Distributed Landing Gear Actuation Architecture
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Solution Overview
Problem
Current landing gear systems for aircraft are cumbersome due to the need for dedicated controllers and motor drive units for each electromechanical actuator, leading to increased size, weight, and complexity, which can be costly and inefficient.
Innovation Solution
A distributed landing gear system architecture that allocates resources and shares components among subsystems, utilizing a centralized controller and motor drive units to power and control multiple landing gear actuators, including electromechanical and hydraulic actuators, to reduce redundancy and enhance efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If dedicated controllers and motor drive units are provided for each electromechanical actuator, then each actuator can be independently controlled, but the size, weight, and number of parts increase
Solution Approach 1:
The patent combines multiple motor drive units into a single shared drive unit that can sequentially control multiple electromechanical actuators. This merging approach reduces the total number of drive units and controllers, thereby decreasing system weight while maintaining independent control capability through time-multiplexed operation.
Solution Approach 2:
The shared motor drive unit is designed to universally control multiple different actuators for various landing gear subsystems (gear extension, retraction, door operation, brake control). This multi-functional design allows a single drive unit to replace multiple dedicated drive units, reducing overall system weight and part count.
2Reliability
If dedicated controllers and motor drive units are provided for each electromechanical actuator, then each actuator can be independently controlled, but the complexity of the system increases
Solution Approach 1:
The patent merges multiple controllers and motor drive units into a single shared control unit that sequentially manages multiple actuators. This consolidation reduces the number of separate control circuits and drive units, simplifying the overall system architecture while maintaining independent actuator control through time-multiplexed signal distribution.
Solution Approach 2:
The shared motor drive unit operates using periodic action by sequentially switching control signals to different actuators in a time-multiplexed manner. This periodic switching allows a single controller to manage multiple actuators independently without requiring dedicated continuous control circuits for each, thereby reducing system complexity.
3Productivity
If multiple dedicated motor drive units are used, then each actuator can operate independently, but the cost and number of parts increase
Solution Approach 1:
The patent merges multiple dedicated motor drive units into a single shared drive unit that can control multiple actuators sequentially. This consolidation reduces the total number of parts (controllers, drive units, wiring harnesses) while maintaining the capability for each actuator to operate independently through time-multiplexed control signals.
Solution Approach 2:
The shared motor drive unit is designed with universal functionality to control multiple different landing gear actuators (gear extension, retraction, door operation, brake control). This multi-functional design allows a single drive unit to replace multiple dedicated units, reducing part quantity while preserving independent operation capability for each subsystem.
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 approach reduces the overall weight and cost of the landing gear system by allowing simultaneous operation of multiple actuators with a single controller and motor drive unit, improving operational efficiency and reliability while minimizing redundant components.
Implementation Method 1
Electrical landing gear systems may include electromechanical actuators (EMAs), or electric motors, configured to actuate various landing gear subsystems
Implementation Method 2
A single shared motor drive unit may be configured to power an electromechanical actuator and a hydraulic actuator
Data Source
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AI summary
A system for controlling landing gear subsystems may comprise a controller (122) and a first motor drive unit (130) in operable communication with the controller. A first electric motor (132) and a second electric motor (134) may be in operable communication with the first motor drive unit. A second motor drive unit (150) may be in operable communication with the controller. A third electric motor (136) and a fourth electric motor (142) may be in operable communication with the second motor drive unit. An AC/DC converter (200) may be electrically coupled to the first drive unit and the second motor drive unit.