Aircraft Clutch Actuator Assembly With Neutral-Lock Torque Control
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Solution Overview
Problem
Existing vehicle clutch assemblies are not robust or reliable enough to function effectively in an aircraft taxi drive system environment, particularly in terms of selective torque transfer and failsafe capability within the limited space of an aircraft landing gear wheel.
Innovation Solution
A clutch actuator assembly with smaller axial dimensions, integrated with a clutch assembly in an aircraft landing gear wheel-mounted taxi drive system, featuring a bi-directional selector plate and a combination of solenoids and diodes for selective actuation and locking, ensuring reliable operation and torque control within the limited space.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional clutch assemblies are used, then basic torque transfer function is provided, but they are not robust or reliable enough for aircraft taxi drive system environment and fail to provide selective actuation capability
Solution Approach 1:
The clutch assembly is divided into distinct functional segments: a clutch housing, a clutch pack, and a separate actuator assembly with selector plate. This segmentation allows each component to be optimized for its specific function while working together as an integrated system, improving both reliability and selective actuation capability.
Solution Approach 2:
The actuator assembly incorporates a bi-directional selector plate that can be dynamically positioned in multiple states (first position for torque transfer, second position for disengagement, third position for reverse torque transfer). This dynamic positioning capability enables selective actuation and robust operation in the aircraft taxi drive system environment.
2Reliability
If available actuators are used, then basic actuation function is provided, but they do not provide reliable failsafe capability that prevents actuation when unsafe
Solution Approach 1:
The actuator assembly is designed with a default neutral disengaged position that is established before operation. The selector plate is biased toward this safe position, and the system requires deliberate actuation to engage torque transfer. This preliminary configuration ensures failsafe capability by default, preventing actuation when unsafe without requiring complex additional safety mechanisms.
3Volume of stationary object
If conventional clutch assemblies are used, then basic function is provided, but they are not designed or sized to function effectively within the limited volume of an aircraft landing gear wheel
Solution Approach 1:
The clutch assembly is nested within the aircraft landing gear wheel structure, with the actuator assembly integrated into the clutch housing. The selector plate and clutch pack are arranged concentrically around a central axis, maximizing space utilization. This nested configuration enables the clutch assembly to function effectively within the limited volume of the landing gear wheel while maintaining operational reliability.
Solution Approach 2:
The actuator assembly utilizes axial dimension for the selector plate's bi-directional movement, allowing compact radial packaging. The clutch pack is arranged in a radial configuration around the central axis, enabling torque transfer through axial engagement. This dimensional arrangement optimizes the use of limited space within the landing gear wheel volume.
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 clutch actuator assembly provides reliable and predictable operation, ensuring selective torque transfer and maintaining the clutch in a neutral disengaged position when unsafe to operate, thereby enhancing the safety and efficiency of aircraft ground movement.
Implementation Method 1
The clutch actuator assembly is selectively actuable to a first position that transfers torque from the torque input member to the torque output member
Implementation Method 2
The clutch actuator assembly incorporates a combination of solenoids and diodes for selective actuation and locking
Implementation Method 3
a spring returnable to a neutral disengaged position
Data Source
AI summary
A powered clutch actuator assembly for integration with a clutch assembly is provided. The actuator and clutch assemblies, sized to fit within constraints of an aircraft landing gear wheel-mounted taxi drive system, are engineered to occupy a default neutral disengaged position that prevents torque transfer when torque to move the aircraft should not be transferred to the taxi drive system. Multiple solenoids and diodes power rotational motion of the actuator assembly to move a bi-directional clutch component in a desired rotational direction during torque transfer. A locking solenoid automatically locks and maintains the actuator assembly in a neutral disengaged condition when none of the solenoids are powered and disengages the actuator assembly when one solenoid is powered to cause rotation of the actuator assembly. Solenoid supports structured to operate as integral heat sinks may direct heat to an on-aircraft heat sink, prolonging the working life of the actuator assembly.