Patent GB-453597-A (GB)
Title: Flying machines with rotary supporting surfaces
IPC: B64C27/02
Filed: 1935-02-06
Abstract: 453,597. Aircraft with rotary - wing systems. PESCARA, R. P., 115, Rue de la Tour, Paris. Feb. 6, 1935, No. 3908. Convention date, Feb. 6, 1934. [Class 4] A flying-machine with a stationary supporting surface has at least one rotary supporting structure of the normally freely rotative type comprising supple or flexible blades adjustable in length and so arranged that when at their shortest position they have such a free length that their automatic rotation is ensured. In one form, Fig. 2, the framework of a rotor blade comprises radially disposed flexible metal members 1 such as wires, ribbons, &c., fixed to a hub 2 at the end nearest axis O about which the blades are pivoted and at the other end to a rigid or semi-rigid part 3 of sufficient weight to exert a substantial centripetal force. Members 1 may be arranged one above the other or side by side and the outer members only may be connected to end piece 3. One or-more ribs similar to part 3 may be arranged at intervals along the blade ; alternatively transverse cables may be used. The cable system may be replaced by a metal cloth or fabric. The framework above described carries an envelope which in the case of thin blades may comprise a fabric covering 5, Fig. 3, maintained in the desired shape by a filling 6 of resilient material, e.g. sponge rubber. Similar construction may be used for thick blades but with the addition of stiffening elements at the leading and trailing edges, Fig. 4, of stiff fabric or indiarubber. An upper and lower set of cables 1 may be used. In another form, Figs. 8 and 10, an envelope 11 of fluid tight material such as rubberized cloth is maintained in the desired shape by gas pressure. The envelope may be leak proof and inflated to the desired pressure or may be provided with a rearwardly facing jet 12, Fig. 10, in which case air is fed continuously to the envelope through ducts formed in the hub of the blade. The framework may be disposed within the envelope, Fig. 8, or on the outside thereof, Fig. 10, or may be free with respect to the envelope both members however being connected to end piece 3. The angular setting of the blade during rotation may be determined by the provision of masses disposed at intervals along the leading or trailing edges of the blade or at its tip. The effective length of the blades is adapted to be altered by pulling part of the blades inside a hollow hub to which they are attached. In an elementary form, Fig. 12, a hollow hub 14 carries blades P constituted by a single band passing round drums 16 and a pulley 17 which can be pulled downwardly by a cable 19 to reduce the effective area of the blades and allowed to move upwardly under the tension exerted by the centrifugal force exerted in the rotating blades. A winding drum 20 for effecting movement of pulley 17 may be driven either manually or mechanically, e.g. by gearing to the rotor 14. In another form, Fig. 13, separate blades P are anchored at 22 and pass over the pulleys 17 of a movable pulley block. Blades having their framework on the outside of the envelope are used, the framework being wound over drums 23 and the envelope either over a single pulley 17 as in Fig. 12, or over a pulley block comprising two pulleys 17 as shown. Drums 23 are mechanically connected to member 18 carrying pulleys 17 by cables 24 which are fixed at one end to member 18, are wound round pulleys 25 carried by a support 27 subjected to the tension of a spring 28 and are fixed at their other ends to the peripheries of pulleys rigidly fixed to drums 23. In a further modification, Fig. 14, blades P are adapted to be wound up on pulleys 29 carried by a rotor head 30 mechanically driven by shaft 41, and gears 42, 43, 44. Pulleys 29 are geared to a sleeve 32 disposed concentrically with rotor support pillar 33 and a cylindrical extension 31 of rotor head 30. In order to wind in blades P sleeve 32 is rendered fast to stationary pillar 33 by a clutch 34. In order to maintain the blades 1 at any given effective extension sleeve 32 is clutched by dog clutches 35<1>, 35<2> to a spring loaded sliding sleeve 36 keyed to rotor head extension 31 by means of a spring bolt 45 held by member 31 and passing through a slot 46, Fig. 16, in sleeve 36. To allow of the blades unwinding under the action of centrifugal force, clutch 34 and dog clutches 35<1>, 35<2> are held out of engagement leaving sleeve 36 free to turn under the action of gears 37, 38, 39, 40. Control is effected by a lever 52 which when moved to position B, (blade winding up position) engages clutch 34 by means connected to a spring pressed operating rod 60 and slides sleeve 36 iuto its uppermost position, in which it is locked by engagement of the head of bolt 45 in an enlargement 47, Fig. 16, of slot 46. Lever 52 is locked in position B by engagement of its handle with a hook 56<1> formed on a spring 56 interposed between a yoke member 54 coupled to sleeve 36 and a bellcrank lever 53 actuated by the lever 52. Sleeve 32 is threaded and carries a hut 49 keyed to rotor member 31. During the winding up operation nut 49 is caused to screw upwardly by the relative rotation of member 31 and sleeve 36 and eventually comes into engagement with a rounded head formed on the inner end of bolt 45 forcing it outwardly to release sleeve 36 which is thereupon forced downwardly by its associated spring, and flexes spring 56 sufficiently to release lever 52. Lever 52 is thus urged into position A (blade locking position) releasing clutch 34 and permitting engagement of dog 351, 35<2>. In order to allow the blades to wind out, lever 52 is moved to position C (blade unwinding position) in which neither dogs 351, 35<2> nor clutch members 34 are engaged. When such a device is used with blades comprising inflated envelopes, drums 29, Fig. 19, are formed with orifices 29‹ and the ends of the envelope are fixed in a fluid tight manner to the drum. When the blade framework and envelope are to be separately wound the arrangement shown in Fig. 17 is used. This comprises a fluid tight box 62 into which air is fed under pressure and containing a drum or drums 23 on which framework 1 is wound. The blade enters and leaves box 62 through packing means 65, 64, passing between rollers 66. Openings 63 in the envelope allow entry of air while the blade is passing through box 62, these openings being stopped in a fluid tight manner by the framework, Fig. 18. Fig. 23 shows an aircraft having fixed wings 73 and a rotary wing system comprising blades 9 adapted to be driven either mechanically at least during take-off, by jet reaction, or by the relative wind. The disc area of the rotary wing system may, after the aircraft has taken off, be reduced to a very small diameter a-b, the blades continuing to rotate to permit of rapid extension when desired under the action of centrifugal force and the craft being supported by the fixed wings. In order to prevent undue loss of rotor speed during the unfurling operation a flywheel may be geared to the rotor. The blades P may be varied in shape along their length in order to vary their angular setting according to the degree to which they are unwound. The blades may be so shaped that they are caused to adopt a high angle of incidence in their fully unwound position. Means for altering the mean plane of rotation of the blades is shown in Fig. 21 and comprises a disc 77 universally mounted in and keyed to a ring 80 which in turn is slidably keyed to the rotor hub. Disc 77 is controlled by a rod 82. Rotary wing systems such as described above may be applied to detachable passenger-carrying parts of the craft for use as parachutes in emergency. Fig. 24 shows an application to a heavierthan-air craft in which cabin 84 is releasably mounted in guides 85 fixed to the fuselage and carries a rotary wing system P adapted to give additional lift in flight when driven by the relative wind. Fixed wings 73 have their trailing edges cut away at the roots to give clearance to the blade system P in its furled position when the cabin 84 is released. According to the Specification as open to inspection under Sect. 91 rotors such as described above may be employed for propulsion and as wind motors, and the parachute arrangement of Fig. 24 may be employed in lighterthan-air craft both as an emergency device and to provide additional sustentation. In another form, Figs. 24 and 25 (Cancelled) an aircraft comprises two systems of revolving blades P which are driven by shafts 74 passing through fixed wings 73 and gears 75. The blade hubs may be tilted after taking- off into the dotted line position of Fig. 25 (Cancelled), in which the blade systems act as airscrews. The diameter of the blade systems may be varied differentially for controlling the craft. A third rotary wing system may be fitted at front or rear of the body for longitudinal control. This subjectmatter does not appear in the Specification as accepted.