Deployable Satellite Thermal Enclosure with Flexible Blanket
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Solution Overview
Problem
Spacecrafts face challenges in withstanding extreme temperatures during launch, and existing thermal protection systems are heavy and bulky, restricting space and weight available for payloads and often requiring satellites to withstand bending loads or vibrations from connected fairings.
Innovation Solution
A thermal enclosure system featuring an expandable frame supporting a flexible thermally insulating material, which includes a door that opens to permit satellite deployment, allowing for maximum volume and clearance while maintaining structural integrity and minimizing weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a traditional fairing is used for thermal protection during launch, then thermal protection is provided, but weight and volume increase significantly
Solution Approach 1:
The patent employs a deployable shroud structure that transitions from a compact stowed configuration during launch to an expanded operational configuration in space. The shroud includes telescoping struts and expandable framework that allow the thermal protection system to be small during launch (reducing weight impact) and large during operation (providing adequate thermal protection), thus resolving the contradiction between thermal protection effectiveness and payload weight
Solution Approach 2:
The shroud structure is designed to nest within the launch vehicle payload bay during launch, with components such as the framework and thermal blanket folding or telescoping into a compact form. After deployment, these nested components expand to provide full thermal protection coverage, allowing the system to maintain low profile during launch while providing adequate protection when deployed
2Temperature
If a traditional fairing is used for thermal protection during launch, then thermal protection is provided, but available space and volume for payload are reduced
Solution Approach 1:
The deployable shroud provides thermal protection only when needed (during launch), and retracts or compact s to maximum extent when not needed, maximizing payload volume availability. The dynamic transformation allows the system to occupy minimal space during launch and expand to provide adequate thermal protection coverage when deployed in space
Solution Approach 2:
The shroud is divided into multiple modular sections or panels that can be independently folded, telescoped, or deployed. This segmentation allows the thermal protection system to be compact during launch (with panels folded or nested) and expand to provide adequate coverage when deployed, thus maximizing payload volume during launch while providing adequate thermal protection
3Strength
If a rigid thermal enclosure is used, then structural integrity is maintained, but weight and complexity increase
Solution Approach 1:
The patent uses a flexible thermal blanket or membrane as the primary thermal protection layer, supported by a lightweight deployable framework. The flexible blanket provides adequate thermal insulation while being much lighter than rigid enclosures, and the framework provides necessary structural integrity during deployment without the weight penalty of fully rigid construction
Solution Approach 2:
The deployable framework uses telescoping struts and articulated joints that provide structural integrity when extended in space but can be compacted to minimal size during launch. This dynamic configuration allows the structure to maintain strength when needed while minimizing weight and complexity during storage and launch
4Volume of moving object
If a deployable shroud is used to maximize payload volume, then volume constraints are relaxed, but device complexity increases
Solution Approach 1:
The shroud is divided into multiple independent modular sections that can be deployed using simple, standardized mechanisms such as telescoping struts, hinges, or latches. Each module is relatively simple in design, but collectively they provide the desired volume expansion. This segmentation reduces the complexity of any single mechanism while achieving the overall volume objective
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 system provides effective thermal protection during launch, allows for larger satellite designs within given volume constraints, and enables controlled, low-shock expansion, addressing the limitations of traditional thermal protection systems.
Implementation Method 1
a frame supporting a flexible thermal blanket enclosing the satellite
Data Source
AI summary
A satellite assembly is disclosed, including a satellite and a shroud. The satellite is stowed in a launch vehicle and the shroud includes a frame supporting a flexible thermal blanket enclosing the satellite.