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Deployment of Bistable Self-Deployable Tape Spring Booms Using a Gravity Offloading System
KTH, Skolan för teknikvetenskap (SCI), Farkost och flyg.
Kayser Italia.
Kayser Italia.
KTH, Skolan för elektro- och systemteknik (EES), Rymd- och plasmafysik.ORCID-id: 0000-0003-2422-5426
Vise andre og tillknytning
2017 (engelsk)Inngår i: Journal of Aerospace Engineering, ISSN 0893-1321, E-ISSN 1943-5525, Vol. 30, nr 4Artikkel i tidsskrift (Fagfellevurdert) Published
Abstract [en]

Bistable tape springs are suitable as deployable structures thanks to their high packaging ratio, self-deployment ability, low cost, light weight, and stiffness. A deployable booms assembly composed of four 1-m long bistable glass fiber tape springs was designed for the electromagnetically clean 3U CubeSat Small Explorer for Advanced Missions (SEAM). The aim of the present study was to investigate the deployment dynamics and reliability of the SEAM boom design after long-term stowage using onground experiments and simulations. A gravity offloading system (GOLS) was built and used for the onground deployment experiments. Two booms assemblies were produced and tested: a prototype and an engineering qualification model (EQM). The prototype assembly was deployed in a GOLS with small height, whereas the EQM was deployed in a GOLS with tall height to minimize the effects of the GOLS. 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 relaxation, and other factors that act to decrease the deployment force. Experiments and simulations of the deployment dynamics indicate significant viscoelastic energy relaxation phenomena, which depend on the coiled radius and stowage time. In combination with friction effects, these viscoelastic effects decreased the deployment speed and the end-of-deployment shock vibrations. 

sted, utgiver, år, opplag, sider
Journal of Aerospace Engineering, 2017. Vol. 30, nr 4
Emneord [en]
Bi-stable tape spring, CubeSat Boom, Viscoelasticity, Gravity offloading system
HSV kategori
Forskningsprogram
Flyg- och rymdteknik
Identifikatorer
URN: urn:nbn:se:kth:diva-206545DOI: 10.1061/(ASCE)AS.1943-5525.0000709ISI: 000399893000007Scopus ID: 2-s2.0-85017807651OAI: oai:DiVA.org:kth-206545DiVA, id: diva2:1093220
Prosjekter
SEAM
Forskningsfinansiär
EU, FP7, Seventh Framework Programme, 607197
Merknad

QC 20170508

Tilgjengelig fra: 2017-05-05 Laget: 2017-05-05 Sist oppdatert: 2017-05-23bibliografisk kontrollert
Inngår i avhandling
1. Numerical and Experimental Studies of Deployment Dynamics of Space Webs and CubeSat Booms
Åpne denne publikasjonen i ny fane eller vindu >>Numerical and Experimental Studies of Deployment Dynamics of Space Webs and CubeSat Booms
2017 (engelsk)Doktoravhandling, med artikler (Annet vitenskapelig)
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.

sted, utgiver, år, opplag, sider
Stockholm: KTH Royal Institute of Technology, 2017. s. 54
Serie
TRITA-AVE, ISSN 1651-7660 ; TRITA-AVE 2017:28
Emneord
Deployable structure, Space web, Centrifugal force deployment, Deployable boom, Bi-stable tape spring, Fiber-reinforced composite, Viscoelasticity
HSV kategori
Forskningsprogram
Flyg- och rymdteknik
Identifikatorer
urn:nbn:se:kth:diva-206594 (URN)978-91-7729-399-6 (ISBN)
Disputas
2017-05-30, F3, Lindstedtsvägen 26, Kungl Tekniska högskolan, Stockholm, 13:00
Opponent
Veileder
Prosjekter
SEAM
Forskningsfinansiär
EU, FP7, Seventh Framework Programme, 607197
Merknad

QC 20170508

Tilgjengelig fra: 2017-05-08 Laget: 2017-05-05 Sist oppdatert: 2017-05-08bibliografisk kontrollert

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