Spacecraft Separation Locking Structure for Peak Shock Attenuation

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Solution Overview

Problem

Separation devices for spacecraft and launchers generate high shock levels due to internal locking device impacts, posing a risk to thin and lightweight constructions, especially in smaller spacecraft with restricted packing volumes.

Innovation Solution

A separation device with a dampening arrangement that includes a dampening plate and pins to absorb energy, combined with sequential initiator units for controlled energy release, attenuating peak loads and ensuring secure separation while allowing for lightweight construction.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Weight of moving object

If the locking device is made lightweight to reduce overall spacecraft weight, then weight is reduced, but the construction safety margins become thinner and more vulnerable to shock damage

Engineering Contradiction:

Improveweight of separation deviceVSAvoidconstruction safety margins

Core Design Contradiction:

Weight of moving objectVSStrength

Solution Approach 1:

A dampening arrangement with a dampening element is integrated into the locking device to absorb shock energy before it can damage the lightweight construction. The dampening element is positioned to receive impact from the locking device during separation, providing protective cushioning in advance of any potential damage to the thin-walled housing portions.

Inventive Principle:

Principle #11Beforehand cushioning (Prior cushioning)

2Reliability

If high pressure fluid is used to move the locking device for reliable separation, then separation reliability is improved, but shock peaks are generated that can damage the lightweight construction

Engineering Contradiction:

Improveseparation reliabilityVSAvoidshock peaks

Core Design Contradiction:

ReliabilityVSObject-affected harmful factors

Solution Approach 1:

The dampening element serves as an intermediary between the high pressure fluid actuation system and the lightweight housing portions. It mediates the energy transfer by absorbing excess shock peaks generated during the separation process, allowing the high pressure fluid to reliably move the locking device while protecting the vulnerable construction from damage.

Inventive Principle:

Principle #24Intermediary (Mediator)

3Volume of moving object

If the spacecraft is made smaller to reduce launch costs, then launch costs are reduced, but the distance between the shock source and sensitive equipment decreases, increasing vulnerability to shock damage

Engineering Contradiction:

Improvespacecraft volumeVSAvoidshock exposure to sensitive equipment

Core Design Contradiction:

Volume of moving objectVSObject-affected harmful factors

Solution Approach 1:

The dampening arrangement converts the harmful shock energy generated during separation into beneficial energy absorption. By placing the dampening element within the compact spacecraft structure, it absorbs the shock peaks close to their source, preventing them from reaching sensitive equipment. This allows smaller spacecraft to achieve reliable separation without increased vulnerability to shock damage.

Inventive Principle:

Principle #22Blessing in disguise (Convert harm into benefit)

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 effectively reduces shock peaks during separation, ensuring safe and reliable release operations while enabling more lightweight and compact designs for spacecraft components.

Implementation Method 1

an initiator comprising means for providing high pressure fluid to an expansion chamber when the separation device is switched from a locked state to a released state. The high pressure fluid in the expansion chamber moves the locking device from the locking position to the releasing position

Methodology Applied

Scientific EffectHigh pressure fluid: Pressure Increase

Implementation Method 2

a dampening arrangement arranged to attenuate a peak load when the separation device is switched from a locked state to a released state

Methodology Applied

Scientific EffectDampening: Damping

Data Source

PatentEP3676180B1Separation device for spacecraft and a method for separation

Publication Date: 2022.11.02 RUAG SPACE

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AI summary

The invention relates to a separation device (1) for a spacecraft or launcher. The separation device (1) comprises an inner housing (2) divided into at least two portions locked to each other by a locking device (3) in a locking position. The locking device (3) is arranged to move between a locking position and a releasing position. The separation device (1) comprises an initiator (5) comprising means for providing high pressure fluid to an expansion chamber (6) when the separation device (1) is switched from a locked state to a released state. The high pressure fluid in an expansion chamber (6) moves the locking device (3) from the locking position to the releasing position when the separation device (1) is switched from the locked state to the released state. The separation device (1) comprises a dampening arrangement (8) arranged to attenuate a peak load when the separation device (1) is switched from the locked state to the released state.