Tail-less aeroplane constituted by a three-element wing

摘要

375,515. Tailless aeroplane. CHARPENTIER, J. F. G. M. L., 5, Rue TahÚre, St. Cloud, Seine-et-Oise, France. June 1, 1931, No. 15977. Convention date, June 4, 1930. [Class 4.] A tailless aeroplane comprises a central part 1, Fig. 1, having a negative moment coefficient at zero lift, and two outer symmetrical parts 2, 3 of considerably smaller maximum chord each separated by a plane of discontinuity from the central part and together having a surface area substantially equal to that of the central part. The portion 1 may have a separately adjustable trailing edge flap 4 for altering its camber, and may also carry a fixed fin 11 and rudder 10. Passengers, goods, engines, &c. are contained in the part 1 and in some cases in the root portions of wings 2, 3. Wings 2, 3 have hinged leading and trailing edges 6, 7 and 8, 9 respectively which are operable as elevators as shown in Figs. 4 and 5. The parts 8, 9 may be divided as shown at 8, 8<1>, Fig. 7, and the trailing parts 8<1> may be operated independently of parts 8 as ailerons for lateral control. Alternatively separate ailerons situated toward the wing tip such as 7<1>, 9<1>, Fig. 1, may be employed, or means may be provided for operating the flaps 8, 9 differentially. Steering may be effected by the rudder 10 if fitted or by oppositely movable flaps 32, 33, 32<1>, 33<1> at the wing tips, Figs. 1 and 11. Control of the flaps 6, 8 may be effected by means of cables 15, 16, Fig. 13, acting on a lever 12 fulcrumed at either end on abutments 18, 19 respectively and connected by rods 13, 14 to the pivoted flaps. A pull on cable 15 causes the lever 12 to rock about the stop 19 and thus to depress the flap 8 leaving flap 6 unaffected ; a pull on cable 16 has the contrary effect. The parts 81 are independently actuated. In the form shown the aeroplane has a dihedral on both surfaces and is shaped at its underside to form a hull surface which may be adapted for landing and taking off on the water. Central wheels 23 and retractable side wheels 24, 25, Fig. 2, disposed under the motors are provided. The tyres of the lateral wheels are stated to act as floats when the aeroplane alights on water. According to the Specification as open to inspection under Sect. 91 (3) (a) the central wheels 23, Fig. 16 (Cancelled), are secured to the wing framework by shock absorbers 26, the wheel axles being provided with a fairing 27 which continues the shape of the boat-like hull in flight. This subject-matter does not appear in the Specification as accepted.