可重复使用飞行器制导控制一体化技术

崔乃刚; 李浩; 卢宝刚; 韦常柱

doi:10.3788/OPE.20172514.0052

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可重复使用飞行器制导控制一体化技术

更新时间：2020-08-13

- 可重复使用飞行器制导控制一体化技术
- Integrated guidance and control for reusable launch vehicle
- 光学精密工程 2017年25卷第12z期页码：52-58
- 作者机构：
  
  1. 哈尔滨工业大学航天学院,黑龙江哈尔滨,150001
  2. 北京航天长征飞行器研究所北京,100076
- 作者简介：
- 基金信息：
  
  微小型航天器技术国防重点学科实验室开放基金资助项目（No.HIT.KLOF.MST.201704）()
- DOI：10.3788/OPE.20172514.0052
  中图分类号： V488.2
- 收稿日期：2017-08-20，
  
  修回日期：2017-09-10，
  
  纸质出版日期：2017-12-31
- 稿件说明：
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崔乃刚, 李浩, 卢宝刚等. 可重复使用飞行器制导控制一体化技术[J]. 光学精密工程, 2017,25(12z): 52-58

CUI Nai-gang, LI Hao, LU Bao-gang etc. Integrated guidance and control for reusable launch vehicle[J]. Editorial Office of Optics and Precision Engineering, 2017,25(12z): 52-58
崔乃刚, 李浩, 卢宝刚等. 可重复使用飞行器制导控制一体化技术[J]. 光学精密工程, 2017,25(12z): 52-58 DOI： 10.3788/OPE.20172514.0052.

CUI Nai-gang, LI Hao, LU Bao-gang etc. Integrated guidance and control for reusable launch vehicle[J]. Editorial Office of Optics and Precision Engineering, 2017,25(12z): 52-58 DOI： 10.3788/OPE.20172514.0052.

摘要

为了确保下一代可重复使用飞行器具有自主再入的能力，避免气动舵故障导致的再入失败，建立了制导控制一体化系统。对该系统所采用的反演制导、控制分配、模型跟踪滤波、抗饱和等算法进行研究。首先，根据再入动力学和运动学方程推导了反演制导算法。接着，由动态逆原理设计了气动舵的分配算法，即先计算控制力矩的伪逆矩阵后进行控制分配。然后，为了提高系统应对模型误差等的鲁棒性，说明了采用前置滤波器进行制导指令跟踪的算法。最后，介绍了系统带宽自适应方法以及积分抗饱和方法。实验结果表明：飞行器安全再入返回的成功率为77%；控制系统的跟踪精度为0.1°。一体化系统可以有效地提高气动舵故障后飞行器再入的安全性，且控制系统具有精度高、抗干扰能力强等要求。

Abstract

In order to assure the automatic re-entry ability for next generation Reusable Launch Vehicle (RLV)

and avoide the failure lead by breakdown of actuators

an integrated guidance and control system was established. And its applied algorithms such as backstepping guidance

control allocator

model following prefilter

anti-windup and etc were investigated. First

backstepping guidance algorithm was deduced based on entry dynamics and kinematics. Actuators control allocator was analyzed by utilizing the dynamic inverse theory

thus computing the pseudo-inverse matrix based on moments command to reassign actuator commands. Then the algorithm of prefilter by guidance commands following was analyzed to improve the system robustness for model errors. Finally

the method of reference model bandwidth attenuation and integrator anti-windup were discussed. Experimental results indicate that the success ratio of re-entry is 77% and the precision of the control error is within 0.1°. The integrated system can satisfy the system requirements of higher precision and robustness

and increase re-entry safety while RLV's actuators failed to work normally.

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references

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