缩比验证机轴对称矢量喷管设计与验证  

Design and Validation of Axisymmetric Thrust Vectoring Nozzle for Scaled Jet UAVs

作　　者：孟祥喆 赵志俊 郑浩[1] MENG Xiangzhe;ZHAO Zhijun;ZHENG Hao(Chinese Flight Test Establishment,Xi'an 710089,China)

机构地区：[1]中国飞行试验研究院,西安710089

出　　处：《机械科学与技术》2021年第11期1793-1797,共5页Mechanical Science and Technology for Aerospace Engineering

摘　　要：在某缩比验证机推力矢量系统研制中,首先采用两套电动舵机驱动的连杆机构的设计方案,实现了矢量喷管的轴对称偏转。通过分析矢量喷管偏转过程中作动机构受力关系和运动关系,得到舵机需提供的最大扭矩与最大铰链力矩的关系。分别采用工程估算和CFD数值模拟两种方法对矢量喷管偏转产生的铰链力矩进行了计算。通过地面试验和飞行试验验证了所研制的轴对称推力矢量系统满足工程应用要求。In the development of thrust vectoring system of a scaled jet UAV,the axisymmetric rotating function has been achieved by designing a kind link mechanism,which is driven by two electric steering servos.By analyzing the force and motion states in the process of thrust vectoring nozzle rotating,the relationship between the maximum servo torque needed and the maximum hinge torque is obtained.Then,methods of engineering estimation and CFD numerical simulation have been implemented on calculating the hinge moment generated by the thrust vectoring nozzle when rotating.The calculation results of hinge moment were used to select suitable electric steering servo,which has enough torque to against the hinge moment.Finally,the results of ground test and flight test demonstrated good performance of the axisymmetric thrust vectoring system,which meeting requirements of engineering application.

关 键 词：轴对称矢量喷管 铰链力矩 动量定理 数值模拟 飞行试验 

分 类 号：V228.7[航空宇航科学与技术—飞行器设计]