Aircraft Motor Controller for Self-Powered Damping During Voltage Interrupts
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Solution Overview
Problem
Permanent magnet motors in aircraft systems face inefficiencies due to passive magnetic damping losses and require a continuous power supply for electromagnetic damping, making them inoperable during voltage interrupts, necessitating an improved damping solution.
Innovation Solution
A controller that harnesses kinetic energy from the motor to power damping components, enabling damping even without an external power supply by using electrical energy to activate damping components through a signal, allowing for efficient damping and motoring modes without additional energy consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If passive magnetic damping is used to prevent damage during power failure, then damping function is provided, but motor drive efficiency is reduced due to additional losses
Solution Approach 1:
The controller uses electrical energy generated by the motor itself during kinetic energy recovery to power the damping control function. The controller receives electrical energy from the permanent magnet motor and uses this self-generated energy to activate damping components, eliminating the need for external power supply and avoiding continuous energy consumption during normal operation.
2Reliability
If electromagnetic damping is used to provide damping control, then damping function is provided, but the system requires continuous external power supply which is unavailable during voltage interrupts
Solution Approach 1:
The system powers itself by harvesting electrical energy from the motor during operation. The controller receives electrical energy directly from the permanent magnet motor and uses this self-generated power to drive the damping control function, enabling operation during external power failures without requiring continuous external power supply.
3Reliability
If damping components are continuously powered to ensure readiness, then damping function is available, but energy is consumed during normal operation
Solution Approach 1:
The damping components are activated periodically or on-demand rather than continuously. The controller activates damping components only when needed by providing control signals during specific operating conditions, such as during kinetic energy recovery or power failure events, rather than maintaining continuous power to damping components during normal motoring operation.
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
The solution provides reliable and efficient damping to permanent magnet motors, optimizing energy use and ensuring safe deceleration without external power, enhancing motor drive efficiency and safety during power failures.
Implementation Method 1
the controller receives electrical energy from the permanent magnet motor, wherein the electrical energy is produced as a result of kinetic energy in the aircraft assembly
Implementation Method 2
uses the electrical energy to send a first signal to control a transfer of electrical energy from the permanent magnet motor to a damping component to provide damping
Data Source
AI summary
A controller for an aircraft assembly. The aircraft assembly includes a permanent magnet motor. The controller is configured to control the permanent magnet motor according to a damping mode. In the damping mode the controller receives electrical energy from the permanent magnet motor, wherein the electrical energy is produced as a result of kinetic energy in the aircraft assembly. The controller uses the electrical energy to send a first signal to control a transfer of electrical energy from the permanent magnet motor to a damping component to provide damping to the permanent magnet motor.