Patent GB-882073-A (GB)
Title: Improvements in or relating to aircraft
Inventor: GRIFFITH ALAN ARNOLD
IPC: B64D5/00
Filed: 1957-02-26
Abstract: 882,073. Composite aircraft. ROLLS-ROYCE Ltd. Feb. 21. 1958 [Feb. 26, 1957], No. 6497/57. Class 4. [Also in Group XXVI] A composite aircraft comprises a first aircraft having forward propulsion means and aerofoil surfaces generating lift in forward flight, and a second aircraft adapted to have the first mounted thereon so as to be disconnectable during flight, and having power plant capable of generating lift independently of that generated aerodynamically during flight. Fig. 4 is a plan view, showing the two aircraft connected together for take-off, and Fig. 7 is a vertical lateral section. On attaining a given speed, the two components separate, the Upper one 10 continuing its flight, and the lower one landing. The upper aircraft has two banks 11 of jet propulsion engines, and is of all wing delta form. The lower aircraft has twin fuselages 14 connected by beams in fairings 16, and stub tail planes 17. Each fuselage 14 contains sixteen pairs of turbo-jet engines (one pair shown in Fig. 7), with nozzles 19d. These engines are tiltable about lateral axes to provide propulsive and lifting thrust independent of forward flight, allowing vertical take off and forward acceleration until the aircraft 10 has attained flying speed. The outer face 23 of each fuselage is apertured and open to a plenum chamber 24 feeding the turbo-jet air intakes. Control in pitch is obtained by relative throttling of the turbo jets. Air is tapped from all the turbo-jet compressors, and fed rearwards by ducts 26 to ducts 27 extending spanwise across the tail planes. There are four such ducts, in line behind one another, the foremost being shown in broken lines, Fig 7. The two ends of a duct are each formed by a bulbous chamber 27a, containing a body 28, the two bodies in each duct being connected. The air finally exhausts through downwardly pointing nozzles 30 at the tips of the tail planes. Lateral movement of the bodies 28 decreases the flow through one chamber 27a and increases that through the other chamber, providing control in roll. Air tapped from the compressors is also led by ducts 32 across the apertured faces 23 for de-icing. Fuel tanks are located at 34. The undercarriage of the lower aircraft comprises vertical legs 20 attached to the fuselages and connected through shock absorbers (not shown) to feet 22. The upper surfaces 14a of the fuselages are shaped to facilitate location of the upper aircraft 10, which has no undercarriage, but is received on suction cups 36 mounted on pistons working in cylinders 37 formed in extensions of the legs 20, so that when on the ground, the weight of the upper aircraft is not borne by the fuselages 14. The cups 36 are movable to a limited extent relatively to the fuselages 14 to facilitate re-engagement during flight. On re-engagement, the cups are locked and received in recesses 35 in the fuselages 14. The upper aircraft may have powerplant generating lift independently of forward flight, and its own landing gear, and may have jet propulsion engines mounted in pods slung beneath the wings. The lower aircraft may have a wheeled undercarriage.