The design of a large angle three-axis attitude servomechanism for spacecraft
Design equations for large angle three-axis attitude servomechanism for controlling spacecraft
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Design equations for large angle three-axis attitude servomechanism for controlling spacecraft
Compensatory tracking experiments between single and two-axis tracking systems, determining training effects on model parameters of human operator
Operator performance in single and two-axis compensatory tracking systems
Spin axis for spinning satellite determined from range rate data
Equations of motion and gyroscopic stability of single axis platform gyroscope
Velocity axis response of ion mass spectrometer on spherical satellite calculated based on Explorer 32 data
Three axis attitude control system for spacecraft under random perturbations
Errors due to solar radiation pressure effect, when determining semimajor axis of satellite orbit correcting mean motion
Rectification errors of strapdown single axis platform spacecraft guidance system under structural vibration inputs, using digital computer prediction methods
Torqued two axis gimbaled boom actuator satellite attitude control
This Phase II Body-Fixed, Three-Axis Reference System Study Final Report is the result of a follow-on contract awarded by NASAIMSFC to TRW Systems in April 1966, under Contract No, NASS-20209. of the Phase I1 Study was to refine and supplement the strapdown inertial ’ reference assembly (SIRA), software, airborne computer, and alignment analyses performed during Phase I of the same contract. The purpose Specifically, the Phase I results in many areas were those which could be achieved using simplifying assumptions (linearization) and hand analyses. It was the purpose of the Phase I1 studies to investigate the validity of the Phase I results by means of more sophisticated computer simulations, in which no simplifying assumptions were made, for each of the areas analyzed. The Phase 11 analyses were directed, therefore, at confirming the analytical feasibility asserted by the Phase I results.
Two-axis winching and traversing device is used for installing liquid-propellant rocket-engine fuel and liquid oxygen suction ducts between the valves and the rocket engine on a test stand. The device raises and maneuvers the duct into the required position where it can be safely installed by mechanics.
Responsiveness of three axis, large angle attitude control systems of highly maneuverable spacecraft capable of tracking time-varying target attitudes
Performance characteristics of grease lubricated spiral groove bearings for gyro spin axis
Galactic-Jupiter probe spin axis direction determination
Nimbus-D attitude control system tested about each of its control axis
Discharge nozzle coefficients for thick plate orifices with approach flow perpendicular and inclined to orifice axis
Wall streaming, creeping and parade motion in Ni-Fe films excited by hard axis pulses