固体火箭技术2013，Vol.36Issue(1)：1-5,16,6.DOI:10.7673/j.issn.1006-2793.2013.01.001
基于修正Newton法的固体火箭能量管理弹道设计
Energy management trajectory design of solid launch vehicle based on modified Newton method
李新国 1王晨曦 2王文虎3
作者信息
- 1. 西北工业大学航天学院,西安 710072
- 2. 航天飞行动力学技术重点实验室,西安 710072
- 折叠
摘要
Abstract
In order to adapt to the lanching requirement of new payload,a proper trajectory design method considering different energy with multiple terminal constraints at cut-off point was developed. In this paper,an energy management technology based yaw attitude maneuver program in the rockets 3rd stage was proposed,and then the trajectory design of solid rocket was translated into parameters design problem which can be solved based on modified Newlon method. In additional, the glide capability of common aero vehicle ( CAV) with different energy was analyzed, which verified the feasibility of this design method used in lanching of new kind of payload.
关键词
固体运载火箭/耗尽关机/能量管理/修正Newton法Key words
solid launch vehicle/ depleted shutdown/ energy management/ modified Newton method分类
航空航天引用本文复制引用
李新国,王晨曦,王文虎..基于修正Newton法的固体火箭能量管理弹道设计[J].固体火箭技术,2013,36(1):1-5,16,6.
