为了改善某小型无人涡喷飞机的性能，设计一种矢量喷口回路。在满足轴对称矢量喷管控制系统控制要求的条件下，在涡喷发动机尾部设计了一种轴对称矢量喷口，基于 TMS28335控制器研究并实现了喷口横纵向的控制，以部分替代常规气动舵面进行飞行控制，并进行了喷口的半实物仿真。仿真结果表明，喷管的响应速度随偏转角的增大而降低。该研究为解决推力矢量的应用实现问题提供了一种有效的方法。%For improving performance of certain type small size unmanned turbojet aircraft, design a vector nozzle loop. Based on satisfying control requirements of axis symmetry vector pipe control system, design axial symmetry vector jet in the end of turbojet engine, based on TMS28335 controller, study and realize lateral and longitudinal control of the jet that controlling the flight by partially replacing conventional starting control surface. Carry out the jet semi-object simulation. The simulation results show that the pipe response velocity is decreased when deflexion angle is increased. The research provides a useful method for solving thrust vector application realization method.
展开▼
