Reflector Satellite Assembly for Precise Large-Aperture Beam Pointing
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Solution Overview
Problem
Satellites face challenges in achieving high gain and precise directivity of radio frequency radiation due to limitations in the size of reflectors, which are typically capped at 20 meters in diameter, making it difficult to meet increasing performance requirements while maintaining precise pointing angles.
Innovation Solution
A satellite assembly comprising a reflector satellite and a source satellite, where the reflector satellite has a diameter greater than 50 meters, with a simplified mechanical architecture and controlled positioning and orientation systems, including articulations, telescopic masts, and reaction wheels, allowing for precise pointing and compensation of disturbances without a physical mechanical link.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If the reflector diameter is increased to improve gain and directivity, then the antenna performance is improved, but the mechanical complexity and deployment difficulty increase significantly
Solution Approach 1:
The patent divides the single-satellite antenna system into two separate satellites: a source satellite carrying the radiofrequency source and a reflector satellite carrying the large reflector. This segmentation allows each satellite to be independently designed and deployed, avoiding the mechanical complexity of deploying a single satellite with both components while maintaining the benefits of a large reflector diameter for improved pointing precision and antenna gain.
Solution Approach 2:
The patent introduces a wireless communication link as an intermediary between the source satellite and reflector satellite to maintain their relative positioning. Instead of using complex mechanical connections for positioning, the system uses radiofrequency communication and control signals to coordinate the two satellites, significantly reducing mechanical complexity while maintaining precise pointing capability.
2Measurement precision
If the reflector diameter is increased to exceed 50 meters to meet performance requirements, then the antenna gain is improved, but the launch and deployment complexity increase
Solution Approach 1:
By segmenting the antenna system into two separate satellites, the patent enables the reflector to be launched in a folded or compact state on the reflector satellite while the source satellite carries the radiofrequency source. The two satellites are deployed independently and positioned relative to each other through wireless control, avoiding the need to launch and deploy a single complex integrated structure with a 50+ meter diameter reflector.
Solution Approach 2:
The patent employs dynamic positioning and orientation systems on both satellites, including articulations, telescopic masts, and reaction wheels, that allow the satellites to adjust their relative positions and orientations in orbit. This dynamic adjustment capability enables the system to achieve and maintain the required antenna gain and pointing precision after deployment, while the satellites themselves can be manufactured and launched in more manageable configurations.
3Stability of the object's composition
If a mechanical link is used to maintain relative position between source and reflector, then positioning stability is improved, but the system flexibility and complexity increase
Solution Approach 1:
The patent replaces the mechanical link system with a wireless control system that uses radiofrequency communication between the source satellite and reflector satellite. The relative positioning is maintained through active control using thrusters, reaction wheels, and articulations on each satellite, coordinated via wireless signals. This substitution eliminates the need for complex mechanical connections while maintaining positioning stability through active control mechanisms.
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
Enables increased pointing precision and robustness, reduces power requirements, and enhances flexibility, allowing for larger reflector diameters while simplifying the mechanical structure and facilitating different mission applications.
Implementation Method 1
a reflection surface 44t adapted to reflect radiofrequency waves
Implementation Method 2
each positioning and orientation system includes at least one reaction wheel, the reaction wheels being controlled to at least partially compensate for attitude perturbations
Implementation Method 3
the supporting structure comprises at least one articulation and/or at least one telescopic mast for deploying the positioning and orientation systems and extending a canvas forming said reflection surface
Data Source
Figure 1~2
Figure 3~4
Figure 5~6a
AI summary
The invention relates to a reflective satellite (1) comprising at least one curved reflection surface (11), the satellite (1) being characterised in that it comprises at least one load-bearing structure (10) connected to at least four positioning and orientation systems (12) for controlling the attitude and the orbit of the reflective satellite, said positioning and orientation systems comprising at least one thruster system, said positioning and orientation systems being synchronised and arranged so as to allow orientation of the reflector satellite relative to at least two axes of rotation. A satellite assembly including a source satellite and a reflective satellite is also disclosed.