基于飞发综合性能控制的喷管出口面积调节方法及装置
By obtaining the aircraft's cruising altitude and Mach number from the aero-engine data, discretizing the nozzle exit area, calculating the aircraft's drag and thrust, and selecting the area with the minimum low-pressure converted speed as the adjustment plan, the influence of the nozzle exit area on the aircraft's drag was resolved, achieving comprehensive optimization of the engine's performance, reducing fuel consumption and increasing range.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- AECC SHENYANG ENGINE RES INST
- Filing Date
- 2023-11-03
- Publication Date
- 2026-07-17
AI Technical Summary
The current control of the nozzle exit area of aero engines does not take into account the impact of aircraft drag, which affects the aircraft's horizontal acceleration, climb and other technical indicators and maneuverability. Furthermore, the lack of comprehensive optimization of the engine and flight performance increases fuel consumption and reduces range and flight time.
By obtaining the aircraft's cruising altitude and Mach number, the engine thrust and area before nozzle exit area optimization are determined. Multiple areas are discretized, and the aircraft drag and required thrust are calculated. The area corresponding to the minimum low-pressure converted speed is selected as the adjustment plan value to achieve comprehensive optimization of flight and engine performance.
It reduces aircraft drag, improves aircraft flight performance, reduces engine fuel consumption, and increases range and flight time.
Smart Images
Figure CN117329020B_ABST