The dynamics instrumentation is described which will be flown in the end-mass of the first tethered satellite to be deployed from a Delta II launch vehicle with the SEDS (Small Expendable Deployer System) low-tension deployer. Transducers, signal conditioning, power supply design, data acquisition procedures and data recovery plans are discussed. The effects of temperature variations and other potential error sources are considered.
End-mass instrumentation for the first SEDS/Delta II mission
1990-01-01
Conference paper
No indication
English
Post Deployment Recontact Issues for the SEDS/SEDSAT Mission
British Library Conference Proceedings | 1996
|NTRS | 2019
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