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在寻的制导中,气动控制的导弹的传递函数是整个寻的制导和姿态控制反馈回路的一部分。因此,为完成寻的制导,导弹的空气动力特性必须满足一定的约束。对于雷达寻的制导系统,这些约束必须非常严格,这样,自动驾驶仪才能利用弹上设备和内反馈回路来控制气动传递函数。无论哪种驾驶仪,气动力矩参数 (如M_α和M_δ)的选取范国必须在导弹系统的初步设计时给予考虑。本文讨论了这些约束的物理性质和来源,通过数值计算的例子说明所要求的参数范围。
In seeking guidance, the transfer function of a pneumatically-controlled missile is part of the entire feedback and attitude control feedback loop. Therefore, in order to complete guidance, the aerodynamic characteristics of missiles must meet certain constraints. For radar-oriented guidance systems, these constraints must be very strict so that the autopilot can use the onboard equipment and the internal feedback loop to control the aerodynamic transfer function. No matter what kind of pilot, the choice of the aerodynamic torque parameters (such as M_α and M_δ) must be considered in the initial design of the missile system. This article discusses the physical properties and sources of these constraints. The examples of numerical calculations illustrate the required range of parameters.