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本文提出了一种导弹在定常和非定常机动条件下,非线性气动力和力矩的分析方法。模拟了导弹上的主要物理流动现象,包括背风面分离涡。对任意时刻非定常气动特性的估算,考虑了导弹与随时间变化的流场间的相互干扰。气动估算方法与六自由度运动方程的解相配合,可以求解导弹的弹道、受迫弹道、或振动运动模型。本文还用测压的试验数据与估算方法进行了比较,并得到了验证。导弹振动运动时周围的流场还同流场照片进行了比较。
This paper presents a method for the analysis of nonlinear aerodynamic forces and moments of missiles under both steady and unsteady maneuver conditions. The simulation of the main physical flow on the missile phenomenon, including the leeward vortex separation. The estimation of unsteady aerodynamic characteristics at any time takes into account the mutual interference between the missile and the flow field over time. The aerodynamic estimation method, in conjunction with the solution of the six-degree-of-freedom equations of motion, solves the trajectory, forced trajectory, or vibrational model of a missile. In this paper, we also use the test data of pressure measurement and the estimation method to compare and verify. The flow field surrounding the missile during vibrational motion is also compared with the flow field photo.