Miniature Satellite Deployable Release Mechanism Using Threaded Interface

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Traditional restraint mechanisms for small satellites and nanosatellites are unreliable and inefficient due to the unpredictable burning of monofilament lines, which can stretch and fail to provide a rigid preload interface, leading to potential damage and vibration issues.

Innovation Solution

A release mechanism with a secure threaded interface that includes a housing structure, retracting pins, release springs, a breakable link, and a circuit board with a heating device to heat the breakable link, allowing for controlled release of deployables without using internal satellite space.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Volume of moving object

If monofilament line is used to secure deployables to the exterior of small satellites, then internal space is preserved, but the release mechanism becomes unreliable and the deployables lack rigid constraint

Engineering Contradiction:

Improveinternal spaceVSAvoidrelease mechanism reliability

Core Design Contradiction:

Volume of moving objectVSReliability

Solution Approach 1:

A breakable link made of heat-compromisable material serves as an intermediary between the heating device and the retracting pin. The link transmits force during launch and then fails in a predictable manner when heated, enabling reliable release without compromising internal satellite space.

Inventive Principle:

Principle #24Intermediary (Mediator)

Solution Approach 2:

The patent replaces the unpredictable mechanical burning process of monofilament line with a controlled thermal field applied by a heating device to a breakable link made of heat-compromisable material. This substitution provides predictable and reliable release timing.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

2Volume of moving object

If monofilament line is used to constrain deployables, then internal space is not sacrificed, but the deployables experience stretching and vibration issues

Engineering Contradiction:

Improveinternal spaceVSAvoiddeployable constraint stability

Core Design Contradiction:

Volume of moving objectVSStability of the object's composition

Solution Approach 1:

The breakable link acts as a rigid intermediary that maintains stable constraint during launch. It provides a solid mechanical connection between the retracting pin and housing structure, eliminating the stretching and vibration problems associated with flexible monofilament line.

Inventive Principle:

Principle #24Intermediary (Mediator)

Solution Approach 2:

The patent uses a breakable link made of heat-compromisable material that combines the properties of rigidity for launch stability with controlled failure characteristics for reliable release. This composite material approach solves both the stability and release reliability problems.

Inventive Principle:

Principle #40Composite materials

3Strength

If a threaded interface is used to secure deployables, then rigid constraint is achieved, but internal space is consumed

Engineering Contradiction:

Improveconstraint strengthVSAvoidinternal space

Core Design Contradiction:

StrengthVSVolume of moving object

Solution Approach 1:

The patent extracts the threaded interface functionality from the internal satellite structure and places it on an external housing structure. The release mechanism attaches to the satellite exterior, providing rigid constraint through the threaded interface without consuming internal satellite space.

Inventive Principle:

Principle #2Taking out (Extraction)

Solution Approach 2:

The patent moves the constraint mechanism from the internal dimension to the external dimension. By attaching the housing structure to the exterior of the satellite, the threaded interface provides strong constraint in three-dimensional space without occupying valuable internal volume.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

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 mechanism provides a reliable and predictable release of deployables, ensuring secure constraint during launch and deployment, with a high success rate and ability to withstand significant forces, while maintaining a compact size suitable for small satellites and nanosatellites.

Implementation Method 1

a circuit board including at least one heating device configured to heat the breakable link to compromise the breakable link

Methodology Applied

Scientific EffectJoule heating: Joule Heating

Data Source

PatentUS9546008B1Miniature release mechanism or diminutive assembly for nanosatellite deployables (DANY)

Publication Date: 2017.01.17 UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR NAT AERONAUTICS & SPACE ADMINISTRATION

AI summary

Miniature release mechanisms constrain objects, such as deployables during the launch of space vehicles, such as small satellites and nanosatellites, and enable the release of the objects once a desired destination is reached by the space vehicle. Constraint and release of the objects are achieved by providing a secure threaded interface that may be released by the release mechanisms. The release mechanisms include a housing structure; a release block can include a threaded interface; one or more retracting pins; one or more release springs; a breakable link, such as a plastic link; a cable harness clamp; and a circuit board. The release mechanism can be 0.1875 inches (approximately 4.8 mm) thick.