GB412057A - Improvements in aeroplane construction - Google Patents

Abstract

412,057. Controlling aircraft. ZAP DEVELOPMENT CORPORATION, Dunkalk P.O., Baltimore, U.S.A. Aug. 8, 1933, Nos. 22159 and 22160. Convention dates, Aug. 8, 1932 and July 21, 1933. [Class 4.] An aeroplane is fitted with ailerons distinct from the main wing and arranged to influence the flow over the main wing in addition to the reaction upon the aileron itself as it is tilted, with or without a flap on the main wing movable to vary the airflow over the aileron. The ailerons 29 are mounted on brackets 30 with their pivots located above the upper surface of the wing a distance of about one-third of an aileron chord to two aileron chords, and with their leading edges two aileron chords in front to one aileron chord behind the trailing edge of the wing. The ailerons have rearwardly inclined arms 31 connected by rods 34 to three-armed levers in the wings connected by cables to the pilot's control, the inclination of the arms on the three armed levers ensuring unequal movements upwardly and downwardly from the mean position for equal movements of the control. These ailerons may also be arranged to float by connecting them as shown in Figs. 15 and 22 wherein arms 103 on the ailerons are linked to cranks 107 on shafts 108 which have arms 111 linked to a lever 117 on a shaft 118 capable of tilting within a vertical guide 119. The shaft 118 is connected by a universal joint to a shaft 122 rotatable by lateral movements of a control lever 125. Flaps 27, Fig. 3, normally resting beneath the trailing edge of the wing are hinged at their forward edges and are tiltable by links 21, 22 connected to nuts 20 on screws 19 universally jointed at 18 to shafts 17 driven by bevel gear 15, 16 from transverse shafts 13 in the wings. Alternatively the flaps may be moved by single links connected to nuts on screws in fixed bearings and driven from the shafts 13. Fig. 8 shows another alternative wherein the shafts 13 are screwed and actuate links 67 connected to the flaps and to nuts on the shafts 13 by universal joints. Fig. 22 shows a flap 210 connected at its forward edge to nuts 208 on screwed shafts 205 and at points 211 to links 212 so that the trailing edge of the flap always lies substantially vertically below the trailing edge of the wing.