Rotating Support Arms with Hollow Mounting Module for Satellite Thermal Management
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Solution Overview
Problem
Geostationary satellites face challenges in managing spatial requirements and heat dissipation due to equipment constraints, with radiators being limited by the satellite's dimensions and exposed to solar radiation, leading to inefficiencies and increased manufacturing costs.
Innovation Solution
A spacecraft design featuring rotatable supporting arms with devices offset from the body, allowing for sun-synchronous rotation to shield equipment from solar rays and reduce spatial requirements, using a mounting module with a hollow structure for the arms to minimize footprint and facilitate heat transfer through coolant fluid circulation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If radiators are mounted on the north or south face of the satellite, then they are shielded from solar radiation, but their surface area is limited by the dimensions of these faces
Solution Approach 1:
The patent extends the radiator mounting from the limited north/south faces into the third dimension by using deployable arms that position radiators away from the satellite body. This allows radiators to achieve larger surface areas while maintaining protection from solar radiation through strategic positioning in space rather than being constrained to the satellite's surface area.
Solution Approach 2:
The satellite structure is segmented by separating the radiator mounting function from the main satellite body. Deployable arms act as intermediate structures that carry radiators away from the body, allowing the radiators to be positioned optimally for both heat dissipation and solar radiation shielding without limiting their surface area to the satellite's face dimensions.
2Productivity
If deployable radiators are used to increase surface area, then heat dissipation efficiency improves, but the field of view of antennas is obstructed
Solution Approach 1:
The patent positions radiators in three-dimensional space away from the satellite body using deployable arms, allowing them to be placed in locations that do not obstruct the antenna field of view. This spatial separation enables both large radiator surface area for efficient heat dissipation and unobstructed antenna operation.
Solution Approach 2:
The deployable arms are positioned asymmetrically on the satellite body, allowing radiators to be placed in specific locations that optimize heat dissipation while avoiding interference with antenna coverage zones. The asymmetric placement enables coexistence of thermal management and communication functions.
3Object-affected harmful factors
If mirrors are used to cover radiators to reduce solar radiation, then heat dissipation efficiency improves, but manufacturing costs increase
Solution Approach 1:
The patent extracts the solar radiation shielding function from expensive mirror coatings and replaces it with a geometric solution using deployable arms that position radiators in shadow zones. This eliminates the need for additional protective materials while maintaining thermal performance.
Solution Approach 2:
The deployable arms act as intermediary structures that provide passive shadowing of radiators from solar radiation. Instead of applying reflective coatings to the radiators themselves, the arms serve as mediating elements that block sunlight geometrically, reducing manufacturing costs.
4Object-affected harmful factors
If blocking devices are added to shield radiators from solar rays, then heat dissipation efficiency improves, but overall spatial requirement increases
Solution Approach 1:
The deployable arms serve multiple functions simultaneously: they position radiators away from the satellite body to avoid antenna obstruction, provide passive shielding from solar radiation through geometric shadowing, and enable larger radiator surface areas. This multi-functionality eliminates the need for separate blocking devices.
Solution Approach 2:
The patent merges the radiator support structure with the solar radiation shielding function by designing deployable arms that naturally cast shadows over the radiators. The structural element that holds the radiators also serves as the blocking device, consolidating multiple functions into a single component.
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 reduces spatial requirements, maintains equipment at lower temperatures, and enhances heat dissipation efficiency while minimizing manufacturing costs and design complexity, maintaining performance throughout the satellite's lifetime.
Implementation Method 1
The pair of supporting arms further comprises a hollow module for the rotatable mounting of the first arm on the body, the mounting module comprising an opening through which the axis of rotation and the second supporting arm pass.
Implementation Method 2
radiators, which have the function of removing heat to cold space
Implementation Method 3
The first device is offset with respect to the axis of rotation of the first arm... allowing for sun-synchronous rotation to shield equipment from solar rays
Data Source
AI summary
Space craft comprising a body, at least one pair of supporting arms, a first device mounted on a first supporting arm and a second device mounted on a second supporting arm. The first arm is rotatably mounted on the body of the craft about an axis of rotation. The second arm is fixed to the body, and in which craft of the first device and the second device at least one is offset from the axis of rotation of the first arm. The pair of supporting arms further comprises a hollow module for the rotatable mounting of the first arm on the body. The mounting module comprising an opening through which the axis of rotation and the second supporting arm pass.