Deployable Flexible Solar Array for Microsatellite Volume Constraints
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Solution Overview
Problem
Microsatellites designed as auxiliary payloads face challenges due to limited launch costs and availability, restrictive volume constraints, which result in poor performance due to small solar panels and antennas, leading to ineffective missions, especially for high-energy applications like communication.
Innovation Solution
A deployable microsatellite with a flexible solar array and deployment mechanism that expands to increase surface area, combined with a robotic arm docking mechanism, allowing the satellite to fit within auxiliary payload volume constraints while enhancing power generation and communication capabilities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If rigid solar cells are mounted directly to the satellite body, then the satellite structure is simplified, but the solar panel area and power generation capacity are severely limited
Solution Approach 1:
The patent employs deployable solar panels that transition from a compact stowed configuration during launch to a fully extended operational configuration in orbit. This dynamic transformation allows the solar panels to occupy minimal space during launch while maximizing surface area for power generation once deployed, directly resolving the contradiction between structural simplicity and power generation capacity.
Solution Approach 2:
The solar panels are designed to be nested or folded within the satellite body during launch, similar to a nested doll structure. This nesting approach allows the large-area solar panels to be contained within the limited launch volume while maintaining the ability to expand to full operational size in orbit, thereby achieving both compact stowed volume and large deployed area.
2Power
If rigid deployed solar wings are used, then power generation area is increased, but satellite weight and launch volume requirements increase
Solution Approach 1:
The patent utilizes flexible solar panels with thin-film solar cells that can be folded and compressed into a compact form during launch. These flexible panels maintain their structural integrity when deployed while using significantly less material and weight compared to rigid solar wings, thus achieving high power generation area without proportionally increasing satellite weight.
Solution Approach 2:
The deployable solar panel mechanism allows the system to transition from a low-weight, compact stowed state to a high-area operational state only when needed. This dynamic deployment means the satellite carries the capability for large-area power generation without permanently bearing the weight and volume penalty of fully extended rigid structures throughout the entire mission lifecycle.
3Device complexity
If non-deployment antennas are used, then the satellite structure is simpler, but antenna size and communication throughput are severely limited
Solution Approach 1:
The patent implements deployable antenna structures that remain compact during launch and then extend to full operational size in orbit. This dynamic deployment allows the antenna to achieve large aperture dimensions for high communication throughput while maintaining a small stowed profile that does not compromise satellite structure during launch.
Solution Approach 2:
The antenna elements are designed to be nested or folded within the satellite body during launch, similar to the solar panel approach. This nesting allows the large-area antenna aperture to be contained within the limited launch volume while maintaining the ability to expand to full operational size for high communication throughput.
4Device complexity
If body-mounted solar panels are used, then thermal control is simplified, but heat dissipation capability is reduced
Solution Approach 1:
The deployable solar panel structure provides dynamic thermal management by allowing the panels to be positioned or oriented to maximize heat dissipation to space. When deployed, the large surface area of the solar panels can radiate heat effectively, and their positioning can be adjusted to optimize thermal control, thereby improving heat dissipation capability while maintaining relatively simple thermal control systems.
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 significant performance improvements by increasing solar array area and antenna size, enabling higher power output and effective communication, while maintaining low volume and weight within auxiliary payload limits, thus facilitating frequent and cost-effective access to orbit.
Implementation Method 1
a first spring sheet metal frame which is in a compressed condition while wound around the satellite body so as to move to a natural position which is the deployed position on initiation of a deployment process
Implementation Method 2
at least one second spring which is compressed against the body in the stowed position, to deploy from the panel surface in order to enlarge the bending moment of inertia
Data Source
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AI summary
Micro satellite is disclosed with foldable solar panels that may be winded around the body of the micro satellite so that the growth in outer dimensions of the satellite is no more than 10-20 mm along each one of the length, width and height of the microsatellite so that the micro satellite may be launched in an auxiliary payload volume of a launcher. The foldable solar panels may be deployed to employ area that exceeds 9 times the product of the length by the width of the satellite and 6 times the product of the height by the length. The solar power produced by the solar panel and their light weight enable carrying of cargo that is at least 0.6 of the of the total mass of the satellites.