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Multi-input multi-output power system for rotary wing aircraft and control method of multi-input multi-output power system

A technology of rotating wings and power systems, applied to the transmission device driving multiple propellers, the type of power device, the type of power plant, etc., can solve the problems of heavy structural mass, single design state, complex design state, etc., to achieve The effects of improving flight efficiency, improving working conditions, and increasing working life

Active Publication Date: 2019-06-21
南京灵龙旋翼无人机系统研究院有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] 1. The structural quality is very heavy. For example, the existing friction clutch structure that realizes the connection and disconnection of different power sources is very heavy, and it is difficult to meet the take-off weight requirements of rotary wing aircraft
[0009] 2. In fact, the electric drive part of a gasoline-electric hybrid vehicle only plays an auxiliary role in saving fuel, and the design state is single; while a rotary-wing aircraft has multiple flight stages, in different flight stages, its corresponding input power The requirements are different, so it is necessary to comprehensively design multiple input sources according to the requirements of different flight stages, and the design state is complicated
[0010] 3. The output of the power system of the gasoline-electric hybrid vehicle is a single output, and the output form is simple, which is not suitable for the multi-output requirements of the rotary wing aircraft; in the rotary wing aircraft, due to the existence of multiple flight stages, the power system Power output devices such as main rotor, front pull / back push propeller, and tail rotor are required, and a multi-output design that is different from the single output of existing gasoline-electric hybrid vehicles must be designed

Method used

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Embodiment Construction

[0040] The embodiments of the present invention will be described in detail below. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals indicate the same or similar elements or elements with the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to explain the present invention, but should not be construed as limiting the present invention.

[0041] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", " "Back", "Left", "Right", "Vertical", "Horizontal", "Top", "Bottom", "Inner", "Outer", "Clockwise", "Counterclockwise" and other directions or The positional relationship is based on the position or positional relationship shown in the drawings, and is only for the convenience of describing the present inventio...

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Abstract

The invention provides a multi-input multi-output power system for a rotary wing aircraft and a control method of the multi-input multi-output power system. The multi-input multi-output power system comprises a rotary wing, a propeller for providing forward flying power, a main power source for providing power for the propeller in a fixed wing flight mode phase of the rotary wing aircraft, an auxiliary power source for providing power for the rotary wing together with the main power source in a vertical take-off and landing phase of the rotary wing aircraft, a front transmission mechanism fromthe main power source to the propeller, and a main transmission mechanism from the main power source and the auxiliary power source to the rotary wing. According to the invention, a plurality of power sources, such as a fuel engine and a motor, are adopted; the power of the power sources is converged and split through a speed change device of the power system; the power is redistributed through different control strategies according to different flight phases of the rotary wing aircraft, so that a comprehensive power system with requirements of multi-input power converging and splitting and multi-output realized by control distribution is formed; and the power system not only can meet a high-power requirement of the rotary wing mode, but also can work in an optimal economic state in the fixed wing mode.

Description

Technical field [0001] The present invention relates to the technical field of rotating wing aircraft, in particular to the power matching technology of medium and large rotating wing aircraft, in particular to a multiple input and multiple output power system and control method for rotating wing aircraft. Background technique [0002] Rotary-wing aircraft is a new type of unmanned aircraft that combines the vertical take-off and landing performance of a helicopter and the high-speed cruise performance of a fixed-wing aircraft. The Chinese patent with the patent number ZL201110213680.1 and the name "A Rotating Wing Aircraft with Variable Flight Mode" is a typical model. The aircraft has a three-wing aerodynamic layout. Among them, in the helicopter flight mode, the main wing can be used as a rotor to rotate to provide the aircraft with the required pulling force. At the same time, when the aircraft has a certain flying speed, it can be locked as a fixed wing to achieve high-effi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/02B64D35/02B64D35/04
Inventor 高正红那洋张珊珊冯尚龙何澳
Owner 南京灵龙旋翼无人机系统研究院有限公司
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