The invention discloses a control method of a manned aircraft, and relates to the technical field of aircraft equipment. Thrust is generated through seven micro turbojet engines on the aircraft to keep the aircraft flying; the thrust generated by the seven micro turbojet engines is controlled by adjusting the accelerator; a thrust vectoring nozzle at an output port of the micro turbojet engine E5 is adjusted to assist front and back control of the aircraft; the thrust vectoring nozzles at the output ports of the four micro turbojet engines E1, E2, E3 and E4 are adjusted to control the front-back and left-right hybrid control of the aircraft; the course adjustment of the aircraft is controlled by adjusting thrust vectoring nozzles at output ports of the micro turbojet engines E6 and E7 on the two sides of the aircraft; and the flight attitude of the aircraft is obtained through the gyroscope, so that stable control on the manned aircraft can be realized.
本发明公开了一种载人飞行器的控制方法,涉及飞行器设备技术领域,所述载人飞行器的控制方法包括;通过飞行器上的七个微型涡喷发动机产生推力保持飞行器飞行;通过调节油门大小来控制七个微型涡喷发动机产生的推力大小;通过对微型涡喷发动机E5输出口处的矢量喷管进行调整来辅助飞行器的前后控制;通过对四个微型涡喷发动机E1、E2、E3和E4输出口处的矢量喷管进行调整来控制飞行器的前后左右混合控制;通过飞行器两侧的微型涡喷发动机E6和E7输出口处的矢量喷管进行调整来控制飞行器的航向调整;通过陀螺仪获取飞行器的飞行姿态,以此能够实现对载人飞行器的稳定控制。
Manned aircraft control method
一种载人飞行器的控制方法
2024-03-29
Patent
Electronic Resource
Chinese
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