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Post-launch analysis of the deployment dynamics of a space web sounding rocket experiment
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
2016 (English)In: Acta Astronautica, ISSN 0094-5765, E-ISSN 1879-2030, Vol. 127, 345-358 p.Article in journal (Refereed) Published
Abstract [en]

Lightweight deployable space webs have been proposed as platforms or frames for a construction of structures in space where centrifugal forces enable deployment and stabilization. The Suaineadh project was aimed to deploy a 2 x 2 m2 space web by centrifugal forces in milli-gravity conditions and act as a test bed for the space web technology. Data from former sounding rocket experiments, ground tests and simulations were used to design the structure, the folding pattern and control parameters. A developed control law and a reaction wheel were used to control the deployment. 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 from the information recorded in inertial measurement units and cameras. The nonlinear torque of the motor used to drive the reaction wheel was calculated from the results. Simulations show that if the Suaineadh 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.

Place, publisher, year, edition, pages
Elsevier, 2016. Vol. 127, 345-358 p.
Keyword [en]
Space web, Reaction wheel, Centrifugal deployment, Centrifugal stabilization
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-193975DOI: 10.1016/j.actaastro.2016.06.009ISI: 000383525100033Scopus ID: 2-s2.0-84975144678OAI: oai:DiVA.org:kth-193975DiVA: diva2:1037759
Note

QC 20161018

Available from: 2016-10-18 Created: 2016-10-14 Last updated: 2017-05-10Bibliographically 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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Citation style
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