Aircraft power supply positioning clamp
By designing aircraft power positioning fixtures, using the combination of limit plates, limit clamps and shock absorbing pillars, the problem of unstable position of the power system during flight in the prior art is solved, and the stable output of the power system is achieved.
CN222320403UActive Publication Date: 2025-01-07HUBEI YUEXUN TECHNOLOGY CO LTD
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Patent Information
- Application Number
- CN202420887771.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-04-26
- Publication Date
- 2025-01-07
- Estimated Expiration
- 2034-04-26
AI Technical Summary
Technical Problem
The existing aircraft power positioning fixture cannot fully fix the power system, causing the power position to move during the bumpy aircraft, affecting the normal use of the power system.
Method used
A aircraft power positioning fixture is designed, including base, fixture, limit slot, limit plate, limit clamp ring, shock absorbing support and connecting plate, through the coordination between limit plate and limit slot, limit clamp ring The connection between fixing and bolts, combined with the use of shock absorbing struts, ensures stable positioning of the power supply during flight.
Benefits of technology
It effectively avoids the displacement of the aircraft power supply due to shaking and bumps, and ensures the normal operation of the aircraft's power system.
✦ Generated by Eureka AI based on patent content.
Abstract
The utility model discloses an aircraft power supply positioning clamp which comprises a base, a clamp body is arranged on the base, an aircraft power supply is arranged on the inner side of the clamp body, a limiting groove is formed in the base, the aircraft power supply and the limiting groove correspond to each other in position and are matched with each other, a power supply box covers the aircraft power supply, and the base is arranged in a power supply box body. A controller is arranged on the upper side of the power box, a damping supporting column is installed at the lower end of the base and arranged in the power box body, and a connecting plate is connected to the rear end of the power box. According to the utility model, the aircraft power supply is arranged in the limiting groove on the base through the limiting plate which is arranged on the clamp and fits the shape of the aircraft power supply, and then the positions of all devices in the aircraft power supply are fixed by utilizing the limiting snap ring, so that the effects of positioning and damping are achieved under the matching use of the damping strut below the base in the flight process of the aircraft; displacement caused by shaking and bumping of an aircraft power supply is effectively avoided, and normal use of an electric power system of an aircraft is guaranteed.
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