Accordion Spacecraft Dispensing to Prevent Release Collisions
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Solution Overview
Problem
The existing tie-down and release mechanisms for launching multiple spacecraft result in collisions and structural damage due to simultaneous release, which can degrade performance and damage sensitive equipment.
Innovation Solution
A system using dis-engageable links and payload dispensing hinge assemblies to hold spacecraft in an accordion configuration, allowing controlled separation and deployment at precise angles to prevent collisions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If hold-down rods are released simultaneously to dispense the stack of spacecraft, then the entire stack is released at once, but spacecraft bump into each other causing structural damage and performance degradation
Solution Approach 1:
The patent divides the simultaneous release of the entire spacecraft stack into sequential individual releases. Each spacecraft is equipped with its own hold-down rod that can be released independently, transforming one collective action into multiple discrete actions occurring at different times. This segmentation prevents collisions while maintaining efficient deployment.
Solution Approach 2:
The patent introduces dynamic control over the release sequence, allowing the system to adjust the timing and order of spacecraft dispensing based on real-time conditions. The hold-down rods are released in a controlled sequence rather than statically all at once, enabling adaptive management of the deployment process to prevent collisions.
2Device complexity
If hold-down rods are released simultaneously, then the release mechanism is simple, but the spacecraft collide and cause structural damage
Solution Approach 1:
The release mechanism is segmented into multiple independent control units, each managing a specific hold-down rod. This segmentation increases control capability while keeping each individual control unit relatively simple, avoiding the need for complex centralized control systems.
Solution Approach 2:
Each spacecraft effectively manages its own release through its dedicated hold-down rod, with the system automatically coordinating the sequence. This self-service approach reduces the complexity of external control mechanisms while ensuring safe deployment.
3Quantity of substance
If spacecraft are dispensed in a stack configuration, then multiple spacecraft can be launched with one vehicle, but sensitive equipment is damaged due to bumping
Solution Approach 1:
The patent segments the deployment process into individual spacecraft releases rather than collective dispensing. This allows multiple spacecraft to be launched in sequence from the same vehicle, maintaining the quantity advantage while eliminating the harmful collision effects through temporal separation of release events.
Solution Approach 2:
The system performs preliminary positioning and sequencing before the actual release. Each spacecraft is prepared and positioned in advance with its own release mechanism, ensuring that when deployment occurs, the spacecraft are released in a pre-planned sequence that prevents collisions and protects sensitive equipment.
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
Prevents spacecraft collisions and maintains performance by ensuring controlled deployment of spacecraft, reducing structural damage and equipment degradation.
Implementation Method 1
The payload dispensing hinge assembly includes a spring configured to apply a force to rotate the rotatable arm around the hinge pin
Implementation Method 2
The payload dispensing hinge assembly includes a spring configured to apply a force to rotate the rotatable arm around the hinge pin
Data Source
AI summary
Technology is disclosed herein for dispensing stacked spacecraft. A stack of spacecraft may be joined together in an accordion configuration by dis-engageable links. A dis-engageable link may join two adjacent spacecraft at one edge of the spacecraft. Some of the links are on one side of the stack with other links on an opposite side of the stack to provide the accordion configuration. After the tie-down mechanism releases the stack of spacecraft from a launch adaptor the stack unfolds. Initially, the dis-engageable links continue to hold the spacecraft together in the accordion configuration with the angle between each pair of adjacent spacecraft increasing. After a pair of adjacent spacecraft have unfolded a sufficient amount to prevent collision, the dis-engageable links release one of the spacecraft to thereby dispense the spacecraft.