Low-altitude aircraft

By designing an adjustable arm structure and detachable rotor on a low-altitude aircraft, the performance limitation caused by the fixed arm length is solved, enabling dynamic adjustment of the arm length and flexible replacement of the rotor, adapting to various mission requirements and reducing maintenance costs.

CN224061202UActive Publication Date: 2026-03-31QIHANG AEROSPACE TECHNOLOGY (NINGBO) CO LTD
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Patent Information

Application Number
CN202520851542.3
Authority / Receiving Office
CN · China
Patent Type
Utility models(China)
Current Assignee / Owner
Filing Date
2025-04-30
Publication Date
2026-03-31
Estimated Expiration
2035-04-30

AI Technical Summary

Technical Problem

The fixed arm length of existing low-altitude aircraft limits their performance and makes it difficult to meet the needs of different missions. Users need to purchase multiple models to adapt to different terrains and weather conditions.

Method used

Design a low-altitude aircraft that uses a movable boom connected to a fixed boom, and adjusts the boom length using locking and pressure components. Locking is achieved using a combination of a locking pin and a wedge block, and quick unlocking or locking is achieved using a combination of a rotating sleeve and a connecting ring. The rotor components can be independently disassembled and replaced.

Benefits of technology

It enables dynamic adjustment of boom length, adapts to different terrains and weather conditions, optimizes lift and thrust efficiency, reduces maintenance and replacement costs, and facilitates transportation and storage.

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Abstract

The utility model discloses a low-altitude aircraft which comprises an aircraft body, four fixed machine arm rods are arranged in the cross direction of the aircraft body, the surfaces of the fixed machine arm rods are movably connected with movable machine arm rods, one sides of the movable machine arm rods are provided with locking pieces, and the other sides of the movable machine arm rods are connected with the locking pieces. The locking piece comprises fixing frames fixed to the top and the bottom of one end of the movable machine arm rod, a connecting plate is arranged on one side of each fixing frame, and a clamping column is fixedly connected to the inner side of each connecting plate. The fixed machine arm rod can move in the inner cavity of the movable machine arm rod, so that the total length of the fixed machine arm rod and the movable machine arm rod can be changed, the length of the machine arm can be adjusted, the two clamping columns enter the through holes, the adjusted length can be locked, the length of the machine arm can be adjusted according to task requirements, and the machine arm is convenient to use. The aircraft arm is suitable for different terrains and weather conditions, dynamic adjustment of the arm of force of the propeller is achieved, lift and thrust efficiency is optimized, and the fixed aircraft arm rod and the movable aircraft arm rod can be rapidly detached and replaced.
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