Impulse type secondary jet flow thrust vector control system

Abstract

The invention relates to an impulse type secondary jet flow thrust vector control system which comprises a rocket engine (1), an annular high pressure gas storage tank (2), a gas transporting pipeline(3), a pressure maintaining valve (4), a gas collecting cavity (5), an impulse jet flow control valve (6), a jet flow spout (7) and an engine jet pipe (8). The system facilitates flight control of anaircraft and adopts the secondary jet flow thrust vector control to reduce energy consumption, enhance the deflection capacity of secondary flow and effectively reduce the flow rate of the secondaryflow needed to be sprayed into.

Description

technical field [0001] The invention relates to a rocket engine secondary jet thrust vector control system, which belongs to the field of rocket engine thrust vector control. Background technique [0002] As a non-traditional flight control technology, thrust vector control technology is widely used in missiles, rockets and other fields. Generally, the attitude of the missile is adjusted by the aerodynamic control force generated by the aerodynamic control surface on the missile body. However, with the improvement of combat requirements and the improvement of the mobility of the attack target, the traditional aerodynamic control method has exposed many difficult problems, such as: low speed in the initial stage of launch, insufficient aerodynamic control force; low air density at high altitudes, reducing control efficiency ; In the final stage of hitting the target, the target may be missed due to insufficient overload and so on. It can be seen that only using traditional ...

AI Technical Summary

Problems solved by technology

Although the use of proportional control valves improves the precision of thrust vector control, it increases the secondary flow channel and Coanda effect surface, which increases the complexity of the system and the quality and size of the structure

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