Aircraft Actuator Movable Disk Decoupling Mechanism
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Solution Overview
Problem
Existing aircraft flight control surface actuators face issues with seizure, leading to potential damage and the need for decoupling mechanisms that are bulky and prone to jamming, with rupture thresholds not adaptable to varying flight conditions.
Innovation Solution
A flight control surface actuator with a coupling mechanism featuring a movable disk and a retaining part that can be precisely controlled for decoupling using a shape-memory material or pyrotechnic rupture member, allowing for efficient torque transmission and space-saving design.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a decoupling mechanism is added to the actuator to enable separation in case of seizure, then reliability is improved, but device complexity increases
Solution Approach 1:
The patent combines the decoupling function with the normal operation coupling mechanism by using a single disk that serves both purposes. The disk normally couples the movable gear to the output ring for torque transmission, and when the retaining part ruptures, the same disk disengages to decouple the actuator. This merging eliminates the need for separate decoupling mechanisms, reducing device complexity while maintaining reliability.
2Reliability
If a bulky decoupling mechanism is included to ensure reliable decoupling, then reliability is improved, but volume increases
Solution Approach 1:
The patent merges the decoupling function into the existing coupling disk structure. The disk that normally transmits torque also serves as the decoupling element when the retaining part fails. This integration eliminates the need for additional bulky decoupling mechanisms, achieving reliable decoupling while minimizing volume increase.
3Manufacturing precision
If a fixed rupture threshold is used in the retaining part, then manufacturing precision is improved, but adaptability deteriorates
Solution Approach 1:
The patent uses a retaining part with a predefined rupture threshold that can be adjusted by changing material properties or geometric parameters during manufacturing. This allows the rupture threshold to be optimized for different flight control applications while maintaining manufacturing precision. The retaining part is designed to rupture at a specific torque threshold, and this threshold can be tailored to match the specific requirements of different flight control surfaces.
4Reliability
If the retaining part is designed to rupture at a predefined torque threshold, then reliability is improved, but manufacturing precision deteriorates
Solution Approach 1:
The patent designs the retaining part with a controlled rupture mechanism where the rupture threshold is determined by material selection and geometric parameters rather than requiring extremely precise manufacturing tolerances. The retaining part can be manufactured with standard tolerances while still achieving reliable rupture at the desired torque threshold through careful selection of material properties and dimensional parameters.
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 reliable decoupling of the actuator from the control surface in case of jamming while maintaining torque transmission, with adjustable rupture thresholds and reduced bulk, minimizing the risk of damage and jamming hazards.
Implementation Method 1
the rupture member comprises a block formed from a shape-memory material, the block being capable of changing shape when it is subjected to an electric or magnetic field so as to apply a tensile stress to the retaining part, causing the rupture of the retaining part
Implementation Method 2
the rupture member comprises a pyrotechnic composition capable of exploding when it is subjected to an electrical current, causing the rupture of the retaining part
Data Source
AI summary
An actuator for a flight control surface of an aircraft, including: a fixed annulus for fixing to the fuselage, an rotatable annulus with respect to the fixed annulus about an axis of rotation, an output ring which can be fixed to the control surface, and a coupling mechanism having a disc with translational mobility with respect to the mobile annulus in a direction parallel to the axis of rotation, the disc able to move between an engaged position, and a disengaged position, in which the disc is disengaged from the mobile annulus to disconnect the output ring from the mobile annulus. A retaining piece keeps the disc in the engaged position, and a rupture member activates to break the retaining piece to allow the disc to move into the disengaged position.