Integrated test rig for tether hardware, real-time simulator and control algorithms: Robust momentum transfer validated

Details Integrated test rig for tether hardware, real-time simulator and control algorithms: Robust momentum transfer validated Integrated test rig for tether hardware, real-time simulator and control algorithms: Robust momentum transfer validated

Feb 2001

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2001aipc..552..532k&link_type=abstract

Space Technology and Applications International Forum - 2001. AIP Conference Proceedings, Volume 552, pp. 532-539 (2001).

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Spaceborne And Space Research Instruments, Apparatus, And Components, Artificial Earth Satellites, Observatories And Site Testing

Scientific paper

In preparation of the ESA demonstration mission for a tethered sample return capability from ISS, a breadboard test has been performed to validate the robust StarTrack tether dynamics control algorithms in conjunction with the constructed hardware. The proposed mission will use hardware inherited from the YES mission (Kruijff, 1999). A tether spool is holding a 7 kg, 35 km Dyneema tether. A 45 kg re-entry capsule will be ejected by springs and then deployed by gravity gradient. The dynamics are solely controlled by a barberpole type friction brake, similar to the SEDS hardware. This hardware is integrated in a test rig, based on the TMM&M stand, that has been upgraded to accommodate both a Space Part (abruptly applied initial tether deployment speed, fine tensiometer, real-time space tether simulator using the tensiometer measurements as input, take-up roller deploying the tether at a simulator-controlled speed) and a Satellite Part (infra-red beams inside the tether canister, control computer estimating deployed length and required extra braking from the IRED interrupts, `barberpole' friction brake). So the set-up allows for a tether deployment with closed loop control, all governed by a real-time comprehensive tether dynamics simulation. The tether deployment is based on the two-stage StarTrack deployment. This scheme stabilizes the tether at an intermediate vertical stage (with 3 km deployed). When the orbit and landing site have synchronized, a high-speed deployment follows to a large angle. When the fully deployed 35-km tether swings to the vertical at approximately 40 m/s, it is cut at a prefixed time optimized for landing site accuracy. The paper discusses the tests performed to characterize the designed hardware, maturing of the developed algorithms with respect to the hardware noise levels and the difficulties and limitations of the test rig. It is found that the set-up can be applied to a variety of tether pre-mission tests. It is shown that the performed tests give confidence in a successful flight application. .

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