Aircraft Flight Controller Retention Mechanism
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Solution Overview
Problem
Existing solutions for securely mounting and removing portable electronic devices, such as flight controllers, in aircraft cockpits face challenges in withstanding vibration and applying the necessary force to engage and disengage electrical contacts, often requiring significant force and tools.
Innovation Solution
A retention mechanism featuring a base with pivoted levers and a manual actuator that rotates between orientations to securely engage and disengage the device, providing mechanical leverage to manage the force required for contact engagement and disengagement without tools, using a combination of levers, links, and a manual actuator for efficient retention and release.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If portable flight controller is made removable for upgrades and relocation, then adaptability is improved, but the force required to engage and disengage electrical contacts increases significantly
Solution Approach 1:
The system transitions from a static connection to a dynamic one where the flight controller can be easily inserted and removed. The electrical connector and receptacle are designed to accommodate repeated engagement and disengagement cycles, maintaining electrical connectivity while enabling portability.
Solution Approach 2:
An electrical connector with multiple contacts acts as an intermediary between the flight controller and the display device. This connector includes a spring-loaded mechanism that distributes the engagement force across multiple contacts, reducing the force required at each individual contact point while maintaining secure electrical connection.
2Reliability
If significant force is applied to engage electrical contacts, then reliable electrical connection is achieved, but ease of operation deteriorates and tool requirement increases
Solution Approach 1:
The electrical connector incorporates a spring-loaded mechanism that dynamically adjusts during engagement. The spring gradually compresses as the connector is inserted, distributing the engagement force over time and distance, which reduces the peak force required and eliminates the need for tools while maintaining reliable electrical contact.
Solution Approach 2:
The electrical connection is segmented into multiple individual contacts rather than a single large-contact connection. This segmentation allows each contact to engage independently with reduced force, while the cumulative effect of multiple contacts provides reliable overall electrical connectivity.
3Ease of operation
If mechanical leverage is used to reduce engagement force, then ease of operation is improved, but device complexity increases
Solution Approach 1:
A spring-loaded plunger mechanism provides automatic mechanical leverage during engagement. The spring accumulates energy as the plunger is compressed during insertion, then releases this energy to secure the flight controller in place. This dynamic mechanism provides the necessary mechanical advantage without requiring complex external actuation systems.
Solution Approach 2:
The retention mechanism is designed to be self-actuating during the engagement process. The actuator itself is compressed by the user's insertion motion, and this compression automatically triggers the release mechanism that secures the flight controller. The system uses the user's own input motion to activate the retention function, eliminating the need for separate actuation 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
The mechanism securely mounts and removes electronic devices while withstanding aircraft vibrations and applying the necessary force to engage/disengage electrical contacts, ensuring reliable operation and tool-free handling.
Implementation Method 1
at least one lever that is mounted by a pivot to the base. The lever(s) have an engaging portion on one side of the pivot that is adapted to engage an engaged portion of the electronic device and an actuation portion on an opposite side of the pivot. The actuation portion is adapted to rotate the lever(s) about said pivot
Implementation Method 2
the force needed to join and to separate the electrical contacts may be very large, such as up to 35 pounds of force or more
Data Source
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AI summary
An aircraft electronic device retention mechanism and method of removeably supporting an aircraft electronic device having first electrical contacts within a cockpit having compatible second electrical contacts includes a base that is generally configured to the size and shape of a surface of the electronic device and at least one lever that is mounted by a pivot to the base. The lever(s) has an engaging portion that is adapted to engage an engaged portion of the electronic device and an actuation portion. The actuation portion is adapted to rotate the lever(s) about said pivot between a first orientation in which the engaging portion retains the engaged portion and a second orientation in which the engaging portion does not retain said engaged portion. A manual actuator is connected with the actuation portion of the pivot.