Aircraft Thrust Reverser Electric Actuation Power Architecture
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Solution Overview
Problem
Existing thrust reverser systems for aircraft are heavy due to complex hydraulic or pneumatic actuation systems and require multiple power sources, leading to maintenance challenges and power dissymmetry issues when multiple thrust reversers do not deploy simultaneously.
Innovation Solution
A single power-conversion module with autotransformers and rectifier stages supplies electric motors for multiple thrust reversers, reducing the number of power sources and weight, and incorporating a supervisor for monitoring and control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If hydraulic or pneumatic actuation systems are used for thrust reversers, then reliable actuation is achieved, but the system becomes heavy and complex requiring maintenance
Solution Approach 1:
The patent replaces hydraulic or pneumatic actuation systems with electric motors to drive the thrust reverser cowls. This substitution eliminates the need for hydraulic fluid distribution networks and pneumatic compression systems, significantly reducing system complexity and weight while maintaining reliable actuation through electric control
Solution Approach 2:
The patent explicitly moves away from pneumatic and hydraulic systems by using electric motors instead. The invention avoids the complexity of fluid distribution networks, compression systems, and associated maintenance requirements while achieving the same actuation function through electrical means
2Adaptability or versatility
If multiple power sources are used for each thrust reverser actuator, then independent operation is enabled, but the number of power lines and system weight increases
Solution Approach 1:
The patent merges the power supply architecture by using a single power source that can distribute power to multiple thrust reverser actuators through a common electrical network. This consolidation reduces the total number of power lines and power conversion modules while maintaining the capability for independent operation of each actuator through controlled power distribution
Solution Approach 2:
The single power source is designed to serve multiple functions by powering several thrust reverser actuators simultaneously or independently. The electrical architecture provides universal power distribution that adapts to different operational scenarios, enabling versatile control without requiring separate power sources for each actuator
3Ease of operation
If segregated actuation systems are used for each thrust reverser, then independent control is achieved, but power dissymmetry occurs when reversers do not deploy simultaneously
Solution Approach 1:
The patent incorporates feedback mechanisms that monitor the operational state of each thrust reverser actuator and adjust power distribution accordingly. This feedback control enables the system to detect when reversers are deployed or retracted and dynamically balance power consumption, minimizing power dissymmetry while maintaining independent control capability
Solution Approach 2:
The power distribution system is designed to be dynamic rather than static, automatically adjusting power allocation based on the real-time operational status of each thrust reverser. This dynamic adaptation allows the system to handle asymmetric deployment scenarios efficiently, reducing energy loss while preserving independent control of each actuator
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
This solution simplifies the electrical architecture, reduces weight, and minimizes current harmonics, allowing simultaneous operation of thrust reversers with reduced maintenance needs and power sources, while ensuring efficient power distribution.
Implementation Method 1
the power-conversion module comprises at least one autotransformer supplied with an alternating electric voltage by the power source of said aircraft
Implementation Method 2
connected to at least one rectifier stage adapted for converting said alternating voltage into direct voltage
Data Source
AI summary
A thrust reverser device for an aircraft includes at least two thrust reversers, and each of them includes a movable cowl movably actuated by an actuator driven by an electric motor. The electric motor is powered by a single power-conversion module including at least one autotransformer which is supplied with an alternating electric voltage and connected to at least one rectifier stage converting the alternating electric voltage into a direct voltage. The rectifier stage is connected to a current balancing stage and a current smoothing stage, supplying with the direct voltage the electric motor of the electric actuator of the movable cowl.