Satellite Deployment Adaptor with Segmented Plates
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Solution Overview
Problem
Current satellite deployment adaptor systems are complex, costly, and often limited to specific launch vehicles, posing challenges in safe and reliable satellite release, with components exposed to damage and increasing the cost due to additional components attached to the satellite.
Innovation Solution
A two-part adaptor system with a dispenser plate staying with the launch vehicle and a mounting plate that separates with the satellite, featuring an actuator-release mechanism, bend/shear restraint assembly, and biasing element for safe and reliable satellite separation, along with an optional shroud for enhanced safety and security.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional adaptor systems are used for satellite deployment, then reliable satellite release can be achieved, but the system becomes complex and costly
Solution Approach 1:
The adaptor system is divided into two separate parts: a launch vehicle adaptor plate that remains with the launch vehicle and a satellite mounting plate that separates with the satellite. This segmentation simplifies the overall system by eliminating the need for a single complex integrated adaptor structure, while maintaining reliable separation through the actuator-release mechanism assembly.
Solution Approach 2:
The release mechanism and mounting functionality are extracted from a complex integrated adaptor and distributed across two simpler plates connected by the actuator-release mechanism. This extraction reduces the complexity of individual components while maintaining the critical separation function.
2Reliability
If traditional adaptor systems are used, then satellite deployment can be achieved, but the cost increases due to additional components
Solution Approach 1:
By segmenting the adaptor into two separate plates, each plate can be manufactured independently using simpler, more cost-effective processes. The separation of functions allows for optimized manufacturing of each component without the need for complex integrated structures, reducing overall production costs.
Solution Approach 2:
The launch vehicle adaptor plate remains with the launch vehicle and is not recovered with the satellite, eliminating the need for expensive recovery and reuse operations for this component. Only the satellite mounting plate travels with the satellite, reducing the total cost of adaptor system recovery and storage.
3Reliability
If adaptor systems are configured for specific launch vehicles, then reliable integration is achieved, but versatility is limited
Solution Approach 1:
The adaptor system is designed with universal interfaces and standardized mounting patterns that can accommodate multiple launch vehicle types. The actuator-release mechanism assembly and biasing element configuration can be adjusted to work with different launch vehicles, enabling a single adaptor design to serve multiple platforms.
Solution Approach 2:
The system incorporates adjustable and reconfigurable components that can be dynamically adapted to different launch vehicle configurations. The biasing element and actuator-release mechanism can be configured for different separation requirements, allowing the same basic adaptor structure to serve multiple launch vehicles.
4Productivity
If components are exposed during separation, then deployment can be conducted, but damage risk increases
Solution Approach 1:
The biasing element is pre-configured to provide controlled separation force that cushions the separation process. This predetermined cushioning force ensures smooth, controlled separation that protects components from impact damage while maintaining efficient deployment timing.
Solution Approach 2:
The actuator-release mechanism assembly serves as an intermediary between the launch vehicle adaptor plate and satellite mounting plate. This intermediary mechanism provides a controlled, protected interface for separation, shielding the satellite components from direct exposure to potentially damaging forces during the separation process.
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 provides a simple, reliable, and cost-effective means for satellite integration and deployment across various launch vehicles, enabling flexible and scalable satellite launches with reduced risk of damage and increased efficiency.
Implementation Method 1
a biasing element configured to provide a configurable force 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
Implementation Method 2
a bend/shear restraint assembly configured to handle in-plane load while releasably coupling the space vehicle separation plate to the launch vehicle adaptor plate
Data Source
AI summary
An adaptor system includes 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 for release of the space vehicle from the launch vehicle, an actuator release mechanism assembly, a bend/shear restrain assembly that is non-coaxial with the actuator-release connector, and a biasing element. The actuator-release mechanism assembly may be configured to separably couple the space vehicle separation plate to the launch vehicle adaptor plate. The actuator-release mechanism assembly may pass through the launch vehicle adaptor plate to engage the space vehicle separation plate to hold the space vehicle separation plate substantially parallel to the launch vehicle adaptor plate prior to release of the space vehicle separation plate.