A Variable Thrust Micro Solid Rocket Motor Flexible Nozzle System

Abstract

The invention discloses a variable-thrust miniature solid rocket motor flexible nozzle system, which belongs to the technical field of aerospace power propulsion devices. It includes a displacement acquisition module, a control module, a flexible nozzle and several servo mechanisms arranged in the circumferential direction of the flexible nozzle; the two ends of the flexible nozzle are respectively fixedly connected with the nozzle contraction section and the nozzle expansion section, and the servo mechanism includes a servo motor, The transmission rod and the transmission sheet, the servo motor is connected with the transmission rod, the transmission rod is connected with the transmission sheet, and the transmission sheet is attached to the outer wall of the flexible nozzle; the displacement acquisition module is used to collect the displacement data of the diameter change of the flexible nozzle. The displacement acquisition module and The servo motors are respectively connected to the control module, and the control module is connected to the upper computer. The invention has a simple and reliable structure, is suitable for a miniature solid rocket motor, and greatly improves the response speed of the thrust change. At the same time, the input and output signals are fed back in real time through the displacement acquisition module and the control module, which improves the control accuracy of the thrust.

Description

technical field [0001] The invention belongs to the technical field of aerospace power propulsion devices, in particular to a flexible nozzle system of a variable-thrust miniature solid rocket motor. Background technique [0002] Miniaturization and miniaturization are an important direction for the development of modern spacecraft and weaponry. Whether it is in the field of aerospace or equipped with weapons, the system is required to have the characteristics of fast response, high precision and high reliability, and the above characteristics are directly related to the micro solid rocket motor system, which puts forward higher requirements for the solid rocket motor system. [0003] Micro solid rocket motors are often used in weapon equipment propulsion systems, spacecraft attitude adjustment systems, etc. due to their high reliability, long storage time, and short preparation time. However, its combustion controllability is poor, and the thrust of conventional solid rock...

AI Technical Summary

Problems solved by technology

However, its combustion controllability is poor. The thrust of conventional solid rocket motors is closely related to its grain, and the thrust cannot be adjusted and changed in real time during the combustion propulsion process.

Weapons and equipment often require thrust changes such as low-speed cruise and accelerated defense penetration during flight. The spacecraft needs to precisely control the thrust of the engine to achieve precise attitude adjustment. Conventional miniature solid rocket motors cannot meet this demand.

[0004] At present, the thrust control of solid rocket motors is mainly divided into engine grain design and throat plug type variable thrust design; engine grain design mainly achieves thrust changes in different combustion stages by pouring different combustion sections or propellants at different stages, but it cannot be realized. More real-time flight conditions for thrust changes; the throat plug variable thrust design has a long response time, severe ablation and complex devices, which are not suitable for miniature solid rocket motors

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