Ranger 6-9 spacecraft reliability study final report
Analytical model for determining spacecraft reliability of Rangers VI through IX during five phases of flight based on system failure effects analysis
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Analytical model for determining spacecraft reliability of Rangers VI through IX during five phases of flight based on system failure effects analysis
Television subsystem for Ranger missions
Subsystem analysis of Ranger television subsystem
Ranger television subsystem design
Evaluation of Ranger television subsystem - flight model performance
Ranger and Surveyor spacecraft systems engineering in terms of lunar exploration objectives, system design and flight experience
Earth based radio tracking and orbit determination accuracies for Ranger and Mariner missions
Electronic and electromechanical systems used in spacecraft control systems
Six-camera two channel television subsystem designed for use in Ranger VI through IX SPACECRAFT
Ranger lunar probe photograph analysis, crater size and shape measurements and dominant topographic features including camera and command systems
Rangers VI through IX TV subsystem testing under simulation of Atlas and Agena launch characteristics, midcourse motor action and deep space environment
Earth based radio tracking and orbit determination accuracies for Ranger and Mariner missions
Ranger lunar observation program objectives and accomplishments
Extensive vibration measurements from ground test acoustic simulations of Ranger spacecraft launch, and transonic vibration excitation modes
Vibration tests on Ranger spacecraft with single point control of input vibratory accelerations
Ground test acoustic simulation of liftoff and transonic vibration applied to Ranger flight vibration data
The dynamic environment of the Ranger spacecraft (I through IX)during the launch portion of flight is defined in this Report. Flight data from each of nine spacecraft launches have been reviewed and are included. The environments receiving emphasis herein include liftoff acoustics, liftoff and transonic vibration, and the transient vibrations of the various pyrotechnic and staging events in the launch sequence. The systems for data acquisition and analysis are briefly described. In addition, post-flight comparison of flight data and ground test specification levels is made, and the dynamic test program is briefly discussed.
Statistical analysis of pyrotechnic shock data from Ranger and Mariner test programs