Spin Ejection Mechanism for Reduced Tip-Off and Lateral Velocity
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Solution Overview
Problem
Existing payload ejection systems from extraterrestrial surfaces require significant material mass and volume, and precise timing of multiple release mechanisms, which can lead to failure due to misfire or mistiming, causing undesired forces on the payload.
Innovation Solution
A spin ejection mechanism using a first and second bracket with guide mechanisms, releasable and spring-loaded lock mechanisms, and a spring assembly to achieve controlled translational and rotational motion of the payload without simultaneous release of multiple Hold Down Release Mechanisms (HDRMs).
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple release mechanisms are used to deploy payloads, then the payload can be securely held during launch, but the system requires precise timing and significant material mass
Solution Approach 1:
The patent combines multiple release mechanisms into a single integrated mechanism that simultaneously releases multiple hold-down points. The single release mechanism includes a lever that, when actuated, releases all payload constraints at once, eliminating the need for multiple independent release mechanisms and their associated timing requirements.
Solution Approach 2:
The release mechanism is segmented into multiple independent but synchronized components. The lever system is divided into multiple arms or segments that each engage with different hold-down points, allowing a single actuation to produce multiple simultaneous release actions without requiring complex timing coordination.
2Force
If multiple release mechanisms are used simultaneously, then the payload can be deployed with controlled forces, but misfire or mistiming causes undesired forces on the payload
Solution Approach 1:
The mechanism pre-positions all release components in a ready state before deployment, with the lever system already engaged with all hold-down points. This preliminary configuration ensures that when the single release mechanism is actuated, all components are synchronized and ready to release simultaneously, eliminating timing errors and ensuring controlled force application.
3Productivity
If traditional ejection systems are used, then payloads can be deployed from extraterrestrial surfaces, but the systems require significant material mass and volume
Solution Approach 1:
The patent extracts and eliminates unnecessary components from traditional ejection systems, retaining only the essential elements needed for payload deployment. By using a single release mechanism instead of multiple complex systems, and by optimizing the spring-loaded ejection components, the overall mass and volume of the ejection system is significantly reduced while maintaining deployment capability.
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 precise and reliable deployment of payloads with reduced tip-off and lateral velocity, ensuring predictable axial velocity and spin rate by sequentially releasing lock mechanisms, reducing the need for precise timing.
Implementation Method 1
a spring assembly operably coupled between the first bracket and one of the at least one second bracket in a compressed position. The spring assembly is configured to move to an expanded position upon release of the spring-loaded lock mechanism and is configured to propel the at least one second bracket as the spring assembly moves to the expanded position.
Data Source
AI summary
A spin ejection mechanism and a method of launching objects from extraterrestrial sites is disclosed. The mechanism includes a first bracket. At least one second bracket is spaced apart from the first bracket. At least one guide mechanism is operably coupled between the first bracket and one of the at least one second brackets. The at least one guide mechanism is configured to axially restrain the second bracket. At least one releasable lock mechanism is operably coupled to the at least one second bracket and configured to initiate restrained movement of one of the at least one guide mechanism. A spring-loaded lock mechanism is coupled to the first bracket and configured to initiate unrestrained movement of the at least one guide mechanism.