Spacecraft Separation Locking Structure for Low-Shock Release
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Solution Overview
Problem
Traditional separation devices for spacecraft payloads generate high shock levels due to internal locking device impacts, which is problematic for thin and lightweight constructions, especially in smaller spacecraft with restricted packing volumes and shorter distances between shock sources and equipment.
Innovation Solution
A separation device with an inner housing divided into portions and a locking arrangement that uses high-pressure fluid to move from a locked to a released state, reducing shock levels by employing a piston and locking elements to manage pretension and radial loads, and featuring angled abutment surfaces to redirect forces efficiently.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional locking devices are used in separation devices, then the locking mechanism is simple and reliable, but high shock levels are generated during activation
Solution Approach 1:
The patent employs a pneumatic system where compressed gas stored in a reservoir is rapidly released into an expansion chamber, generating high-pressure gas that drives the separation mechanism. This pneumatic approach replaces traditional mechanical spring-based or explosive systems, reducing shock transmission to the payload while maintaining reliable separation. The gas pressure directly acts on the locking elements to overcome friction and release the payload.
Solution Approach 2:
The separation device is divided into distinct functional segments: a locking mechanism with friction elements, an expansion chamber for gas pressure buildup, a reservoir for compressed gas storage, and a separation interface. This segmentation allows each component to be optimized independently - the locking elements can be designed for high friction holding force while the pneumatic system handles the release action, reducing overall system shock.
2Weight of moving object
If lightweight materials and thin constructions are used in spacecraft, then the mass is reduced, but the construction safety margins become thinner and more vulnerable to shock
Solution Approach 1:
The pneumatic separation system generates controlled gas pressure that can be precisely regulated to provide just enough force for separation without excessive shock. The gradual pressure buildup in the expansion chamber allows for controlled, smooth separation rather than sudden mechanical impact, protecting the lightweight spacecraft structure and its thin-walled components from damage.
Solution Approach 2:
The compressed gas acts as an intermediary between the locking mechanism and the payload. Instead of direct mechanical contact between heavy separation components and the payload, the gas pressure mediates the separation force, distributing it evenly and reducing peak shock loads on the lightweight spacecraft structure.
3Volume of moving object
If smaller spacecraft are used with restricted packing volume, then the launch capacity is optimized, but the distance between shock sources and equipment is shortened increasing shock impact
Solution Approach 1:
The pneumatic system uses compressed gas stored in a compact reservoir that expands into a separation chamber, generating high pressure in a small volume. This allows effective separation force generation without requiring large mechanical components or long actuation distances, making the system ideal for compact small spacecraft with limited space between the separation mechanism and sensitive equipment.
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 lowers the separation force and shock experienced by spacecraft components, enhancing the reliability and safety of payload release by distributing loads evenly and minimizing shock transmission.
Implementation Method 1
an initiator which comprises 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 arrangement from the locking configuration to the releasing configuration
Data Source
AI summary
A separation device for a spacecraft or launcher, separation device being movable from a locked state, in which the separation device is arranged to lock onto a component of a spacecraft or launcher, to a released state, in which component is released, separation device including: an inner housing divided into at least two portions for locking onto component of spacecraft or launcher, and a locking arrangement arranged to move between a locking configuration and a releasing configuration, wherein the locking configuration is such that said at least two portions of inner housing are prevented from separating, wherein said locking arrangement includes: a first part arranged to at least partially enclose said at least two portions of inner housing when locking arrangement is in the locking configuration.