摘要
将飞船返回控制过程按不同阶段进行分解,分析返回各阶段的返回控制精度影响因素,并标定返回制动推力系数。根据返回控制精度分析结果,进行技术状态改进,在神舟十号返回任务成功验证了引入返回泄压模型进行轨道预报、采用返回制动推力系数标定结果计算返回控制参数,可以有效提高返回控制精度,对如何减小返回控制误差,在工程设计上具有借鉴作用。
By dividing the course of spaceship return into Clltterent stages, me lactt,~ m^Ll.~ control accuracy in each stage were analyzed and the thrust-coefficient of brake engine was calibrated. Based on the control accuracy analysis, some technical improvements were made. During the return of Shenzhou 10 manned spaceship, pressure relief model was introduced into the trajectory forecasting and thrust-coefficient of brake engine was used to calculate the control parameters. The results showed that the control accuracy was effectively improved which was of great significance for the engineering application. The analysis of factors affecting the return accuracy level could serve as a reference for the error reduction of spaceship return control as well as trajectory design.
出处
《载人航天》
CSCD
2014年第1期21-25,共5页
Manned Spaceflight
关键词
返回控制
再入制导
泄压
制动推力系数
返回轨道设计
return control
reentry guidance
pressure relief
thrust-coefficient of brake engine
re- turn trajectory design
