Archives: Gmedia Albums

Relic of main alcohol valve with manufacturer code aeq (aeq = Bartoc & Co., Maschinenfabrik u. Giesserei Hedwikow,bei Caslau (Caslav) Czech Republic). An air (nitrogen) inlet pressure of 440 to 530 psi (30 to 36 Bar) was required to close this valve against its internal spring and the force of the turbo-pump. The large nut at the top is the connection for the fuel return (or ‘revolving’line) pipe, and the air and electrical input ports can be seen to the right (air), and left (elec.) just below this point. V2RH image

Original mpe 1944 drawing number 3207 C of main fuel valave. (mpe = Heimat-Artillerie-Park Karlshagen, Werk Nord Peenemünde).

Relic of main alcohol valve showing seat flange and fibre sealing washer. the ten fuel pass-through holes can be seen on the central core of the valve. V2RH image

Relic of main alcohol valve with manufacturer code aeq (aeq = Bartoc & Co., Maschinenfabrik u. Giesserei Hedwikow,bei Caslau (Caslav) Czech Republic). An air (nitrogen) inlet pressure of 440 to 530 psi (30 to 36 Bar) was required to close this valve against its internal spring and the force of the turbo-pump. The large nut to the right is the connection for the return (or ‘revolving’line) pipe. The valve is shown in the closed position. V2RH image

Photo shows main valves. Photo copyright: The Horst Beck Collection

This photo shows a presentation of important vales from the A4-V2 missile. From the left: Main alcohol/B stoff valve (from the centre of injector head. Alcohol tank valve. Main LOX valve (with sub valve). Alcohol (B stoff) tank pressuring valve. Image courtesy Horst Beck Collection

Photo shows main valves. Photo copyright: The Horst Beck Collection

Close-up detail showing independent pathway for fuel passing into injector head and fuel passed down from the head to be used for veil cooling system. Fig. A shows vertical passages for overall fuel feed to the head and Fig.B shows horizontal pathway for veil coolant fed from the head via the veil coolant distributor ring or manifold. 3D model by Alexander Savochkin

View of injector head showing 18 liquid propellant (LOX and fuel) diffuser cups and head fuel valve seating ring at centre, (see other images for insert and position nomenclature). Visible immediately below the valve seat are the large connecting holes that allow fuel to flow from the inlet manifold and cooling jacket to the injector space (some brass injector inserts can be seen through the holes) after the head fuel valve is released to be opened by the turbo-pump supply pressure. The four veil cooling inlet connectors are well shown as are two of the outlet connection holes immediately above them. 3D model by Alexander Savochkin

A close-up view of the head fuel valve mounting flange (showing 12 fastener holes). Visible immediately below the top flange are the large connecting holes that allow fuel to flow from the inlet manifold and cooling jacket to the injector space (some brass injector inserts can be seen through the holes) after the head fuel valve is released to be opened by the turbo-pump supply pressure.

Here the 18-pot head model has been cutaway to show the fuel cooling and fuel delivery spaces. the cooling jacket layer can be seen in the lowermost area of the head – below the centrally positioned fuel valve seat, between each cup at the lowest point, and ruining down toward the first set of veil cooling pores and the topmost coolant distributor ring. Note that the veil cooling system does not communicate with the regenerative cooling jacket and has its own feed pipes drawing fuel from the head injector space and not the cooling space. Visible immediately above the valve seat are the large connecting holes that allow fuel to flow from the inlet manifold and cooling jacket to the injector space after the head fuel valve is released to be opened by the turbo-pump supply pressure. 3D model by Alexander Savochkin

Liquid propellent (LOX and fuel) diffuser cup, showing three rings or echelons (A,D,& E) of brass injector inserts as well as two rows of drilled fuel feed holes. The LOX spray head is shown in the centre. Note the simple ‘shower head or watering can’ design of the LOX diffuser. A sealing washer can be seen fitted between the LOX diffuser and the steel cup. 3D model by Alexander Savochkin

Incomplete V2 missile on rail transporter. All 4 control compartments are well shown. The fuel tank connection pipe can be seen but not much else. All of the control equipment has been removed. Plainly visible is the chicken wire holding the fiber wool tank insulation in place. Today this would be called ‘Galvanised hexagonal network restraining matrix, and be supplied by a blue chip Aerospace company for $800 per square inch. In the 1940s, it was just chicken wire at a 2 dollars for a 100 ft roll.

Control compartments 1 (upper) & 4 (lower) Image copyright Imperial War Museum

Control compartments 3 showing gyro mounting platform with two gyros and DC motor driven 3 phase AC voltage generator. The alcohol tank pressurisation pipe is also shown running through the equipment bay (large silver coloured pipe). Image copyright Imperial War Museum

Control compartments 1. Image copyright Imperial War Museum

Control compartment 2 showing plywood separation panels, Oemig umformer (DC to 3 phase AC voltage generator), and voltage frequency control box. Towards the rear the ground connection plugs can just be seen and the mechanism of the cable release trap door (see cat flap!). Image copyright Imperial War Museum

Control compartment 1 top right, 2 top left, 3 bottom left, and 4 bottom right. The fuel tank pressurisation pipe upper connection point is well shown at about 6 o’clock (compartment 3) and just above and to the right the upper plate of the air (N) tank rack (tan colour). Image copyright Imperial War Museum
showing plywood separation panels, Oemig umform