Description and performance of the Saturn launch vehicle's navigation, guidance, and control system
Walter Haeussermann, United States. National Aeronautics and Space Administration, George C. Marshall Space Flight Center
National Aeronautics and Space Administration, 1970 - Technology & Engineering - 44 pages
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acceleration accuracy actuator AEGLE amplified angular attitude control attitude correction axis AY m/s bending mode bits burn center of mass center of pressure checkout CNMPUTE command components computation cycle control computer control frequency control sensors control system coordinate system crossrange cutoff data adapter DATA ADDRESS delay lines DETECTOR digital computer duplex dynamic earth orbit engine function gas bearing gimbal angle ground launch computer guidance and control GUTTAECE hicle hydraulic inertial input Instrument Unit Integrating Gyro Accelerometer intermediate IGM parameters Iterative Guidance Mode logic magnetic amplifiers major loop measured memory modules minor loop Navigation and Guidance parity bit Pendulous Integrating Gyro pitch pogo propellant propulsion rate gyro reliability S-IVB S-TVB Saturn launch vehicle SERVO servoloop shown in Figure signals sloshing stabilize stable platform steering SWITCH SELECTOR T-TVB telemetered telemetry third stage thrust vector torquer torques trajectory translunar injection triple modular redundancy TTTE values velocity versus VTTTR