Unmanned aircraft cruise hybrid power system and control method thereof

By designing an unmanned aircraft cruise hybrid system and using the dual power output of the engine and electric motor, the existing unmanned aircraft power system's endurance and power shortage are solved, and the effect of higher power and longer battery life is achieved, and the safety performance and fuel savings are doubled.

CN119683046APending Publication Date: 2025-03-25BEIJING HANPIN HANGTONG TECH DEV CO LTD
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Patent Information

Application Number
CN202510107916.5
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2021-08-11
Publication Date
2025-03-25

AI Technical Summary

Technical Problem

In the existing drone cruise power system, fuel engines and brushless motors have their own advantages and disadvantages, insufficient battery life and power, and cumbersome maintenance.

Method used

Design an unmanned aircraft cruise hybrid system, including engine, motor and propeller, through a dual clutch structure composed of one-way bearing and propeller shaft, to achieve dual power output of the engine and the motor, and to complement the respective advantages of the engine and the motor.

Benefits of technology

It achieves higher power output and longer continuous power output time, has double safety performance, and reduces fuel consumption by optimizing the engine operating status in real time; at the same time, the excess kinetic energy is stored in the battery, saving battery volume and weight.

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Abstract

The invention discloses an unmanned aircraft cruise hybrid power system and a control method thereof.The unmanned aircraft cruise hybrid power system comprises an engine, a motor and a propeller, the motor is arranged between the engine and the propeller, and an output shaft of the engine is in transmission connection with a rotating shaft of the propeller through a first one-way bearing; the outer circle face of the output shaft is in gapless contact connection with an inner side roller pin of the first one-way bearing, and the outer side face of a steel ring of the first one-way bearing is in interference fit connection with the inner circle face of the rotating shaft. A rotor of the motor is in transmission connection with the rotating shaft through a second one-way bearing, the inner circle face of the rotor is in interference fit connection with the outer side face of a steel ring of the second one-way bearing, and an inner side roller pin of the second one-way bearing is in gapless contact connection with the outer circle face of the rotating shaft. By arranging a double-clutch structure composed of the one-way bearing and the propeller shaft, two powers are output to one propeller, the limited weight distribution share of the aircraft can be utilized to the maximum degree, and the excellent performance of high energy-weight ratio and high power-weight ratio is achieved.
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