Automatic checkout in the Saturn program.
Automation techniques for stage checkout in Saturn program noting equipment, time factor, etc
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Automation techniques for stage checkout in Saturn program noting equipment, time factor, etc
Acceptance checkout equipment spacecraft for centralized control and LEM and CSM systems testing
Self-contained and vehicle integrated on-board checkout systems, considering controller-evaluator and sensors
Onboard Checkout System /OCS/ design, considering system selection techniques, design development, equipment, etc, with orientation on OCS design by NASA/MSC
The Spitzer Space Telescope was injected into heliocentric orbit on August 25, 2003 to observe and study astrophysical phenomena in the infrared range of frequencies. The initial 60 days was dedicated to Spitzer's "In-Orbit Checkout (IOC)" efforts. During this time high levels of Helium venting were used to cool down the telescope. Attitude control was done using reaction wheels, which in turn were de-saturated using cold gas Nitrogen thrusting. Dense tracking data (nearly continuous) by the Deep Space network (DSN) were used to perform orbit determination and to assess any possible venting imbalance. Only Doppler data were available for navigation. This paper deals with navigation efforts during the IOC phase. It includes Dust Cover Ejection (DCE) monitoring, orbit determination strategy validation and results and assessment of non-gravitational accelerations acting on Spitzer including that due to possible imbalance in Helium venting.
Discussion of the checkout procedure for the equipment associated with the manned lunar landing program
Man-machine interaction during prelaunch testing and checkout of space vehicles
Known dc voltage is applied and then removed suddenly in a method to permit checkout of the mechanical and electrical condition of piezoelectric transducers of the cantilever beam type, while installed in a system.
Manufacturing checkout of orbital operational Saturn S-IVB stage and instrument unit for parking orbit operations
Input current measurement in testing of Centaur launch vehicle checkout
Telemetry checkout station is designed to automatically perform measurements on the vehicle telemetry. Its features include real-time digitizing and computer controlled station setup, data processing, and self-check. The station can handle a wide variety of automatic tests by changing its computer programs.
Study demonstrates that sonic signal analysis technique provides a powerful tool for mechanical component checkout. The technique also provides the unique capability of predicting component failures by detecting incipient malfunctions.
Computer program requirements for onboard checkout and data management system of Saturn/Apollo application program
Performance, design, test, and qualification requirements of computer programs for support system for on-board checkout and data management system of Saturn/Apollo application program
Interlocking plan for entire countdown checkout process by combining subsystems simulated as partially controlled stochastic process
Computerized simulation model of a launch vehicle/ground support equipment system optimizes assembly, checkout, and operation of the system. The model is used to determine performance parameters in three phases or modes - /1/ systems optimization techniques, /2/ operation analysis methodology, and /3/ systems effectiveness analysis technique.
Computer program technique, called Analog Computer Check-Out Routine Digitally /ACCORD/, generates complete setup and checkout data for an analog computer. In addition, the correctness of the analog program implementation is validated.
Test matrix technique for checkout and launching of Apollo-Saturn spacecraft