GB830520A - Improvements in or relating to aircraft - Google Patents

Abstract

830,520. Aircraft. EDDIE, W. L. Dec. 10, 1957 [Sept. 10, 1956], No. 27560/56. Class 4. An aircraft comprises a central disc shaped portion incorporating at least four gas turbine and/or rocket motors each movable between horizontal and vertical operating positions, and an outer annular portion coaxial with and rotatable around the central portion and incorporating at least two gas turbine and/or rocket motors. In Fig. 1, the central portion 1 has four vertically extending passages, in each of which is mounted a pair of gas turbines 3, 4 (see also Fig. 7) on a support 17, rotatably mounted and rigid with an arm 16. Two pairs of hydraulic jacks 14, 15 (one pair shown) are mounted one pair each side of support 17, and extension of jacks 14 holds turbines 3, 4 in the horizontal operating position shown, whereas extension of jacks 15 rotates the turbines to a vertical working position providing direct lift. Ball races (not shown) on the central portion support two contra-rotated annular members, the upper member 5 being shown. Each member is provided with four gas turbines 7 each in a duct comprising an air intake 8 and exhaust nozzle 9, these turbines rotating the member, which is stated to result in stability of the aircraft. Fuel tanks 10 are provided in the annular members. The central member has three turrets, an upper turret 12, and lower turrets 11 (below turret 12, but not shown) and 13. Each turret houses a gas turbine having two air intakes 20 and two exhaust nozzles 21 inclinable away from the aircraft. Further, each turret is rotatable about a vertical axis through a complete revolution, by electric motors and ball race mountings (not shown). The central portion has two upwardly discharging rocket motors 19, and two similarly placed downwardly discharging rocket motors (not shown) somewhat inboard of motors 19. For vertical take-off, the turbines 3, 4 are all turned to the vertical operating positions. For forward flight, and for take-off from a runway, turbines 3, 4 are turned to the horizontal positions, and the exhaust of the turbines in the lower turrets 11 and 13 is directed downwardly. The turrets 11, 12 and 13 may be rotated about the vertical together to control the direction of flight of the aircraft, and turrets 11 and 12 may be operated in the opposite sense to turret 13 to rotate the aircraft about its vertical axis. The upwardly and downwardly discharging rocket motors, e.g. 19 are used to control the aircraft in roll, and the nozzles of the turbines in the turrets may be inclined to control the aircraft in pitch. The upper annular member 5 and the lower annular member may be rotated at different speeds. The gas turbine engines are controlled electrically through slip rings and brushes. Twin stabilizing fins may be mounted on each of turrets 11 and 12. According to the Provisional Specification, the central portion may have wings with ailerons both above and below the annular members, and may have a tailplane with elevators and a rudder above the annular members.