Rotary Ball Lock Latching Mechanism for Aircraft Panels
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Solution Overview
Problem
Conventional latching mechanisms for aircraft panels require torqueing fasteners, leading to wear, loosening, and potential hazards, while also compromising aerodynamic and low observable characteristics, and do not facilitate easy installation or removal without surface contact.
Innovation Solution
A latching mechanism using a rotatable sleeve and post engagement system that allows panels to separate from the support member without surface contact, utilizing mechanical, hydraulic, or pneumatic actuators, and incorporating a spring for secure locking and easy removal, with a spiral groove and deformable sleeve for locking engagement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional fasteners (screws) are used to engage panels to aircraft surface, then the panel can be securely attached, but the fasteners require torqueing which leads to wear, loosening, and potential hazards
Solution Approach 1:
The patent extracts the fastener function from conventional screws and replaces it with a post engagement mechanism. The post extends through the panel and engages with a retention mechanism that uses a ball and groove system instead of threaded fasteners, eliminating wear and loosening issues associated with conventional screws.
Solution Approach 2:
The patent replaces the mechanical threading system of conventional fasteners with a ball-and-groove retention system. The ball engages with a groove in the post to provide locking without requiring torque, eliminating the wear and loosening problems inherent in threaded fastener systems.
2Reliability
If conventional fasteners are used to attach panels, then secure attachment is achieved, but fasteners can fall into aircraft interior creating hazardous conditions
Solution Approach 1:
The patent removes conventional fasteners from the system and replaces them with an integrated post engagement mechanism. The retention ball and groove system is contained within the panel structure, preventing any loose components from falling into the aircraft interior while maintaining secure attachment.
3Reliability
If conventional fasteners are used for panel attachment, then panels can be secured, but installation and removal require touching the panel upper surface and are time-consuming
Solution Approach 1:
The patent implements a self-latching mechanism where the ball automatically engages with the groove when the post is inserted, and the spring automatically maintains engagement. For removal, a tool simply needs to depress the release button, allowing single-person operation without touching the panel upper surface during critical operations.
Solution Approach 2:
The patent introduces a release button as an intermediary control mechanism. This button, accessible from below the panel, controls the engagement and disengagement of the retention ball, allowing operators to install and remove panels without touching the upper surface.
4Reliability
If conventional fasteners are used to attach panels, then panels can be secured, but surface irregularities are created that compromise aerodynamic and low observable characteristics
Solution Approach 1:
The patent removes conventional protruding fasteners from the aircraft surface and replaces them with a flush-mounted post engagement system. The post extends through the panel but engages from below, allowing the panel surface to remain smooth and flush with the aircraft skin, preserving aerodynamic and low observable characteristics.
5Ease of operation
If a latching mechanism is designed for rapid panel removal, then ease of operation is improved, but sealing characteristics may be compromised
Solution Approach 1:
The patent separates the attachment function (post engagement mechanism) from the sealing function (gasket system). The post provides rapid mechanical engagement and disengagement, while the gasket maintains the seal independently, allowing fast operation without compromising sealing characteristics.
Solution Approach 2:
The patent introduces a gasket as an intermediary sealing element between the panel and aircraft skin. This gasket handles the sealing function while the post engagement mechanism handles the mechanical attachment, allowing the two functions to operate independently - rapid removal is enabled by the post mechanism without affecting the seal integrity.
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 rapid and secure installation and removal of aircraft panels without surface contact, maintaining aerodynamic and low observable characteristics, while providing airtight and watertight sealing and minimizing debris entry into the aircraft.
Implementation Method 1
the spring is operative to oppose translation out of the post engagement mechanism, upon termination of power to the actuator or the rotatable sleeve
Implementation Method 2
The post engagement mechanism defines a rotatable sleeve, which rotates for locking and unlocking engagement between the post and the post engagement mechanism
Implementation Method 3
The post engagement mechanism may utilize various types of actuators, including mechanical, hydraulic, and pneumatic
Data Source
AI summary
A latching mechanism is provided for engaging an aircraft surface panel to a support member. The aircraft panel is provided with a post extending from the lower surface, which extends through a panel support member into a post engagement mechanism. The post engagement mechanism defines a rotatable sleeve, which rotates for locking and unlocking engagement between the post and the post engagement mechanism. Locking engagement continues when power to the post engagement actuator is terminated. The post engagement mechanism may utilize various types of actuators, including mechanical, hydraulic, and pneumatic. The aircraft panel and the panel support member are translatable into and out of abutting engagement independent of the need for any contact with the aircraft panel upper surface.