Satellite Radiator Protrusions for Thermal Rejection and Signal Clearance
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Solution Overview
Problem
Geostationary satellites face challenges in achieving a balance between compact size for air transport and launch compatibility, high thermal rejection capacity, accommodating large tanks, and installing multiple reflectors while maintaining signal transmission quality.
Innovation Solution
The satellite design features North and South faces with protruding main radiators covered in high infrared emissivity materials, allowing for efficient heat dissipation and accommodating multiple reflectors without interfering with signal transmission, along with a cylindrical support structure suitable for launchers like Proton, enabling increased payload capacity and efficient load transfer.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If deployable radiators are installed on the North and South faces to increase heat rejection capacity, then thermal rejection capacity is improved, but device complexity increases due to deployment mechanisms and fluid loops with flexible fluid connections
Solution Approach 1:
The patent applies the Dynamics principle by making the radiators deployable rather than fixed. The radiators can be extended or retracted as needed, allowing the system to adapt its thermal rejection capacity dynamically based on operational requirements. This resolves the contradiction by providing high thermal capacity when needed while maintaining a compact form when deployment is not required.
Solution Approach 2:
The radiator system is divided into multiple segments that can be independently deployed or retracted. This segmentation allows for flexible configuration where only the necessary portions are extended, reducing the complexity of fluid connections and deployment mechanisms compared to a single large deployable structure.
2Temperature
If deployable radiators are installed to increase heat rejection capacity, then thermal rejection capacity is improved, but signal transmission quality deteriorates because the radiators protrude over a considerable length obstructing signal transmission to the lateral reflectors
Solution Approach 1:
The radiators are designed to be dynamically deployable rather than permanently protruding. They can be retracted when not needed for thermal rejection, thereby clearing the path for signal transmission to the lateral reflectors. This dynamic capability allows the system to optimize both thermal management and communication performance as needed.
3Quantity of substance
If the satellite is designed to accommodate large tanks and support large payloads, then payload capacity is improved, but the satellite size increases making it difficult to load onto existing air transport vehicles and launch vehicles with small-diameter fairing
Solution Approach 1:
The satellite employs a nested structure where the cylindrical support structure serves as a central core, and various components including tanks and payloads are arranged concentrically or in nested configurations around it. This nesting allows maximum payload capacity within a compact diameter that fits existing launch vehicle fairings and air transport vehicles.
Solution Approach 2:
Instead of increasing satellite diameter to accommodate larger tanks and payloads, the design utilizes the longitudinal dimension (along the launch direction) to arrange components vertically. This dimensional transition allows high payload capacity while maintaining a compact cross-sectional diameter suitable for existing transport and launch infrastructure.
4Loss of information
If large diameter reflectors are installed on the East and West faces to improve transmission and reception quality, then signal transmission quality is improved, but the satellite size increases affecting launch compatibility
Solution Approach 1:
The satellite employs asymmetric face dimensions where the East and West faces are optimized for reflector installation with sufficient lateral space, while the North-South dimension is extended to compensate for the reduced East-West dimension. This asymmetric configuration allows large diameter reflectors for high-quality transmission while maintaining overall compact size for launch compatibility.
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 configuration enhances thermal rejection, supports multiple reflectors, and maintains signal quality, while being simpler, reliable, and cost-effective, allowing for the use of large-diameter reflectors and accommodating large tanks, thus addressing the balance of size, thermal capacity, and transmission requirements.
Implementation Method 1
the inner face of said at least one projecting part is covered with a material having an infrared emissivity greater than 0.7
Data Source
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AI summary
The invention concerns an artificial satellite comprising one face from the North face and the South face supporting at least one main radiator (42, 44) having an outer face turned towards space and an inner face opposite the outer face. The satellite comprises a bearing structure carrying the North face, the South face, the East face and the West face. At least one part (54, 56) of said at least one main radiator (42, 44) protrudes from at least one face from the East face and the West face (36). The inner face of said at least one protruding part (54, 56) is covered with a high infrared emissivity material. The value of the dimension (L54,56) of said at least one protruding part (54, 56) is between 19% and 50% of the value of the distance (Lc) between the East and West faces.