Aircraft Latch Mechanism for Secure Locking Under High Vibration
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Solution Overview
Problem
Aircraft latches face challenges in securely closing and locking larger structures over long distances while withstanding high vibrations and loads, and maintaining a flush surface for spatial and kinematic requirements.
Innovation Solution
The latch mechanism employs a combination of cam members, over-center links, toggle links, and a roller mechanism to enable secure closure and locking, allowing for long-distance motion with limited handle rotation, and includes a locking mechanism and release mechanism for secure operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the latch is designed to draw together larger structures over long distances, then the locking capability is improved, but the device complexity increases
Solution Approach 1:
The latch mechanism is divided into multiple functional segments: cam members for converting rotational motion to linear motion, over-center links for providing mechanical advantage and locking action, and a separate locking mechanism. This segmentation allows each component to perform its specific function efficiently while working together to achieve reliable locking over long distances.
Solution Approach 2:
The latch employs dynamic elements including movable cam members that change position during operation, over-center links that transition between locked and unlocked states, and a roller that moves along the cam perimeter. These dynamic components enable the latch to adapt its mechanical properties during the latching cycle, providing both long-distance capability and reliable locking.
2Strength
If the latch is designed to withstand high vibrations and loads, then the strength is improved, but the device complexity increases
Solution Approach 1:
The latch incorporates a pre-loaded spring mechanism that maintains continuous contact between the roller and cam member, ensuring the locking surfaces are already engaged before external vibrations or loads are applied. This preliminary action prevents loss of locking under vibration while avoiding the need for overly complex vibration-damping structures.
Solution Approach 2:
The cam members feature curved perimeters and rounded contact surfaces that distribute loads more evenly across the locking interfaces. The roller component provides point-contact rolling motion that reduces friction and wear under high loads. These curved geometries enhance strength and vibration resistance without requiring additional complex reinforcement structures.
3Volume of moving object
If the latch maintains a flush surface with the aircraft body, then the spatial requirements are improved, but the kinematic requirements become more difficult to meet
Solution Approach 1:
The latch mechanism employs nested linkages where the over-center links are positioned within the space defined by the cam members and latch body. The roller is nested within the recesses of the cam members during operation. This nesting arrangement allows the latch to maintain a compact, flush profile with the aircraft body while still providing sufficient internal clearance for the required kinematic motion between open and closed positions.
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 mechanism ensures secure closure and locking of aircraft components, preventing accidental opening under high loads and vibrations, while meeting spatial and kinematic requirements, and allowing for efficient operation between open and closed positions.
Implementation Method 1
a roller rotatably attached to the first pair of cam members. When the latch mechanism is moved from the open position to the closed position, the roller travels along at least a portion of the perimeter of the second cam member, forcing the second cam member toward the latch body
Implementation Method 2
A pair of first cam members flanks the latch body and a handle is pivotally attached to the first end of each of the first cam members. The second ends of the first cam members are pivotally attached to the first ends of a pair of rear over-center links
Implementation Method 3
Another aspect of the invention provides a locking mechanism for retaining the latch mechanism in a closed position
Data Source
AI summary
An aircraft latch mechanism has a latch body having a front end and a rear end and a longitudinal slot extending along a portion of the length of the body. A pair of first cam members flanks the latch body. A handle is pivotally attached to the first cam members. The first cam members are also attached to a pair of over-center links. A mounting bushing extends through the longitudinal slot at the pivot where the first cam members and over-center links attach. Movement of the handle causes a corresponding movement of the first cam members, over-center links, and the connecting structure extending through the slot.