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Gearbox integrated on small single-rotor-wing unmanned helicopter rack

An unmanned helicopter and gearbox technology, applied in the field of gearboxes, can solve the problems of increasing the flight load of the unmanned helicopter, the weight of the unmanned helicopter, and the existence of potential safety hazards, so as to improve the working stability and reliability, the structure is simple, the Overall weight reduction effect

Inactive Publication Date: 2017-06-13
衡阳云雁航空科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, the frame of small single-rotor unmanned helicopter mostly adopts the plate box structure, which has the following disadvantages: 1. The gearbox and the frame are independent of each other, and the gearbox is connected to the frame through connecting parts, resulting in overweight of the unmanned helicopter , increasing the flight load of the unmanned helicopter
2. The overall rigidity of the plate-type frame is poor, and the overall low-frequency vibration is relatively large during flight, which poses safety hazards and interferes with electronic equipment (gyroscope or flight control equipment)

Method used

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  • Gearbox integrated on small single-rotor-wing unmanned helicopter rack
  • Gearbox integrated on small single-rotor-wing unmanned helicopter rack
  • Gearbox integrated on small single-rotor-wing unmanned helicopter rack

Examples

Experimental program
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Embodiment 1

[0024] Such as Figure 1-7 Shown: the gearbox integrated on the frame of the small single-rotor unmanned helicopter, including the gearbox lower plate 3 and the gearbox upper cover 4. The gearbox upper cover 4 is installed on the upper end of the gearbox lower plate 3, and is combined with the gearbox lower plate 3 to form a gearbox case.

[0025] The gearbox lower plate 3 is provided with an electric starter motor installation hole 31, an engine positioning hole 32, a primary shaft bearing hole A33, a propeller shaft bearing hole A34, a tension wheel shaft hole 35 and a tail pipe seat fixing screw hole 36. A plurality of positioning slots 39 are provided on the side of the gearbox lower plate 3 . The gearbox upper cover 4 is provided with a propeller shaft bearing hole B41 and a primary shaft bearing hole B42.

[0026] The primary shaft bearing hole A33, the propeller shaft bearing hole A34, the propeller shaft bearing hole B41 and the primary shaft bearing hole B42 are all...

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Abstract

A gearbox integrated on a small single-rotor-wing unmanned helicopter rack comprises a gearbox lower plate and a gearbox upper cover. The gearbox upper cover is mounted at the upper end of the gearbox lower plate, and the gearbox upper cover and the gearbox lower plate are combined to form a gearbox body. The assembled unmanned helicopter rack has the following beneficial effects that the rack is provided with a cavity, namely, an inner cavity between the gearbox upper cover and the gearbox lower plate, and a transmission component can be mounted in the cavity. No gearbox needs to be additionally mounted, and the overall weight of an unmanned helicopter is reduced.

Description

technical field [0001] The invention relates to a frame structure, in particular to a gearbox integrated on the frame of a small single-rotor unmanned helicopter. Background technique [0002] Unmanned helicopters have the advantages of flexible maneuverability, convenient take-off and landing, hovering in the air, and controllable flight speed. They are widely used in military, agricultural, and civilian fields. [0003] At present, the frame of small single-rotor unmanned helicopter mostly adopts the plate box structure, which has the following disadvantages: 1. The gearbox and the frame are independent of each other, and the gearbox is connected to the frame through connecting parts, resulting in overweight of the unmanned helicopter , increasing the flight load of the unmanned helicopter. 2. The overall rigidity of the plate-type frame is poor, and the overall low-frequency vibration is relatively large during flight, which poses safety hazards and interferes with elect...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16H57/02
CPCF16H57/02F16H2057/02039
Inventor 王国初李宝进李兆志
Owner 衡阳云雁航空科技有限公司
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