论文部分内容阅读
采用燃气/空气双组元冻结流模型,基于任意多块对接结构网格求解三维N-S方程,数值分析了导弹助推器分离前侧向卸压喷流对尾舵气动力的干扰特性。得到了助推器推力终止侧向卸压过程中,喷流与外流干扰的非定常流场结构以及尾舵气动力的变化历程。分析结果表明,卸压开始后的一段时间内尾舵受到卸压喷流的屏蔽作用,尾舵气动力不能提供足够的分离冲量,此时对其进行舵偏控制将是无效的,尾舵控制时序应该自卸压开始延迟180 ms。
The gas-air two-component freezing model was used to solve the three-dimensional N-S equation based on the grids of any number of docking structures. The disturbance characteristic of the tail-rudder aerodynamic force was analyzed numerically before the separation of the missile booster. The unsteady flow field structure and the aerodynamic evolution of tail rudder were obtained during the lateral pressure relief by the thrust of booster. The results show that the tail rudder is shielded by the pressure relief jet for some time after the start of pressure relief, and the aerodynamic force of the tail rudder can not provide sufficient separation impulse. At this time, the control of the rudder will be invalid, and the rudder control timing The self-depressurization should be delayed 180 ms.