This library features material related to the A4-V2 missile's combined propellant injection head, combustion chamber, and nozzle; or what is more commonly referred to simply as - the combustion chamber.
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
| Album | Equipment bays |
| Category | Guidence |
LEV-3 V2 missile gyroscope system with mounting plate. The third component of this system, the Muller gyroscopic accelerometer, is missing - the 2x mounting points can be seen on the right-hand side of the mounting plate.
| Album | Missile guidance equipment |
| Categories | Missile guidence, Sub-assemblies |
Photo shows rare surviving complete set of 8 lead acid battery cells from one of the V2 rocket's 32 volt (100 amp) lead acid batteries. Two sets of batteries like this were used to provide the direct current (DC) voltage used aboard the V2 missile to power the DC to 3-phase alternating current (AC) generators, that in turn, powered the gyroscopes, electro-hydraulic servos, trim motors and other vital guidance and control devices. Photo copyright: The Horst Beck Collection
Photo shows rare surviving 1.2 volt cell from the V2 missile's 50 volt command or signalling battery used in its gyro guidance system (note, the terminal connection on the left is missing from this exhibit, it would be identical to the one on the right). This wet nickel-cadmium battery cell was combined in pairs to a total set of 21 providing a 50.4 voltage at 300mA. The cells were contained in a wooden box that was held on a rack in equipment bay III. Its function was to provide the direct current (DC) signalling voltage that communicated the moment to moment resistance of the gyroscope's potentiometers to the analog guidance computer (Mischgerät = Mixer-device or control amplifier) aboard the V2 missile. It was critical that the signalling voltage was maintained between 48 and 50.4 volts. Photo copyright: The Horst Beck Collection
The Muller mechanical or Pendulous Integrating Gyroscopic Accelerometer - today normally referred to as a PIGA. Designed by Fritz K Muller.
The J device no1 (J Gerate Eins). The full name of this device is: the Muller Pendulous (or mechanical) Integrating Gyroscopic Accelerometer - today normally referred to as a PIGA. The device, designed by Fritz K Muller, operates as a switch to initiate rocket engine shutdown and is able to smoothly record and accumulate every moment of acceleration, without any kind of recording resolution or discrete time interval limit, of the rocket's entire motor burn phase, and at the same time process this accumulated acceleration with respect to time as a gradually increasing velocity. In the case of the V2 missile, when the correct predetermined velocity is reached, the velicity sufficient to achieve the desired range of the missile, the device trips the relays that close valves that shutdown the supply of steam to the turbo-pump, and thus shutdown the rocket motor itself.
