Payload-Centric Satellite Antenna Configuration
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Solution Overview
Problem
The cost of launching satellites increases with the size and mass of the satellite, particularly due to the need for larger antenna apertures, which traditionally require larger launch vehicles, resulting in higher costs and reduced efficiency.
Innovation Solution
A payload-centric satellite configuration where the large antenna aperture is positioned at the center, with spacecraft support functions attached to the periphery, allowing for a smaller launch vehicle and reduced stowed size while maintaining a larger antenna aperture, achieved through a deployable truss structure and distributed equipment compartments.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If the satellite uses a larger antenna aperture to improve communications performance, then the antenna gain and data rate increase, but the satellite diameter and mass increase, requiring larger and more expensive launch vehicles
Solution Approach 1:
The satellite is divided into two functional segments: a compact bus section containing all spacecraft support functions (power, propulsion, control) and a separate deployable antenna aperture section. This segmentation allows the antenna to be launched in a compact, stowed configuration within the satellite bus, then deployed in orbit to achieve the required large aperture for high gain communications without increasing the launch vehicle size requirement
Solution Approach 2:
The antenna aperture transitions from a static, fixed-size structure to a dynamic, deployable structure. The antenna is stowed in a compact configuration during launch to minimize satellite diameter and mass, then deployed in orbit to achieve the large aperture needed for high antenna gain. This dynamic transformation resolves the contradiction between launch constraints and operational performance
2Productivity
If the satellite uses a larger antenna aperture to increase data rate, then the communications capacity increases, but the launch vehicle size and cost increase
Solution Approach 1:
The large antenna aperture is nested within the compact satellite bus during launch, similar to a nested doll structure. The antenna aperture is stowed inside the fairing along with the bus, allowing the entire satellite to fit within standard launch vehicle dimensions. Once in orbit, the antenna deploys outward from the bus to achieve the large aperture required for high data rate communications without requiring a larger launch vehicle
3Ease of operation
If the satellite is configured with traditional vehicle-support-centric arrangement, then the support functions are easily accessible, but the antenna aperture size is limited by launch vehicle constraints
Solution Approach 1:
The traditional satellite configuration is inverted: instead of placing the antenna on the periphery with support functions in the center, this design places the large antenna aperture at the center and distributes the support functions around it. The bus containing power, propulsion, and control systems is positioned peripherally, allowing both excellent accessibility to support functions and maximum antenna aperture area within the same launch constraints
Data Source
Figure 1A
Figure 1B
Figure 2~3
AI summary
In one aspect, a space vehicle includes a structure configured to expand from a first configuration to a second configuration and at least two equipment compartments attached to the periphery of the structure. The structure includes at least one of an antenna mesh, a light-shielding mesh, an optical reflector mesh and a net. In another aspect, a space vehicle includes an antenna structure configured to expand from a first configuration to a second configuration and at least two equipment compartments attached to the periphery of the antenna structure. At least one of the at least two equipment components include a solar panel, a propulsion system and an antenna feed.