GB700293A - Improvements in or relating to jet propelled aircraft - Google Patents

Abstract

700,293. Rotary wing aircraft. POPE, P. Oct. 11, 1951 [July 11, 1950], No. 3558/50. Class 4 An aircraft comprises a central body portion, an outer shell disposed around said central body portion and rotatable with respect thereto about a normally vertical axis, a plurality of blades projecting outwardly and horizontally from said outer shell, said blades being adapted on rotation of said outer shell to impart lift to the aircraft, jet means for rotating said outer shell and means for preventing corresponding rotation of said central body portion, and jet means for imparting forward motion to the aircraft. An inner body 1 comprises frame members 6 which support a pair of spaced annular collars 5 adapted to support a rotatable hub section 4 formed with a plurality of radial spars 3. The spars support an outer shell 2 and carry aerofoils 7 at their extremities, the spars and the aerofoils being formed internally with air and fuel conveying passages 10 and 11 that supply jet propulsion units 9 housed in the outer extremities of the aerofoils. The main propulsion unit comprises a pair of turbo jet units 15, 16 connected to an air compressor 17 by means of couplings 18, 19, the turbo jet units and the compressor being supplied with air from a common intake 24 and the efflux from the turbo jet units being exhausted rearwardly through pairs of pipes 20, 21. The lower pipes 21 are formed with deflectors 22 whereby the exhaust gases may be directed downwardly through pipes 23 to produce direct lift and if desired these deflectors may be actuated in conjunction with a retractable undercarriage. Compressed air is fed to the passage 10 by conduits 28 and rotary seals for air and fuel are provided between the members 4 and 5. A plurality of windows 30 are provided in the body 1 and a large number of corresponding apertures 29 are formed in the outer shell 2 to provide all-round visibility. Rotation of the inner body with the outer shell may be prevented by directional fins or gyroscopes mounted within the inner body on horizontal axes, and directional control of the aircraft may be achieved by controlling the relative gas flow from the pipes 20, 21.