Patent GB-369248-A (GB)
Title: Improvements in devices ensuring propulsion and lift of aircraft
IPC: B64C23/00
Filed: 1930-12-11
Abstract: 369,248. Lifting, propelling, and controlling air and water craft. OEHMICHEN, E., Rue des Graviers, Valentigney, Doubs, France. Dec. 11, 1930, No. 37368. Convention date, Dec. 13, 1929. [Classes 4 and 114.] A propelling device for an aircraft incorporating an envelope containing gas partially balancing the weight of the craft comprises a propeller or group of propellers of variable action in combination with one or more auxiliary propellers of variable action, the axes of the propellers being keyed at a fixed angle of inclination less than 90‹ relatively to the horizontal plane comprising the axis of the hull and passing through a fixed straight line which is perpendicular to the vertical plane of symmetry of the apparatus and passes through the centre of aerostatic pressure on the hull. It is stated that if the axis of a slow-running propeller is inclined at an angle between 30‹ and 45‹ to the vertical a lifting component is obtained and a tractive component which is greater than would be obtained from a normally placed propeller absorbing the same power. Fig. 5 shows the application of the invention to a craft having a hull L containing a light gas wherein C represents the centre of aerostatic thrust which is substantially coincident with the centre of resistance, G represents the centre of gravity vertically beneath the point C and E represents a control' surface. A main propeller p<1> is inclined at 35‹ to the normal CV to the longitudinal axis AX and auxiliary propellers p<2>, p<3> are also fitted having their axes passing through G. CF<1> represents the thrust of propeller p<1> which may be resolved into vertical and horizontal components. If the propeller p<2> is driven with its pitch reversed to produce a thrust CF<2> the tractive component of the thrust of the main propeller vanishes and the craft is subjected solely to a reduced dynamic lift, conversely by adjusting p<2> to give a thrust CF<1>2 increased lift and increased tractive effort is obtained. Propulsion of the craft in all directions may thus be obtained by the suitable disposition of the propellers and by variations of their speed of rotation or pitch angles. An alternative arrangement is shown in Fig. 6. The single propellers shown may be replaced by groups of propellers of which the axes are parallel to the plane of symmetry of the craft or at an angle of not more than 15‹ to this plane and converging on the point C. The hull may be fitted with equatorial parachutes. According to the Specification as open to inspection under Sect. 91 (3) (a) an aircraft having an inclined main propeller p<1>, Fig. 7 (Cancelled), is associated with an auxiliary propeller p<2> of variable reversible pitch of which the function is to change the direction of the thrust line of p<1> by tilting the apparatus. The Specification as open to inspection also comprised the modifications now forming the subject-matter of Specification 369,237. All the above embodiments were stated to be applicable to aircraft without an aerostatic hull in which case the centre of aerostatic thrust is replaced by the centre of gravity of the apparatus or, in the case of submarines, by the centre of hydrostatic thrust. This subjectmatter does not appear in the Specification as accepted.