Flexible Deployable Arms for Satellite Telescope Support

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Solution Overview

Problem

Satellite observation instruments, such as telescopes, are over-engineered to withstand launch stresses, resulting in excessive mass and inertia, limiting their agility and image acquisition time, and requiring larger rockets for launch, which restricts the number of satellites that can be launched simultaneously.

Innovation Solution

A deployable support device using flexible arms that can change configuration from a compact, folded position to a longer, unfolded position, reducing mass and inertia while maintaining the necessary separation between telescope elements, allowing for increased image acquisition speed and efficient launch logistics.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If the support structure is over-engineered to withstand launch stresses, then the structure can withstand mechanical stresses during launch, but the mass and inertia of the structure increase excessively

Engineering Contradiction:

Improveability to withstand launch stressesVSAvoidmass of support structure

Core Design Contradiction:

ReliabilityVSWeight of moving object

Solution Approach 1:

The patent applies the dynamics principle by using flexible arms that can change their mechanical properties between two states: a rigid configuration during launch to withstand stresses, and a flexible configuration during operation to reduce mass and inertia. The arms transition from a straight, load-bearing position during launch to a curved, low-inertia position during satellite operation, allowing the structure to adapt its properties to different operational phases.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The patent implements parameter changes by modifying the physical state and geometric configuration of the support arms. The arms change their shape parameter from straight to curved, and their mechanical property parameter from rigid to flexible, depending on the operational phase. This allows the same component to satisfy different performance requirements at different times.

Inventive Principle:

Principle #35Parameter changes

2Reliability

If the support structure is over-engineered to withstand launch stresses, then the structure can withstand mechanical stresses during launch, but the transverse inertia increases limiting the rate of change of aim point

Engineering Contradiction:

Improveability to withstand launch stressesVSAvoidrate of change of aim point

Core Design Contradiction:

ReliabilityVSProductivity

Solution Approach 1:

The flexible arms enable dynamic adaptation of the telescope's moment of inertia. During launch, the arms are rigid to withstand stresses. During operation, the arms become flexible and can be positioned to minimize transverse inertia, thereby increasing the rate of change of aim point and improving the telescope's agility for rapid repositioning and mosaic image acquisition.

Inventive Principle:

Principle #15Dynamics

3Reliability

If the support structure is over-engineered, then the structure can withstand launch stresses, but additional mass requires higher capacity rockets

Engineering Contradiction:

Improveability to withstand launch stressesVSAvoidmass requiring launch capacity

Core Design Contradiction:

ReliabilityVSWeight of stationary object

Solution Approach 1:

The support arms undergo parameter changes in their mechanical properties, transitioning from a rigid state during launch to a flexible state during operation. This allows the same structure to satisfy launch stress requirements while presenting a lower effective mass and inertia during the satellite's operational phase, reducing the launch capacity required.

Inventive Principle:

Principle #35Parameter changes

4Reliability

If the support structure is over-engineered, then the structure can withstand launch stresses, but additional bulk limits the number of satellites that can be launched from the same rocket

Engineering Contradiction:

Improveability to withstand launch stressesVSAvoidbulk of support structure

Core Design Contradiction:

ReliabilityVSVolume of stationary object

Solution Approach 1:

The flexible arms can dynamically adjust their configuration to minimize the volume occupied by the support structure. During launch, they provide the necessary structural support. During operation, they can be positioned to reduce the overall bulk of the instrument, allowing more instruments or satellites to be accommodated within the same launch vehicle payload volume.

Inventive Principle:

Principle #15Dynamics

Data Source

PatentUS8186121B2Support device for elements on a piece of space equipment with flexible deploying arms

Publication Date: 2012.05.29 THALES SA

AI summary

A device supporting a first and a second element of a piece of space equipment. The device includes at least two deployable flexible arms each having a first end and a second end, the ends are secured respectively to the first and second elements and each designed to adopt at least one initial position folded in curves and an unfolded final position, in which positions they hold the first element away from the second element by first and second chosen distances respectively, the second distance being greater than the first.