一种整流罩排气系数的仿真获取方法
By calibrating and correcting the CFD numerical calculation model and constructing an exhaust coefficient database based on wind tunnel test data, the problem of inaccurate exhaust coefficient in the design of the pressure difference between the inside and outside of the fairing was solved, and the fine calculation of the internal pressure of the fairing was realized, which improved the safety and economy of the rocket.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- BEIJING INST OF ASTRONAUTICAL SYST ENG
- Filing Date
- 2023-08-25
- Publication Date
- 2026-07-17
AI Technical Summary
Existing technologies do not calculate the exhaust coefficient accurately enough in the design of the pressure difference between the inside and outside of the fairing, resulting in an overly conservative structural design that affects the safety, reliability and economy of the rocket.
By calibrating and correcting the CFD numerical calculation model, and combining single-hole exhaust wind tunnel test data and rocket flight data, an exhaust coefficient database is constructed to achieve refined calculation of variable exhaust coefficient pressure relief of the fairing along the flight trajectory.
It improves the accuracy of fairing internal pressure prediction, supports the refined design of internal and external pressure differential loads, and enhances the safety and economy of rockets.
Smart Images
Figure CN117236207B_ABST