摘要
针对地面发射快速响应空间需求问题,考虑轨道参数和弹道参数之间互为输入、深度耦合的实际,首先根据简化弹道模型给出了快速访问回归轨道设计方法,然后以轨道参数为输入开展快响火箭弹道规划,在此基础上以规划得到的弹道参数修正简化弹道参数,通过不断迭代,直至简化弹道参数与规划得到的弹道参数之间的误差满足要求,进而得到了满足任务需求的快响回归轨道及弹道参数。具体算例证明了该方法的可用性和有效性,可为快速响应轨道及弹道规划提供理论路径和技术支撑。
Regarding the fact that the orbit parameters and trajectory parameters are the inputs among each other and deeply coupled,the design method of fast access recursive orbit is obtained based on the simplified trajectory model for the mission of operationally responsive space by emergency launch.Then,the design method of launch vehicle trajectory is proposed by the use of orbit parameters.On the basis,the simplified trajectory parameters are modified by the planned trajectory parameters.Through the iteration,the fast ac⁃cess regressive orbit parameters and trajectory parameters that meet the mission requirements are obtained,when the error between the simplified trajectory parameters and the planned trajectory parameters is reduced into the restricted region.The usability and effectiveness of this method is verified by a specific example.The theoretical path and technical support for responsive orbit and trajectory planning can be provided by using this method.
作者
贺绍飞
谷振丰
徐慧娟
许晓
池嘉诚
He Shaofei;Gu Zhenfeng;Xu Huijuan;Xu Xiao;Chi Jiacheng(Jiuquan Satellite Launch Centre,Jiuquan 732750,China)
出处
《航天控制》
CSCD
北大核心
2023年第6期24-29,共6页
Aerospace Control
基金
装备预先研究项目(JH20182A030125)。
关键词
空间快速响应
快访回归轨道
火箭弹道
一体规划
Operationally responsive space
Fast access recursive orbit
Launch vehicle trajectory
Inte⁃grated design
作者简介
贺绍飞(1989-),男,硕士,主要研究方向为火箭测试发射技术,E⁃mail:shaofei_he@163.com;谷振丰(1984-),男,博士,主要研究方向为火箭测试发射技术;徐慧娟(1979-),女,硕士,主要研究方向为火箭测控技术;许晓(1993-),男,硕士,主要研究方向为卫星轨道仿真;池嘉诚(1998-),男,硕士,主要研究方向为火箭弹道设计。
