Satellite Deployment Mechanism Perpendicular Ejection
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Solution Overview
Problem
Existing satellite deployment systems are limited by geometry, particularly when deploying small satellites, as they often require a long axis alignment that restricts the use of space in common berthing mechanisms, limiting the number of satellites that can be deployed from a single spacecraft.
Innovation Solution
A satellite deployment mechanism with an enclosure, lift table, and spring system that ejects satellites perpendicular to the enclosure's plane, allowing for deployment in the limited space of a common berthing mechanism, utilizing previously unused space and enabling multiple satellite deployments without modifying the berthing mechanism.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If satellites are deployed using traditional deployment mechanisms with long axis alignment, then the deployment mechanism can reliably eject satellites, but the geometric constraints limit the number of satellites that can be deployed from a single spacecraft
Solution Approach 1:
The patent changes the deployment direction from traditional long-axis alignment to a perpendicular ejection direction relative to the enclosure face. This dimensional change allows multiple deployment mechanisms to be arranged in a compact configuration within the common berthing mechanism, increasing the number of satellites that can be deployed from a single spacecraft without increasing the overall footprint.
2Productivity
If multiple satellite deployment mechanisms are installed in the common berthing mechanism, then more satellites can be deployed, but the space utilization becomes constrained by geometric limitations
Solution Approach 1:
By orienting the ejection direction perpendicular to the enclosure face rather than along the long axis, the deployment mechanisms can be packed more efficiently within the common berthing mechanism volume. This allows multiple mechanisms to share the limited space without requiring excessive length in any single direction.
Solution Approach 2:
The deployment mechanisms are designed to fit within the existing structural envelope of the common berthing mechanism, utilizing previously unused space. The compact perpendicular ejection geometry allows the mechanisms to be nested or arranged in a space-efficient manner within the constrained volume of the berthing mechanism.
3Productivity
If the deployment mechanism uses a compact perpendicular ejection design, then more satellites can be deployed from limited space, but the mechanism must be attached to existing spacecraft structures without modification
Solution Approach 1:
The mounting system is designed to interface with the universal attachment points and structural features of existing spacecraft, specifically the common berthing mechanism. This universal interface allows the deployment mechanisms to be installed on standard spacecraft platforms without requiring custom modifications, facilitating ease of manufacture and deployment.
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 efficient deployment of multiple small satellites from a single spacecraft by utilizing unused space within the common berthing mechanism, overcoming geometric limitations and reducing costs associated with launching individual satellites.
Implementation Method 1
a spring arranged to apply force to the lift table
Implementation Method 2
a spring arranged to apply force to the lift table
Data Source
AI summary
A method and apparatus for deploying satellites is disclosed a satellite deployment mechanism includes an enclosure having at least one door, a lift table implemented therein, and a spring arranged to apply force to the lift table. A mounting system is arranged to allow for the satellite deployment mechanism to be mounted to a portion of a spacecraft. Responsive to opening the at least one door, the spring may cause the lift table to eject one or more satellites from the enclosure.