Single-Blade Rotor Stopping by Closed-Loop Electric Machines
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Solution Overview
Problem
Current rotary wing aircraft designs require complex and heavy clutch systems and separate brakes to stop single-blade rotors during transition from hover to forward flight, leading to increased system complexity, weight, and wear.
Innovation Solution
A rotary wing aircraft with a simplified drive system using electric machines that operate in a closed loop configuration to brake single-blade rotors to zero rotation speed, eliminating the need for dedicated brakes and additional components, and allowing for energy recuperation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate brakes and clutch systems are used to stop single-blade rotors during transition from hover to forward flight, then the rotor stopping function is achieved, but system complexity and weight increase
Solution Approach 1:
The patent combines the clutch and brake functions into a single integrated system. The clutch connection between the power plant and rotor is used to simultaneously achieve both power transmission and rotor deceleration, eliminating the need for separate brake components while maintaining reliable rotor stopping during transition phases
Solution Approach 2:
The clutch system is designed to perform multiple functions: power transmission during hover, power disconnection during transition, and rotor braking through controlled slip. This multi-functional design reduces overall system complexity by eliminating dedicated brake components while achieving the same rotor stopping reliability
2Reliability
If separate brakes and clutch systems are used to stop single-blade rotors, then rotor stopping is achieved, but system weight increases
Solution Approach 1:
The patent merges the brake function into the existing clutch mechanism, eliminating the need for separate brake components. The clutch's friction elements and control system are utilized for both power transmission and rotor deceleration, significantly reducing the weight of the overall stopping system
Solution Approach 2:
The clutch system performs dual functions of power transmission and rotor braking, eliminating redundant components. By making the clutch system multi-functional, the patent reduces system weight while maintaining reliable rotor stopping capability during transition from hover to forward flight
3Reliability
If traditional clutch and brake systems are used, then rotor stopping is achieved, but maintenance requirements increase
Solution Approach 1:
The patent combines clutch and brake functions into a single system, reducing the number of components that require maintenance. The integrated design means fewer separate systems to inspect, adjust, and repair, while maintaining the same rotor stopping reliability through coordinated control of the clutch connection
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
Enables efficient and fast rotor stoppage during transition, reducing weight and complexity by avoiding the need for additional components, and minimizing heat generation, while allowing for energy recovery.
Implementation Method 1
The closed loop operation of electric machines allows for secure and reliable stopping of single-blade rotors without heat generation
Data Source
AI summary
A rotary wing aircraft that extends along a roll axis between a nose region and an aft region, comprising: at least one first single-blade rotor and at least one second single-blade rotor which are spaced apart from each other along the roll axis; at least one first electric machine and at least one second electric machine which are at least configured to drive in motor mode the at least one first single-blade rotor and the at least one second single-blade rotor for generating lift in hover condition of the rotary wing aircraft; at least one propulsion device that is at least configured to generate forward thrust in forward flight condition of the rotary wing aircraft; and a fixed-wing arrangement that is at least configured to provide lift in the forward flight condition.