Dual-Use Spring Antenna for CubeSat Deployment Volume

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Solution Overview

Problem

Small satellites, such as CubeSats, face volume constraints in deployment containers due to the space occupied by conventional ejection mechanisms, leading to increased development time and cost, as well as limited launch availability.

Innovation Solution

A dual-use spring that functions as both a deployment mechanism to eject the satellite from the container and a communications antenna, replacing the conventional spring and pusher plate, thereby optimizing the use of limited container volume.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Volume of moving object

If a conventional ejection mechanism (spring and pusher plate) is used in the deployment container, then the satellite can be successfully ejected from the container, but the volume available for satellite components is reduced

Engineering Contradiction:

Improvevolume available for satellite componentsVSAvoidcomplexity of ejection mechanism

Core Design Contradiction:

Volume of moving objectVSDevice complexity

Solution Approach 1:

The patent combines the ejection mechanism and antenna into a single integrated spring component. The spring serves dual functions: providing the mechanical force to eject the satellite from the deployment container and simultaneously serving as the communications antenna. This merging eliminates the need for a separate pusher plate and reduces the volume occupied by ejection mechanisms, thereby increasing the available volume for satellite components.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The spring component is designed to perform multiple functions: it acts as both the ejection mechanism (providing mechanical propulsion) and the communications antenna (transmitting and receiving signals). This multi-functionality reduces the overall number of components needed in the deployment container, freeing up volume for other satellite components while maintaining both ejection and communication capabilities.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Reliability

If separate antenna deployment mechanism is added to the satellite, then the antenna can be deployed after ejection, but the development time and cost increase

Engineering Contradiction:

Improveantenna deployment reliabilityVSAvoiddevelopment time

Core Design Contradiction:

ReliabilityVSLoss of time

Solution Approach 1:

The ejection mechanism and antenna are merged into a single spring component. Since the spring is already present and functional as part of the ejection mechanism, it can simultaneously serve as the antenna without requiring a separate antenna deployment mechanism. This eliminates the need for additional deployment steps and reduces development time while maintaining antenna functionality.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The spring is designed with universal functionality to serve both mechanical ejection and electromagnetic communication purposes. By making the spring conductive and shaping it appropriately, it becomes a functional antenna without requiring separate deployment mechanisms, thereby reducing development complexity and time while ensuring reliable antenna operation from the moment of ejection.

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Force

If conventional ejection mechanism components are used, then the satellite can be ejected with sufficient force, but the mass of the satellite increases

Engineering Contradiction:

Improveejection forceVSAvoidmass of satellite

Core Design Contradiction:

ForceVSWeight of moving object

Solution Approach 1:

The spring and pusher plate are merged into a single spring component. This integration eliminates the mass of the separate pusher plate while maintaining the ejection force capability through proper spring design. The unified spring structure provides sufficient mechanical force for ejection without the additional mass penalty of separate components.

Inventive Principle:

Principle #5Merging (Combining)

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

This solution increases available volume by approximately 12% within the deployment container, eliminates the need for a secondary antenna deployment stage, reduces mass and volume, and simplifies satellite design by integrating the ejection and antenna functions into a single component.

Implementation Method 1

One end of a compressed deployment spring is attached to the back of the deployment container and the other end of the spring is attached to a pusher plate. When the deployment container door opens, the spring pushes the pusher plate and ejects the CubeSat(s) out the deployment container door

Methodology Applied

Scientific EffectElastic potential energy: Spring

Data Source

PatentUS11588221B1Small satellite communications antenna and container deployment mechanism

Publication Date: 2023.02.21 UNITED STATES OF AMERICA THE AS REPRESENTED BY THE SEC OF THE ARMY

AI summary

A dual-use spring attached to a small satellite that performs two common functions for small satellites including operating as a communications antenna for the small satellite, which eliminates the need for a separate antenna deployment step, and ejecting the small satellite from a modified deployment container mounted on a launch vehicle. The deployment container is modified by removing a conventional deployment spring and pusher plate, which increases available container space.