control design based on fully actuated system method [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(1): 628891-628891.
[2]	Leyan FANG, Han MENG, Mingzhe HOU. Iterative learning sliding mode control with precise parameter estimation and its application [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(1): 628889-628889.
[3]	Zeyang YIN, Youpeng XING, Fei HAN, Caisheng WEI, Yuxin LIAO. Fully-actuated prescribed performance control of spacecraft formation for flying cooperatively around non-cooperative target [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(1): 628904-628904.
[4]	Xinyu HOU, Fan ZHANG, Panfeng HUANG, Xiaofei MA, Jialong ZHU, Yang LI. Integrated attitude and vibration control of space large antenna with truss [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S1): 727552-727552.
[5]	Wu LIU, Yunyan WU, Wei LIU, Mingming TIAN, Tianpeng HUANG. Re-entry robust fault tolerant attitude control for RLVs considering unknown disturbances [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S1): 727787-727787.
[6]	Xu ZHAO, Guoyuan QI, Xinchen YU, Jianbing HU, Xia LI. Compensation function observer and its application in flight vehicle attitude control [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(9): 327224-327224.
[7]	Zheng LI, Jianqiao YU, Xinyun ZHAO. Fixed⁃time convergent sliding mode control for agile turn of air⁃to⁃air missiles [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(8): 327262-327262.
[8]	Yongzhi SHENG, Jiahao GAN, Chengxin ZHANG. Fractional order sliding mode guidance law design with trajectory adjustable and terminal angular constraint [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(7): 327073-327073.
[9]	Shihao XU, Yingzi GUAN, Jialun PU, Changzhu WEI. Predefined-time sliding mode control for VTHL launch vehicle in reentry phase [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(7): 326857-326857.
[10]	Zhongsen WANG, Yuxin LIAO, Caisheng WEI, Ting DAI. Fast terminal sliding mode fault⁃tolerant control of hypersonic vehicle with guaranteed performance [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(24): 328476-328476.
[11]	Linkun HE, Wenchao XUE, Ran ZHANG, Huifeng LI. Guidance and control for powered descent and landing of launch vehicles: Overview and outlook [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(23): 628462-628462.
[12]	Liang ZHANG, Danyu LI, Naigang CUI, Yuan LI. Full flight profile prescribed performance control for vertical take-off and vertical landing reusable launch vehicle [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(23): 628103-628103.
[13]	Xiao MENG, Dan MA, Hongjun LIN, Chao CHEN. Prescribed performance control of thermoacoustic instability in aero-engine combustion chambers [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(17): 128182-128182.
[14]	Bo LIU, Zhongjie MENG. Tanker/UAV formation tracking control with hose connection constraints [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(17): 328210-328210.
[15]	Hao ZHANG, Peng WANG, Guojian TANG, Weimin BAO. Event-triggered fast finite time control for hypersonic morphing vehicles [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(15): 528494-528494.