Resettable Shockless Hold-Down Release Mechanism for Spacecraft
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Solution Overview
Problem
Existing Hold Down and Release Mechanisms (HDRMs) for spacecraft components face challenges in releasing components with minimal mechanical shock, as they often result in significant shocks due to rapid tension release, and require consumable parts that need replacement after each release cycle, limiting testing and reliability.
Innovation Solution
The Actuated Resettable Shockless (AReS) HDRM employs actuator-driven sliding wedges to provide a structural connection that can be released without mechanical shock, allowing for repeated resetting without damaging or consuming any components, enabling reliable and tested preloaded connections.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If existing HDRMs release tension quickly to enable component release, then release speed is improved, but mechanical shock increases
Solution Approach 1:
The patent applies beforehand cushioning by introducing a damping element that is pre-positioned to absorb shock during release. The damping element is installed in advance and actively cushions the mechanical shock when the hold-down mechanism releases the component, preventing the harmful shock effects without compromising release speed.
Solution Approach 2:
The patent uses an intermediary approach by introducing a damping element as a mediator between the release mechanism and the secured component. This intermediary element absorbs and dissipates the mechanical shock energy, allowing quick release while protecting the component from harmful shock forces.
2Ease of operation
If consumable parts are used in HDRM release mechanism, then release function is achieved, but reliability decreases due to untested components after launch
Solution Approach 1:
The patent applies self-service by designing a release mechanism where the damping element serves multiple functions: it cushions shock during release and simultaneously acts as a sacrificial consumable component that can be replaced during routine maintenance. This self-service approach allows the critical damping function to be tested and validated before launch while maintaining operational reliability.
Solution Approach 2:
The patent implements discarding and recovering by designing the damping element as a replaceable consumable component. After the damping element has served its purpose of cushioning shock during release operations, it can be discarded and replaced with a fresh, tested component during maintenance cycles, ensuring reliability for subsequent missions.
3Object-affected harmful factors
If structural robustness is increased to mitigate shock damage, then shock resistance is improved, but spacecraft mass increases
Solution Approach 1:
The patent applies taking out by extracting the shock mitigation function from the main structural components and placing it in a dedicated, localized damping element. This allows the primary spacecraft structure to remain lightweight while the specific shock protection function is handled by a separate, optimized component that can be precisely sized and positioned only where needed.
Solution Approach 2:
The patent implements local quality by concentrating shock mitigation capabilities in a localized damping element at the specific interface where shock occurs during release, rather than reinforcing the entire spacecraft structure. This localized approach provides necessary shock resistance only where required, minimizing overall mass increase.
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 AReS HDRM achieves shockless release and resettable functionality, enhancing reliability and reducing mass by eliminating the need for consumable parts, allowing for pre-flight testing of critical components and repeated securement with consistent structural integrity.
Implementation Method 1
The present disclosure relates to a resettable mechanism for releasably securing components of a spacecraft together during launch until such time as the mechanism is commanded to release those components. Upon command, the components are then released with extremely low shock forces being transmitted to the previously secured components due to the release.
Data Source
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AI summary
The present disclosure relates to a mechanism for releasably securing components of a spacecraft together during launch until such time as the mechanism is commanded to release those components. Upon command, the components are then released with extremely low shock forces being transmitted to the previously secured components due to the release.