Truss-Backed Solar Array Deployment Without Over-Swing
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Solution Overview
Problem
Existing passively deployed solar panel systems in space face challenges with mechanical indeterminacy, leading to risks of over-swing and potential impact with satellites or other equipment, while also requiring additional motors for controlled deployment, which increases weight, complexity, and cost.
Innovation Solution
A passively deployed solar panel array with a truss backing system that provides synchronized deployment of solar panels, using hinge linkages, springs, and diagonal trusses to ensure mechanical determinacy and stiffness, while minimizing mass and volume occupied by support systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If additional motors are used for controlled deployment, then deployment control and reliability are improved, but weight, complexity, and cost increase
Solution Approach 1:
The solar array deployment system uses passive deployment mechanisms where the structure deploys itself through pre-loaded springs and geometric constraints without requiring active motors during deployment. The system serves itself by utilizing stored elastic energy in springs and the inherent mechanical advantage of the truss geometry to achieve controlled deployment, eliminating the need for additional motors and reducing system complexity
Solution Approach 2:
The deployment system transitions from a static motor-driven approach to a dynamic passive deployment mechanism. The pre-loaded springs provide dynamic force during deployment, and the parallelogram linkages provide dynamic geometric constraints that guide the deployment motion. This dynamic approach replaces complex motor control systems with simpler elastic and geometric mechanisms
2Reliability
If additional motors are used for controlled deployment, then deployment control is improved, but weight increases
Solution Approach 1:
The system uses self-contained deployment mechanisms where pre-loaded springs and geometric constraints enable controlled deployment without additional motors. The support structure weight is minimized by replacing motor assemblies with lighter spring and linkage components that provide sufficient control through passive mechanical means
Solution Approach 2:
The patent replaces the mechanical motor-driven deployment system with a spring-based elastic energy storage system combined with geometric constraints. This substitution eliminates heavy motor assemblies, gear trains, and control electronics, replacing them with lighter spring elements and linkage geometry that achieve the same deployment control function with reduced weight
3Device complexity
If passive deployment is used, then weight and complexity are reduced, but mechanical indeterminacy leads to over-swing risk
Solution Approach 1:
The solar array support structure is segmented into multiple discrete truss elements and parallelogram linkages that work together in a determinate mechanical system. Each segment has defined degrees of freedom and constraints, creating a mechanically determinate overall system that prevents over-swing while maintaining passive deployment simplicity
Solution Approach 2:
The parallelogram linkages act as intermediary mechanical elements that mediate between the deploying solar array panels and the support structure. These linkages provide geometric constraints that guide the deployment motion and prevent over-swing, serving as mechanical mediators that ensure safe deployment without requiring active control systems
4Weight of moving object
If support systems are minimized for passive deployment, then mass and volume are reduced, but mechanical indeterminacy increases
Solution Approach 1:
The support system is segmented into discrete truss elements and linkage components that form a mechanically determinate structure. This segmentation allows the system to achieve deployment determinacy through geometric constraints and defined degrees of freedom while keeping each individual component lightweight and the overall mass minimized
Solution Approach 2:
The patent employs composite structural elements combining truss backing with parallelogram linkages to create a support system that achieves mechanical determinacy without excessive mass. The composite approach integrates multiple functional elements (structural support, deployment guidance, geometric constraint) into a unified lightweight system that provides deployment control with minimal mass
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 truss-backed solar panel array achieves synchronized and deterministic deployment, reducing the risk of over-swing and impact, while minimizing mass and volume, and eliminating the need for additional motors, thus enhancing reliability, efficiency, and cost-effectiveness.
Implementation Method 1
A passively deployed solar panel array with a truss backing system that provides synchronized deployment of solar panels, using hinge linkages, springs, and diagonal trusses
Data Source
AI summary
A passively deployable solar panel array. A truss backing is attached to the back of the solar panels and has longerons and hinge linkages that form a series of moveable parallelograms operable to fold and unfold. The truss backing further has springs and diagonals, with at least one spring and one diagonal associated with each of the parallelograms. The springs are operable to deploy the solar panels from a folded position to a deployed position. Each diagonal is operable to become in tension diagonally across its associated parallelogram once the solar panels are deployed into a final position.