Flaps and retractable landing gear simulating means for grounded aviation trainer

摘要

623,589. Ground trainers for aircraft pilots. LINK AVIATION, Inc. Jan. 6, 1947, No. 424. Convention date, Jan. 30, 1946. [Class 4] A ground trainer is arranged so as to simulate the effect of the operation of the landing flaps and/or the undercarriage on aircraft speed, trim, and rate of climb. The invention is shown as applied to a trainer of the type comprising a universally-mounted fuselage, such as described in Specifications 370,128 and 481,375. General arrangement (Fig. 2).-The dummy flap operating lever 376 and undercarriage lever 550, operate electric motors in a unit A which in turn actuate a dummy flap and undercarriage indicator 448. The unit A is connected by pipe lines 474, 70 to a suction source 40 and a bellows 72, to the latter of which is attached a cord 76 passed around a shaft 78 operating self synchronous units 86, 102 connected to dummy airspeed indicators 92 and an air speed follow-up unit 108. The airspeed unit is of the type described in Specification 623,573. Flap simulating system (Figs. 9 and 10).- Movement of the flap lever 376 to the "down " position closes contacts 392, 396 in the circuit of a reversible shaded-pole motor 386, which rotates until a spring member 424 engages in a notch 426 on the periphery of a cam 422. A lamp 436 is lit to show the instructor that the pupil has taken action appropriate to lowering the flaps. The motor 386 drives the imput shaft 442 of a transmitter 444 which is connected by a cable 446 to the flap element of the indicator 448. The indicator element consists of a pivoted magnet 452, the angular position of which depends upon the position of the rotor shaft 442. In order to simulate the drop in air speed resulting from lowering of the flaps, the motor 386 drives a pinion 460 to move the needle of the flap control valve 464 from its seating, to admit air through an inlet 470 into the pipes 474, 70 and thus expand the bellows 72. The movement of the latter causes appropriate variation of the reading of the airspeed indicators 92. Expansion of the bellows 72 rotates the housing of the transmitter 102 by means of which the elevator control valve is operated to cause the nose of the fuselage to be lowered or raised according to the type of aircraft whose characteristics are being simulated. The dive and climb valves are also operated to cause appropriate variations in the readings of the rate of climb indicator and altimeter. Undercarriage simulating system (Figs. 13 and 14).-Contacts 562, 563 are closed by movement of the lever 550 to the "down" position, to start a motor 556 which rotates until a spring member 588 engages a notch 589 in a cam 580. A permanent magnet 598 is moved to operate the indicator 448 and a lamp 599 is lit. The motor 556 also controls the degree of opening of a control valve 608 connected to the pipeline 70, to cause appropriate variations of the readings of the air speed and rate of climb indicators, the altimeter, and also to cause the fuselage to assume a nose up or nose down attitude. With the undercarriage in the assumed " up " position a buzzer 658 sounds if the pupil retards the throttle beyond a predetermined point, as when landing. Specification 587,779 also is referred to.