Deployable Reflector Antenna Layout for Imaging Microsatellites
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Solution Overview
Problem
Microsatellites face challenges in incorporating high-gain antenna systems due to size and mass constraints, which limits data transmission rates and antenna gain, while also needing to accommodate imaging systems without increasing complexity or cost.
Innovation Solution
An integrated reflector antenna system is designed to fit within the microsatellite body without obstructing the imaging system, with a movable door mechanism that deploys the antenna system to provide a high gain and data transmission rate within the allocated size and frequency band, using a paraboloid reflector and antenna feed support to optimize gain and transmission rates.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a large antenna system is incorporated to achieve high data transmission rates, then the data transmission rate is improved, but the size and mass of the microsatellite increases
Solution Approach 1:
The antenna system is designed to be deployable, transitioning from a compact stowed configuration during launch to a deployed operational configuration in orbit. The reflector and feed assembly can extend outward from the satellite body, providing a large effective aperture for high-gain communication without permanently increasing the satellite's mass or launch volume requirements.
Solution Approach 2:
The antenna system is nested within the satellite body during launch, with the reflector and feed structure folded or retracted into the limited space available. This allows the large antenna to be accommodated within the compact microsatellite form factor while maintaining high data transmission capability when deployed.
2Power
If a large antenna system is incorporated to achieve high antenna gain, then the antenna gain is improved, but the volume available for imaging system is reduced
Solution Approach 1:
The antenna system utilizes deployable structures that extend from the satellite body, allowing high-gain performance without permanently occupying internal volume. The reflector can be positioned externally or on the satellite surface when deployed, preserving internal space for imaging instruments while achieving the required antenna gain for high data transmission rates.
3Productivity
If the antenna system is configured to maximize data transmission rate, then the data transmission rate is improved, but the system complexity increases
Solution Approach 1:
The antenna system is integrated with the satellite body structure, where the reflector may be formed from or attached to existing satellite surfaces or booms. This merging approach reduces the number of separate components and assembly steps, achieving high data transmission capability without proportionally increasing system complexity.
4Adaptability or versatility
If a deployable door mechanism is used to accommodate both antenna and imaging system, then the adaptability is improved, but the device complexity increases
Solution Approach 1:
The door or access panel serves multiple functions: it provides structural closure for the satellite body, serves as a mounting surface for the antenna reflector, and can be opened to allow imaging system access to the external field of view. This multi-functionality reduces the need for separate mechanisms for each function, achieving configuration flexibility without proportionally increasing complexity.
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
The solution enables microsatellites to achieve data transmission rates between 1 Mbit/s and 100 Mbit/s with an antenna gain of at least 25 dBi, while maintaining a compact form factor and unobstructed imaging capabilities, suitable for launch as a secondary payload.
Implementation Method 1
using a paraboloid reflector and antenna feed support to optimize gain and transmission rates
Data Source
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AI summary
Examples of imaging microsatellites are described that have an imaging system and antenna system disposed within the microsatellite body when the microsatellite is in a non-deployed state. The properties of the antenna system can be adjusted such that the antenna system does not impact, contact, or displace the imaging system when the microsatellite is in the non-deployed state. The properties of the antenna system can be adjusted such that the antenna system does not contact or impact the body of the microsatellite or any other structure when the microsatellite transitions to a deployed state. The antenna system can be configured to achieve a desired gain and/or data transmission rate by adjusting properties of the antenna system based on the radiation pattern of an antenna feed and geometric constraints imposed by the imaging system. Examples of methods for designing such imaging microsatellites are provided.