中国空间科学技术

中国空间科学技术

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载人航天器的再入制导控制与仿真计算

张守信，冯书兴   

  1. 国防科工委指挥技术学院
  • 发布日期:1995-02-25

GUIDANCE, CONTROL AND SIMULATION OF MANNED SPACECRAFT IN REENTRY PHASE

Zhang Shouxin;Fong Shuxing(The Institute or Command and Technology, CONSTIND, Beijing 101407)   

  • Online:1995-02-25

被引次数

3

摘要： 研究了弹道一升力式载人航天器的再入制导规律和各种再入误差源对其落点的影响。主要包括以下内容：再入纵向制导和侧向制导规律的确定；分析各种单项误差对落点的影响；用ＭｏｎｔｅＣａｒｌｏ方法模拟各种再入误差源及其对落点偏差的综合影响。通过大量的模拟计算，掌据各种再入误差对落点偏差的影响，提出再入误差应具有的指标要求，并得到一些有益的结论。计算结果表明，确定的制导规律可以达到满意的落点控制效果。

关键词: 航天器, 再入轨道, 再入制导, 控制, 蒙特卡罗法, 计算

Abstract: his paper studies the reentry guidance rules and the effects of the reentry errors on the landing spot of a spacecraft. Its contents reads as follows: the study of the laws of vertical direction and side direction, to analyze the effect of each error on landing spot; simulation calculating the comprehensive effects of all of errors on the landing spot.It gives the level of the effects of the reentry errors on the landing spot and presents the accuracy levels which the reentry errors must satisfy. The results of simulation prove that the guidance laws can make satisfactory control accuracy of the landing spot.