中国科技核心期刊

中文核心期刊

CSCD来源期刊

空间控制技术与应用

• 论文与报告 • 上一篇    下一篇

深空探测转移轨道自主中途修正方法研究

张晓文1,2,王大轶1,2,黄翔宇1,2   

  1. 1. 北京控制工程研究所, 北京 100190;2. 空间智能控制技术国家级重点实验室, 北京 100190
  • 收稿日期:1900-01-01 修回日期:1900-01-01 出版日期:2009-08-26 发布日期:2009-08-26

Study on the Autonomous Midcourse Correction during Cruise Phase of
Interplanetary Exploration

ZHANG Xiaowen1,2, WANG Dayi1,2, HUANG Xiangyu1,2   

  1. 1. Beijing Institute of Control Engineering, Beijing 100190, China;
    2. National Laboratory of Space Intelligent Control, Beijing 100190, China
  • Received:1900-01-01 Revised:1900-01-01 Online:2009-08-26 Published:2009-08-26

摘要: 针对深空转移轨道,提出以B平面参数为终端参数,采用脉冲控制和线性制导的自主中途修正方法。由自主导航系统定期确定探测器当前位置和速度,之后利用精确动力学积分递推状态至B平面,得到打靶误差,若误差超出目标精度范围又在自主修正系统修正能力范围内,则立即利用以B平面参数为终端参数的线性制导公式并结合牛顿迭代计算出修正轨道的速度增量。利用中心差分公式计算终端参数对控制参数的敏感矩阵。蒙特卡罗仿真表明,在小偏差前提下该方法能够达到制导目标。

关键词: 中途修正, B平面, 转移轨道, 深空探测

Abstract: Autonomous midcourse correction is a key technique to facilitate autonomy of an interplanetary spacecraft. Using B-plane parameters as target parameters and impulse control method combined with linear guidance, an autonomous orbit correction method used during cruise phase of interplanetary orbit is proposed.First, the navigation system periodically determines positions and velocities of the spacecraft. The state is than mapped forward to the B-plane by integrating the dynamics model precisely. If deviation from the desired encounter condition is large enough and isn’t out of the capability of autonomous midcourse correction system, the velocity increment for correction maneuver is computed by using linear guidance formula combined with Newton iteration method. The sensitivity matrix of target parameters relative to control parameters is numeri-cally computed using finite central difference formula. Monte Carlo Simulation shows that this method is capa-ble of guiding the spacecraft to a successful encounter.

Key words: midcourse correction, B-plane, transfer orbit, deep space exploration

中图分类号: 

  • v448.2