A detailed study of manual backup control systems for the Saturn 5 launch vehicle
Reliability study of Saturn 5 launch vehicle manual backup control system
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Reliability study of Saturn 5 launch vehicle manual backup control system
The Saturn Launch Vehicle Operations Simulator (LVOS) was developed for NASA at Kennedy Space Center. LVOS simulates the Saturn launch vehicle and its ground support equipment. The simulator was intended primarily to be used as a launch crew trainer but it is also being used for test procedure and software validation. A NASA/contractor team of engineers and programmers implemented the simulator after the Apollo XI lunar landing during the low activity periods between launches.
The launch operations test and checkout plan is a planning document that establishes all launch site checkout activity, including the individual tests and sequence of testing required to fulfill the development center and KSC test and checkout requirements. This volume contains the launch vehicle test and checkout plan encompassing S-1B, S-4B, IU stage, and ground support equipment tests. The plan is based upon AS-208 flow utilizing a manned spacecraft, LUT 1, and launch pad 39B facilities.
Nitrogen and helium storage facility for Launch Complex 37B of Saturn I /SA-10/ launch vehicle
Evaluating land landing problem from prelaunch measured wind effects on launch escape vehicle aborts from Saturn 1B launch vehicle
Saturn V launch vehicle digital computer and data adapter for checkout and guidance functions
Design approach, testing and checkout program of Saturn V launch vehicle
S-II stage of Saturn V launch vehicle, its mission, stage systems, structural components and fabrication techniques
The Saturn launch vehicle program has become a major element in our national space effort within little more than 3 years. At the beginning of the program, in 1958, various Saturn configurations were planned to lift instrumented payloads of 20,000 to 40,000 lb. into Earth orbit. As research and development progressed, it became apparent that the vehicle design approach had far more potential than anticipated that it was, in fact, a breakthrough into a new class of heavy launch vehicles. Thus, within the space of a few years, it was possible to consider even more advanced missions. In addition to placing multiton payloads in orbit, we can seriously conceive sending over 90,000 lb. of instruments on escape missions, using advanced Saturn-class vehicles. With these vehicles, we plan to accomplish lunar reconnaissance and manned lunar landings scheduled for the latter part of this decade. Likewise, these vehicles will permit flight tests of advanced nuclear power plants and stages.
Advanced post-Saturn earth launch vehicle design and chemonuclear propulsion system performance
Evaluation of sandwich shaped nose fairings for Saturn launch vehicle
Effects of flow separation on aeroelastic characteristics of Saturn IB and Saturn V launch vehicles with Apollo payload
Wind tunnel stability tests of scale model Saturn IB/Apollo, and Saturn IB/Apollo/ Minuteman launch vehicle
Technical development status of S-IC stage of Saturn V launch vehicle
Saturn launch vehicle systems in terms of design, operating characteristics and potential applications, showing need for reusable space shuttle systems
Saturn launch vehicle gust penetration loads, presenting separated flow and associated time lag effects
Saturn V launch vehicle and Apollo spacecraft hardware systems applied to unmanned exploration of Jupiter
Systems analysis applied to identification of Saturn V launch vehicle support system requirements and establishment of baseline logic for vehicle prelaunch processing simulation and systems optimization