Drive system for rotorcraft

By introducing switchable coupling units and sensor networks into rotorcraft, the problem of transmission overload caused by main drive component failure is solved, enabling safe and economical drive system transition and separation, and reducing maintenance requirements.

CN121532331APending Publication Date: 2026-02-13COPTIC DEUTSCHLAND GMBH
View PDF 10 Cites -1 Cited by

Patent Information

Application Number
CN202480039461.1
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Priority Date
2023-07-20
Filing Date
2024-04-11
Publication Date
2026-02-13

AI Technical Summary

Technical Problem

Existing rotorcraft drive systems are prone to transmission overload and permanent damage when the main drive component fails or power decreases. They also require high maintenance, increasing operating costs and workload.

Method used

The system employs a switchable connection unit to connect or disconnect the auxiliary or emergency drive assembly from the main drive system. It uses sensors and a computing network to detect the current speed and torque, control torque transmission, avoid overload, and controllably separate the auxiliary or emergency drive assembly from the main drive system during normal flight operations.

Benefits of technology

It enables a seamless transition to auxiliary drive in the event of a failure in the main drive component or a decrease in power, reduces maintenance interval requirements, reduces operating costs and workload, and allows for less impact on the main drive system during normal flight.

✦ Generated by Eureka AI based on patent content.

Smart Images

  • Figure CN121532331A_ABST
    Figure CN121532331A_ABST
Patent Text Reader

Abstract

The invention relates to a drive system for a rotorcraft (10), the drive system comprising: a main drive assembly (7) configured to generate power capable of driving a main rotor (1) of the rotorcraft (10); a main transmission (6) configured to convert the power generated by the main drive assembly (7) into a torque acting on the main rotor (1); an additional or emergency drive assembly (2) also configured to generate power for driving the main rotor (1) wherein the additional or emergency drive assembly (2) is arranged to be connectable to the main transmission (6) via the switchable coupling unit (3). The invention also relates to a rotorcraft (10) having such a drive system.
Need to check novelty before this filing date? Find Prior Art

Citation Information

Patent Citations

  • Helicopter rotor transmission

    EP3323718A1

  • Drive, especially for the main rotor of a rotary wing aircraft

    EP3921231B1

  • Rotorcraft with hybrid drive for driving a main and / or rear rotor of the rotorcraft

    EP4015377A1

  • Hybrid electric power drive system for a rotorcraft

    US10759280B2

  • Propulsion system for a single-engine helicopter

    US20190352001A1