Planar Dynamic Isolator With Thin-Film Damping for Launch Vibration

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Solution Overview

Problem

Existing vibration isolation systems for spacecraft are often heavy, bulky, and limited in their effectiveness across various frequencies and amplitudes, making them impractical for launch vehicles and imposing constraints on design and geometry, which can lead to adverse effects on delicate equipment due to unmitigated vibrations during launch.

Innovation Solution

A vibration isolation system comprising a rigid retaining device with an internal space and a damping material sandwiched between the retaining device and an anchoring device, which limits vibration transfer through a linkage member, allowing for effective damping of shear, axial, and bending loads, and is designed to be lightweight and adaptable to launch mount constraints.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Object-affected harmful factors

If traditional vibration isolators are used to protect spacecraft from launch vibrations, then vibration protection is improved, but weight and volume increase making them impractical for launch

Engineering Contradiction:

Improvevibration protectionVSAvoidisolator weight

Core Design Contradiction:

Object-affected harmful factorsVSWeight of moving object

Solution Approach 1:

The patent employs thin film damping layers (e.g., viscoelastic materials) sandwiched between rigid layers to create a lightweight vibration isolation system. This flexible film approach provides effective damping without the weight and bulk of traditional isolators, directly resolving the contradiction between vibration protection and weight reduction for spacecraft launch applications.

Inventive Principle:

Principle #30Flexible shells and thin films

2Object-affected harmful factors

If traditional vibration isolators are used to protect spacecraft from launch vibrations, then vibration protection is improved, but the isolator becomes bulky and impractical for launch

Engineering Contradiction:

Improvevibration protectionVSAvoidisolator volume

Core Design Contradiction:

Object-affected harmful factorsVSVolume of moving object

Solution Approach 1:

The thin film damping approach creates a low-profile vibration isolation system that is compact and suitable for spacecraft launch. The multi-layer structure with thin damping layers provides effective vibration protection without occupying excessive volume, directly addressing the contradiction between vibration protection and volume reduction.

Inventive Principle:

Principle #30Flexible shells and thin films

3Adaptability or versatility

If vibration isolators are designed with specific geometry for launch constraints, then adaptability to launch mount constraints is improved, but effectiveness across various frequencies and amplitudes is reduced

Engineering Contradiction:

Improveadaptability to launch mount constraintsVSAvoidvibration isolation effectiveness

Core Design Contradiction:

Adaptability or versatilityVSReliability

Solution Approach 1:

The patent implements local quality by varying the thickness and material properties of damping layers at different locations within the isolator structure. This allows the system to be adapted to specific launch mount constraints while maintaining broad frequency and amplitude effectiveness through localized optimization of damping characteristics.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The isolator uses composite material structures combining rigid layers with viscoelastic damping layers, allowing simultaneous achievement of structural adaptability to launch constraints and broad-spectrum vibration isolation effectiveness. The composite construction enables tuning of mechanical properties to match specific application requirements.

Inventive Principle:

Principle #40Composite materials

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 system effectively dampens vibrations across a range of frequencies and amplitudes, protecting sensitive equipment and reducing the mass of the satellite, thereby optimizing fuel consumption and ensuring safe launch conditions.

Implementation Method 1

A damping material may be sandwiched between the retaining device and the anchoring device, and may be configured to limit transfer of vibration between the retaining device and the anchoring device.

Methodology Applied

Scientific EffectVibration damping: Damping

Implementation Method 2

a damping material sandwiched between the retaining device and the anchoring device, and may be configured to limit transfer of vibration

Methodology Applied

Scientific EffectInternal friction: Friction

Data Source

PatentUS11802606B2Planate dynamic isolator

Publication Date: 2023.10.31 THE BOEING CO

AI summary

A vibration isolation system is disclosed, including a rigid retaining device having an internal space, a first external side, and a second external side. A rigid anchoring device is retained in the internal space of the rigid retaining device. The anchoring device has a linkage member that extends from the internal space to the first external side of the retaining device and is configured for rigid connection to a first apparatus. The second side of the retaining device is configured for attachment to a second apparatus. A damping material is sandwiched between the retaining device and the anchoring device, and is configured to limit transfer of vibration between the retaining device and the anchoring device.