亚轨道飞行器能量管理段轨迹设计
收稿日期: 2016-04-21
修回日期: 2016-05-27
网络出版日期: 2016-06-12
Trajectory design for terminal area energy management of suborbital reusable launch vehicle
Received date: 2016-04-21
Revised date: 2016-05-27
Online published: 2016-06-12
臧希恒 , 胡永太 . 亚轨道飞行器能量管理段轨迹设计[J]. 航空学报, 2016 , 37(S1) : 99 -105 . DOI: 10.7527/S1000-6893.2016.0170
The energy of suborbital reusable launch vehicle (SRLV) is controlled and managed by flying along a specific path, so the method of trajectory design is a key technology for terminal area energy management (TAEM). The principle, criterion and process of trajectory design methodology for TAEM of SRLV are represented. An approach of reference dynamic pressure profile design based on distance-to-go is proposed. The subsonic state for entering heading alignment phase is ensured by adjusting the dynamic pressure at heading alignment phase, in this way the SRLV turning overshoot is avoided. In order to ensure the TAEM/approach and landing interface constraints to be met in the presence of severe headwinds, the reference dynamic pressure is designed in tailwind conditions as default. Finally, according to the example simulation analysis, the validity of the TAEM trajectory design method is proved.
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