Spacecraft Separation Locking Mechanism With Shock Dampening
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Solution Overview
Problem
Separation devices for spacecraft payloads 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 guiding mechanism for rotational movement and a dampening plate with pins to absorb energy, along with multiple initiator units for sequenced ignition, to attenuate peak loads and ensure secure release while allowing for lightweight construction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the locking device moves directly from locking position to releasing position, then the separation is achieved quickly and reliably, but high shock peaks are generated that threaten the lightweight construction
Solution Approach 1:
A dampening arrangement is arranged to attenuate a peak load when the separation device is switched from a locked state to a released state. The dampening arrangement includes a dampening element arranged to be deformed when the locking device moves from the locking position to the releasing position, thereby absorbing energy and reducing shock peaks before they can harm the lightweight construction.
Solution Approach 2:
The dampening element acts as an intermediary between the locking device and the housing structure. When the locking device moves to the releasing position, the dampening element deforms to absorb the impact energy, mediating the force transmission and preventing direct shock transmission to the sensitive lightweight components.
2Weight of moving object
If thin and lightweight constructions are used to reduce spacecraft weight, then weight is reduced and packing volume is optimized, but construction safety margins become restricted and more vulnerable to shock
Solution Approach 1:
The dampening arrangement is pre-configured in the separation device to provide shock protection. The dampening element is arranged to deform during the separation process, absorbing energy before it can compromise the lightweight construction's safety margins, thus enabling the use of thinner and lighter materials without sacrificing structural integrity.
3Object-affected harmful factors
If the dampening arrangement deforms the dampening element to absorb energy, then shock peaks are attenuated, but additional space is required for the dampening components
Solution Approach 1:
The dampening element is designed as a flexible component that can deform to absorb energy. By using flexible materials and thin-film structures, the dampening arrangement achieves effective shock attenuation while occupying minimal space within the separation device, thus not significantly increasing the overall volume.
4Reliability
If multiple initiator units are used for sequenced ignition, then separation reliability is improved, but device complexity increases
Solution Approach 1:
The initiator system is segmented into multiple initiator units that can be ignited in sequence. Each initiator unit is responsible for activating one or more locking devices, and by distributing the ignition function across multiple units, the system achieves improved reliability through redundancy and sequenced operation, while each individual unit remains relatively simple in design.
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 release operations and enabling more lightweight and slim spacecraft designs by absorbing energy through rotational movement and sequenced ignition, thus enhancing construction safety.
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
Implementation Method 2
a dampening arrangement arranged to attenuate a peak load when the separation device is switched from the locked state to the released state
Implementation Method 3
a guiding mechanism for rotational movement and a dampening plate with pins to absorb energy
Data Source
AI summary
The invention relates to a separation device for a spacecraft or launcher. The separation device includes an inner housing divided into at least two portions locked to each other by a locking device in a locking position. The locking device is arranged to move between a locking position and a releasing position. The separation device includes an initiator including 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 an expansion chamber moves the locking device from the locking position to the releasing position when the separation device is switched from the locked state to the released state. The separation device includes a dampening arrangement arranged to attenuate a peak load when the separation device is switched from the locked state to the released state.