Solar Array Spring Elements for Stackable Spacecraft Launch Loads
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Designing solar arrays for stackable spacecraft to survive launch forces while efficiently deploying and meeting power and weight requirements poses technological challenges.
Innovation Solution
Implementing solar array spring elements at nodes of a frame structure, which provide support and form load paths between solar arrays and neighboring spacecraft, reducing central bowing and facilitating deployment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If solar arrays are designed to withstand significant launch forces, then structural strength is improved, but device complexity and mass increase
Solution Approach 1:
The patent combines the solar array frame structure with spring elements to create a unified load-bearing system. The frame tubes are configured to act as compression members that directly contact neighboring spacecraft, merging the structural support function with the launch load resistance function into a single integrated system, thereby reducing overall device complexity while maintaining strength
Solution Approach 2:
The solar array frame serves multiple functions: it provides structural support for the solar panels, acts as a spring element to resist launch forces through compression, and creates load paths to neighboring spacecraft. This multi-functionality reduces the need for separate components, thereby reducing device complexity while maintaining structural strength
2Strength
If solar arrays are designed to withstand significant launch forces, then structural strength is improved, but mass increases
Solution Approach 1:
The patent merges the solar array frame with spring elements to create a unified structure that provides both support and launch load resistance. This integration eliminates the need for separate reinforcement components, reducing mass while maintaining the required structural strength to withstand launch forces
Solution Approach 2:
The spring elements act as intermediaries between the solar array frame and neighboring spacecraft, providing a compliant connection that distributes launch forces. This intermediary mechanism allows the use of lighter frame structures while still achieving the required strength through the distributed load path
3Productivity
If spacecraft are stacked in a launch vehicle, then productivity is improved, but solar arrays experience increased forces during launch
Solution Approach 1:
The patent configures the solar array frame tubes to be pre-loaded in compression before launch. This preliminary compression state allows the solar arrays to actively participate in resisting launch forces by creating load paths to neighboring spacecraft, thereby enabling higher stacking density without proportionally increasing the forces experienced by each solar array
Solution Approach 2:
The spring elements serve as intermediaries that distribute launch forces across multiple spacecraft in the stack. By providing a compliant connection between solar arrays and neighboring spacecraft, these intermediaries reduce the peak forces experienced by individual solar arrays while enabling increased stacking productivity
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
Enhances the ability of solar arrays to withstand launch forces, reduces mass, and enables efficient deployment by providing additional load paths and damping vibrations.
Implementation Method 1
a spring element of the solar array is spring-loaded to apply a force between the solar array and one or more components of a neighboring spacecraft
Implementation Method 2
a spring-loaded hinge attached to the solar array, the spring-loaded hinge configured to apply a torque on the solar array such that the solar array exerts a force on the neighboring spacecraft
Data Source
AI summary
An example of an apparatus includes a spacecraft body and a solar array that is attached to the spacecraft body. In addition, a solar array spring element is configured to provide a force between the solar array and one or more components of a neighboring spacecraft in a stack of spacecraft.