Spring-Guided Hand Actuator With Positive Locking for Aircraft Panels
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Solution Overview
Problem
Existing aircraft hand actuators lack efficient mechanisms for guiding and locking the handle structure, leading to increased wear and instability during longitudinal movement, which affects the reliability and durability of aircraft components like cowl and hatch operations.
Innovation Solution
The proposed aircraft assembly incorporates a guide system with pivotally coupled guide elements and spring elements, which guide the handle structure between positions, reducing vertical loads on the tracks and slides, and utilizing a cable assembly to actuate aircraft components, providing positive locking and reduced wear through compression of spring elements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a guide system with spring elements is added to guide the handle structure, then wear on the guide system is reduced and stability is improved, but device complexity increases
Solution Approach 1:
The guide system is segmented into multiple guide elements (first guide element with first spring element, second guide element with second spring element) that are pivotally coupled at different locations. This segmentation allows each guide element to independently manage specific aspects of handle structure guidance, reducing overall wear while distributing the complexity across modular components rather than a single complex mechanism.
Solution Approach 2:
Spring elements are integrated into the guide elements to provide beforehand cushioning during handle structure movement. The spring elements pre-load and absorb shocks and vertical loads before they reach the track and slide, reducing wear on the guide system components and improving stability during operation.
2Duration of action of stationary object
If the guide system uses multiple pivotally coupled guide elements with spring elements, then wear on tracks and slides is reduced, but manufacturing complexity increases
Solution Approach 1:
The guide system is divided into separate guide elements that can be manufactured independently and then assembled through pivotal coupling. This segmentation allows each guide element to be optimized for its specific function and manufactured using standard processes, reducing overall manufacturing complexity compared to a single integrated complex guide mechanism.
Solution Approach 2:
The spring elements within each guide element provide self-adjusting cushioning and load absorption during handle structure movement. This self-service mechanism reduces wear on the track and slide without requiring external adjustment mechanisms or complex control systems, simplifying the overall manufacturing process while extending component durability.
3Ease of operation
If the guide system is designed to reduce vertical loads on tracks and slides, then wear is minimized and operation is smoother, but device complexity increases
Solution Approach 1:
Spring elements are integrated into the guide elements to provide beforehand cushioning during handle structure movement. The spring elements pre-load and absorb shocks and vertical loads before they reach the track and slide, reducing wear on the guide system components and improving stability during operation.
Solution Approach 2:
The spring elements act as intermediaries between the handle structure and the track-slide mechanism. They mediate the transmission of vertical loads by absorbing and dampening shocks, allowing smooth handle movement while protecting the track and slide from excessive wear without requiring complex active control systems.
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 enhances the reliability and durability of aircraft components by minimizing wear on the guide system, ensuring stable and efficient operation of aircraft components such as cowl and hatch mechanisms, while allowing for smooth and controlled actuation.
Implementation Method 1
The first guide element includes a first spring element. The second guide element includes a second spring element.
Implementation Method 2
utilizing a cable assembly to actuate aircraft components, providing positive locking and reduced wear through compression of spring elements
Data Source
AI summary
An assembly is provided for an aircraft. This aircraft assembly includes an actuator and a cable assembly. The actuator includes a support structure, a handle structure and a guide system configured to guide movement of the handle structure longitudinally along the support structure between a first position and a second position. The guide system includes a first guide element and a second guide element. The first guide element includes a first spring element and is pivotally coupled to the handle structure at a handle structure pivot axis. The second guide element includes a second spring element and is pivotally coupled to the handle structure at the handle structure pivot axis. The cable assembly includes a sleeve and a cable projecting longitudinally out of the sleeve. The sleeve is attached to the support structure. The cable is coupled to the handle structure.