宇航学报 ›› 2012, Vol. 33 ›› Issue (11): 1630-1635.doi: 10.3873/j.issn.1000-1328.2012.11.011

• 制导、导航与控制 • 上一篇    下一篇

受输入饱和约束的导弹直接侧向力/气动力

胥彪, 周荻   

  1. 哈尔滨工业大学航天学院,哈尔滨 150001
  • 收稿日期:2011-09-18 修回日期:2011-11-09 出版日期:2012-11-15 发布日期:2012-12-05
  • 作者简介:10001328(2012)11163006
  • 基金资助:
    国家自然科学基金(61174203);教育部新世纪人才支持计划(NCET-08-0153);总装备部预研基金(9140A01010212HT01005);航空科学基金(20110177002)

Dual Aero/Propulsive Missile Control Subject to Input Saturation

XU Biao, ZHOU Di   

  1. School of Astronautics, Harbin Institute of Technology, Harbin 150001, China
  • Received:2011-09-18 Revised:2011-11-09 Online:2012-11-15 Published:2012-12-05

摘要: 针对受输入饱和约束的直接侧向力与气动力复合控制的导弹,研究其自动驾驶仪设计问题。导弹的执行机构分别是舵机和侧向脉冲发动机。舵机提供的是连续的控制量,而侧向脉冲发动机提供的是离散的控制量。首先采用最优控制方法设计连续的舵控制器。再对设计好舵控回路的新受控弹体,基于含有界干扰项离散饱和系统不变集分析方法进行直接侧向力控制器的设计。设计过程中,充分考虑了舵偏角的饱和非线性因素以及侧向脉冲发动机点火数取整产生的量化误差。最后,利用数值仿真验证了所提出控制方法的有效性。

关键词: 复合控制, 饱和非线性, 不变集, 量化误差

Abstract: For a missile controlled by the combination of lateral pulse thrusters and aerodynamic fins subject to input saturation, an autopilot is designed. The aerodynamic fins are continuous actuators, while the lateral pulse thrusters are discrete ones. A continuous controller for aerodynamic fins is first designed by using the linear quadratic optimal control method, and then the discrete lateral pulse thrusters control system is designed based on the continuous aerodynamic fins control system. An optimization\|based approach is developed to design the controller of lateral pulse thrusters by utilizing the invariant set analysis with bounded disturbance rejection. In the design process, the actuator saturation of fins and the quantized error of thrusters are considered. Numerical simulation shows the effectiveness of the presented approach.

Key words: Dual control, Saturation, Invariant set, Quantized error

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