摘要
为克服现有运载火箭在空间飞行器直接定点入轨控制方法上的缺陷,在继承美国土星-5火箭IMG和航天飞机LTG方法各自优点的基础上,提出了一种有效抑制初始偏差干扰和具有大偏航自适应控制能力的直接定点入轨控制方法,六自由度数值仿真算例验证表明:该方法和算法简单可靠,非线性迭代稳定性好,直接定点入轨精度可小于5km,利用该方法可控制空间飞行器直接定点入轨。
To eliminate the defects of traditional control method for spacecraft entering orbit with direct pin-point,on the basis of succeeding to the respective advantages of Saturn-5 IMG method and Space Shuttle LTG method, a direct pin-point orbital entry control method with large yaw self-adaptive capability was presented to suppress initial disturbance efficiently. Six degree of freedom numerical simulation shows that the method and its algorithm are simple and reliable, and non-linear iterative stability is good , the error of direct pin-point orbital entry is smaller than 5 km. By the proposed method,the spacecraft can be controlled to enter orbit with direct pin-point.
出处
《弹道学报》
CSCD
北大核心
2013年第1期1-4,共4页
Journal of Ballistics
基金
航天基金项目(UCS20110518)
关键词
空间飞行器
制导
控制
定点入轨
实时弹道规划
spacecraft
guidance
control
pin-point orbital entry
trajectory planning in-line
