Spacecraft Exoskeleton Truss Structure Thermal Management
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Conventional spacecraft structural support systems face challenges in sustaining large loads during launch, managing temperature excursions, and maintaining precise component alignment while efficiently dissipating heat and optimizing payload electronics placement.
Innovation Solution
A 3-D exoskeleton truss structure mechanically couples interior equipment panels and external radiator panels with a structural interface adapter, utilizing graphite tube members and coupling nodes to form a thermally stable frame that supports heat dissipating units and reduces mass by relocating heat dissipating electronics to interior panels, thermally coupled with radiator panels via heat pipes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If heat dissipating electronics are placed on exterior radiator panels, then thermal management is improved, but mass efficiency and payload placement flexibility deteriorate
Solution Approach 1:
The spacecraft structure is segmented into distinct functional zones: exterior radiator panels for thermal management, interior equipment panels for payload placement, and a 3-D truss structure for mechanical support. This segmentation allows heat dissipating electronics to be thermally coupled to exterior radiators while physically located on interior panels, optimizing both thermal management and mass efficiency.
2Strength
If a rigid structural support system is used to sustain large launch loads, then structural strength is improved, but mass efficiency and alignment precision deteriorate
Solution Approach 1:
The 3-D truss structure utilizes composite materials and optimized geometries to achieve high strength-to-weight ratio. The structure mechanically couples interior and exterior panels while sustaining large launch loads, providing both structural strength and mass efficiency simultaneously.
3Manufacturing precision
If components are tightly coupled to maintain precise alignment, then alignment precision is improved, but thermal expansion effects and structural complexity worsen
Solution Approach 1:
The 3-D truss structure serves as an intermediary mechanical coupling system between interior equipment panels and exterior radiator panels. It maintains precise component alignment while accommodating thermal expansion effects through its flexible yet rigid design, avoiding direct tight coupling that would increase structural complexity.
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 solution provides a lightweight, mass-efficient structure that maintains precise component alignment, reduces waveguide line losses, and enhances payload efficiency by clustering heat dissipating components closer to the earth-facing portion, while allowing for flexible payload electronics placement and improved thermal management.
Implementation Method 1
The at least one interior panel may be thermally coupled with the at least one radiator panel by heat pipes
Data Source
AI summary
A spacecraft includes a structural interface adapter for mating to a launch vehicle, at least one radiator panel, at least one interior equipment panel and a 3-D truss structure. The 3-D truss structure is mechanically coupled with the structural interface adapter, the at least one radiator panel, and the at least one interior equipment panel, and at least a portion of the 3-D truss structure is disposed between the radiator panel and the interior panel.