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EXPERIMENTS AND ANALYTICAL MODELING FOR DESIGNING TAPE SPRING COMPOSITES
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.ORCID iD: 0000-0001-6802-8331
(English)Manuscript (preprint) (Other (popular science, discussion, etc.))
Abstract [en]

Lightweight fiber reinforced tape spring composites are proposed for deployable space structures for nanosatellites. Neutral stable carbon fiber tape springs and bi-stable glass fiber tape springs were manufactured and their self-deployabilities after stowage were experimentally tested. The viscoelastic effects of the composites used were experimentally investigated. An analysis methodology that predicts neutral stability or bi-stability in appropriately arranging fiber directions, layups and fabric properties is presented. A design method flowchart is presented to give a reference for designing neutral or bi-stable tape springs based on the experiments and the analytical model, e.g., material type, layup, fibers direction andstability parameters. The tape spring properties before and after stowage can be predicted. The analytical model shows that fabrics of high strength fibers and low shear modulus resin with layer angle ±45o are good choices for neutrally tape springs and adding inner 0o/90o layers can increase the deployment force for bi-stable tape springs. The bi-stable glass fiber tape springs that can self-deploy after more than 6 months of stowage and high strength carbon fiber neutrally tape springs were fabricated.

National Category
Aerospace Engineering
Research subject
Aerospace Engineering
Identifiers
URN: urn:nbn:se:kth:diva-206556OAI: oai:DiVA.org:kth-206556DiVA: diva2:1093247
Projects
SEAM
Funder
EU, FP7, Seventh Framework Programme, 607197
Note

QC 20170508

Available from: 2017-05-05 Created: 2017-05-05 Last updated: 2017-05-08Bibliographically approved
In thesis
1. Numerical and Experimental Studies of Deployment Dynamics of Space Webs and CubeSat Booms
Open this publication in new window or tab >>Numerical and Experimental Studies of Deployment Dynamics of Space Webs and CubeSat Booms
2017 (English)Doctoral thesis, comprehensive summary (Other academic)
Abstract [en]

In this thesis, experiments and simulations are performed to study the deployment dynamics of space webs and space booms, focusing on the deployment and stabilization phases of the space web and the behavior of the bi-stable tape spring booms after long-term stowage.

The space web, Suaineadh, was launched onboard the sounding rocket REXUS-12 from the Swedish launch base Esrange in Kiruna on 19 March 2012. It served as a technology demonstrator for a space web. A reaction wheel was used to actively control the deployment and stabilization states of the 2×2 m2 space web. After ejection from the rocket, the web was deployed but entanglements occurred since the web did not start to deploy at the specified angular velocity. The deployment dynamics was reconstructed by simulations from the information recorded by inertial measurement units and cameras. Simulations show that if the web would have started to deploy at the specified angular velocity, the web would most likely have been deployed and stabilized in space by the motor, reaction wheel and controller used in the experiment. A modified control method was developed to stabilize the out-of-plane motions before or during deployment. New web arms with tape springs were proposed to avoid entanglements.

A deployable booms assembly composed of four 1-m long bi-stable glass fiber tape springs was designed for the electromagnetically clean 3U CubeSat Small Explorer for Advanced Missions (SEAM). The deployment dynamics and reliability of the SEAM boom design after long-term stowage were tested by on-ground experiments. A simple analytical model was developed to predict the deployment dynamics and to assess the effects of the GOLS and the combined effects of friction, viscoelastic strain energy relaxation, and other factors that act to decrease the deployment force. In order to mitigate the viscoelastic effects and thus ensure self-deployment, different tape springs were designed, manufactured and tested. A numerical model was used to assess the long-term stowage effects on the deployment capability of bi-stable tape springs including the friction, nonlinear-elastic and viscoelastic effects. A finite element method was used to model a meter-class fully coiled bi-stable tape spring boom and verified by analytical models.

Place, publisher, year, edition, pages
Stockholm: KTH Royal Institute of Technology, 2017. 54 p.
Series
TRITA-AVE, ISSN 1651-7660 ; TRITA-AVE 2017:28
Keyword
Deployable structure, Space web, Centrifugal force deployment, Deployable boom, Bi-stable tape spring, Fiber-reinforced composite, Viscoelasticity
National Category
Mechanical Engineering
Research subject
Aerospace Engineering
Identifiers
urn:nbn:se:kth:diva-206594 (URN)978-91-7729-399-6 (ISBN)
Public defence
2017-05-30, F3, Lindstedtsvägen 26, Kungl Tekniska högskolan, Stockholm, 13:00
Opponent
Supervisors
Projects
SEAM
Funder
EU, FP7, Seventh Framework Programme, 607197
Note

QC 20170508

Available from: 2017-05-08 Created: 2017-05-05 Last updated: 2017-05-08Bibliographically approved

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