Dispensing Hinge Assembly for Sequential Spacecraft Deployment
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Solution Overview
Problem
The current tie-down and release mechanisms for launching multiple spacecraft in a stack often result in spacecraft colliding with each other upon release, causing structural damage and performance degradation due to the simultaneous release of tension rods.
Innovation Solution
The use of dis-engageable links in an accordion configuration to hold and dispense spacecraft, where the links engage and disengage based on the angle between adjacent spacecraft to prevent collisions during deployment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If hold-down rods are released simultaneously to dispense the stack of spacecraft, then the deployment speed is improved, but the spacecraft collide with each other causing structural damage and performance degradation
Solution Approach 1:
The tie-down and release mechanism is divided into multiple independent dispensing structures, each responsible for dispensing individual spacecraft or small groups. Each dispensing structure has its own hold-down rods and release mechanisms, allowing sequential rather than simultaneous release of spacecraft throughout the stack.
Solution Approach 2:
The mechanism pre-positions hold-down rods and springs in a loaded state during launch preparation. The springs are compressed and the hold-down rods are tensioned in advance, ready for rapid sequential deployment. This preliminary preparation enables fast deployment while maintaining controlled separation between spacecraft.
2Reliability
If tension rods are highly tensioned to securely hold the spacecraft stack, then the holding reliability is improved, but the force required to release and dispense the spacecraft increases
Solution Approach 1:
Compressed springs are pre-loaded in each dispensing structure to provide cushioning force that assists in rapidly releasing the tensioned hold-down rods. When the release mechanism is activated, these pre-compressed springs expand to push the spacecraft away from the launch vehicle adaptor, reducing the force needed to overcome the highly tensioned hold-down rods.
Solution Approach 2:
The system transitions from a static highly-tensioned state during launch to a dynamic sequential release process. The springs convert stored potential energy into kinetic energy, creating a dynamic release mechanism that rapidly reduces tension forces while maintaining secure holding during launch vibrations and acceleration.
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
This solution allows for the precise control of spacecraft deployment angles, preventing collisions and ensuring the structural integrity and performance of the spacecraft, thereby reducing the risk of damage and degradation.
Implementation Method 1
a spring coupled between the rotatable arm and the second bracket. The spring is configured to apply a force to rotate the rotatable arm around the hinge pin
Data Source
AI summary
Technology is disclosed herein for a payload dispensing hinge assembly. The payload dispensing hinge assembly has a first hinge-half and a second hinge-half that are joined by a hinge pin. The first hinge-half may be connected to a payload that is to be dispensed at a target angle. The second hinge-half may be connected to a payload base. The first hinge-half may have a first mounting bracket and a rotatable arm that are shaped to form interlocks that serve to dis-engageably link these two components. A biasing mechanism rotates the rotatable arm and hence the first mounting bracket and payload about a hinge line. The second hinge-half has a hinge stop that stops the rotation of the rotatable arm at a target angle, whereby the first bracket dis-engages from the rotatable arm to dispense the payload at the target angle.