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A passively controlled appendage deployment system for the San Marco D/L spacecraftThe analytical simulation of deployment dynamics of these two axis concepts as well as the evolution of practical designs for the add on deployable inertia boom units is described. With the boom free to swing back in response to Coriolis forces as well as outwards in response to centrifugal forces, the kinematics of motion are complex but admit the possibility of absorbing deployment energy in frictional or other damping devices about the radial axis, where large amplitude motions can occur and where the design envelope allows more available volume. An acceptable range is defined for frictional damping for any given spin rate. Inadequate damping allows boom motions which strike the spacecraft; excessive damping causes the boom to swing out and latch with damaging violence. The acceptable range is a design parameter and must accommodate spin rate tolerance and also the tolerance and repeatability of the damping mechanisms.
Document ID
19840017013
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lang, W. E.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Frisch, H. P.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Schwartz, D. A.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
August 12, 2013
Publication Date
May 1, 1984
Publication Information
Publication: The 18th Aerospace Mech. Symp.
Subject Category
Mechanical Engineering
Accession Number
84N25081
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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