Emergency Detection System

The EDS is one element of several crew safety systems. EDS design is a coordinated effort of crew safety personnel from several NASA centers. The EDS senses initial development of conditions which could cause vehicle failure. The EDS reacts to these emergency situations in either of two ways. If breakup of the vehicle is imminent, an automatic abort sequence is initiated. If, however, the emergency condition is developing slowly enough, or is of such a nature that the flight crew can evaluate...

Electrical Power System

The electrical power system consists of six dc bus systems and a ground supplied ac bus system. In flight the electrical power system busses are energized by four zinc-silver oxide batteries. See figure 5-16 for battery characteristics. An integral heater and temperature probe are included in each battery. Power for battery heaters and for auxiliary hydraulic pump motors is supplied by GSE and is available only during prelaunch operations. Stage-mounted motor driven power transfer switches are...

Hold And Recycle Criteria

Interruption of the countdown due to equipment failure, weather or other causes may occur at any time. When the countdown is interrupted, subsequent feasible actions depend on the function taking place at the time. These actions include holding and or recycling. Feasible actions also, in sotnc cases, are affected by previous operations conducted on the vehicle, such as the number of pressure cycles the propellant tanks have undergone. A hold is defined as an interruption of the countdown for...

Lox Loading And Delivery

As the oxidizer in the bi-propellant propulsion system, lox is contained and delivered through a separate tank and delivery system (figure 4-13). The 345,000 gallon tank is filled through two 6-inch fill and drain lines. Shortly after T-6 hours lox loading begins. Three fill rates are used sequentially a 300 gpm for tank chilldown, a 1500 gpm slow fill rate to stabilize the liquid level and thus prevent structural damage, and a fast fill rate of 10,000 gpm. At approximately 95 full, the rate is...

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Plight Control System, Saturn S-1I February 1, 1965 SID 62-140. Flight Dynamics Analysis, Saturn V Launch Vehicle, AS-507 July 24. 1969 Boeing Report DS-lSS09 F -7. Flight Manual, Saturn V, SA-506 June 10, 1969 MSFC-MAN-506. Flight Manual, Saturn V, SA-507 August IS, 1969 M8FC-MAN-S07. Flight Operations Planning and Preparation for Manned Orbital Missions John H. Boynton and Christopher C. Kraft, Jr. AIAA Paper No. 66-904. Flight Performance Handbook for Powered Flight Operations Space...

Sivb Slingshot

After the S-IVB evasive maneuver is completed, the S-IVB slingshot procedure is initiated by maneuvering the the LV S-IVB IU SLA to the slingshot attitude. See figure 10-3 . A retrograde velocity differential is attained by a liquid oxygen dump through the J-2 engine, hydrogen propulsive venting, and a burn of the S-IVB APS ullage engines. This reduces vehicle velocity and changes the trajectory so that the LV coasts past the trailing side of the moon. The retrograde velocity differential is a...

Tail Service Mast

Provides lox fill and drain Interfaces. Umbilical wlthdrav.al by pneumatically driven compound parallel linkage device. Arm may be reconrected to vehicle from LCC. Retracted at T-30 seconds. Retract time 1s 13 seconds. Reconnect tine is approximately 5 minutes. S-IC Forward prsfiight . Provides pneumatic, electrical, and air-conditioning Interfaces. Umbilical withdrawal by pneumatic disconnect 1n conjunction with pneumatically driven block and tackle lanyard device....

Flame Trench

Checkout of the facilities during the absence of the launchrr and vehicle. The PTCR is a two-story hardened structure within the fill on the west side of the launch support structure. The launch pedestal and the deflector area are located immediately adjacent to this structure. Each of the floors of this structure measures approximately 136 feet by 56 feet. Entry is made from the west side of the launch support structure at ground level into the fint floor area. Instrumentation cabling from the...

Saturn Flight Control Computer

The center engine is fixed in place while the four outer engines are gimbaled in accordance with electrical signals from the flight control computer in the IU for thrust vector control. Each outboard engine is equipped with a separate, independent, closed-loop, hydraulic control system figure 5-10 . The system includes two servoactuators mounted perpendicular to each other that provide control over the vehicle pitch, roll and yaw axes. The servoactuators are capable of deflecting the engine 7...

Radio Command System

The CCS provides for digital data transmission from ground stations to the LVDC. This communications link is used to update guidance information, or to command certain other functions through the LVDC. Command data originates in the Mission Control Center, and is sent to remote stations of the MSFN for transmission to the launch vehicle. At the time of spacecraft separation from the IU S-1VB, the IU CCS transmitter will be commanded off for a short period of time, to preclude interference with...