Patent GB-569248-A (GB)
Title: Improvements in aviation trainer
IPC: G09B9/20
Filed: 1943-05-26
Abstract: 569,248. Apparatus for training aviators. LINK AVIATION DEVICES, Inc. May 26, 1943, No. 8418. Convention date, July 29, 1942. [Class 4] Apparatus for training aviators, of the kind described in Specifications 370,128 and 481,375, is provided with means for demonstrating the effect of throttle control on the engine manifold pressure and engine speed, the effect on these latter of certain conditions of flight, and also the effect on a twin-engined aircraft of unequal throttle settings. A dummy throttle lever 30 operates a bellows 60 through linkwork 38, 42, a capsule 54 and compression spring 62, the bellows being in communication by means of a pipe 68 with a regulator bellows 70 and suction source 72. The bellows 60 is provided with a gauge 76 indicating the manifold pressure, the reading being governed by the degree of opening of a valve controlling the connection 64 with the suction source. The movement of the lover 30 determines the compression of the spring 62, the force exerted by which in turn governs the partial vacuum produced in the bellows 60 and the reading of the gauge 76. A bellows 150 provided with a tachometer gauge 164, and actuated by a rod 184 and compression spring 178 from the lever 30 is provided to demonstrate the effect of throttle opening on engine speed as indicated by the tachometer. In order to simulate a twin-engined aircraft a second dummy throttle lever 84 may bo fitted to actuate bellows 106, 152, carrying gauges 116, 172. For the purpose of demonstrating the effect of altitude on manifold pressure, a pressure tank 122 of the kind described in Specification 481,375, and provided with an altimeter 124 and vertical speed indicator 126 is connected to the capsules 54, 100, by a pipe 120, the variation of pressure in which alters the force exerted by the springs 62, 104, to vary the readings of the manifold gauges 76, 116. To simulate the effect on manifold pressure and engine speed of aircraft attitude, the training apparatus is provided with members 146, 148, 144, which, as the result of movement of the fuselage about a transverse axis, cause the crank members 40, 92, to rotate about their points of connection with the links 38, 90, to operate the manifold and tachometer bellows. The response of an aircraft to unequal throttle settings is shown by connecting the levers 30, 84, by means of links 194, 198, to an ann 196, attached to a valve 202 capable of moving vertically within guides. The valve consists of three ported discs which may be put into communication with atmosphere, or a suction source by means of a connection 228, and is connected by pipes 252, 254, to bellows 256, 258, associated with the rudders 270, 272. Unequal movements of the levers 30, 84, result in the valve putting one of the bellows in communication with the suction source and the other into communication with the atmosphere, to produce rotation of the rudder bar 262, and corresponding movement of the fuselage body about a vertical axis, as described in Specification 481,375. The control valve 202 may be provided with a link connected with an air speed indicator, altimeter and vertical speed indicator as described in Specification 569,249. The effect of banking in reducing the turning of an aircraft produced by unequal throttle settings is simulated by means of links 292, 286, 224, which, by means of the rotation of an arm 222 on the valve 202 cause a reduction in the partial vacuum and the pressure obtaining in the respective rudder bellows when the trainer banks, thus reducing the torque on the rudder bar. Manually adjustable mechanism may be provided for compensating the turning effect due to different throttle openings, consisting of a worm gear 298 by means of which the forces exerted by springs 310, 312, connected to the rudder pedals by a chain passing over a pulley 306, may be varied. The worm gearing may be provided with a suitable scale 318 to enable the student to make the necessary adjustment for any assumed difference of engine speeds.