带末端攻击角度约束的三维一体化制导控制律

针对某些导弹要求限制末端攻击角度的作战要求,基于滑模控制控制方法,提出一种带末端攻击角度约束的三维一体化制导控制律.建立导弹在俯仰平面和偏航平面内控制一体化模型,然后对所建立的数学模型进行非线性坐标变换,变换成适于应用非线性控制方法设计的标准型.通过滑模控制方法,设计了能使导弹能以期望攻击角度命中目标的三维一体化制导控制律.为验证所提出一体化设计方案的有效性,进行仿真实验.仿真结果证明所提出的一体化制导控制律能导引导弹以期望攻击角度命中目标的同时,使得导弹自身的状态保持稳定.

Three-dimensional integrated guidance-control law for missile with terminal impact angle constraint

According to the requirements of some types of missile which attack targets with special terminal impact angle constraint at the terminal point,a new three-dimensional integrated guidance-control law based on sliding mode control approach for missile with terminal impact angle constraint was presented.First,mathematical models of an integrated guidance-control model in pitch plane and yaw plane were established,and then nonlinear coordinate transformation was employed to transform the mathematical model into a standard form suittable for nonlinear control theory method design.To verify the effectiveness of the proposed integrated design scheme,the numerical simulation of missile has been made,the simulation results demonstrate that the proposed guidance-control law can guide the missile to hit the target accurately with desired impact angle and desired flight attitude angle simultaneously in three-dimensional space.