GB472567A - Improvements in aerofoils with variable camber - Google Patents

Abstract

472,567. Variable - camber aerofoils. LUTTMAN, H. C. Aug. 31, 1936, No. 23758. [Class 4] A hinge unit between the rear spar or subsidiary member of a fixed aircraft component and the spar of a control component is constituted by links-pin jointed at the ends and diagonally connecting the upper and lower booms of the two spars. A rigid control surface BD, Fig. 1, is hinged to a spar AC by pin-jointed links AB, CD, Fairings 1, 2 hinged adjacent to B and D, slide under the surfaces of the main component and over the spar AC. Fairings 1, 2 are acted on to adjust surface B. Two or more sets of links may be added as shown in Fig. 2, in which units BED H, E G H F are added to units A B C D. The units are connected by links A H, C E, B F or D G if symmetrical movement is required or if asymmetrical movement links A H, B F, D B and E H are provided. In a constructional form, Fig. 4, eye bolts at A and C through the top and bottom booms of the rear spar of the main component serve for attachment of the rib links which are made of strip material and have a bushed hole at each end. A rigid trailing edge portion is a flanged pressing. The skin comprises panels 1 to 6, Fig. 5, and a trailing edge panel 7, Fig. 7. The panels are interconnected by piano hinges w, x, y and z, supported by links Dw, Bx, Hy and Ez. The panels are stiffened by angle sections M, N, Fig. 7. with the exception of panels 1 and 2 which are flexible in those parts which slide into the main component. Control forces are applied through the skin by push and pull rods P. The positions of G and F may be interchanged as shown in Fig. 8, so that links DG, EG do not cross. The resulting movement of the trailing component is such as to produce the effect of a servo tab.