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Aviation History
1955
1955 - 1469.PDF
FLIGHT, 7 October 1955 579 HIGH-SPEED DRONE A New Canadian Approach to Target-aircraft Design: The Caeta Project AMONG the projects under way at the Montreal plant oft^ Canadian Aviation Electronics, Ltd., on the occasion of a J- -*- recent Flight visit, was the design of a radio-controlledtarget aircraft capable of high subsonic speeds. This machine, known as the model P-l, or Caeta (from the initials of CanadianAviation Electronics Target Aircraft), has been put forward to meet a specific need, and in a most original way. An investigation by the company showed that nowhere wasthere available a target aircraft capable of operation at extreme altitudes, with useful flight duration and at speeds closelyapproaching Mach 1. For the reliable evaluation of armament and fire-control systems, interception techniques and operationaluses of modern military aircraft, such a device appeared essential. An exceptionally well qualified group was available to tacklethis design at C.A.E., consisting of engineers experienced in aero- dynamics, stability and control, automatic flight and the design launching and air-launching were both to be practicable, andthe radius of command control was to be 100 miles and 50 miles respectively. Design studies indicated that a simple target aircraft, weighingno more than 1,500 lb and powered by one Rolls-Royce RSr. 2 Soar turbojet, could be designed rapidly and would form asuitable platform for the required equipment. The airframe would be conventional and, provided the wing thickness/chord ELFVATOR STATIC, PRESSURE TRANSDUCER (ALTITUDE CONTROLLER) ROLLS-ROYCE SOAR TURBOJET ENGINE MAIN- MOUNTINC FRAME Structural layout and principal equipment of the Caeta. The modified Lear autopilot, with phase detector and servo amplifier, is enclosed in the two-axis amplifier controller unit. Output to elevators and inboard ailerons is from the dual actuator. Not visible are the flotation bags (normally stowed beneath the wing roots) and the air cylinder which actuates the landing-skid shock-struts and inflates the bags. of electronic systems. Previous work on flight and radar simula- tors had given the aerodynamicists in particular an unusually extensive knowledge and appreciation of electronic systems; and the result of the team's effort and previous background was the design described below. , , r , ,The performance of the drone was to match that of bomber aircraft which might be used over the next decade. Mach num-bers between 0.9 and 1.0 were to be achieved over the entire altitude range, which was from sea level to 60,000ft, and a halt-hour endurance at this upper height was specified. Ground- ratio did not exceed six per cent, sweepback would not be required.For control and guidance, it was decided to use existing equip- ment as far as possible, for reasons of reliability and speed ofproduction. A simplified version of the Lear F-5 autopilot, with rudder control deleted and a single actuator adapted to operateboth elevators and ailerons, was selected. At this stage a com- plete general arrangement, of mid-wing configuration, was drawnup. The high tailplane required a fairly high fin thickness/chord ratio, and so considerable sweepback was given to the fin; this
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