RLV再入标准轨道制导与轨道预测制导方法比较分析

Comparisons Between Reference-trajectory and Predictor-corrector Entry Guidances for RLVs

提出只更新飞行剖面参数的航程更新方法及相应的RLV再入标准轨道制导规律;结合轨道在线生成与跟踪技术,采用Runge-Kutta-Fehlberg自适应变步长轨道快速预报方法,研究了RLV再入轨道预测制导。进一步对两种制导方法进行了比较分析研究,研究认为标准轨道制导与轨道预测制导都是可行的RLV再入制导方案,其有机结合是未来可重复使用跨大气层飞行器再入制导的发展趋势。

A new reusable launch vehicle （RLV） entry guidance algorithm with ranging technique which only needs to update flight profile parameters was developed and a predictor-corrector entry guidance methodology using Runge-Kutta-Fehlberg method for RLVs combined with trajectory online generation technology was studied. Comparisons between the two guidance schemes were performed, and simulation results show that the two guidance methods are feasible, which indicates that the integration of reference-trajectory entry guidance and predictor-corrector entry guidance is a promising entry guidance scheme for future RLVs.