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Mallol, P., Mao, H. & Tibert, G. (2018). Experiments and simulations of the deployment of a bistable composite boom. Journal of Spacecraft and Rockets, 55(2), 292-302
Open this publication in new window or tab >>Experiments and simulations of the deployment of a bistable composite boom
2018 (English)In: Journal of Spacecraft and Rockets, ISSN 0022-4650, E-ISSN 1533-6794, Vol. 55, no 2, p. 292-302Article in journal (Refereed) Published
Abstract [en]

The rapidly growing use of small satellites for space missions requires deployable 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 boom, exploiting the bistable nature of composite shells. Experimental tests were performed on a boom prototype suspended in a gravity 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. Because friction and strain energy relaxation were not included in the model, the finite element simulations predicted deployment times up to five times shorter than those of the gravity offloaded boom experiments. The quick deployment and violent end-of-deployment shock created boom deployment dynamics that were not seen in the experiments. The observed differences between the finite element model and the tests were mainly due to inaccurate material and friction models.

Place, publisher, year, edition, pages
American Institute of Aeronautics and Astronautics Inc., 2018
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-225495 (URN)10.2514/1.A33906 (DOI)000428346600004 ()2-s2.0-85044458459 (Scopus ID)
Note

QC 20180406

Available from: 2018-04-06 Created: 2018-04-06 Last updated: 2019-09-20Bibliographically approved
Mao, H. & Tibert, G. (2017). Experiments and analytical modeling for designing tape spring composites. In: ICCM International Conferences on Composite Materials: . Paper presented at 21st International Conference on Composite Materials, ICCM 2017, 20 August 2017 through 25 August 2017. International Committee on Composite Materials
Open this publication in new window or tab >>Experiments and analytical modeling for designing tape spring composites
2017 (English)In: ICCM International Conferences on Composite Materials, International Committee on Composite Materials , 2017Conference paper, Published paper (Refereed)
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 and stability 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 ±45° are good choices for neutrally tape springs and adding inner 0°/90° 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. 

Place, publisher, year, edition, pages
International Committee on Composite Materials, 2017
Keywords
Bi-stable tape springs, Fiber reinforced composites, Neutrally stable tape springs, Tape spring design, Viscoelasticity
National Category
Materials Engineering
Identifiers
urn:nbn:se:kth:diva-236824 (URN)2-s2.0-85053136408 (Scopus ID)
Conference
21st International Conference on Composite Materials, ICCM 2017, 20 August 2017 through 25 August 2017
Funder
EU, FP7, Seventh Framework Programme
Note

QC 20190107

Available from: 2019-01-07 Created: 2019-01-07 Last updated: 2019-01-07Bibliographically approved
Mao, H., Sinn, T., Vasile, M. & Tibert, G. (2016). Simulation and control of a space web deployed by centrifugal forces in a sounding rocket experiment. In: AIAA Modeling and Simulation Technologies Conference, 2016: . Paper presented at AIAA Modeling and Simulation Technologies Conference, 2016, 13 June 2016 through 17 June 2016. American Institute of Aeronautics and Astronautics Inc, AIAA
Open this publication in new window or tab >>Simulation and control of a space web deployed by centrifugal forces in a sounding rocket experiment
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
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:nbn:se:kth:diva-195557 (URN)10.2514/6.2016-4421 (DOI)2-s2.0-84985930003 (Scopus ID)9781624104299 (ISBN)
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
Balmer, G., Berquand, A., Company-Vallet, E., Granberg, V., Grigore, V., Ivchenko, N., . . . Yuan, Y. (2015). ISAAC: A REXUS STUDENT EXPERIMENT TO DEMONSTRATE AN EJECTION SYSTEM WITH PREDEFINED DIRECTION. In: EUROPEAN ROCKET AND BALLOON: PROGRAMMES AND RELATED RESEARCH. Paper presented at 22nd ESA Symposium on European Rocket and Balloon Programmes and Related Research, JUN 07-12, 2015, Tromso, NORWAY (pp. 235-242).
Open this publication in new window or tab >>ISAAC: A REXUS STUDENT EXPERIMENT TO DEMONSTRATE AN EJECTION SYSTEM WITH PREDEFINED DIRECTION
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2015 (English)In: EUROPEAN ROCKET AND BALLOON: PROGRAMMES AND RELATED RESEARCH, 2015, p. 235-242Conference paper, Published paper (Refereed)
Abstract [en]

ISAAC - Infrared Spectroscopy to Analyse the middle Atmosphere Composition was a student experiment launched from SSC's Esrange Space Centre, Sweden, on 29th May 2014, on board the sounding rocket REXUS 15 in the frame of the REXUS/BEXUS programme. The main focus of the experiment was to implement an ejection system for two large Free Falling Units (FFUs) (240 mm x 80 mm) to be ejected from a spinning rocket into a predefined direction. The system design relied on a spring-based ejection system. Sun and angular rate sensors were used to control and time the ejection. The flight data includes telemetry from the Rocket Mounted Unit (RMU), received and saved during flight, as well as video footage from the GoPro camera mounted inside the RMU and recovered after the flight. The FFUs' direction, speed and spin frequency as well as the rocket spin frequency were determined by analyzing the video footage. The FFU-Rocket-Sun angles were 64.3 degrees and 104.3 degrees, within the required margins of 90 degrees +/- 45 degrees. The FFU speeds were 3.98 m/s and 3.74 m/s, lower than the expected 5 +/- 1 m/s. The FFUs' spin frequencies were 1.38 Hz and 1.60 Hz, approximately half the rocket's spin frequency. The rocket spin rate slightly changed from 3.163 Hz before the ejection to 3.117 Hz after the ejection of the two FFUs. The angular rate, sun sensor data and temperature on the inside of the rocket module skin were also recorded. The experiment design and results of the data analysis are presented in this paper.

Series
ESA Special Publications, ISSN 0379-6566 ; 730
Keywords
ISAAC, REXUS, ejection system, pre-defined direction
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:kth:diva-186694 (URN)000373647300032 ()978-92-9221-294-0 (ISBN)
Conference
22nd ESA Symposium on European Rocket and Balloon Programmes and Related Research, JUN 07-12, 2015, Tromso, NORWAY
Note

QC 20160608

Available from: 2016-06-08 Created: 2016-05-13 Last updated: 2016-06-08Bibliographically approved
Yuan, Y., Ivchenko, N., Tibert, G. & Schlatter, N. (2015). RECONSTRUCTION OF ATTITUDE DYNAMICS OF FREE FALLING UNITS. In: EUROPEAN ROCKET AND BALLOON: PROGRAMMES AND RELATED RESEARCH. Paper presented at 22nd ESA Symposium on European Rocket and Balloon Programmes and Related Research, JUN 07-12, 2015, Tromso, NORWAY (pp. 107-113).
Open this publication in new window or tab >>RECONSTRUCTION OF ATTITUDE DYNAMICS OF FREE FALLING UNITS
2015 (English)In: EUROPEAN ROCKET AND BALLOON: PROGRAMMES AND RELATED RESEARCH, 2015, p. 107-113Conference paper, Published paper (Refereed)
Abstract [en]

Attitude reconstruction of a free falling sphere for the experiment Multiple Spheres for Characterization of Atmosphere Temperatures (MUSCAT) is studied in this paper. The attitude dynamics is modeled through Euler's rotational equations of motion. To estimate uncertain parameters in this model such as the matrix of inertia and the lever arm for the dynamic pressure with respect to the center of mass, the dynamics reconstruction can be formulated as an optimization problem. The goal is to minimize the deviation between the measurements and the propagation from the system equations. This approach was tested against a couple of flight data sets which correspond to different periods of time. The result is very reasonable compared to the laboratory test. The estimate can be improved further through allowing drag coefficients variable and taking advantage of measurements from a magnetometer in numerical calculation.

Series
ESA Special Publications, ISSN 0379-6566 ; 730
National Category
Computational Mathematics Applied Mechanics
Identifiers
urn:nbn:se:kth:diva-186693 (URN)000373647300012 ()978-92-9221-294-0 (ISBN)
Conference
22nd ESA Symposium on European Rocket and Balloon Programmes and Related Research, JUN 07-12, 2015, Tromso, NORWAY
Note

QC 20160608

Available from: 2016-06-08 Created: 2016-05-13 Last updated: 2016-06-08Bibliographically approved
Bergström, R., Crimella, M., Ivchenko, N., Karlsson, A., Lindberg, H., Persson, L., . . . Westerlund, S. (2015). SCATTERING OF RADAR WAVES ON AEROSOLS IN PLASMAS. In: EUROPEAN ROCKET AND BALLOON: PROGRAMMES AND RELATED RESEARCH. Paper presented at 22nd ESA Symposium on European Rocket and Balloon Programmes and Related Research, JUN 07-12, 2015, Tromso, NORWAY (pp. 87-94).
Open this publication in new window or tab >>SCATTERING OF RADAR WAVES ON AEROSOLS IN PLASMAS
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2015 (English)In: EUROPEAN ROCKET AND BALLOON: PROGRAMMES AND RELATED RESEARCH, 2015, p. 87-94Conference paper, Published paper (Refereed)
Abstract [en]

To study the physical mechanisms of phenomena such as polar mesospheric summer echoes, the SCRAP (Scattering of Radar waves on Aerosols in Plasmas) experiment aimed to validate theories on density fluctuations in dusty plasmas. The SCRAP team developed two identical free falling units (FFUs) designed to create a cloud of copper particles once they eject from the REXUS17 sounding rocket 124 seconds after launch. By using the EISCAT incoherent scatter radar system to observe the cloud, the SCRAP experiment proposed to relate theoretical predictions to a controlled object. The SCRAP experiment was launched from ESRANGE on March the 17th 2015. The FFUs GPS signal was lost during launch and the units were therefore not found. Moreover, no backscattering from the copper cloud was observed by the radar.

Series
ESA Special Publications, ISSN 0379-6566 ; 730
Keywords
Free falling units, specific unit, common unit, copper, radar, rocket experiment for university students, polar mesospheric summer echoes
National Category
Fusion, Plasma and Space Physics
Identifiers
urn:nbn:se:kth:diva-186692 (URN)000373647300009 ()978-92-9221-294-0 (ISBN)
Conference
22nd ESA Symposium on European Rocket and Balloon Programmes and Related Research, JUN 07-12, 2015, Tromso, NORWAY
Note

QC 20160608

Available from: 2016-06-08 Created: 2016-05-13 Last updated: 2016-11-28Bibliographically approved
Sinn, T., McRobb, M., Wujek, A., Skogby, J., Rogberg, F., Wang, J., . . . Mao, H. (2015). THE EXPERIMENT THAT CAME FROM THE COLD: RESULTS FROM THE RECOVERED REXUS12 SUAINEADH SPINNING WEB EXPERIMENT. In: EUROPEAN ROCKET AND BALLOON: PROGRAMMES AND RELATED RESEARCH. Paper presented at 22nd ESA Symposium on European Rocket and Balloon Programmes and Related Research, JUN 07-12, 2015, Tromso, NORWAY (pp. 449-459).
Open this publication in new window or tab >>THE EXPERIMENT THAT CAME FROM THE COLD: RESULTS FROM THE RECOVERED REXUS12 SUAINEADH SPINNING WEB EXPERIMENT
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2015 (English)In: EUROPEAN ROCKET AND BALLOON: PROGRAMMES AND RELATED RESEARCH, 2015, p. 449-459Conference paper, Published paper (Refereed)
Abstract [en]

The Suaineadh experiment had the purpose to deploy a 2m x 2m web in milli gravity conditions by using the centrifugal forces acting on corner sections of a web that is spinning around a central hub. Continuous exploration of our solar system and beyond requires ever larger structures in space. But the biggest problem nowadays is the transport of these structures into space due to launch vehicle payload volume constrains. By making the space structures deployable with minimum storage properties, this constrain may be bypassed. Deployable concepts range from inflatables, foldables, electrostatic to spinning web deployment. The advantage of the web deployment is the very low storage volume and the simple deployment mechanism. These webs can act as lightweight platforms for the construction of large structures in space without the huge expense of launching heavy structures from Earth. The Suaineadh experiment was launched onboard the sounding rocket REXUS12 in March 2012. After achieving the required altidue, the Suaineadh experiment was ejected from the rocket in order to be fully free flying. A specially designed spinning wheel in the ejected section was then used to spin up the experiment until the required rate is achieved for web deployment to commence. Unfortunately during re-entry, the probe was lost and also a recovery mission in August 2012 was only able to find minor components of the experiment. After 18 month, in September 2013, the experiment was found in the wilderness of Northern Sweden. In the following months all data from the experiment could be recovered. The images and accelerometer data that has been analysed showed the deployment of the web and a very interesting three dimensional behaviour that differs greatly from on ground two dimensional prototype tests. This paper will give an overview on the recovered data and it will present the analysed results of the Suaineadh spinning web experiment.

Series
ESA Special Publications, ISSN 0379-6566 ; 730
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:kth:diva-186695 (URN)000373647300062 ()978-92-9221-294-0 (ISBN)
Conference
22nd ESA Symposium on European Rocket and Balloon Programmes and Related Research, JUN 07-12, 2015, Tromso, NORWAY
Note

QC 20160608

Available from: 2016-06-08 Created: 2016-05-13 Last updated: 2016-06-08Bibliographically approved
Mallol, P. & Tibert, G. (2013). Deployment modeling and experimental testing of a Bi-stable composite boom for small satellites. In: 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference: . Paper presented at 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference; Boston, MA; United States; 8 April 2013 through 11 April 2013. American Institute of Aeronautics and Astronautics
Open this publication in new window or tab >>Deployment modeling and experimental testing of a Bi-stable composite boom for small satellites
2013 (English)In: 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, American Institute of Aeronautics and Astronautics, 2013Conference paper, Published paper (Refereed)
Abstract [en]

The rapidly growing use of nano- and pico-satellites for space missions requires deployable 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 SIMPLE boom by Thomas W. Murphey - exploiting the bi-stable nature of composite shells. Experimental tests were also carried on a boom prototype suspended in a gravity off-loading system. The strain energy level, deployment time and spacecraft displacements of the models agree well with analytical analyses, confirming the theoretical accuracy of the finite element model. However, the simulations show that the boom deploys six times faster than the real prototype. The quick deployment and violent end-of-deployment shock provokes the boom deployment dynamics to be unrealistic but still shows a reasonable behavior given the nature of the deployment. Future improvements in the material and friction models will, most likely, provide us with a more realistic finite element model.

Place, publisher, year, edition, pages
American Institute of Aeronautics and Astronautics, 2013
Keywords
Analytical analysis, Bi-stable composite, Deployable systems, Deployment dynamics, Experimental testing, Future improvements, Modeling and simulation, Theoretical accuracy
National Category
Engineering and Technology
Identifiers
urn:nbn:se:kth:diva-134115 (URN)10.2514/6.2013-1672 (DOI)2-s2.0-84880844136 (Scopus ID)978-162410223-3 (ISBN)
Conference
54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference; Boston, MA; United States; 8 April 2013 through 11 April 2013
Note

QC 20131118

Available from: 2013-11-18 Created: 2013-11-18 Last updated: 2013-11-18Bibliographically approved
Mallol, P. & Tibert, G. (Eds.). (2013). Deployment modelling and experimental testing of a bi-stable composite boom for small satellites. Paper presented at 54thAIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and MaterialsConference in Boston (8–11 April 2013).
Open this publication in new window or tab >>Deployment modelling and experimental testing of a bi-stable composite boom for small satellites
2013 (English)Conference proceedings (editor) (Other academic)
Abstract [en]

The rapidly growing use of nano- and pico-satellites for space missions requires deployable systems to be highly storable yet large and with adequate mechanical properties when deployed. This paper focuses on the modelling and simulation of a meter-class passively deployable boom – based on the SIMPLE boom by Thomas W. Murphey – exploiting the bi-stable nature of composite shells. Experimental tests were also carried on a boom prototype suspended in a gravity off-loading system. The strain energy level, deployment time and spacecraft displacements of the models agree well with analytical analyses, confirming the theoretical accuracy of the finite element model. However, the simulations show that the boom deploys six times faster than the real prototype. The quick deployment and violent end-of-deployment shock provokes the boom deployment dynamics to be unrealistic but still shows a reasonable behaviour given the nature of the deployment. Future improvements in the material and friction models will, most likely, provide us with a more realistic finite element model.

National Category
Applied Mechanics Composite Science and Engineering
Identifiers
urn:nbn:se:kth:diva-121766 (URN)
Conference
54thAIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and MaterialsConference in Boston (8–11 April 2013)
Note

QC 20130506

Available from: 2013-05-03 Created: 2013-05-03 Last updated: 2013-05-06Bibliographically approved
Sinn, T., McRobb, M., Wujek, A., Skogby, J., Rogberg, F., Wang, J., . . . Tibert, G. (2013). Lessons learned from REXUS12'S suaineadh experiment: Spinning deployment of a space Web in milli gravity. In: L. Ouwehand (Ed.), 21st ESA Symposium: European Rocket & Balloon Programmes and Related Research. Paper presented at 21st ESA Symposium om European Rocket and Balloon Programmes and Related Research; Thun; Switzerland; 9 June 2013 through 13 June 2013 (pp. 329-338). ESA Communications
Open this publication in new window or tab >>Lessons learned from REXUS12'S suaineadh experiment: Spinning deployment of a space Web in milli gravity
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2013 (English)In: 21st ESA Symposium: European Rocket & Balloon Programmes and Related Research / [ed] L. Ouwehand, ESA Communications , 2013, p. 329-338Conference paper, Published paper (Refereed)
Abstract [en]

On the 19th of March 2012, the Suaineadh experiment was launched onboard the sounding rocket REXUS 12 (Rocket Experiments for University Students) from the Swedish launch base ESRANGE in Kiruna. The Suaineadh experiment served as a technology demonstrator for a space web deployed by a spinning assembly. Following launch, the experiment was ejected from the ejection barrel located within the nosecone of the rocket. Centrifugal forces acting upon the space web spinning assembly were used to stabilise the experiment's platform. A specifically designed spinning reaction wheel, with an active control method, was used. Once the experiment's motion was controlled, a 2 m by 2 m space web is released. Four daughter sections situated in the corners of the square web served as masses to stabilise the web due to the centrifugal forces acting on them. The four daughter sections contained inertial measurement units (IMUs). After the launch of REXUS 12, the recovery helicopter was unable to locate the ejected experiment, but 22 pictures were received over the wireless connection between the experiment and the rocket. The last received picture was taken at the commencement of web deployment. Inspection of these pictures allowed the assumption that the experiment was fully functional after ejection, but probably through tumbling of either the experiment or the rocket, the wireless connection was interrupted. A recovery mission in the middle of August was only able to find the REXUS 12 motor and the payload impact location.

Place, publisher, year, edition, pages
ESA Communications, 2013
Series
ESA Special Publication, ISSN 0379-6566 ; SP-721
Keywords
Active control methods, Centrifugal Forces, Impact locations, Inertial measurement unit, Reaction wheels, Recovery mission, University students, Wireless connection
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:kth:diva-138842 (URN)2-s2.0-84893546094 (Scopus ID)978-92-9092-285-8 (ISBN)
Conference
21st ESA Symposium om European Rocket and Balloon Programmes and Related Research; Thun; Switzerland; 9 June 2013 through 13 June 2013
Note

QC 20140409

Available from: 2013-12-20 Created: 2013-12-20 Last updated: 2014-04-09Bibliographically approved
Organisations
Identifiers
ORCID iD: ORCID iD iconorcid.org/0000-0001-6802-8331

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