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

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...

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

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