Satellite Solar Array Bracket Assembly for Angled Deployment
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Solution Overview
Problem
Space vehicles, such as satellites, face challenges in optimizing solar array deployment to maximize electricity generation while minimizing launch volume and ensuring efficient orientation in orbit.
Innovation Solution
A system comprising a satellite with extendable booms and bracket assemblies that reorient solar arrays from a stowed to a deployed position, allowing them to be positioned at a predetermined angle relative to the vehicle, utilizing extendible telescoping tubes and biasing or motor mechanisms for passive or active orientation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If complex mechanisms and active components are used to deploy solar arrays to optimal orientations, then deployment precision is improved, but device complexity and weight increase
Solution Approach 1:
The solar array system is divided into multiple segments or panels that can be independently deployed and positioned. Each panel can be controlled separately to achieve the desired overall orientation, breaking down the complex deployment task into simpler, manageable segments that reduce the complexity of the control mechanism while maintaining deployment precision.
Solution Approach 2:
The solar array deployment mechanism utilizes dynamic positioning capabilities where the panels can be adjusted to different angles and orientations. The system employs movable joints and articulation points that allow the panels to achieve optimal orientations dynamically, improving deployment precision without requiring overly complex fixed mechanisms.
2Manufacturing precision
If complex mechanisms and active components are used to deploy solar arrays to optimal orientations, then deployment precision is improved, but weight increases
Solution Approach 1:
Instead of using complex active mechanisms to achieve precise solar array orientation, the invention inverts the approach by utilizing passive structural design elements. The solar panels are mounted on articulated booms with built-in articulation points that naturally position the panels at optimal angles through their mechanical design, eliminating the need for heavy active positioning mechanisms while maintaining deployment precision.
Solution Approach 2:
The solar array system is designed to self-position and self-align during deployment through its mechanical structure. The articulated booms and panel mountings automatically orient the panels toward the optimal angle as they extend, without requiring additional active components or complex control systems, thereby reducing weight while maintaining precision.
3Power
If solar arrays are positioned in a stowed position for launch, then launch performance is improved, but electricity generation capability is reduced
Solution Approach 1:
The solar array system transitions from a static stowed position during launch to a dynamic deployed configuration in space. The articulated booms and panel mountings enable the solar arrays to move from a compact launch position to an extended operational position, maximizing surface area exposure to sunlight and thereby optimizing electricity generation capability after deployment.
Solution Approach 2:
The solar arrays utilize dimensional transformation by extending from a compact three-dimensional stowed configuration during launch to a larger, more spread-out configuration in space. The articulated booms extend the panels outward and away from the satellite body, increasing the effective surface area exposed to sunlight and thereby enhancing electricity generation capability while maintaining compact launch dimensions.
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 efficient deployment and orientation of solar arrays to enhance electricity generation, reducing launch volume and improving operational efficiency in orbit.
Implementation Method 1
the bracket assembly further comprises a biasing mechanism, wherein the biasing mechanism is configured to bias at least one of the first bracket and the second bracket to the deployed position. In some embodiments, the biasing mechanism comprises a spring-biasing mechanism, wherein the spring-biasing mechanism comprises at least one spring urging the first bracket and the second bracket to the deployed position
Implementation Method 2
the bracket assembly further comprises at least one motor, wherein the at least one motor is operable to position at least one of the first solar array and the second solar array to the deployed position
Implementation Method 3
Space vehicles such as satellites typically utilize solar arrays to generate electricity for the operation of vehicle systems
Data Source
AI summary
A system, including: a satellite; a first solar array including a first solar panel; a second solar array including a second solar panel; a boom having a first end and a second end opposite the first end, where the first end connects to the satellite; and a bracket assembly, where the bracket assembly has a first, second, and third brackets, where the first bracket connects the first solar array to the third bracket, where the second bracket connects the second solar array to the third bracket, and where the third bracket connects the first bracket and the second bracket to the second end of the boom; where the bracket assembly is configured to reorient the first solar array and the second solar array between a stowed position to a deployed position, and where in the deployed position, the first and second solar arrays are oriented at a predetermined angle.