摘要
为了通过弹道修正引信控制弹丸按照特定弹道飞行以击中目标,基于空气动力学和优化控制原理建立了以弹道修正控制消耗能量最小为目标的弹道控制优化模型。应用极大值原理求解该优化模型,其中的初值问题采用牛顿迭代法求解。算例优化结果表明:在给定初始修正点和目标点情况下,由优化模型得到的法向过载优化值能够控制弹丸击中目标位置。文中优化结果为弹道修正机构的设计提供了理论依据。
An optimum model of trajectory control based on aerodynamics and the optimal control theory with the least energy cost was established to command projectile to move along a certain path up to hitting a target by the trajectory correction fuze. The optimum model was solved by maximum principle and in which the initial value problem was solved using Newton iteration procedure. A demonstration illustrates that optimal values of the normal overload obtained from the optimization model can control the projectile up to hitting the target by giving the controlled starting point and the target point. The optimal results provide a theoretical basis for the design of the trajectory correction mechanism.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2007年第3期301-304,共4页
Acta Armamentarii
关键词
飞行器控制导航技术
优化控制
极大值原理
引信
导航
control and navigation technology of aerocraft
optimized control
maximum principle
fuze
navigation
