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CSM docked DAP/orbital assembly bending interaction-axial caseA digital autopilot which can provide attitude control for the entire Skylab orbital assembly using the service module reaction control jets is described. An important consideration is the potential interaction of the control system with the bending modes of the orbital assembly. Two aspects of this potential interaction were considered. The first was the possibility that bending induced rotations feeding back through the attitude sensor into the control system could produce an instability or self-sustained oscillation. The second was whether the jet activity commanded by the control system could produce excessive loads at any of the critical load points of the orbital assembly. Both aspects were studied by using analytic techniques and by running simulations on the all-digital simulator.
Document ID
19720026203
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Turnbull, J. F. (Massachusetts Inst. of Tech. Cambridge, MA, United States)
Jones, J. E. (Massachusetts Inst. of Tech. Cambridge, MA, United States)
Date Acquired
September 2, 2013
Publication Date
July 1, 1972
Subject Category
Space Vehicles
Report/Patent Number
E-2704
NASA-CR-128543
Accession Number
72N33853
Funding Number(s)
CONTRACT_GRANT: NAS9-4065
PROJECT: DSR PROJ. 55-23890
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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