By Maftoon Naqshband
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The coarse-pointing/gimbal assembly includes elevation and lateral gimbals with torque motors and resolvers and allows arbitrary orientation of the vernier fine-pointing axis relative to the Shuttle. The vernier pointing assembly attaches between the gimbal/vernier interface structure and the payload mounting plate. It is noted that the payload mounting plate will attach directly to this interface structure for those experiments not requiring the vernier accuracy or roll freedom. The vernier includes three axial magnetic bearing assemblies (two shown), two radial magnetic bearing assemblies, and a roll motor and resolver.
1976). CXOflHMOCTL H CKOpocTB cxoflMMocTja UTeparaBHHx CTOxacTH^ecKHx ajiropMTMOB. I . OÖIHHÄ cjiyqaö. B «ypHane "AßTOMaTHica H TejceMexaHHKa" f $ 12. M. Π. TapaceHKo. (1978). 3KCTpeMajiBHaH paBHOHaBMraipafl. "Hayica11, MocKBa. OPTIMAL CONTROL OF LARGE ANGLE ATTITUDE MANEUVERS FOR FLEXIBLE SPACECRAFT R. W. Longman1 and K. T. Alf riend Space Systems Division, Naval Research Laboratory, Washington, DC. A. Abstract. Future satellite projects will require that methods be developed for slewing yery large and very flexible space vehicles through large angles, and simultaneously controlling the shape of the vehicles.
I XB \à ( XB , Y B , Z B ] Fig. 2 Cantangle a 0 and slit-pattern geometry. Fig. 3 Direction to star known in {xc} (sky model). p = constant rotation matrix (known) 4 {*«} ■ TBL {\} T ? L U ( t ) , e(t), ψ(ΐ)} time-varying rotation matrix 4 (V>P) Fig. 4 Fig. 5 projection of star on slit pattern plane, Eq. (2) Transformations for determining the (time-varying) projection of a known star on the slit pattern plane. Errors in the estimated transverse attitude angles. t(s) Fig. 6 Estimated standard deviations of estimated transverse attitude angles.