Stackable Plate Satellite Design for Launch Volume Optimization
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Solution Overview
Problem
Current satellite deployment technologies face challenges in efficiently utilizing launch vehicle capacity due to volume and mass limitations, particularly for CubeSats, which restrict the number of satellites that can be launched and deployed in multiple orbital planes, and do not fully leverage the capabilities of smaller launch vehicles.
Innovation Solution
A satellite and deployer design featuring a structural plate with a thickness smaller than its width, allowing for stacking and distribution of launch loads across multiple satellites, with contact points for secure stacking and deployment, and incorporating a deployer that holds the stack during launch and releases satellites individually in orbit.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If CubeSats are launched as rideshare payloads on large launch vehicles, then the cost per satellite is reduced, but the number of satellites that can be deployed in multiple orbital planes is limited
Solution Approach 1:
The launch vehicle interface is segmented into multiple independent satellite interfaces, allowing multiple satellites to be launched simultaneously in different orbital planes. Each satellite has its own interface and deployment mechanism, enabling parallel deployment operations without interference.
Solution Approach 2:
The system transitions from deploying satellites in a single orbital plane to multi-orbital-plane deployment by adding the orbital plane dimension to the deployment architecture. This allows satellites to be distributed across multiple inclined orbital planes from a single launch vehicle.
2Quantity of substance
If the number of satellites in a constellation is increased to fill launch vehicle capacity, then the economic viability improves, but the volume and mass constraints of CubeSats limit the number of satellites per launch
Solution Approach 1:
The satellite design is segmented into a modular plate structure that can be stacked with other identical plates. This segmentation allows multiple satellites to be compactly arranged in the launch vehicle payload volume, maximizing the number of satellites per launch.
Solution Approach 2:
The satellite uses a thin plate structure with deployable solar panels and antennas. The thin-profile design minimizes the volume occupied during launch, while deployable surfaces provide the necessary functional area in orbit.
3Ease of manufacture
If CubeSats use a standardized box design, then manufacturing is simplified and costs are reduced, but the ability to distribute satellites across multiple orbital planes is hindered
Solution Approach 1:
The standardized satellite is segmented into a plate design with defined attachment interfaces. These interfaces enable the satellites to be stacked and oriented in different configurations, allowing adaptation to multi-orbital-plane deployment requirements while maintaining manufacturing simplicity.
Solution Approach 2:
The plate design serves multiple functions: it provides a standardized manufacturing form, enables compact stacking for volume efficiency, and offers configurable orientation for different orbital plane deployments. The universal interface allows the same design to be used across various deployment scenarios.
4Weight of moving object
If the satellite mass is reduced to fit CubeSat constraints, then more satellites can be launched, but the structural integrity and load distribution capability are compromised
Solution Approach 1:
The satellite structure uses composite materials that provide high strength-to-weight ratio. This allows the satellite to maintain structural integrity and load distribution capability while keeping the mass low enough to fit CubeSat constraints and maximize the number of satellites per launch.
Data Source
AI summary
An apparatus includes a satellite in the form of a plate having a thickness being smaller than a width of the satellite. The apparatus also includes a plurality of contact points distributed on a face of the satellite, allowing for one or more additional satellites to be stacked upon the satellite.