垂直发射巡弋飞行器总体设计方法研究

Design Method of Vertical-Launch Loitering UAV

关键词:  固体火箭发动机  涡喷发动机  垂直发射  飞行器总体设计  推力损失系数

Key words:  Solid rocket motor  Turbojet engine  Vertical launch  UAV overall design  Thrust loss coefficient

摘要:

垂直发射巡弋飞行器采用由固体火箭发动机与涡喷发动机组合而成的动力系统，飞行器与动力系统一体化设计更为复杂。本文提出双质量迭代算法，通过装药质量与燃油质量的迭代计算实现垂直发射巡弋飞行器总体参数初步设计，对飞行器与动力系统的一体化设计问题进行研究，基于典型任务剖面分析了关键设计参数对于飞行器总体性能的影响规律。结果表明，飞发集成引起的涡喷发动机推力损失系数和固体火箭发动机推重比均会对飞行器总体性能产生重要影响，当推力损失系数在0.2以下时，该系数每提高0.05，起飞质量增大约3%，涡喷发动机的最大推力指标提高约5%。在总体方案设计时应尽可能降低涡喷发动机推力损失系数，并将固体火箭发动机推重比控制在4～8的范围内。

Abstract:

The propulsion system of the vertical-launch loitering UAV is composed of a rocket and a turbojet. Therefore， the parameter integrated design is more complicated compared with conventional UAV. In order to solve the integrated design problem of propulsion system parameters， a method of iterating over two different variables has been proposed to design the parameters of the vertical-launch loitering UAV and the two variables are charge mass and fuel mass. This method realized the integrated design of the two engines mass and the design of vertical-launch loitering UAV. Then， the parameter design of the UAV was carried out and the effects of parameter on the UAV performance were analyzed. The results show that the turbojet thrust loss coefficient and rocket thrust weight ratio were the key parameters in the vertical-launch loitering UAV design. When the thrust loss coefficient is below 0.2， if it increases by 0.05， the takeoff mass increases by about 3%， and the maximum thrust demand of turbojet engine increases by about 5%. Hence， turbojet thrust loss coefficient should be designed as small as possible. And rocket thrust weight ratio should be controlled in the range of 4 to 8.