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Aviation History
1955
1955 - 0009.PDF
7 January 1955I 'hese small sketches show the two main erial vehicles, the battery radar tracker nd (right) the beam transmitter. Both are neat, yet rugged, vehicles, able to goI nywhere that wheeled traffic could be assigned. (e) A switching amplifier for automatically changing over from coarse to fine beam control and also for the transformation of conical into cylindrical co-ordinates and polar into cartesian co-ordinates. (f) A computing amplifier and gyro assembly for the introduction ofthe steering coefficients as a function of time, for the transformation of space into missile co-ordinates to compensate for rolling and also fordamping missile oscillations about the transverse axes. (g) An electro-hydraulic servo system for steering the missile bydeviating the thrust chamber and propelling nozzle and moving the fins. (h) A source of auxiliary power consisting of a nitrogen-driven turbineand a synchro-generator. Naturally enough, a guided missile is an extremely costly weaponand, in peacetime, it must be made recoverable wherever possible. The present Oerlikon Type 54 can, in fact, be recovered aftertest and troop-training flights, and for this purpose is arranged to break into two portions, each equipped with a parachute. At apre-determined time after burn-out, the missile is separated into a forward portion, housing the electronic circuits, and a rearsection accommodating the rocket motor. Each section is then allowed to fall freely, for a time depending upon the estimatedburn-out height, in order to prevent the two sections from drifting over great distances. At a comparatively low altitude, the para-chute in each section is streamed automatically. To guard against loss of control of the missile for any reasonwhatever, it is possible to cut off the rocket motor by radio and effect emergency separation into the nose and tail portions withimmediate deployment of the parachutes. As might be expected, present missiles are fitted with a tele-metering system, which supervises the steering and flight perform- ice during test and training flights. As already mentioned, the guidance of the powered part of theflight path is effected by deflecting the entire thrust chamber (and with it the propelling gas jet) with assistance from the fourtail fins which are deflected simultaneously with the thrust chamber and thus produce the required turning moment aboutthe centre of gravity of the missile. After burn-out, the propelling jet no longer exists, and all guidance has to come from the tailfins. The steering system is therefore so controlled that, at the moment of burn-out, the angular movements of the fins are con-siderably amplified. During flight, the delta-shaped wings are displaced longitudin-ally according to a pre-determined time programme, so permitting the steering ability of the missile to be maintained within therequired limits in spite of the rapid changes in weight, lift and e.g. position. Rolling about the longitudinal axis is not preventedaerodynamic-ally but is allowed for by making the characteristics of the steering mechanism such that rolling has no influence onthe response of the missile to guidance commands. It will be noted, of course, that the missile has cruciform wingsof equal area (like all British missiles of which photographs have been revealed), and therefore it does not need to bank duringturns. The Oerlikon Type 54 missile, together with its ground equip-ment and the appropriate training devices, is reported to be in limited production for issue to specially formed anti-aircraft unitsof the Swiss Army. It is not stated whether the Swiss Government are prepared to export the weapon; if they are, it would seem thatthis will be the first missile capable of being bought "over the counter." n outline of the ground organization which would be employed in a defence system equipped with ground/air guided missiles of the Oerlikon type. The central group command post, on the left, would control three firing batteries of the type shown in the main part of the diagram. CROUP COMMAND POST BATTERY I |, I EARLY WARNING • i ! RADAR NETWORK ^ 1 J • ANTI - JAMMING^ j TRANSMITTER •*" PUTTER-ON RADAR WITH IFFANDMTI SIZE OF SEARCH ZONE IN ATO BE CONTROLLED MANUALLY CROUP COMMAND POST o Oooo PPI PPI JPpJ OPEB- COM- FOR ATOP MANOER BATTERIES TRANSMISSION OF TARCET POSITION IN a AND r MONITORING SICNAL PARALLAX COMPUTER COORDINATE TRANSFORMER FOR SCANNING IN A COMBINED RADAR AND OPTICAL TRACKER BATTERY 2 BATTERY 3 HORIZONTAL^ AXIS. ALL REMOTE COMMANDS HORIZONTAL AXIS CHT0 BL DETERMINED WITH RESPECT TO ATTACK DIRECTION BEAM TRANSMITTERPLATFORM WITH SPEED ANDACCELERATION LIMITER DYNAMIC LEAD COMPUTER PARALLAX COMPUTER ALL MONITORING IMPULSES BATTERY COMMAND POST CO-ORDINATE TRANSFORMER LEAD COMPUTER (BEAM MOVEMENT DURING FIRST 6 sec) FURTHER LAUNCHERS 1 LOADING POSITION 2 GYRO SPEED-UP POSITION 3 LAUNCHING POSITION
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