Patent GB-572313-A (GB)
Title: Improvements in aviation trainer
IPC: G09B9/14
Filed: 1943-08-13
Abstract: 572,313. Apparatus for training pilots. LINK AVIATION DEVICES, Inc. Aug. 13, 1943, No. 13176. Convention date, Sept. 9, 1942. [Class 4] Apparatus for training pilots comprises a fuselage mounted so as to be capable of imitating the turning and banking of an aircraft in flight, movement of the control column rearwardly from its neutral position causing the fuselage to turn when banked, to illustrate the increased rate of turn or " turn tightening " resulting from elevator movement when an aircraft is in a banked turn. In the arrangement shown the fuselage is mounted on a universal joint 12 and is capable of being tilted about longitudinal and transverse axes, to simulate banking and pitching, by the actuation of pairs of bellows through " aileron " and " elevator " valves 62, 108 connected to a source of reduced pressure, and may be rotated about a vertical axis, to simulate turning, by an electric motor controlled by a " rudder " valve 158, as described in Specifications 370,128 and 481,375. The aileron valve 62 is actuated by the control wheel 76, rotation of which turns a wheel 80 whose movement is transmitted to the valve through levers 84, 86, 90. Movements of the control column 122 in the longitudinal plane are transmitted to the elevator valve 108 through a link 126, and the rudder pedals 172, 174 actuate the rudder valve 158 through links 188, 190, 194, 196, 198, 208, 218. The valve 158 is in communication with the bellows controlling the tilting of the fuselage about the transverse horizontal axis, and is so arranged that movement of the valve in either direction actuates the pitching bellows to cause a " nosing down " of the fuselage, similar to the diving which results in an aircraft from a turn in either direction. A " turn tightening " valve 292 in communication with the elevator valve 62 and the turning motor control mechanism is connected by a link 314 to an arm 312 secured to a longitudinal shaft 244. When the fuselage is in a banked position a transverse shaft 240 secured to the fuselage supporting the pedestal 14 rotates the longitudinal shaft 244 which, through the members 312, 314 moves the valve 292 from its neutral position. Thus, if the control column 122 is moved rearwardly with the fuselage banked, the elevator valve 108 is rotated and placed in communication with the turning motor control mechanism through the valve 292, and the fuselage rotates, the direction of turning being determined by the direction of banking. If the fuselage is turning about its vertical axis when banked, actuation of the control column results in an increased rate of turning. Banking of the fuselage also causes its turning about the vertical axis, rotation of the shaft 244 causing an arm 246 at the end thereof to rotate the lever 198 about its lower end, which movement actuates the rudder valve 158. The turning produced by combined banking and movement of the control column may be offset by appropriate actuation of the rudder pedals 172, 174. Banking of the fuselage as the result of rudder operation, together with spinning, may also be demonstrated by the apparatus as described in Specifications 572,326 and 572,327.