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Simulation and control of a space web deployed by centrifugal forces in a 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: AIAA Modeling and Simulation Technologies Conference, 2016, American Institute of Aeronautics and Astronautics Inc, AIAA , 2016Conference paper, Published paper (Refereed)
Abstract [en]

A deployable space web is a flexible structure that can act as a lightweight platform for construction of large structures in space. In order to save space and energy for small deployable structures, a one-step deployment method was a possible choice for future web deployment without complicated extending mechanisms. The aim of the Suaineadh experiment was to deploy and stabilize a space web by centrifugal forces and act as a test bed of the one-step deployment. Suaineadh, a 2 × 2 m2 space web, was ejected from the nose cone of REXUS-12 sounding rocket and deployed in a micro-gravity environment. A developed control law and a reaction wheel were used to control the deployment. Results from ground tests, simulations and former sounding rocket experiments were used to design the structure, folding pattern, control parameters and the deployment. During the experiment, the web was deployed but entanglements occurred since the web did not start to deploy at the specified proper initial angular velocity. It might be due to the broken inertial measurement unit which failed to detect the required spin rate of the hub or other unknown problems. The deployment dynamics was reconstructed from the information recorded by inertial measurement units and cameras. Simulations show that if the Suaineadh space web started to deploy at the specified proper 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. In actual flight, out-of-plane motions were observed both in deployment and stabilization phases. In order to stabilize the out-of-plane motions and reduce the risk of entanglement observed from experiment, simulation results show that small reaction wheels could be used before or during web deployment. Tape springs could also be used as web arms to avoid entanglement.

Place, publisher, year, edition, pages
American Institute of Aeronautics and Astronautics Inc, AIAA , 2016.
Keywords [en]
Angular velocity, Centrifugation, Flexible structures, Flight dynamics, Units of measurement, Wheels, Centrifugal Forces, Control parameters, Deployable structure, Deployment dynamics, Deployment methods, Inertial measurement unit, Large structures, Out-of-plane motion, Sounding rockets
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-195557DOI: 10.2514/6.2016-4421Scopus ID: 2-s2.0-84985930003ISBN: 9781624104299 (print)OAI: oai:DiVA.org:kth-195557DiVA, id: diva2:1048469
Conference
AIAA Modeling and Simulation Technologies Conference, 2016, 13 June 2016 through 17 June 2016
Note

QC 20161121

Available from: 2016-11-21 Created: 2016-11-03 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. p. 54
Series
TRITA-AVE, ISSN 1651-7660 ; TRITA-AVE 2017:28
Keywords
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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