Deployable Spacecraft Body Using Hinged Composite Panels
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Solution Overview
Problem
Conventional spacecraft designs rely on a fixed central framework, which limits structural flexibility and efficiency in terms of volume usage and deployment, as well as posing challenges in managing environmental factors like temperature and radiation.
Innovation Solution
A deployable spacecraft body composed of panels connected by hinges that can fold into a stowed configuration and unfold into a deployed configuration, with elastic energy storage and a powered deployment mechanism for controlled deployment and re-stowage, using composite materials for enhanced stiffness and mass reduction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a fixed central framework (bus) is used in conventional spacecraft, then structural integrity and component protection are provided, but structural flexibility and volume usage efficiency are limited
Solution Approach 1:
The spacecraft body is divided into multiple panels connected by hinges, allowing the structure to be segmented and reconfigured. This segmentation enables the body to transition between different configurations (stowed and deployed), providing structural flexibility while maintaining integrity through the modular panel design.
Solution Approach 2:
The spacecraft body transitions from a static fixed framework to a dynamic deployable structure. The hinges enable movement and reconfiguration of panels, allowing the structure to adapt its shape and volume based on operational requirements, thus improving structural flexibility and volume usage efficiency.
2Volume of stationary object
If a deployable spacecraft body with panels and hinges is used, then volume usage efficiency and structural flexibility are improved, but structural integrity and protection against environmental factors may be compromised
Solution Approach 1:
The panels are pre-configured and connected by hinges in a way that ensures structural integrity upon deployment. The hinge design and panel arrangement are predetermined to maintain reliability while enabling volume efficiency during launch and protection during operation.
Solution Approach 2:
The use of composite materials in the panel and hinge construction provides both the necessary structural integrity and the flexibility required for deployment. Composite materials offer high strength-to-weight ratios, ensuring that the deployable structure maintains reliability while achieving volume efficiency.
3Ease of operation
If elastic energy storage in hinges is used for automatic deployment, then deployment control is improved, but device complexity increases
Solution Approach 1:
The hinges are designed to store and release elastic energy automatically, enabling the spacecraft body to deploy without external power or complex control systems. This self-service mechanism simplifies the overall device by eliminating the need for powered deployment mechanisms while maintaining ease of operation.
Solution Approach 2:
The elastic energy storage and release in the hinges creates a periodic action that drives the deployment process. The hinges are pre-loaded with elastic energy that is released in a controlled sequence, providing automatic deployment control without requiring continuous power input or complex actuation systems.
4Strength
If panels are configured with higher stiffness than hinges, then structural rigidity is improved, but manufacturing complexity increases
Solution Approach 1:
The composite material structure is designed with local quality variations, where panels are configured with higher stiffness properties and hinges with appropriate flexibility. This local differentiation optimizes the structural performance of each component while managing manufacturing complexity through targeted material property assignment.
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
This design allows for a compact stowed configuration, efficient use of launch vehicle space, and a larger deployed surface area, improving structural integrity and reducing mass while enabling controlled deployment and re-stowage for optimal performance and environmental protection.
Implementation Method 1
one or more of the plurality of hinges are configured to store elastic energy in the stowed configuration for automatically deploying the spacecraft body
Data Source
AI summary
A spacecraft is disclosed, comprising a deployable spacecraft body (110) comprising a plurality of sub-systems (321-324) for controlling operations of the spacecraft, and a plurality of panels (101, 102) and a plurality of hinges (112-115) each connecting adjacent ones of the plurality of panels, the hinges being arranged to permit the plurality of panels to be folded into a stowed configuration and unfolded into a deployed configuration, wherein the plurality of sub-systems are fixed to and supported by one or more of the plurality of panels. By forming the body of the spacecraft from a deployable structure, the overall size of the spacecraft can be significantly reduced in the stowed configuration. In some embodiments, a plurality of the spacecraft in the stowed configuration can be combined into a modular spacecraft assembly prior to launch, with data and power connections between the plurality of stowed spacecraft being used to transfer power from, and data to, a payload monitoring unit on the launch vehicle.