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Experiments and Simulations of the Deploymentof a Bi-stable Composite Boom
KTH, School of Engineering Sciences (SCI), Mechanics.
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]

The rapidly growing use of nano- and pico-satellites for space missions requires de-ployable systems to be highly storable yet large and with adequate mechanical properties when deployed. This paper focuses on the modeling and simulation of a meter-class passively deployable boom, based on the self-contained linear meter-class deployable(SIMPLE) boom by Thomas W. Murphey, exploiting the bi-stable nature of compositeshells. Experimental tests were carried on a boom prototype suspended in a gravityo-offloading system. The strain energy level, deployment time and spacecraft displacements calculated from the finite element method agree well with analytical analyses, confirming the theoretical accuracy of the finite element method. Since friction and strain energy relaxation were not accurately included in the model, the finite element simulations predict deployment times up to five times shorter than those of the gravity off-loaded boom experiments. The quick deployment and violent end-of-deployment shock create boom deployment dynamics which are not seen in the experiments. 

Keyword [en]
CubeSat, deployable boom, tape spring, bi-stable boom, space boom, finite element method, gravity off loading system
National Category
Aerospace Engineering
Identifiers
URN: urn:nbn:se:kth:diva-206590OAI: oai:DiVA.org:kth-206590DiVA: diva2:1093425
Note

QC 20170509

Available from: 2017-05-05 Created: 2017-05-05 Last updated: 2017-05-09Bibliographically 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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