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Available online:PDF According to this, the ASC-15 and the ST-90 were used in the active guidance system, while the ST-124 was part of the passenger system. "Saturn V Flight Manual SA-507." A 244-page description of Saturn-Apollo 507, dated 5 October 1969. Includes a chapter about the instrument unit (Section VII, PDF page 149). Available on ...
The reduction in parts costs is aided by using selective laser melting in the production of some metallic parts. [13] [18] The resulting F-1B engine is intended to produce 1,800,000 lbf (8.0 MN) of thrust at sea level, a 15% increase over the approximate 1,550,000 lbf (6.9 MN) of thrust that the mature Apollo 15 F-1 engines produced.
The J-2, commonly known as Rocketdyne J-2, was a liquid-fuel cryogenic rocket engine used on NASA's Saturn IB and Saturn V launch vehicles. Built in the United States by Rocketdyne, the J-2 burned cryogenic liquid hydrogen (LH 2) and liquid oxygen (LOX) propellants, with each engine producing 1,033.1 kN (232,250 lb f) of thrust in vacuum.
The cable was connected to a cylindrical weight inside a tube. The weight rested on a lever controlled by a pneumatic solenoid valve. When the valve was actuated from the Launch Control Center (LCC), the pneumatic pressure of 600 psi (4,100 kPa) GN2 (nitrogen gas) rotated the lever down allowing the weight to drop down the tube.
The Apollo Command Module reentered with the center of mass offset from the center line; this caused the capsule to assume an angled attitude through the air, providing a sideways lift to be used for directional control. Rotational thrusters were used to steer the capsule under either automatic or manual control by changing the lift vector.
Launch of AS-506 space vehicle on July 16, 1969, at pad 39A for mission Apollo 11 to land the first men on the Moon. The Apollo program was a United States human spaceflight program carried out from 1961 to 1972 by the National Aeronautics and Space Administration (NASA), which landed the first astronauts on the Moon. [1]
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 ...
The Orion spacecraft, which was developed to follow the Space Shuttle program, uses a Mercury and Apollo-style escape rocket system, while an alternative system, called the Max Launch Abort System (MLAS), [4] was investigated and would have used existing solid-rocket motors integrated into the bullet-shaped protective launch shroud.