Satellite Release System Using Segmented Plates and Biasing Elements
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Solution Overview
Problem
Current satellite release systems are complex, costly, and often limited to specific launch vehicles, with components exposed to damage and increasing the mass, volume, and cost of satellites, while lacking flexibility and reliability in separation mechanisms.
Innovation Solution
A two-part release system comprising a launch vehicle adaptor plate and a space vehicle separation plate, using a linear Marman-style clamp assembly and biasing elements for reliable and efficient separation, with optional shroud protection for environmental and electromagnetic interference.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a traditional release system is used, then satellite separation can be achieved, but the system becomes complex and costly
Solution Approach 1:
The release system is divided into two separate components: a launch vehicle adaptor plate that remains on the launch vehicle, and a flyaway plate that attaches to the satellite. This segmentation allows each component to be optimized independently, reducing overall system complexity while maintaining separation reliability.
Solution Approach 2:
The release mechanism is extracted from the satellite itself and placed on the launch vehicle adaptor plate. This removes the complexity of the release system from the satellite, reducing satellite mass and complexity while the launch vehicle side handles the separation function.
2Reliability
If a traditional release system is used, then satellite separation can be achieved, but the cost increases
Solution Approach 1:
The flyaway plate is designed as a disposable component that is discarded after separation. This allows the use of simpler, lower-cost materials and manufacturing methods for the flyaway plate, reducing overall system cost while maintaining reliable separation functionality.
Solution Approach 2:
The launch vehicle adaptor plate is designed with universal interfaces that can accommodate multiple different satellite types and mission requirements. This multi-functionality reduces the need for custom-designed release systems for each mission, lowering manufacturing costs through standardization.
3Reliability
If a traditional release system is used, then satellite separation can be achieved, but the satellite mass increases
Solution Approach 1:
The release mechanism is extracted from the satellite and placed on the launch vehicle adaptor plate. This removes the mass of the release system from the satellite, directly reducing satellite mass while the launch vehicle side absorbs the weight of the separation mechanism.
Solution Approach 2:
The flyaway plate is designed as a lightweight disposable component with minimal mass. Since it is discarded after separation, its mass does not need to be recovered, allowing for optimized lightweight design that reduces satellite mass while maintaining separation reliability.
4Reliability
If a traditional release system is used, then satellite separation can be achieved, but the satellite volume increases
Solution Approach 1:
The release system components are extracted from the satellite body and placed on the launch vehicle adaptor plate. This removes the volume occupied by release mechanism components from the satellite, reducing satellite volume while maintaining separation functionality.
Solution Approach 2:
The flyaway plate is designed as a thin, lightweight disposable component with minimal volume. Its temporary nature allows for optimized compact design that reduces satellite volume while providing reliable separation when needed.
5Reliability
If a traditional release system is used, then satellite separation can be achieved, but the system lacks flexibility for different launch vehicles
Solution Approach 1:
The launch vehicle adaptor plate is designed with universal interfaces and standardized mounting features that can accommodate multiple different launch vehicle types. This multi-functionality allows the same adaptor plate design to work across different launch vehicles, providing flexibility and adaptability while maintaining reliable separation.
Solution Approach 2:
The release system is segmented into modular components with standardized interfaces. This modularity allows different combinations of adaptor plates and flyaway plates to be configured for different launch vehicle and satellite combinations, enhancing system flexibility and adaptability.
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 system provides a simple, reliable, and flexible means for satellite separation from launch vehicles, reducing costs and mass, while ensuring safe and controlled release, and enabling mixed topology launches across various launch vehicles.
Implementation Method 1
The biasing element assembly may be configured to provide a configurable force in a first direction normal to a surface of the launch vehicle adaptor plate to separate the space vehicle separation plate from the launch vehicle adaptor plate
Implementation Method 2
The actuator-release mechanism assembly may comprise a clamp assembly configured to clamp an edge of the space vehicle separation plate together with an edge of launch vehicle adaptor plate to fix a surface of the space vehicle separation plate in proximity to a surface of the launch vehicle adaptor plate
Data Source
AI summary
A release system may include a space vehicle separation plate operably coupled to a space vehicle, a launch vehicle adaptor plate operably coupled to a launch vehicle capable of carrying the space vehicle into space or into a ballistic (non-orbital) trajectory for release of the space vehicle from the launch vehicle, an actuator release mechanism assembly and a biasing element assembly. The actuator release mechanism assembly may be configured to separably couple the space vehicle separation plate to the launch vehicle adaptor plate. The biasing element assembly may be configured to provide a configurable force in a first direction normal to a surface of the launch vehicle adaptor plate to separate the space vehicle separation plate from the launch vehicle adaptor plate when the actuator-release mechanism assembly is triggered to release the space vehicle separation plate from the launch vehicle adaptor plate.