一种末端能量管理段结合PD控制的标称轨迹制导律

doi:10.3969/j.issn.1674-1579.2016.03.011

空间控制技术与应用

• 技术交流 • 上一篇

一种末端能量管理段结合PD控制的标称轨迹制导律

陈阳

北京控制工程研究所，北京 100190

出版日期:2016-06-23 发布日期:2016-06-27
作者简介:作者简介：陈阳（1990—），女，硕士研究生，研究方向为航天器导航、制导与控制.
基金资助:
*国家自然科学基金资助项目（61333008,61273153）.

A Nominal Trajectory Method Combined with PD Control in TAEM Phase

CHEN Yang

（Beijing Institute of Control Engineering, Beijing 100080， China）

Online:2016-06-23 Published:2016-06-27

摘要/Abstract

摘要： 摘要：为了提高制导律的精度和适应性，针对大升阻比再入飞行器的末端能量管理段(TAEM段)的飞行特性，提出一种飞行轨迹制导律.该方法的制导律由标称制导指令和PD控制指令两部分组成，标称制导指令由离线生成的标称轨迹的几何特性结合飞行器的飞行状态实时生成，PD控制指令则由飞行器当前飞行状态与期望飞行状态的误差计算生成.该方法经数学仿真表明，具有较好的控制效果.

关键词: 关键词： PD控制, 标称轨迹, TEAM段, 制导律设计

Abstract: Abstract：In order to enhance the precision and the flexibility of the guidance law, considering the flight characters of the reentry vehicle with large lift drag ratio during the terminal area energy management (TAEM) phase, a guidance law of planning the trajectory is given. This method is composed of two parts, the nominal control orders and the PD control orders. The nominal control orders are built realtime based on the geometrical characters of the nominal trajectory that are gained offline and by the current status of the vehicle at the same time, while the PD control orders are calculated according to the error signals between the current status and the excepted status. After simulating and verifying, the effect and the advantage of this method can be shown.

Key words: Keywords：PD control, nominal trajectory, TAEM phase, guidance design

中图分类号:

V448.2

陈阳. 一种末端能量管理段结合PD控制的标称轨迹制导律[J]. 空间控制技术与应用, 2016, 42(3): 58-62.

CHEN Yang. A Nominal Trajectory Method Combined with PD Control in TAEM Phase[J]. , 2016, 42(3): 58-62.

参考文献

［1］李惠峰. 高超声速飞行器制导与控制技术(上)［M］. 北京：中国宇航出版社，2012. ［2］BRYSON A E, DENHAM W F, CARROLL F J, er al. Determination of the lift or drag program that minimizes reentry heating with acceleration or range constraints using a steepest descent computation procedure［J］. Aerospace Science, 1962(29):420430. ［3］BRYSON A E, MIKAMI K, BATTLE C T. Optimum lateral turns for a reentry glider ［J］. Aerospace Engineer,1962(21):1823. ［4］LEVINSKY E S. Application of inequality constrains to variational problems of lifting reentry［J］. Aerospace Science, 1962(29):400409. ［5］LEONDES C T, OSGOOD W R. Optimization of threedimensional reentry trajectories ［J］. Transactions on Aerospace and Electronic System,1969, 5(2):345346. ［6］胡建学,陈克俊,赵汉元,等. RLV再入混合制导方法研究［J］. 宇航学报, 2007, 28(1):213217. HU J X, CHEN K J, ZHAO H Y, et al. Hybrid entry guidance for reusable launch vehicles［J］. Journal of Astronautics, 2007, 28(1):213217. ［7］潘乐飞,李国新.衍化的加速度再入制导律方案研究［J］.计算机仿真, 2007,24(2):2225. PAN L F, LI G X. Study of evolved acceleration reentry guidance［J］.Computer Simulation, 2007,24(2):2225. ［8］陈敬志,杨一栋.一种新的空间飞行器再入制导律研究［J］. 飞行力学,2007,25(3):5861. CHEN Z J, YANG Y D.Research of the guidance law based on a new method in spacecraft entry［J］. Flight Dynamics, 2007,25(3):5861. ［9］杨俊春,胡军,倪茂林. 基于特征模型的再入飞行器自适应制导律设计［J］. 中国科学：信息科学, 2008, 38(12):21342149. YANG J C, HU J, NI M L. Adaptive control method based on characteristic model［J］. China Science：Information Science, 2008, 38(12):21342149. ［10］张钊,胡军,王勇. 基于特征模型的再入飞行器制导律设计［J］.空间控制技术与应用,2010,36(4):1217. ZHANG Z, HU J, WANG Y.Characteristic modelbased reentry vehicle guidance law design［J］. Aerospace Control and Application, 2010,36(4):1217. ［11］胡建学,陈克俊,赵汉元,等. 改进的RLV再入制导方法及其性能分析［J］.宇航学报, 2006,27(6):14091413. HU J X, CHEN K J, ZHAO H Y,et al. An evolved entry guidance and performance analysis for reusable launch vehicles［J］.Journal of Astronautics, 2006, 27(6):14091413. ［12］精确制导与控制研究所. 大升阻比再入飞行器TEAM段控制技术报告［D］. 西安：西北工业大学，2014. Faculty of Aerospace Engineering. The control technology of the reentry vehicle with large lift drag ratio in team phase ［D］. Xian:Delft University of Technology，2014.

[1]	蔺君, 黄盘兴, 何英姿. 高升阻比再入飞行器阻力加速度设计及跟踪制导[J]. 空间控制技术与应用, 2020, 46(1): 16-.
[2]	句美琪, 何英姿. 基于高度跟踪的末端能量管理段制导[J]. 空间控制技术与应用, 2014, 40(4): 42-46.

一种末端能量管理段结合PD控制的标称轨迹制导律

A Nominal Trajectory Method Combined with PD Control in TAEM Phase

PDF (PC)

赞

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 2

Metrics

本文评价

推荐阅读 0