Satellite Multiple Aspect Ratio Modules for Launch Constraints
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Solution Overview
Problem
Spacecraft designers face challenges in meeting increasing payload capacity demands while maintaining compatibility with conventional launch vehicle constraints, as existing configurations often compromise between antenna reflector size and thermal radiator area due to fixed aspect ratios.
Innovation Solution
A satellite configuration with multiple aspect ratios, allowing for larger spacecraft elements like antenna reflectors and solar array panels to be arranged within the launch envelope of conventional launch vehicles by using at least two modules with different aspect ratios, enabling larger antenna reflectors and increased thermal radiator area without exceeding launch vehicle constraints.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a spacecraft is configured with a single aspect ratio to simplify design and manufacturing, then device complexity is reduced, but the ability to accommodate larger antenna reflectors and thermal radiators within launch vehicle constraints is limited
Solution Approach 1:
The spacecraft is divided into multiple modules, each with different aspect ratios. This segmentation allows each module to be optimized for specific functions (e.g., antenna reflectors in modules with larger aspect ratios, thermal radiators in modules with smaller aspect ratios) while collectively meeting launch vehicle constraints and maximizing payload capacity
Solution Approach 2:
Different modules are assigned different aspect ratios tailored to their specific functional requirements. For example, modules housing antenna reflectors use aspect ratios that maximize reflector area, while modules with thermal radiators use aspect ratios that optimize radiator surface area, thereby achieving local optimization without compromising overall system performance
2Quantity of substance
If the spacecraft payload capacity is increased to meet market demands, then higher power and larger antenna apertures are achieved, but compatibility with conventional launch vehicle constraints is compromised
Solution Approach 1:
The spacecraft configuration transitions from a single aspect ratio to multiple aspect ratios across different modules. This dimensional change in configuration space allows the spacecraft to achieve larger payload capacity through optimized module arrangements while still fitting within the mass and fairing envelope constraints of conventional launch vehicles
Data Source
Figure 1A
Figure 1B~1D
Figure 2A~2B
AI summary
A high capacity satellite (300) having multiple aspect ratios is configured to have at least two modules (312, 314). Each module includes a first panel and a third panel facing, in an on -orbit configuration, respectively, toward north and south and having a width in an east-west direction (EW width); and a second and a fourth panel oriented, in the on-orbit configuration, respectively, east and west and having a width in the north -south direction (NS width). Each module has a respective aspect ratio of EW width to NS width, a first module (312) is configured with a first aspect ratio, a second module (314) is configured with a second aspect ratio; and the second aspect ratio is substantially larger than the first aspect ratio. At least one antenna reflector (380) is disposed, during launch, proximate to at least one of the first and third panel of the second module.