Instrument Unit

The instrument unit umbilical service plate (figure 4-51) is located on the skin of the instrument unit between fin lines I and II. Routing, mounting, and retraction of ground support electrical, pneumatic, air-conditioning, and liquid nitrogen lines to the vehicle is provided by umbilical swing arm number 3 mounted on the umbilical tower at the 158 foot level. The umbilical tower-is so designed that it taper s away from the vehicle drift parameter anticipated during a launching. In addition,...

Info

Electromagnetic Docking Mechanism

S-IV Stage Hydrogen Vent Line, Swing Arm No. 3 Figure 4-42. S-IV Stage Hydrogen Vent Line, Swing Arm No. 3 disconnect the umbilical quick-release housing assembly. The second redundant method of release and disconnect was.provided by vehicle motion. If the pneumatic and hydraulic lanyard release and retract method failed, vehicle motion was supposed to shear the pins on the vehicle umbilical plate and the quick-release housing would be forcibly disconnected due to vehicle travel....

Introduction

The Redstone missile was basically the same type of vehicle as the V-2, with an increased payload and range. The major Redstone umbilical connection advances were in the electrical connections, the development and use of ball-lock release mechanisms, and the addition of a heater-cooler drop tank assembly. One of the significant differences of the ground power supply electrical wiring between the Redstone and the V-2 was the electrical cabling to the instrument compartment. The wiring on the...

Electrical

The. electrical connections were located at the base of fins II, III, and IV. These were AN-type connectors fitted with snap covers that closed at liftoff. These connectors provided ground support power to the following AC and DC supply, tactical networks, payload, measuring distributor network, guidance, and emergency cutoff (figure 2-12). multiple pneumatic coupling connector multiple pneumatic coupling connector hydrogen peroxide overflow and vent port

CH

Electromagnetic Docking Mechanism

Tail Service Mast Carrier Locking and Release Mechanism (Preliminary) cycle is shown in figure 5-8. Mast retraction is accomplished through a closed hydraulic system that is pneumatically charged and electrically controlled. Normal disconnect, release, and retraction time is 3. 0 seconds. In the event of pneumatic failure of the pushoff foot, continued vehicle motion will, through mechanical linkage, cause four pushoff pistons to extend and aid the release of the umbilical carrier....

Boattail Conditioning And Water Quench System

The boattail conditioning and water quench system (figure 4-1) is a fire protection system that transfers water to the boattail area for combating fires that may occur before vehicle liftoff. In addition, the installation is used in conjunction with the environmental control system and deluge purge system to provide a controlled atmosphere in the boattail area for personnel safety and vehicle protection during various phases of prelaunch preparation while the vehicle is on the launch platform....

Umbilical Coupling

Coupler For Umbilical

S-II Intermediate Propellant Coupling (Preliminary) disconnect of the propellant couplings and the umbilical carrier. Simultaneously with the pneumatic release of the ball-lock pins, pushoff pistons (four in the.carrier and two at each propellant coupling) extend, disconnecting the umbilical connections. Disconnect .of the carrier starts the withdrawal and retract sequence. The spacing of two propellant lines and the large umbilical carrier re-, quires three separate withdrawal...

Mercury Redstone Umbilical System

The heater-cooler tank assembly (figure 2-15) was attached to the missile and supported by a boom with a pivot point at the aft end (yoke and pin) and a retaining lock assembly (quick-release mechanism) at. the forward end of the mast. The quick-release mechanism was actuated by an explosive squib (figure 2-17). This was the first automatic, remote controlled lock and release mechanism developed and used by the United States. The mounting plate on which the retaining lock assembly...

Foreword

The purpose of this manual is to trace the evolution in design of umbilical connections for the V-2, Redstone, Jupiter, Saturn I (Block I and Block II), and Saturn V liquid propellant missiles and space vehicles. This manual compiles in one document the experience of approximately 20 years of research and development in the design and operation of umbilical connectors. The manual will provide National Aeronautics and Space Administration (NASA) and contractor personnel with guidelines for the...

Redstone

Chrysler Corporation Missile Division, n. d. ME-M48, Boom Flexure Study of the Redstone External Cooler Assembly. Technical Memorandum, Chrysler Corporation, Missile Division, 1961. ME-M72, LQX Replenishing Valve Icing Failures. Technical Memorandum, Chrysler Corporation, Missile Division, 1961. B-480, Liquid Nitrogen Heater Cooler Coupling Device Test and Drop Tests. Technical Bulletin, Chrysler Corporation, Missile Division, 1958. B-481, Evaluation Test of the Redstone...

Lox Venting

The LOX venting connections (figure 4-10) are located at the forward end of the vehicle. The 7-inch vent line connects to LrOX container LI at a point above the service structure's first service platform. The two 4-inch vent lines connect to the vent valves on LOX containers L3 and L4 in the same general location as the 7-inch LOX vent assembly. Each vent line is 50 feet long and serves to direct the venting LOX away from the workmen working on the tower at this level. Figure 4-10. Lox Venting...

Lox Replenishing

The LOX replenishing arm assembly (figure 3-14), mounted on the inside surface of the auxiliary ring near fin I, connected the LOX replenishing line to the missile. The LOX replenishing arm assembly was installed at the missile assembly and maintenance area. A line from the LOX replenishing arm to a connection at the base of the LOX filling mast connected the arm to the LOX transfer lines. Also, a line connected the LOX replenishing arm to the Y-connection of the LOX start coupling. A 2-inch...

Pneumatic

The multiple pneumatic coupling connector figure 2-9 was located in a balcony housing on the lower outside of the tail unit between fins II and HI. The coupling provided for ground control of on-board pneumatic systems, including fill of the high pressure spheres, pressuri-zation of the LOX tank, LOX replenishing control, alcohol bubbling line, pressurization of igniter alcohol tank, LOX vent control, and LOX sensing. The balcony also housed the alcohol injector purge line and the alcohol seal...

FUELING

The fuel filling assembly figure 3-3 , mounted on the auxiliary ring between fins I and IV, conducted RP- 1 fuel from the fuel supply hose to the filling port on the missile tail unit. The filling assembly consisted of a 6-inch stainless steel tube approximately 142 inches in length, a masthead assembly, a.lower support bracket assembly, ring supports, a hydraulic arrestor, and a pressure switch. The masthead assembly consisted of a 90-degree elbow, a locking and release mechanism,...

Sivb Stage

Saturn Launch Umbilical Carrier

All the service lines on the arm interface in a common umbilical carrier figure 5-14 . This arm is located at the 220 foot level on the LUT. The lines include two 6-inch ID propellant lines, a 10-inch air-conditioning line, six electrical cables, and eleven pneumatic and small cryogenic lines. The carrier connects at vehicle station 27 60.000. The propellant couplings are the ball and sphere type, with an expandable bellows providing the sealing force. Pneumatic and electrical...

Apollo Spacecraft

Saturn Launch Umbilical Carrier

The umbilical requirements for the arm have not been definitely established at this time however, all lines will interface in a common umbilical carrier similar to that used for the Saturn I Apollo spacecraft figure 5-16 . This arm is located between the 300 and 320 foot levels on the LUT. Tentatively, the lines will include a 6-inch air-conditioning duct, Figure 5-16. Service Module Umbilical three electrical cables, five pneumatic and small cryogenic lines, and two coolant...

Sic Stage

Apollo Saturn Hold Down Arm

Three tail service masts located on the deck of the launcher figure 5-1 provide the means of routing, connecting, releasing, and retracting the umbilical service lines to the tail section of the.S-IC stage from the LUT interface. Figure 5-1. Tail Service Mast Locations Preliminary Figure 5-1. Tail Service Mast Locations Preliminary Each tail service mast figure 5-2 is basically the same for all locations. The number, kind, and type of service lines differ at each location....

Saturn V Arming Tower

The Saturn V will be a multistage, liquid-fueled launch vehicle us d for the Apollo manned lunar and planetary exploration program. Five engines, fueled with a mixture of RF-1 diesel and LOX, power the S-IC, first stage of the launch vehicle. Engines, fueled with a mixture of liquid hydrogen LH and LOX, power the S-II, second stage, and the S-IVB, third stage of the vehicle. An instrument unit containing in-flight control and monitoring equipment will be located between the S-IVB stage and the...

Siv Stage

Umbilical Systems

Swing Arm Number 2 Saturn I Block II . Swing arm number 2 provides for routing and support of the propellant loading lines, air-conditioning duct, electrical cables, and pneumatic and hydraulic lines to the S-IV stage. basic swing arm has an extension arm added figure 4-37 . This is due to the increased distance between the umbilical tower and the vehicle at the 128-foot level. The upper portion of the extension has pulleys and guides to aid in support and movement of the retract arm assembly...

Lox Fueling Coupler

Alcohol valve and flowed into the alcohol manifold surrounding the -thrust chamber. The inert fluid provided lor smoother ignition. After the lithium chloride had been loaded and the main alcohol valve had been closed, the connection from the lithium chloride tank and pump was disconnected and the alcohol filling operation began. The alcohol was metered as it was pumped into the missile. In addition to filling the missile with alcohol, an igniter alcohol container located on the launcher,...

Section V Saturn V

S-II Stage . . . S-1VB Stage Apollo Spacecraft 1-1 Alcohol Fueling 1-2 Lox and Hydrogen Peroxide Fueling Connections 1-2 1-3 Lox and Hydrogen Peroxide Fueling 1-3 1-4 Pumping Hydrogen Peroxide to Measuring Tank 1-3 1-5 Hoisting Sodium Permanganate Tank to Fueling Level . . 1-4 1-6 Fueling Sodium Permanganate 1-4 1-7 Lox Vent 1-8 Lox Topping Valve . . 1-5 1-9 Lox Topping 1-10 Launch Platform with Umbilical Connections 1-7 1-11 Vehicle Pneumatic Five Way Coupling . ....