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本文从现有的外弹道学基本运动方程出发,采用WKB法求解了包含马格努斯力矩系数在内的攻角方程,并积分偏角方程,得到了涡轮式火箭增程弹在起始段、主动段和被动段中诸扰动因素(起始扰动、推力偏心、动不平衡和风)引起的攻角及偏角特征函数。文中分两种情况((?)为常数及不为常数)讨论了主动段的角运动规律,得出对于单一直喷管情况为保证点火时的稳定性,推力加速度存在一个上限,该上限随点火时速度的减小而迅速减小,在选择点火时间时必须考虑这个上限的影响。
In this paper, starting from the existing basic ballistic equations, the WKB method is used to solve the angle of attack equation including the Magnus moment coefficient and to integrate the declination equation, and the turbulence rocket extension projectile is obtained at the initial stage , Active and passive segments of the disturbance factors (initial disturbance, thrust eccentric, dynamic unbalance and wind) caused by the angle of attack and declination features. In this paper, the angular movement law of the active section is discussed in two cases ((?) Is constant and not constant), and the conclusion is drawn that there is an upper limit for the thrust acceleration for a single straight nozzle in order to ensure the stability at ignition Ignition speed decreases rapidly reduced, the choice of ignition time must take into account the impact of this limit.