SEDS deployer design and flight performance

Carroll, Joseph A.

doi:10.2514/6.1993-4764

Cited by 49 publications

(21 citation statements)

References 1 publication

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“…The concept proposed by the managers of the YES2 project is an idea originally devised by Carroll [5] based on the controlled use of friction between the deploying tether and a cylindrical surface around which a few turns of tether are arranged. The principal behind this is that the frictional interaction is maximised for a relatively small volume, and in a controllable way by means of the number of turns of tether that are allowed to slide round the cylinder.…”

Section: Deployment Brake Conceptmentioning

confidence: 99%

“…Five models were considered for the brake, starting with the relatively simple model (Model 1) first proposed by Carroll [5] which considered the energy converted when the tether undergoes a shock due to braking for example. This model was useful for establishing the barberpole concept but does not involve pole design parameters, so cannot be used further.…”

Section: Mathematical Models For the Barberpole Brakementioning

confidence: 99%

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Analysis and design of a friction brake for momentum exchange propulsion tethers

Lennert

Cartmell

2006

Acta Astronautica

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Section: Deployment Brake Conceptmentioning

confidence: 99%

Section: Mathematical Models For the Barberpole Brakementioning

confidence: 99%

Analysis and design of a friction brake for momentum exchange propulsion tethers

Lennert

Cartmell

2006

Acta Astronautica

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“…The usual strand tether deployers can be classified into the Tethered Satellite System (TSS) series type reel systems [10] and Small Expendable Deployer System (SEDS) type fixed spool systems [11]. The TSS type deployer can control both deployment and retrieval of the tether system by driving motorized reel, but the use of active control devices increases the complexity of system dramatically.…”

Section: Quick Deployment Of the Tape Tethermentioning

confidence: 99%

Sounding rocket experiment of bare electrodynamic tether system

et al. 2009

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An overview of a sounding rocket, S-520-25th, project on space tether technology experiment is presented. The project is prepared by an international research group consisting of Japanese, European, American, and Australian researchers. The sounding rocket will be assembled by the ISAS/JAXA and will be launched in the summer of 2009. The sounding rocket mission includes two engineering experiments and two scientific experiments. These experiments consist of the deployment of bare electrodynamic tape tether in space, a quick ignition test of hollow cathode system in space, the demonstration of bare electrodynamic tether system in space, and the test of the OML (orbital-motion-limit) current collection theory.

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“…The success of both SEDS-I (which utilized an open-loop control scheme) and SEDS-II was due in large part to the deployment hardware, which was considerably simpler than that used by the Tethered Subsatellite System 1 (TSS-1), which jammed early during the deployment phase. The major difference in the deployment hardware lies in the fact that the SEDS deployer uses a passive, friction-brake to control the speed of the deployment whereas the TSS-1 mission used an active deployer driven by a reel mechanism [7].…”

Section: Introductionmentioning

confidence: 99%

Deployment/retrieval optimization for flexible tethered satellite systems

Williams¹

2007

Nonlinear Dyn

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A methodology for deployment/retrieval optimization of tethered satellite systems is presented. Previous research has focused on the case where the tether is modeled as an inelastic, straight rod for the determination of optimal system trajectories. However, the tether shape and string vibrations can often be very important, particularly when the deployment/retrieval speed changes rapidly, or when external forces such as aerodynamic drag or electrodynamic forces are present. An efficient mathematical model for flexible tethered systems is first derived, which treats the tether as composed of a system of lumped masses connected via inelastic links. A tension control law is presented based on a discretization of the tether length dynamics via Chebyshev polynomials. A scheme that minimizes the second derivative of length over the trajectory based on physically meaningful coefficients is presented. This is utilized in conjunction with evolutionary optimization methods to minimize the rigid body and flexible modes of the system during deployment/retrieval. It is shown that only a very small number of parameters are required to generate accurate trajectories. The results are compared to the case where the tether is modeled as a straight rod. P. Williams ( ) 1/4 Maylands

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SEDS deployer design and flight performance

Cited by 49 publications

References 1 publication

Analysis and design of a friction brake for momentum exchange propulsion tethers

Analysis and design of a friction brake for momentum exchange propulsion tethers

Sounding rocket experiment of bare electrodynamic tether system

Deployment/retrieval optimization for flexible tethered satellite systems

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