Design and development of a gossamer sail system for deorbiting in low earth orbit

Fernández, Juan M.; Visagie, Lourens; Schenk, Mark; Stohlman, Olive R.; Aglietti, Guglielmo S.; Lappas, Vaios; Erb, Sven

doi:10.1016/j.actaastro.2014.06.018

Cited by 74 publications

(42 citation statements)

References 18 publications

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“…The main hardware components were the electrically controlled panels, central mechanism deployment module and sails. Normally, the centrifugal force deployment of a space web could be split into two steps [3,16,17,18]: in the first step, booms or panels are extended slowly and quasi-statically controlled by guide rollers or other mechanisms; in the second step, the web is extended to a final flat shape by the centrifugal force. However, rollers or other extending mechanisms may take up too much space for small deployable structures.…”

Section: Introductionmentioning

confidence: 99%

“…Experiments are required to verify the viability of the proposed folding and deployment. However, the zero-g condition in space is difficult to simulate on ground tests for large scale web deployment [3,20]. Computational simulations, e.g., the finite element method [11,21], multi-particle models [19,22] and analytical methods [9,11,12,23] have been used to analyze the dynamics of centrifugal force deployment.…”

Section: Introductionmentioning

confidence: 99%

“…A space web is a flexible structure tensioned by thrusters or by centrifugal forces in a spinning assembly. These webs can act as lightweight platforms for construction of large structures in space [1][2][3]. The idea of using space webs originates from the Japanese "Furoshiki Satellite" [4][5][6][7][8], a large membrane structure.…”

Section: Introductionmentioning

confidence: 99%

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Post-launch analysis of the deployment dynamics of a space web sounding rocket experiment

et al. 2016

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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 2×2m2 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

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Post-launch analysis of the deployment dynamics of a space web sounding rocket experiment

et al. 2016

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“…Another example of a telescopic structure for a drag-sail deployment mechanism can be seen in the European Space Agency project Gossamer Deorbiter, 14) which utilizes a massive portion of the structure for the telescope, and is therefore very large. One of the technical challenges of the slender telescope configuration of the DOM is to ensure mechanical strength and stiffness against mechanical launch conditions.…”

Section: Design Challengesmentioning

confidence: 99%

“…Some sail deployment mechanisms have, on the contrary, a single square sail instead of separate triangle films. [14][15][16] In addition, different types of deployment force generation methods exist; they use booms rolled around the spindle with the sail material. Examples include the centrifugal force demonstrated by IKAROS 15) and circumferential force.…”

Section: Introductionmentioning

confidence: 99%

Structural Design of De-orbit Mechanism Demonstration CubeSat FREEDOM

Mogi

Kuwahara

Uto³

2016

AEROSPACE TECHNOLOGY JAPAN

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With increasing number of microsatellite launches, the mitigation of space debris is becoming a pressing problem. An easy-handling de-orbit device is required to deal with this issue. However, existing devices face some problems when being installed in a microsatellite. These problems include the volume, direction in which the booms are extended, and battery consumption. Since 2010, Tohoku University and Nakashimada Engineering Works, Ltd., have been developing a De-Orbit Mechanism (DOM) that deploys a thin film to drag microsatellites down to reenter the atmosphere. A DOM deployment procedure was devised to achieve light weight and low power consumption. For an early orbit demonstration of the DOM technology, Tohoku University and Nakashimada Engineering Works, Ltd., are developing a single-unit-size CubeSat named "FREEDOM," which aims to demonstrate a DOM. The DOM for FREEDOM is capable of deploying a thin square film with edge lengths of 1500 mm out of a total satellite mass of less than 1.33 kg. The film size vs. satellite weight ratio of the FREEDOM will be the highest in Japan and is one of the highest in the world. FREEDOM is planned to be delivered to the International Space Station by the Japan Aerospace Exploration Agency and will be deployed into Low Earth Orbit (LEO) in 2016. This paper describes the structural design and verification results of FREEDOM.

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