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弹箭与制导学报 >

2023 , Vol. 43 >Issue 4: 98 - 104

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2023.04.015

考虑落角约束和气动不确定性的固定时间制导控制一体化设计方法

  • 胡诚伟 ,
  • 韦悠 ,
  • 汪学平
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  • 西安现代控制技术研究所,陕西 西安 710065

胡诚伟(1980—),男,高级工程师,硕士,研究方向:车载武器装备任务管控。

收稿日期: 2022-08-18

  网络出版日期: 2025-02-07

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Fixed-time Integrated Guidance and Control for Impact Angle Constrained Interception with Multiple Uncertainties

  • HU Chengwei ,
  • WEI You ,
  • WANG Xueping
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  • Xi'an Mordern Control Technology Research Institute, Xi'an 710065, Shaanxi, China

Received date: 2022-08-18

  Online published: 2025-02-07

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摘要

文中研究落角约束和气动不确定性条件下的机动目标制导控制一体化设计问题。首先,将目标的加速度和气动不确定性考虑为有界的外部扰动。其次,将典型的反步法与动态曲面控制技术相结合,提出了一种固定时间滑模控制方法来解决制导控制一体化设计问题,并通过引入固定时间微分器有效避免反步法中存在的“微分膨胀”问题。然后,借助于固定时间稳定性理论对闭环系统进行了稳定性分析,表明所提方法能够使所有误差信号在任意初始条件下实现半全局固定时间一致最终有界稳定。最后,通过仿真验证了所提方法的有效性。

关键词： 制导控制一体化设计; 落角约束; 机动目标拦截; 固定时间稳定性; 气动不确定性

本文引用格式

胡诚伟 , 韦悠 , 汪学平 . 考虑落角约束和气动不确定性的固定时间制导控制一体化设计方法[J]. 弹箭与制导学报, 2023 , 43(4) : 98 -104 . DOI: 10.15892/j.cnki.djzdxb.2023.04.015

Abstract

This paper considers the integrated guidance and control (IGC) problem for maneuvering target interception with impact angle constraint and uncertain aerodynamics. The target’s acceleration and uncertain aerodynamics are considered as bounded external disturbances. By combining the typical backstepping idea with dynamic surface control (DSC) technique, a fixed-time sliding mode control approach is presented to address the IGC law design problem and the inherent problem of “explosion of complexity” in typical backstepping design is efficiently avoided by introducing a fixed-time differentiator. Furthermore, fixed-time stability theory is presented to carry out the stability analysis showing that with the proposed control scheme all signals in the sliding mode system can achieve semi-globally fixed-timely uniformly ultimately bounded stabilization independent of initial conditions. Finally, the superiority of the proposed IGC law is demonstrated by simulation results.

Key words： integrated guidance and control; impact angle constraint; maneuvering target interception; fixed-time stability; aerodynamic uncertainties

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参考文献

原文顺序 | 文献年度倒序 | 文中引用次数倒序
[1]
YAN H, TAN S P, HE Y Z. A small-gain method for integrated guidance and control in terminal phase of reentry[J]. Acta Astronautica, 2017, 132: 282-292.

[2]
WANG X H, WANG J Z. Partial integrated guidance and control with impact angle constraints[J]. Journal of Guidance, Control, and Dynamics, 2015: 38(5): 925-936.

[3]
YANG C D, YANG C C. Analytical solution of three-dimensional realistic true proportional navigation[J]. Journal of Guidance, Control, and Dynamics, 2012, 19(3): 569-577.

[4]
OHIMEYER E. Root-mean-square miss distance of proportional navigation missile against sinusoidal target[J]. Journal of Guidance, Control, and Dynamics, 2015, 19(3): 563-568.

[5]
ZHOU D, MU C, XU W. Adaptive sliding-mode guidance for a homing missile[J]. Journal of Guidance, Control, and Dynamics, 1999, 22(4): 589-594.

[6]
MOON J K, KIM Y D. Design of missile guidance law via variable structure control[J]. Journal of Guidance, Control, and Dynamics, 2001, 24(4): 659-664.

[7]
KUMAR S, RAO S, GHOSE D. Nonsingular terminal sliding mode guidance with impact angle constraints[J]. Journal of Guidance, Control, and Dynamics, 2014, 37(4): 610-621.

[8]
ZHANG Y, TANG S J, GUO J. Adaptive terminal angle constraint interception against maneuvering targets with fast fixed-time convergence[J]. International Journal of Robust and Nonlinear Control, 2018, 2: 2996-3014.

[9]
GURFIL P, JODORKOVSKYM M, GUELMAN M. Finite time stability approach to proportional navigation systems analysis[J]. Journal of Guidance, Control, and Dynamics, 1998, 21(6): 853-861.

[10]
CHWA D, CHOI J. Adaptive nonlinear guidance law considering control loop dynamics[J]. IEEE Transactions on Aerospace and Electronic Systems, 2003, 39(4): 1134-1143.

[11]
SUN S, ZHOU D, HOU W T. A guidance law with finite time convergence accounting for autopilot lag[J], Aerospace Science and Technology, 2013, 25(1): 132-137.

[12]
MENON P, OHLMEYER E. Integrated design of agile missile guidance and autopilot systems[J]. Control Engineering Practice, 2001, 9(10): 1095-1106.

[13]
VADDO S, MENON P, OHLMEYER E. Numerical state-dependent Raccati equation approach for missile integrated guidance control[J]. Journal of Guidance, Control, and Dynamics, 2009, 32(2): 699-703.

[14]
XIN M, BALAKRISHNAN S N, OHLMEYER E J. Integrated guidance and control missiles with method[J]. IEEE Transactions on Control Systems Technology, 2006, 14(6): 981-992.

[15]
RADHAKANT P, CHARU C, PRIYA D G. Partial integrated guidance and control of interceptors for high-speed ballistic targets[J]. Journal of Guidance, Control, and Dynamics, 2014, 37(1): 149-163.

[16]
KIM J H, WHANG I H, KIM B M. Finite horizon integrated guidance and control for terminal homing in vertical plane[J], Journal of Guidance, Control, and Dynamics, 2016, 39(5): 1104-1112.

[17]
HE S M, LIN D F, WANG J. Continuous second-order sliding mode based impact angle guidance law[J]. Aerospace Science and Technology, 2015, 41: 199-208.

[18]
SHIN H S, HWANG T, TSOPURDOS A, et al. Integrated intercept missile guidance and control with terminal angle constraint[C]// ICAS. Proceedings of the 26th International Congress of the Aeronautical Sciences. Brisbane: ICAS, 2008: 1875-1884.

[19]
SHEN Y C, YU J Q, LUO G C, et al. Observer-based adaptive sliding mode backstepping output-feedback DSC for spin-stabilized canard-controlled projectiles[J]. Chinese Journal Aeronautics, 2017, 30(3): 1115-1126.

[20]
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.

[21]
RAN M P, WANG Q, HOU D L, et al. Backstepping design of missile guidance and control based on adaptive fuzzy sliding mode control[J]. Chinese Journal of Aeronautics, 2014, 27(3): 634-642.

[22]
HE S M, SONG T, LIN D F. Impact angle constrained integrated guidance and control for maneuvering target interception[J]. Journal of Guidance, Control, and Dynamics, 2017, 40(10): 2652-2660.

[23]
NI J K, LIU L, LIU C X, et al. Fast fixed-time nonsingular terminal sliding mode control and its application to chaos suppression in power system[J]. IEEE Transactions on Circuits and Systems, 2017, 64(2): 151-155.

[24]
NI J K, LIU L, LIU C X, et al. Fixed-time dynamic surface high-order sliding mode control for chaotic oscillation in power system[J]. Nonlinear Dynamics, 2016, 86(1): 401-420.

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