对于寻的制导导弹来说,弹体气动力特性是整个闭环控制系统的一部分。而为了使所设计的自动驾驶仪性能满足要求,必须对弹体气动力特性进行约束。文中首先分析了在无捷联惯导的情况下,导弹自动驾驶仪设计对弹体气动力特性的约束条件;进而讨论了在带有捷联惯导的情况下,导弹自动驾驶仪设计对弹体气动力特性约束情况,并通过仿真验证了这种约束的合理性。

For homing guided missile, the airframe aerodynamic characteristics become a part of an overall close loop control system. In order to satisfy the need of performance in designing autopilot, the airframe aerodynamic characteristics must be constrained. In this paper, the airframe aerodynamic characteristic constraint was analyzed for missile autopilot design without strap-down inertial navigation. According to this, how the airframe aerodynamic characteristics were constrained with strap-down inertial navigation was discussed. At last, the rationality of the constraint was verified by simulation.