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The Apollo flight computer was the first computer to use silicon IC chips. [15] While the Block I version used 4,100 ICs, each containing a single three-input NOR gate, the later Block II version (used in the crewed flights) used about 2,800 ICs, mostly dual three-input NOR gates and smaller numbers of expanders and sense amplifiers.
Apollo Launch Escape System diagram. If the rocket failed in the last five minutes before launch, the CM and the launch escape system (LES, see figure) would separate from the remainder of the rocket below with the LES propelling itself and the CM beneath it upward and eastward to the sea using a small solid-fueled motor (the launch escape motor) at the top of the tower on the launch escape ...
Apollo 1: February 21, 1967 Launch Complex 34 (planned) Gus Grissom Ed White Roger B. Chaffee: Saturn IB (SA-204) — — — Never launched. On January 27, 1967, a fire in the command module during a launch pad test killed the crew and destroyed the module. This flight was originally designated AS-204, and was renamed to Apollo 1 at the ...
Domain/OS is the discontinued operating system used by the Apollo/Domain line of workstations manufactured by Apollo Computer. It was originally launched in 1981 as AEGIS, and was rebranded to Domain/OS in 1988 when Unix environments were added to the operating system. It is one of the early distributed operating systems. [2]
The docking mechanism of the Apollo was a "probe and drogue" system designed to allow the Apollo Command/Service Module (CSM) to dock with the Apollo Lunar Module.The same system was later used for the Skylab 2, Skylab 3 and Skylab 4 CSMs to dock with the Skylab space station, and the Apollo–Soyuz Test Project CSM to dock with a Docking Module adapter which allowed docking with the Soyuz 19 ...
Core rope memory is a form of read-only memory (ROM) for computers.It was used in the UNIVAC I (Universal Automatic Computer I) and the UNIVAC II, developed by the Eckert-Mauchly Computer Corporation in the 1950s, as it was a popular technology for program and data storage in that era.
The ascent propulsion system (APS) or lunar module ascent engine (LMAE) is a fixed-thrust hypergolic rocket engine developed by Bell Aerosystems for use in the Apollo Lunar Module ascent stage. It used Aerozine 50 fuel, and N
Example - a maximum of 400N of force can be applied in the last 50, 300 and 500 mm of travel of a gate, after the initial impact the force must drop to 150N within 0.75 of a second and reduce to 25N within 5 seconds.
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