一种X形加载杠杆
By designing an X-shaped loading lever, the limitations of existing secondary loading levers at installation angles of around 0° are solved, achieving stable connection and high-precision loading, which is suitable for ground verification tests of aircraft structural strength.
CN115946871BActive Publication Date: 2026-07-17CHINA AIRPLANT STRENGTH RES INST
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- CHINA AIRPLANT STRENGTH RES INST
- Filing Date
- 2023-01-20
- Publication Date
- 2026-07-17
AI Technical Summary
Technical Problem
Existing secondary loading lever structures have limitations in scenarios with an installation angle of around 0°, and existing solutions increase the height of the lever system, reducing stability and loading accuracy.
Method used
The system adopts an X-shaped loading lever design, which achieves a primary-secondary lever connection of 0° to 5° through a resultant bearing and bushing structure. The lever body is designed with elongated holes and round holes at both ends to ensure loading accuracy and system stability.
Benefits of technology
Stable connection was achieved at installation angles of 0° to 5°, improving the overall stability and loading accuracy of the lever system and avoiding the limitation of loading caused by deformation of the test piece.
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Figure CN115946871B_ABST
Abstract
本申请属于飞机结构强度地面验证试验领域，特别涉及一种X形加载杠杆。包括：杠杆主体，呈X形，包括主体部以及与主体部连接的第一力臂、第二力臂、第三力臂、第四力臂，第一力臂与第三力臂平行设置，第二力臂与第四力臂平行设置，其中，主体部上开设有轴承安装孔，轴承安装孔中安装有合力点轴承；第一力臂的外端开设有第一长条孔，内端开设有第一拉压垫螺栓安装孔；第二力臂的外端开设有第一圆孔，内端开设有第二拉压垫螺栓安装孔；第三力臂的外端开设有第二长条孔，内端开设有第三拉压垫螺栓安装孔；第四力臂的外端开设有第二圆孔，内端开设有第四拉压垫螺栓安装孔。本申请能够增加整个杠杆系统的结构的稳定性与加载精度。
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