载机滚转条件下的导弹弹射分离横向位移研究

Lateral displacement of missile ejection separation with aircraft rolling

研究载机空中滚转条件下的空空导弹弹射分离时产生的横向位移问题。采用伪坐标形式的拉格朗日方程建立了机载弹射发射机构高速伸展过程的动力学模型,对战机滚转条件下的导弹弹射分离动力学特性进行数值仿真。仿真结果表明:弹射分离速度正常,但是由于受科氏力作用导致弹射机构横向变形显著,致使导弹尾部横向位移大,威胁载机与导弹的发射分离安全性;由于重量和空间限制以及弹射作动时间很短,传统的提高机构刚度法和主动控制法在工程上难以实施,针对横向位移难题,提出对弹射机构前后链路进行刚度匹配设计的新思路。仿真和试验表明该方法有效且易于工程实现,为战机滚转条件下的导弹发射提供理论指导。

Here, lateral displacement of an air-to-air missile ejection separation with aircraft rolling was studied. Using Lagrange’s equations in form of quasi-coordinates, a dynamic model for high-speed stretching process of an airborne ejection launcher was established. Dynamic characteristics of missile ejection separation with aircraft rolling were numerically simulated. The results showed that the missile ejection separation speed is normal, but the lateral deformation of the airborne ejection launcher is significant due to the action of Coriolis force to cause large later displacement of the missile tail, and threat the separation safety between aircraft and ejected missile. Due to constraints of weight and space as well as very short ejection actuation time, the traditional mechanism stiffness-enhancing method and the active control method were difficult to implement in engineering. For this difficult problem, a new idea to do a stiffness matching design for front and rear links of the ejection launcher was proposed. Simulations and tests showed that this method is effective and easy to realize in engineering;it provides a theoretical guidance for missile ejection under the condition of aircraft rolling.