A direct-drive inner rotor starter-generator system for an aero-engine

Abstract

An aero-engine direct-drive internal rotor starter-generator system, which is applied in the field of unmanned aerial vehicle hybrid electric power, installs and fixes the starter-generator outer stator assembly on the aero-engine through a stator bracket, so that the starter-generator system has a compact structure and Short length, high integration, and high power-to-weight ratio; the coaxiality between the starter generator stator and the engine is ensured through the support of the stator bracket, and the starter generator inner rotor assembly is directly installed on the aeroengine shaft, so that the starter generator system There is no need for bearing support near the engine side, and a single bearing support is used on the far engine side, which reduces the heat generation of the bearing and improves the reliability of the bearing; there is also a resolver at the end of the rotor assembly in the starter generator far away from the aeroengine, which can accurately Detect the position of the rotor, so that the starter generator system can output high-power direct current by means of controllable rectification, and the power generation efficiency is high.

Description

technical field [0001] The invention belongs to the technical field of starter-generators for small and medium-sized unmanned aerial vehicles, and in particular relates to a single-bearing support direct-drive inner-rotor starter-generator system with output shafts of small and medium-sized aero-engines for unmanned aerial vehicles arranged in series, and in particular to an all-electrical starter-generator system. Piston aero-engine direct-drive inner rotor starter-generator system for small and medium-sized UAVs. Background technique [0002] In the all-electric propulsion of small and medium-sized UAVs, it is an important development trend to use a small aero-engine to drive the generator to generate electricity to form a DC power supply for the whole machine. The all-electric propulsion UAV platform puts forward the requirements of small size, high integration, high power, and high power-to-weight ratio for the starter-generator system. The structure of the outer rotor ...

AI Technical Summary

Problems solved by technology

The structure of the cantilever beam limits the increase in the axial length of the starter generator, thereby limiting the increase in power, and is not suitable for the higher electric power demand of all-electric propulsion UAVs

In addition, the unmanned aerial vehicle that adopts the all-electric propulsion scheme realizes the decoupling of the engine and the propeller. The propeller is distributed in different positions of the fuselage. The engine and the starter generator are usually required to be installed in the belly, and the rotation of the outer rotor structure starter generator Parts are exposed, which poses a great safety hazard to other equipment in the belly, and is not suitable for all-electric propulsion drones

At the same time, the original structure is not equipped with a resolver, and the rotor position cannot be accurately detected. The AC power of the generator can only be converted into the DC power required by the aircraft by means of uncontrollable rectification. The rectification efficiency is low, and it cannot adapt to the high power of the new starter generator system. Require

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