一种火箭整流罩减速伞开伞过程有限元分析方法
By using finite element analysis and penalty function methods, the problem of accurately predicting the dynamic characteristics and structural stress and strain during the deployment of the rocket fairing deceleration parachute was solved, improving modeling efficiency and safety design.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH
- Filing Date
- 2022-09-28
- Publication Date
- 2026-07-17
AI Technical Summary
Existing technologies cannot accurately predict the dynamic characteristics and structural stress and strain during the deployment of rocket fairing deceleration parachutes, mainly because they do not consider the effects of actual flight trajectories, unsteady wake fields, and parachute permeability.
A geometric model of the rocket fairing deceleration parachute deployment process was established using the finite element method. The fluid-structure interaction was handled by the penalty function method, and the unsteady wake field and parachute permeability were considered. Finite element calculations were performed to predict the dynamic aerodynamic drag and structural stress and strain during the deceleration parachute deployment process.
It enables accurate prediction of the deceleration parachute deployment process, improves the modeling efficiency and mesh quality of the finite element model, and provides a reference for the safety design of the rocket fairing deceleration parachute deployment process.
Smart Images
Figure CN116029170B_ABST