Calculation method of aerodynamic impulse of shock wave swept aircraft wing based on Monte-Carlo simulation
Through the Monte-Carlo simulation method, the complexity and accuracy of the calculation of aerodynamic impulse of the aircraft wing under shock wave sweep is solved, and the effective calculation of aerodynamic impulse and flight safety verification of the wing is achieved.
Patent Information
- Application Number
- CN202411612232.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-13
- Publication Date
- 2025-03-25
- Estimated Expiration
- 2044-11-13
AI Technical Summary
In the shock wave sweep flight state, the aircraft wings are affected by transient high-intensity aerodynamic impulse, resulting in interference from flight performance, structural dynamic stability, flight action mechanical response and flight control system, increasing the difficulty of flight safety verification and verification.
The aerodynamic impulse of the shock wave sweeping aircraft wing was calculated by using the Monte-Carlo simulation method. The steps of Monte-Carlo two-dimensional random sampling and graphing, discrete data relative position interval determination, landing point interval determination and counting statistics are used, and the computer wing resistance, side force and lift impulse.
This method can effectively calculate the aerodynamic impulse of the wing under shock wave sweep, improve the accuracy and efficiency of the calculation, and is versatile, and does not need to be processed separately for different aerodynamics. It is suitable for flight conditions for complex aerodynamic changes under shock wave sweep.