GB595464A - Improvements in aeroplanes - Google Patents

Abstract

595,464. Aircraft. WALLIS, B. N. March 1, 1945, No. 5120. [Class 4] In an aeroplane with one pair of wings the body is so shaped and the wings so shaped and mounted. on the body that in normal flight inherent stability of pitch is obtained by balancing with stable equilibrium the natural pitching moment exerted on the body when inclined at small angles of incidence to the airstream against the pitching moment of the lift acting in the opposite sense, the wings being adjustable relative to the body while in flight to give control of pitch. In the form illustrated the wings 11, 12 are mounted near the tail of the fuselage 10, the conventional empennage being absent, and are capable of the following adjustments : (a) rotation through equal angles about a transverse axis for variation of incidence ; (b) rotation in opposite directions about a transverse axis for control in roll ; (c) bodily fore-and-aft movement for compensating variation of fuselage pitching moment, particularly when taking off and landing ; (d) rotation about a vertical axis for additional control in yaw. High-lift flaps and ailerons may be fitted to the wings. The wings are connected together by a ball-andsocket joint 15, 16 and by links 17 which preserve the flexural continuity of the wings, as described in Specification 595,490, and are mounted on the fuselage by frames 21, 22, supported by rollers 23 running in tracks 24, their adjustment being effected by opposed hydraulic cylinders 25, as described in Specification 595,494. Specification 352,961 also is referred to.