| 弹道式飞行器再入高度惯性控制方案 |
| |
| 引用本文： | 杨辉耀.弹道式飞行器再入高度惯性控制方案[J].航天控制,1998,16(1):50-55. |
| |
| 作者姓名： | 杨辉耀 |
| |
| 作者单位： | 第二炮兵工程学院,西安,710025 |
| |
| 摘 要： | 弹道式飞行器再入时，常常要求在规定高度上发出开伞信号，目前用的过载延时控制方法误差太大。本文以飞行器轴向视速度及其积分为控制信号，用共扼方程法设计了一种惯性高度控制方案。计算结果表明，该方案的控制误差小于１００ｍ。
|
| 关 键 词： | 弹道式飞行器 再入高度 高度控制 |
| 修稿时间： | 1997年8月21日 |
The Inertial Controlling Scheme to Reentry Altitude of Ballistic Vehicle |
| |
| Yang Hueyao.The Inertial Controlling Scheme to Reentry Altitude of Ballistic Vehicle[J].Aerospace Control,1998,16(1):50-55. |
| |
| Authors: | Yang Hueyao |
| |
| Institution: | Yang Hueyao The Second Artillery College Xian 710025 |
| |
| Abstract: | It is usually required to send out an opening parachute signal at the prescribed altitude when the ballistic vehicle reenters. The altitude controlled error through axis apparent acceleration method now used can not meet the required precision. An inertial controlling scheme to the altitude with the signal of the axis apparent velocity and its integral by the method of conjugate equation is presented in this paper. The computation results show that the controlled error of this scheme is less than 100m. |
| |
| Keywords: | Ballistic vehicle\ Reentry altitude\ Altitude control |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
