Solid rocket engine thrust regulation and control system and method based on microwave field
By using microwave energy to enhance combustion in solid rocket engines, and by real-time monitoring and regulating microwave output, the problem of thrust in traditional solid rocket engines cannot be adjusted is solved, achieving efficient and stable thrust regulation effect.
CN119825577AActive Publication Date: 2025-04-15XI AN JIAOTONG UNIV
5 Cites 0 Cited by
Patent Information
- Application Number
- CN202510115803.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-24
- Publication Date
- 2025-04-15
- Estimated Expiration
- 2045-01-24
AI Technical Summary
Technical Problem
The thrust of traditional solid rocket engines cannot be adjusted, which limits its flexibility. The existing thrust regulation measures are low in combustion efficiency and unstable thrust output.
Method used
By feeding microwave energy into the combustion chamber of a solid rocket engine, microwave energy is used to enhance the combustion of solid propellant, and engine performance parameters are collected through pressure, temperature and force sensors, the monitoring terminal adjusts the microwave output size according to working conditions to achieve thrust regulation.
Benefits of technology
It effectively avoids the problems of low combustion efficiency and unstable thrust output, and realizes flexible thrust regulation of solid rocket engines.
✦ Generated by Eureka AI based on patent content.
Abstract
The invention discloses a solid rocket engine thrust control system and method based on a microwave field. The solid rocket engine thrust control system comprises a combustion chamber shell, an annular heat insulation layer arranged around the inner wall of the combustion chamber shell and an annular grain. An empty runner is formed in the middle of the grain; the inner side of the front end of the combustion chamber shell is connected with the heat insulation layer and the igniter; the igniter is mounted on the inner wall of the grain; the gas outlet end of the combustion chamber shell is sequentially provided with a spray pipe convergent section, a spray pipe throat and a spray pipe expansion section. A pressure sensor, a temperature sensor and a force transducer are distributed on the outer side of the expansion section of the spray pipe, and the pressure sensor, the temperature sensor and the force transducer transmit acquired engine performance parameters to a monitoring terminal through electric signals; the monitoring terminal outputs electric signals to the impedance converter and the microwave power supply according to working condition requirements, the intensity of a microwave field is changed, and thrust regulation and control of the solid rocket engine are achieved. The size of microwave output is adjusted according to working conditions, and thrust regulation and control of the solid rocket engine are achieved.
Need to check novelty before this filing date? Find Prior Art