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本文对射程为120km的地地火箭进行了广泛的空气动力计算。第一个目的是研究控制系统对于圆概率误差CEP(相对于理论的误差预算)的影响。介绍了无控制、有姿态控制和有捷联惯性制导控制三种不同情况的结果。证明只有应用捷联惯性制导才能补偿大的总冲偏差的影响。用尾舵可实现火箭的控制。给出的实例也表明静态裕度和轴向力系数对CEP是有影响的。第二个目的是求出能够用气动控制实现完全平衡的最大总冲偏差。
In this paper, a wide range of aerodynamic calculations are performed on ground rockets with a range of 120 km. The first purpose is to study the effect of the control system on the circular probability error CEP (relative to the theoretical error budget). The results of three different cases of no control, attitude control and strapdown inertial guidance control are introduced. Prove that only strapdown inertial guidance can compensate for the impact of large total offset error. Rocket rudder can be used to achieve the control. The examples given also show that static margins and axial force coefficients have an influence on CEP. The second objective is to find the maximum total offset error that can be fully balanced with pneumatic control.