A high-stability aircraft navigation device

By adopting a combined structure of the installation shell and the inner shell in the aircraft navigation equipment, combined with the design of buffer parts and support devices, the problem of easy damage to the navigation equipment under high vibration force is solved, and higher stability and reliability are achieved.

CN119737940AInactive Publication Date: 2025-04-01BEIJING ALL FORTUNE TECH CO LTD
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Patent Information

Application Number
CN202510246372.0
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2025-03-04
Publication Date
2025-04-01
Estimated Expiration
Not applicable · inactive patent

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Abstract

The present application discloses a high-stability aircraft navigation device, which belongs to the technical field of aircraft navigation devices. The key points of its technical solution are that it includes a mounting shell and an inner shell, the mounting shell is used to be connected to the aircraft, the inner shell is arranged in the mounting shell with a distance between the two, the navigation device body is connected to the inner shell, and the inner shell is connected to a fixing device for fixing the navigation device body; a plurality of buffers are arranged between the inner shell and the mounting shell, the plurality of buffers are evenly distributed around the inner shell, one end of the buffer is connected to the inner shell, and the other end is connected to the mounting shell, so as to achieve the vibration reduction effect of the inner shell; and at least one group of supporting devices, which are arranged between the bottom of the inner shell and the mounting shell, the supporting device includes a supporting rod and a vibration reduction assembly, the supporting rod is vertically arranged, one end of the supporting rod is fixedly connected to the inner shell, and the other end is connected to the vibration reduction assembly, the vibration reduction assembly is movably connected to the mounting shell, and the vibration reduction assembly is used to achieve the vibration reduction effect of the inner shell, so as to achieve the effect of improving the stability of the aircraft navigation device.
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Citation Information

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