一种低声爆高升阻比超声速公务机构型
By optimizing the design of the nose, fuselage, wings, and tail of the supersonic business jet, and combining it with beneficial interference methods for sonic boom waves, the problem of suppressing sonic boom intensity in existing technologies has been solved, achieving a design effect of low sonic boom and high lift-to-drag ratio.
CN118811070BActive Publication Date: 2026-07-17TIANMUSHAN LABORATORY
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- TIANMUSHAN LABORATORY
- Filing Date
- 2024-09-18
- Publication Date
- 2026-07-17
AI Technical Summary
Technical Problem
Existing supersonic business jet designs, while maintaining excellent cruise lift-to-drag ratio performance, struggle to effectively suppress sonic boom intensity, posing challenges to aerodynamic layout solutions.
Method used
It adopts a duckbill-like flat nose, slender fuselage, two-section large swept wings, segmented tail and spindle structure, combined with beneficial interference methods of sonic boom, to adjust the aerodynamic layout parameters of the aircraft and optimize the fuselage and tail design.
Benefits of technology
It significantly reduces the size of the sonic boom, reduces the peak sound pressure by 50%, improves the cruise lift-to-drag ratio, maintains the aircraft's aerodynamic performance, and reduces the ground sound pressure level by 7.22 PLdB.
✦ Generated by Eureka AI based on patent content.
Smart Images
Figure CN118811070B_ABST
Abstract
本发明涉及一种低声爆高升阻比超声速公务机构型，包括机头，采用类鸭嘴扁平状形状，且末端底部有向下突起；机身，采用细长型设计；所述机身长细比不低于26，所述机身具有光滑等效面积分布，所述机身具有类椭圆剖面；机翼，位于机身中部承力段两侧，所述机翼展弦比为1.64；尾翼，由分为垂尾与十字水平尾翼组成，所述垂尾的前缘后掠角为67°，所述垂尾顶部添加纺锤体结构，所述十字水平尾翼为两段式小后掠机翼，且展弦比为3.43，前缘后掠角为30‑50°；本发明具有在保持飞机气动性能的同时降低声爆大小的低声爆高升阻比的优点。
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