上海航天
上海航天
상해항천
AEROSPACE SHANGHAI
2012年
3期
1-5
,共5页
肖龙旭%王继平%王安民%焦洋
肖龍旭%王繼平%王安民%焦洋
초룡욱%왕계평%왕안민%초양
需要轨道%入轨点%迭代制导%方法误差
需要軌道%入軌點%迭代製導%方法誤差
수요궤도%입궤점%질대제도%방법오차
Required trajectory%Trajectory entering point%Iterative explicit guidance%Method error
提出了一种基于需要轨道的导弹最优迭代制导方法,以标准弹道上某点建立需要轨道并确定入轨点参数,通过弹上迭代制导实现最优入轨控制,给出了计算模型。该制导方法无需修正地球扁率和再入阻力的影响,可减小方法误差。仿真计算结果证明方法正确。
提齣瞭一種基于需要軌道的導彈最優迭代製導方法,以標準彈道上某點建立需要軌道併確定入軌點參數,通過彈上迭代製導實現最優入軌控製,給齣瞭計算模型。該製導方法無需脩正地毬扁率和再入阻力的影響,可減小方法誤差。倣真計算結果證明方法正確。
제출료일충기우수요궤도적도탄최우질대제도방법,이표준탄도상모점건립수요궤도병학정입궤점삼수,통과탄상질대제도실현최우입궤공제,급출료계산모형。해제도방법무수수정지구편솔화재입조력적영향,가감소방법오차。방진계산결과증명방법정학。
One kind of optimal iterative guidance method based on required trajectory for missile was put forward in this paper. Some point in standard trajectory was adopted to establish the required trajectory and determine the parameters of the trajectory entering point. The optimal injection control was realized by the iterative explicit guidance when the missile was flying. The modelwas given out. The earth earth oblateness and reentry aerodynamic resistance influence were not be modified by using this method, which colud reduce the error. The method was proved by the simulation result.
