GB844537A - Aerodynamic control mechanism for a delta-wing aircraft - Google Patents

Abstract

844,537. Controlling aircraft. UNITED AIRCRAFT CORPORATION. May 28, 1957 [May 31, 1956], No. 16885/57. Class 4. A high lift device provided on a low aspect ratio aircraft wing to improve landing and take-off characteristics comprises the provision along each leading edge 22 of a duct 33 which is connected by a conduit 32 and control valve 48 to either the compression or combustion side of gas turbine power plant 28. A further duct may be provided at the leading edge of each elevon 24 to connect with the power plant through conduit 34 and valve 49. Each duct 33 is formed with an outlet slot 40 and a hinged flap 42 which is moved by an electric motor 46 from the position shown in Fig. 9, to an inoperative position in which it covers the slot and completes the leading edge contour. In a further embodiment the flap is chordally slidable by a fluid pressure motor to a position in which it projects from the leading edge of the wing above the slot 40. In another embodiment the duct 33 is spaced rearwardly from the leading edge and connected by telescopic conduits to a chordally slidable hollow flap having a slot formed along its forward edge, the flap being moved by a fluid pressure motor. An arrangement is described in which two power plants are interconnected by conduits in order that the high lift device may be operated in the event of failure of either power plant. The device may be operated in conjunction with undercarriage lowering mechanism and after landing values 48 may be closed and the full jet-thrust deflected into a thrust reversing system. The high-lift devices may be operated differentially to provide roll control with or without operation of the elevon controls. Fins 16 are pivotally mounted on transverse axes at the rear of the wing for retraction during landing. Specification 647,779 is referred to.