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Output structure of unmanned helicopter engine adopting overrunning one-way clutches

A one-way clutch and unmanned helicopter technology, which is applied to unmanned aircraft, motor vehicles, rotorcraft, etc., can solve the problem of out-of-synchronization between the power output part and the power source part, and increase the payload quality and power The effect of large mass ratio and avoiding economic loss

Pending Publication Date: 2017-07-07
必扬星环(北京)航空科技有限公司
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AI Technical Summary

Problems solved by technology

What this unmanned helicopter adopts is a twin-engine power plant, has two turboshaft engines, and the output end of each turboshaft engine is equipped with an overrunning one-way clutch, and the use of an overrunning one-way clutch solves the problem of the power output part and the power source part. out of sync problem

Method used

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  • Output structure of unmanned helicopter engine adopting overrunning one-way clutches
  • Output structure of unmanned helicopter engine adopting overrunning one-way clutches
  • Output structure of unmanned helicopter engine adopting overrunning one-way clutches

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Embodiment Construction

[0037] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be described in detail below. Apparently, the described embodiments are only some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other implementations obtained by persons of ordinary skill in the art without making creative efforts fall within the protection scope of the present invention.

[0038] Such as Figure 1-Figure 5 Shown:

[0039] An output structure of an unmanned helicopter engine that adopts an overrunning one-way clutch, including a final reducer 1, the final reducer 1 has two power input ends and a power output end, and each power of the final reducer 1 The input end is respectively connected to the overrunning one-way clutch 2, the flexible coupling 3 and the turboshaft engine 4 in sequence, and the power output end of the final re...

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Abstract

The invention relates to an output structure of an unmanned helicopter engine adopting overrunning one-way clutches. The output structure comprises a main reducer which is provided with two power input ends and a power output end. Each power input end of the main reducer is sequentially connected with the corresponding overrunning one-way clutch, a flexible coupler and a turboshaft engine. The power output end of the main reducer is connected with a main rotor wing of an unmanned helicopter. According to the output structure of the unmanned helicopter engine adopting the overrunning one-way clutches, the unmanned helicopter adopts a double-power device and is provided with the two turboshaft engines, the output end of each turboshaft engine is provided with the corresponding overrunning one-way clutch, and the problem that a power output part and a power source part are asynchronous is solved by using the overrunning one-way clutches.

Description

technical field [0001] The invention relates to an unmanned helicopter, in particular to an output structure of an unmanned helicopter engine adopting an overrunning one-way clutch. Background technique [0002] Unmanned helicopter refers to an unmanned, unmanned vertical take-off and landing rotorcraft that flies by radio remote control or autonomous control. It relies on electric motors or piston engines to drive the rotor to generate lift and control force, can take off and land vertically, hover in the air, and can fly flexibly in any direction. [0003] Unmanned helicopters play a unique role in modern warfare, economic construction, and daily life. Taking civilian use as an example, unmanned helicopters have the advantages of relatively low cost, no risk of casualties, strong survivability, good maneuverability, and convenient use. They are widely used in aerial photography, aerial photography, geological and landform mapping, forest fire prevention, Earthquake inves...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/605
CPCB64C27/605B64U10/10
Inventor 田松
Owner 必扬星环(北京)航空科技有限公司
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