Flexible Boom Satellite Deployment via Strain Energy

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Solution Overview

Problem

Small satellites face challenges in meeting weight, volume, and connectivity requirements due to complex deployment mechanisms, which limit mission utility and increase cost, weight, and complexity.

Innovation Solution

A satellite design featuring a pair of payload modules connected by a flexible boom that allows for easy attachment to and passive release from an ESPA-class hub, utilizing stored strain energy for deployment, eliminating the need for complex deployment mechanisms and ensuring continuous connectivity.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of operation

If complex deployment mechanisms are used for each payload module, then deployment capability is achieved, but device complexity, weight, cost, and number of components increase

Engineering Contradiction:

Improvedeployment capabilityVSAvoidcomplexity of deployment mechanisms

Core Design Contradiction:

Ease of operationVSDevice complexity

Solution Approach 1:

The flexible boom serves itself by using its inherent flexibility to enable both attachment and deployment functions without requiring separate complex deployment mechanisms. The boom's natural properties are exploited to provide the deployment capability, eliminating the need for additional active deployment systems.

Inventive Principle:

Principle #25Self-service

Solution Approach 2:

The flexible boom performs multiple functions: it provides structural connection between payloads, enables attachment to the hub by flexing, and facilitates deployment when detached. This multi-functional element replaces what would traditionally require separate specialized mechanisms for each function.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Adaptability or versatility

If interconnection equipment with moving parts is used to stabilize payload modules, then connectivity is achieved, but mission utility is limited due to stabilization requirements and moving parts

Engineering Contradiction:

Improveconnectivity between payload modulesVSAvoidmission utility

Core Design Contradiction:

Adaptability or versatilityVSReliability

Solution Approach 1:

The flexible boom acts as a flexible connection element that maintains physical and functional connectivity between payload modules without requiring rigid stabilization mechanisms or moving parts. Its flexibility allows it to accommodate relative movements while maintaining continuous connection.

Inventive Principle:

Principle #30Flexible shells and thin films

Solution Approach 2:

The invention extracts and removes the moving parts from the interconnection system, replacing them with a flexible passive connection. This eliminates the need for active stabilization mechanisms while maintaining connectivity, thereby improving reliability and mission utility.

Inventive Principle:

Principle #2Taking out (Extraction)

3Weight of moving object

If dense packaging of on-board equipment is implemented to meet weight and volume requirements, then weight and volume specifications are met, but mission utility is lessened

Engineering Contradiction:

Improveweight of satelliteVSAvoidmission utility

Core Design Contradiction:

Weight of moving objectVSAdaptability or versatility

Solution Approach 1:

The satellite is segmented into modular payload modules that can be independently configured and packaged. This segmentation allows for optimized dense packaging of each module while maintaining overall system functionality and mission utility through the flexible connections between modules.

Inventive Principle:

Principle #1Segmentation

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 flexible boom design reduces complexity and cost, enables efficient deployment, and maintains continuous thermal, RF, and electrical connections, enhancing mission utility while meeting stiffness and torque requirements.

Implementation Method 1

Potential energy for enabling the passive release is provided as stored strain energy in the flexible boom when flexed for attachment of the payloads to the attachment hub. The strain energy is released upon release of at least one of the payloads from the attachment hub

Methodology Applied

Scientific EffectStrain energy: Elasticity

Data Source

PatentUS10773835B2Flexible satellite for deployment from attachment hub

Publication Date: 2020.09.15 RAYTHEON CO

AI summary

An exemplary satellite includes a pair of payloads coupled to one another by a flexible boom, where the flexible boom is configured to enable easy manual engagement of the pair of payloads with an associated attachment hub, and also to provide a passive release force for deploying at least one of the payloads in a direction outwardly from the attachment hub. Potential energy for enabling the passive release is provided as stored strain energy in the flexible boom when flexed for attachment of the payloads to the attachment hub. The strain energy is released upon release of at least one of the payloads from the attachment hub, which release may be by way of a non-complex, non-exotic attachment mechanism. Additional payloads may be connected in series to the pair of payloads, with a flexible boom connecting adjacent payloads. The additional payloads may be released from the attachment hub via a non-complex or complex attachment mechanism.