Non-Coaxial Pivot Wing Deployment Mechanism
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Solution Overview
Problem
Existing wing systems for air vehicles with deployable wings face challenges in efficiently transitioning between stowed and deployed configurations, particularly in achieving synchronized levelling and translation operations while maintaining structural integrity and aerodynamic efficiency.
Innovation Solution
A wing system with a deployment mechanism that includes non-coaxial pivot axes for the first and second wings, allowing for synchronized pivoting, levelling, and translation operations. The mechanism features a meshed gear arrangement for pivoting synchronization and a cam arrangement for levelling, enabling efficient transition between configurations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If conventional wing systems use simple folding mechanisms, then the structure is easier to manufacture, but the synchronization and levelling between wings deteriorates
Solution Approach 1:
A cam mechanism acts as an intermediary between the pivot joints and wing sections, mediating the motion transmission to achieve synchronized pivoting and automatic levelling. The cam profile converts rotational motion into controlled combined motion, ensuring precise synchronization without complex control systems.
Solution Approach 2:
The cam mechanism utilizes curved surfaces and rotational geometry to transform simple pivoting motion into synchronized combined motion. The curved cam profile enables automatic levelling through geometric constraints, achieving precise wing alignment through rotational geometry rather than complex mechanical linkages.
2Volume of moving object
If wings are folded in close proximity to fuselage for launch, then the launch configuration is more compact, but the deployment complexity increases
Solution Approach 1:
The mechanism merges pivoting and levelling operations into a single integrated motion sequence. The cam mechanism combines two degrees of freedom (pivoting and levelling) into one actuation system, reducing the number of independent control mechanisms needed while achieving both compact stowing and precise deployment.
Solution Approach 2:
The system transitions from a static folded configuration to a dynamic deployed configuration through controlled motion. The cam mechanism enables dynamic adjustment of wing position during deployment, allowing the wings to automatically level and synchronize as they transition from the compact stowed state to the deployed flight configuration.
3Reliability
If synchronized pivoting and levelling operations are implemented, then aerodynamic efficiency is improved, but the mechanism complexity increases
Solution Approach 1:
The cam mechanism serves as an intermediary that automatically coordinates the timing and sequence of pivoting and levelling operations. This mechanical mediator ensures synchronized wing deployment and proper aerodynamic alignment without requiring complex electronic control systems or multiple independent actuators.
Solution Approach 2:
The cam mechanism enables the wing deployment system to self-regulate and self-synchronize through its geometric design. The cam profile inherently controls the motion sequence, allowing the mechanism to automatically achieve synchronized pivoting and levelling without external control intervention, thereby improving reliability while limiting complexity growth.
Data Source
AI summary
A wing system is provided for an air vehicle, the air vehicle having a fuselage including a fuselage longitudinal axis. The wing system includes a set of wings, configured for transitioning between a stowed configuration and a deployed configuration. The set of wings includes a first said wing having a first wing tip, a first wing longitudinal axis, and a first pivot axis; and a second said wing having a second wing tip, a second wing longitudinal axis, and a second pivot axis. The first pivot axis and the second pivot axis are non-coaxial. In the stowed configuration, the first wing and the second wing are in overlying relationship such that at least a majority of a pressure surface of one wing is facing a suction surface of the other wing, and the first wing tip is spaced from the second wing tip by a first lateral spacing. In the deployed configuration, the first wing is oriented with respect to the second wing such that the first wing tip is spaced from the second wing tip by a second lateral spacing greater than the first lateral spacing. The transitioning includes a pivoting operation, including: pivoting the first wing about the first pivot axis between the stowed configuration and the deployed configuration; and, pivoting the second wing about the second pivot axis between the stowed configuration and the deployed configuration.