Miniaturized Satellite Double Reflector Antenna Design
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Solution Overview
Problem
Reflector antennas for miniaturized satellites face challenges in achieving compactness and lightweight designs while maintaining performance, particularly due to the large volume and complexity of double-reflector systems, which can lead to issues with size constraints and radiation efficiency.
Innovation Solution
A compact electromagnetic system is designed using a primary reflector with a concave shape and a secondary reflector with a convex shape, where the secondary reflector is placed along the symmetry axis, optimizing the focal ratio (f/D) between 0.15 and 0.25 to minimize volume and ensure efficient radiation focusing within the constraints of a miniaturized satellite.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a double-reflector antenna system (Cassegrain or Gregorian) is used to achieve compact design, then the focal point can be positioned conveniently within the spacecraft, but the overall volume and complexity of the system increases
Solution Approach 1:
The patent inverts the conventional double-reflector configuration by placing the secondary reflector between the primary reflector and its focal point, rather than beyond the focal point. This inversion allows the final focal point to be positioned behind the primary reflector, enabling compact integration within CubeSat dimensions while maintaining the benefits of dual-reflector focusing
Solution Approach 2:
The patent nests the secondary reflector within the volume defined by the primary reflector's aperture plane and surface, placing it in the space between the primary reflector and its focal point. This nested arrangement allows both reflectors to occupy minimal space while achieving the desired focusing capability
2Volume of stationary object
If the secondary reflector is placed close to the primary reflector to minimize volume, then compactness is achieved, but the focal ratio optimization becomes more challenging
Solution Approach 1:
The patent optimizes the focal ratio (f/D) to a specific range of 0.15-0.25, representing a significant parameter change from conventional designs. This optimized focal ratio, combined with the inverted configuration, enables compact volume while maintaining focusing performance and simplifying the design space
3Ease of manufacture
If a conventional Cassegrain configuration is used with the secondary reflector beyond the focal point, then the design is straightforward, but the system volume is larger than necessary
Solution Approach 1:
The patent inverts the conventional Cassegrain configuration by placing the secondary reflector between the primary reflector and its focal point, rather than beyond the focal point as in traditional designs. This inversion reduces the overall system volume while maintaining the dual-reflector focusing capability
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 allows for a more compact and efficient antenna system that effectively focuses electromagnetic waves, reducing the overall size and maintaining performance, while ensuring stability and accuracy of the secondary reflector placement within the satellite's limited space.
Implementation Method 1
incident electromagnetic waves are reflected by the primary reflector to generate primary reflected waves
Implementation Method 2
the primary reflected waves are then reflected by the secondary reflector, thereby generating secondary reflected waves focusing at a target point located behind the primary reflector
Data Source
AI summary
Double reflector electromagnetic systems implementable in miniaturized satellites and other applications for compact, light weight, and broadband antennas. The disclosed methods and devices include primary and secondary reflectors, where the secondary reflector is held in the aperture plane of the primary reflector to minimize required space. A specific Cassegrain configuration is also described.