Flexible Solar Array and Thermal Radiator for Spacecraft
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Solution Overview
Problem
Spacecrafts face challenges in accommodating both solar radiation collection and thermal dissipation due to limited available space, particularly for small spacecraft or those with high requirements, necessitating a compact and robust solar array and thermal radiator arrangement that meets stringent geometrical and mechanical specifications.
Innovation Solution
A spacecraft design featuring a solar array and thermal radiator that are articulately connected, allowing them to transition from a stowed state where they are overlapping to a deployed state, with the solar array and thermal radiator being temporarily bent to increase mechanical stiffness and resonance frequency, and using repositionable concentrator reflector members for efficient solar radiation collection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If the solar array and thermal radiator are arranged in an overlapping configuration during stowed state, then the space utilization is improved and compactness is achieved, but the mechanical stiffness and structural robustness deteriorate
Solution Approach 1:
The patent applies curvature by temporarily bending the solar array and thermal radiator into an arc-shaped configuration during the stowed state. This curved arrangement increases the resonance frequency of the structure, shifting it away from the mechanical vibration behavior of the launch vehicle, thereby reducing the probability of unwanted mechanical resonances while maintaining compactness during launch.
2Ease of operation
If the solar array is made flexible to allow bending during stowed state, then the ease of stowage is improved, but the reliability and structural integrity worsen
Solution Approach 1:
The patent employs a dynamic configuration where the solar array and thermal radiator transition between two states: a flexible, bent configuration during stowage and a rigid, deployed configuration during operation. The support panel and radiator substrate are designed with sufficient flexibility to accommodate the bent shape during stowage but provide adequate structural integrity when deployed, ensuring reliability in both states.
3Productivity
If the solar array and thermal radiator are deployed away from the body, then the solar radiation collection efficiency is improved, but the device complexity and deployment mechanism requirements worsen
Solution Approach 1:
The patent combines the solar array and thermal radiator into a single integrated assembly that shares common support structures and deployment mechanisms. The support panel of the solar array and the radiator substrate are articulately connected to the spacecraft body and to each other, allowing both components to be deployed simultaneously using a unified mechanism, thereby reducing overall system 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
This design achieves a compact and robust solar array and thermal radiator arrangement that reduces the probability of unwanted mechanical resonances during launch, enhances dynamic performance, and optimizes space usage while maintaining effective heat regulation and solar radiation collection.
Implementation Method 1
Solar arrays for use in or on spacecraft are typically used for powering the spacecraft based on photovoltaic (PV) conversion of solar radiation
Implementation Method 2
excess heat is rejected via thermal radiation from the side walls of the spacecraft
Implementation Method 3
the support panel is at least partially flexible to allow the solar array to be temporarily retained in a bent panel shape near the body, to provide geometrical stiffness (i.e. temporarily increased mechanical stiffness due to temporary shape deformation)
Data Source
Figure 1
Figure 2A~2B
Figure 2C
AI summary
A spacecraft (10), comprising a body (12), a solar array (30) with a support panel (32) which is connected to the body, and a thermal radiator (50) that is connected to the body and which includes a radiator substrate (52) that is thermally coupled to the body via at least one heat link (64). The solar array and thermal radiator are configured to be transitioned from a stowed state wherein the support panel and the radiator substrate are held fixed in an overlapping arrangement along and near the body, to a deployed state wherein the solar array is unfolded with the support panel positioned at a distance from the body and the radiator substrate is folded away from the body and the solar array. Preferably, the solar array and thermal radiator are flexible, to allow them to be kept in an overlapping and temporarily bent shape in the stowed state.