A Thrust Controllable Secondary Flow Throat Bolt Rocket Engine

Abstract

The invention discloses a secondary-flow pintle rocket engine with a pushing force controllable function, relates to a pintle rocket engine, and belongs to the field of variable-pushing-force rocket engines in pneumatic and mechanical hybrid control. The secondary-flow pintle rocket engine mainly consists of pintle rocket engine basic devices such as a housing, a motor, a guide wheel, a combustion chamber, a pintle and a spray tube. The inner part of the pintle is hollowed out, a secondary-flow gas source is arranged in the hollowed-out part, and a secondary-flow jet hole is formed in the top of the pintle. During working, high-pressure secondary flow generated by the secondary-flow gas source is sprayed at the secondary-flow jet hole, and the jetted high-pressure secondary flow mainly has pushing force control effects as follows: firstly, the formed secondary-flow shearing layer is regulated to regulate the effective area of a throat part by regulating the pressure intensity and the flow rate of secondary flow, so that the pressure intensity of a combustion chamber is regulated, and the pushing force controllable function of the engine is realized; and secondly, total flow of the pintle rocket engine is realized by converging jetted secondary flow and main-flow fuel gas, so that pushing force of the pintle rocket engine is increased.

Description

technical field [0001] The invention relates to a throat plug rocket engine, in particular to a throat plug rocket engine with thrust control combined with secondary flow injection and throat plug mechanical control, and belongs to the field of variable thrust rocket engines controlled by aerodynamic and mechanical hybrid control. Background technique [0002] Secondary fluid injection refers to the injection of secondary jets into the main flow of the engine nozzle throat or the expansion section of the nozzle. The secondary jets interact with the main flow to change the flow conditions of the main flow, thereby changing the magnitude and direction of the engine thrust. Throat bolt control solid rocket motor can achieve the ideal result of stepless adjustment of thrust, and the thrust adjustment range is large, the adjustment ratio is roughly 10-100, and random adjustment can be realized, and the response speed is fast. [0003] Adjusting the thrust by changing the throat a...

AI Technical Summary

Problems solved by technology

This solution needs to place a central split fluid in the combustion chamber, which will increase the structural quality, and the swirling will easily increase the deposition of particles in the combustion chamber

In addition, the gyration will also increase the radial momentum of the jet flow at the outlet of the nozzle, resulting in a decrease in the thrust coefficient. At the same time, the vortex valve scheme can only adjust the thrust, not the thrust direction.

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