大增面比固体推进剂燃速测试发动机及其燃速计算方法
By designing a solid propellant burning rate test engine with a high surface area ratio and its burning rate calculation method, and by adopting a spherical structure and a spherical perforated propellant charge, burning rate testing was achieved in the pressure range of 2MPa to 30MPa. This solved the problems of high test cost and low accuracy in the existing technology and is applicable to solid attitude and orbit control engines.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SHANGHAI XINLI POWER EQUIP RES INST
- Filing Date
- 2025-09-25
- Publication Date
- 2026-07-17
AI Technical Summary
Existing combustion rate testing engines can only be tested under a single pressure, and cannot complete dynamic combustion rate testing within a certain pressure range through a single test, resulting in high testing costs and low accuracy.
A high surface area ratio solid propellant burning rate test engine was designed. It adopts a spherical structure and a spherical perforated propellant charge, combined with components such as a combustion chamber, nozzle, and ignition charge. The burning rate test can be carried out in a single test within the pressure range of 2MPa to 30MPa. A burning rate calculation model is constructed to improve the test accuracy.
It enables dynamic burning rate testing within a certain pressure range, reduces testing costs, improves testing accuracy, and is suitable for high-pressure high-index propellant burning rate testing required for solid rocket motors and other similar applications.
Smart Images
Figure CN121273498B_ABST