Aircraft birotor configuration

By adopting a coaxial staggered rotor blade and ducted fan drive design on the helicopter, the problems of size, weight and noise pollution of rotor drive are solved, realizing the miniaturization of the helicopter and safe and reliable flight control, and improving endurance and maneuverability.

CN224546277UActive Publication Date: 2026-07-24李秋雁
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Utility models(China)
Current Assignee / Owner
李秋雁
Filing Date
2025-09-25
Publication Date
2026-07-24

AI Technical Summary

Technical Problem

Existing helicopter rotor drive systems suffer from problems such as large size, heavy weight, serious noise pollution, high failure rate, high energy consumption, and insufficient range. Furthermore, traditional designs increase air resistance and fuselage instability, making it difficult to achieve miniaturization and widespread use as a personal transportation tool.

Method used

It adopts a design with coaxial upper and lower rotor blades staggered and rotating in the same direction and in opposite directions. It uses a ducted fan to drive the rotor blades to generate lift, and uses a motor to drive the ducted fan to adjust the rotor blade angle of attack. It eliminates the tail rotor and transmission components, and realizes direct drive and autonomous power generation.

Benefits of technology

It improves maneuverability and flight stability, reduces noise and pollution, lowers failure rate and production costs, expands the range of applications, solves range and weight issues, and achieves miniaturization and safety.

✦ Generated by Eureka AI based on patent content.

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    Figure CN224546277U_ABST
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Abstract

The utility model relates to a kind of aircraft double-rotor structure, comprising: an aircraft body, with two shaft poles in front and back;Two groups of the rotor set of upper and lower settings are arranged on each shaft pole, and the rotor set comprises the rotor blade corresponding to each other and being arranged on the two sides of shaft pole, and two propulsion modules vertically opposite with two rotor blades respectively, the rotor blade of the rotor set of same shaft pole is misaligned and is set to same direction rotation, and the rotor blade on two different shaft poles is opposite reverse rotation;Propulsion module includes a track seat, a duct fan is installed in track seat, and one side of duct fan is equipped with a return spring, and a connecting piece is arranged between duct fan and shaft pole, and connecting piece can drive rotor blade to change angle.Therefore, the utility model directly drives rotor blade to generate ascending buoyancy using propulsion module, so as to drive aircraft body to ascend and descend;And flight is stable and comfortable, easy to control, structure is simple, reduce failure, and reduce production working hours and material cost, enhance flight safety.
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Citation Information

Patent Citations

  • Helicopter rotor driving structure

    CN116534248A