US2036587A - Aircraft - Google Patents

Description

" April 7, 1936.

H. G. LIND 2,036,587

AIRCRAFT Filed JulyplS, 193 2 Sweats-Sheet l INVENTOR.

HAKONEILIND.

ATTORNEY.

Patented Apr. 7, 1936 PATENT OFFICE AIRCRAFT 11mm G. Lind,

New York, N. Y.

Application July 13, 1934, Serial No. 734,958

7 Claims.

My invention relates to a new and useful improvement in aeroplanes and other aircraft and particularly to improvements in propelling means to enable the aeroplane to function 'as a hellcopter or autogyro and be sustained in the atmosphere.

An object of the invention is to provide a particularly inexpensive and eflicient aircraft, employing rotating wings of a unique and novel construction for the sustentation type.

A feature of the invention is an arrangement of wings or blades of this type having longitudinal passages in the individual blades through which the atmosphere may be expelled outwardly from the centre by centrifugal force caused by the rotation of the blades, so that air currents passing under the blades, also due to the rotation of the blades, may be forced upward into and out through the passages to exert lifting force or pressure on the under sides of the blades to sustain or lift the aeroplane in the air in a mor eiilcient manner than heretofore.

Another feature of the invention is a blade control arrangement whereby said blades may be adiusted to any desired angle in relation to the central longitudinal axis of the blade and the direction of travel of the plane, to secure lifting, sustentating or descending eifects on the aeroplane as desired.

Referring now to the drawings:

Fig. 1 shows a side view of an'aeroplane constructed in accordance with one embodiment of my invention;

Fig. 2 shows a top view of said aeroplane;

Fig. 3 shows one of the wings or. blades constructed in accordance with my invention;

Fig. 4 shows an end view of the blade shown in Fig. 3 looking from the outer end of the blade;

Fig. 5 shows a side view of the suspension structure for the blades partly in section;

Fig. 6 shows a top view of said structure in Fig. 5 partly in section;

Fig. 7 shows a cross section of one of the adlusting arms for one of the blades, while Fig. 8 shows a cross section of an adJusting arm taken on line 3-8 of Fig. 6.

Referring again to the drawings, a description will be made of the construction of the aeroplane, followed by a description of its functions.

Figs. 1 and 2 show a fuselage I with ordinary aeroplane wings 2, tall plane and rudder 3, ailerons 4 and a propeller 5. Secured to thecentral portion of the fuselage at the top is a superstructure shown in detail in Figs. 5 to 8, on which the blades 1 are suspended for rotation and control in accordance with this invention.

In regard to the blades 1, Figs. 3 and 4 show their construction. A blade 1 consists of the usual rib construction covered with any suitable material and shaped, in regard to the upper surface, in the usual form. The under surface, however, is shaped as shown, with a longitudinal enclosure io, extending from the point I l to the tip of the blade at lit, with the enclosure open at this latter point. This enclosure also opens at the centre of the blade towards the rear, into passages between transverse and diagonally placed partition plates l3.

The blade is suspended on a central axis or tubular shaft [4. This shaft I4 is journalled into a tube i5, secured or clamped in the movable frame structure Iii. To the inner end of the shaft I4 is secured a bearing plate l1, and to the end' of the tube l5 secured to the frame it, is another bearing plate l8. Between these plates are placed balls iii, to form a ball bearing structure to permit the shaft [4 to move freely in tube i5. To the plate I! which surrounds the shaft I4, is secured an arm 20, for the turning or adjusting of the blade I on its axis or shaft i4. The extreme end of the shaft I4 is mounted in a cap 22, which forms part of a ring 23, having four caps 22, one for each shaft I4. Opposite these caps 22, and

integral with the ring 23, are bearings 25, in which rollers 26 are mounted. The opposite ends of the tubes l5 are provided with flanges 21, which are secured to struts 28, connected together at the opposite ends to a plate 3i at the top of the frame it, while struts 29 connect the flanges 21.

The frame it may consist of the four bent members 30, riveted together at the top to plate 3], and at the bottom to a circular member 32. The member 32 is enclosed or journalled in another circular flange shaped member 33, while the plate 3| is mounted, by means of the ball bearing 34, on the stud 35, so that the frame It can rotate freely around the stud 35 and in the flange 33.

The stud 35 is fastened in the frame 40, comprising four upright members 4i, having an outer ring or runway 42 for the rollers 25. Each of these upright members 4| is provided with a vertical slot 43, and terminates in a circular base plate 44, integral therewith. The base plate 44 is provided with outwardly extending supporting ribs 45, to secure the whole frame 40 to the upper part 46 of the fuselage. The frames l6 and 40 may be manufactured in any suitable manner, for example by castings or welded steel ribs.

The control means for changing the angle of the blades to their respective axes, comprises a central bar 48, supported to slide vertically at the top in a bearing or ring 49, which forms part of the frame 40 and is secured thereto by ribs 58, which terminate at their outer ends in the upright members 4|. This bar 48 is also slidably supported at the lower end in a similar ring 5|, which is secured by ribs 52 to the base plate 44. Bar 48 is adjustable, in the vertical direction by a rack 53 cut therein and a worm gear 54 meshing with the rack 53. Said gearv 54 is mounted in ring 5| androtatabie in any suitable manner, for example bythe control rod 55. is provided, approximately at its centre, with a ball socket 55, having four diagonally opposite openings. In this socket rests a ball shaped central portion to which are secured four arms or members 51, each protruding through a corresponding opening in the socket 58. It should be understood that these arms and the central ball shaped portion, as well as the socket in the bar 48, may be constructed in any suitable manner, by properly machined parts assembled so that one pair of arms, extending in opposite directions from the central ball portion, may be moved or adjusted in any position in relation to the horizontal plane, within the limits controlled by the slots 43, through which they extend and the other pair of arms, extending at right angles to the first mentioned pair in opposite directions from the central ball portion, may be moved or controlled in the same manner in relation to the horlmntal plane, within the limits of slots 43, through which these arms extend. The first mentioned arms may be movedby means of the rack 58, rotatably secured at opposite ends to the corresponding opposite arms. The rack 58 is controlled by the gear 68 rotatably mounted in the bar 48. Said gear 60 may be rotated by any suitable lever (not shown). The second mentioned arms may be moved by means of a similar rack 6|, rotatably secured at opposite ends on the corresponding opposite arms. These racks extend, as shown, through a slot in the bar 48, below the ball socket and may be controlled by a gear 82 which is movable by a rod 83. To the outer ends of the arms 51 is secured a ring 64, as shown in Figs. 5 to 8. This ring 64 is provided with runways 65 and 65 on its upper and lower surfaces respectively.

Each arm or lever 20, see Fig. 8, is associated by means of a linking arrangement 81 with the ring 84, comprising a clamp shaped member 68, enclosing balls 69 and 10, with ball 69 running in runway 65 and ball 10 in runway 86 of ring 64. This clamp also holds a pin 12 that is movable in a slot 13 of a member 14, secured to an upright 15. As there are four clamps 68, each with its associated pin I2 and member 14, there is one upright 15 for each such member. Each of these uprights 15 form part of the frame I8, and are similar to uprights 30 and secured at their upper ends in plate 3| and at their lower ends in the ring 32. Each clamp 68 is movably secured to its corresponding arm 20 by means of the ball and socket arrangement, comprising the tubing ll,pinion l8 and nut 19, as clearly shown in Fig. 8, so that the arm 20 is movable in any direction in relation to the clamp 68.

Referring now to the operation of the control mechanism for the blades, each pair of arms 51 may be set at any desired angle in relation to the horizontal plane by their corresponding racks The bar 48' 58 and 6|, controlled by the corresponding gears and control rods, to place the ring 84 in a corresponding tilted position in relation to the horizontal plane. For example, the ring may be tilted at an angle so that the point 80, see Figs. 5 and 6, is raised above, and the point 8| below the horizontal and the point 83 may, for example, be tilted below and point 84 above the horizontal plane, although this latter tilted position of the ring is not possible to show in drawings. Considering now that the aeroplane is moving in the direction of the arrow 85, with the blades in the position shown in Fig. 6 and the blades rotating in the direction of the arrows in Fig. 2 the blade 86 would at this instant be tilted with the forward edge downward, blade 81 also with the forward edge tilted downward, while blades 88 and 89 would be tilted with their forward edges in an upward direction, the same amount as the blades 86 and 81 are tilted downward. When blades 88 and 81 arrive at the positions formerly held by blades 88 and 89 respectively, these blades 86 and 81 would then tilt upward while the blades 88 and 89 would tilt downward. In other words, for each revolution each bladewill have been tilted once upward and once downward. The resulting'effect on the control over the flight of the aeroplane is easily imagined, thatis, the rotation of the blades, due to this control, will actually prevent the drifting oi the aeroplane due to the wind, regardless of the direction from which it comes in relation to the direction of travel of the aeroplane and will further maintain or direct the course of the travel of the aeroplane without regard to the wind condition, whether the course is downward or upward, or in any other direction.

It should be noted also that the angle of incidence may be adjusted to any desired degree by the rod 55 controlling, through the gear 54 and rack 53, the position of the rod 48. By moving the rod 48 upward the angle of incidence may be reduced and by moving it downward this angle may be increased. But regardless of what the angle is the rotation of the blades may, by the position of the ring 64, be so controlled that at any position of opposite blades, one will be tilted in one direction to the same degree as the other is tilted in the opposite direction, although it should be understood that the angle of incidence in one direction of one blade may be greater than the angle of incidence in the opposite direction of the other blade in relation to the horizontal plane.

The sustaining force effective on the blades due to their construction will now be described. If the blades are rotating it is evident that the column of air in the aperture or opening ill will, due to the centrifugal force be driven outward through the end of the blade and thus tend to create a vacuum in the aperture. This will, in turn, drive the air that rushes past the forward edge of the blade, across the lower surface of the blade inward and upward and past the ribs l3 into the aperture and then through the aperture out through the tip of the blade. The diagonal position of the ribs ill will tend to further aid the passage of this air into the aperture III by preventing it from slipping outward across the underside of the blade. Thus it will be seen that these air streams passing into the aperture will tend to exert an upward pressure on the underside of the blade and therefore act to lift the blade upward through the atmosphere to a greater extent than would ordinarily take place in the usual type of blades employed in autogyro type aircraft.

The original position of the rib plates 13 will also tend to keep the blades 1 in rotating motion, acted upon by the wind.

The annular gear 2|, attached to ring 23, and pinion 24, through a clutch connection, driven by the motor, serve to force a rotation of the blades 1. Thus, when a strong vertical lift is necessary, the pinion 24 is, through the clutch, (not shown), connected to the motive power and force is applied to the rotation of the blades, but when mere sustention is needed, the gears 2| and 24 may be disconnected from the power unit and the blades 1 will rotate, driven by the attack of the wind or current of air against the diagonal plates l3.

1 What I claim is:

1. An aeroplane comprising a rotatable structure on the upper surface of the fuselage, four wings mounted on said structure, each of said wings having an upper curved surface, a lower surface extending from the front edge of the wing to approximately the central longitudinal axis of the wing thereby forming an aperture extending longitudinally through the front portion of the wing between said surfaces, transverse ribs on the under side of the wing extending from the rear edge of the wing to approximately the central longitudinal axis of the wing thereby forming enclosures and said wing formed with openings connecting said aperture with the enclosures formed by said ribs.

2. An aeroplane comprising a rotatable structure on the upper surface of the fuselage, four wings mounted on said structure, means for adjusting the angle of incidence of said wings, each of said wings having an upper curved surface extending over the entire upper portion of the wing, a lower surface extending from the front edge of the wing to approximately the central longitudinal axis of the wing thereby forming an aperture extending longitudinally through the front portion of the wing between said surfaces, transverse ribs on the under side of the wing extending from the rear edge of the wing to approximately the central longitudinal axis of the wing thereby forming enclosures and said wing formed with openings connecting said aperture with the enclosures formed by said ribs.

3. An aeroplane comprising a rotatable structure onthe upper surface of the fuselage, four wings, mounted on said structure, means for adjusting the angle of incidence of said wings between two limits once during each revolution for each wing, each of said wings having an upper curved surface, a lower surface extending from the front edge of the wing to approximately the central longitudinal axis of the wing thereby forming an aperture extending longitudinally through the front portion of the wing between said surfaces, transverse ribs on the under side of the wing extending from the rear edge of the wing to approximately the central longitudinal axis of the wing thereby forming enclosures and said wing formed with openings connecting said aperture with the enclosures formed by said ribs.

4. An aeroplane comprising a rotatable structure on the upper surface of the fuselage, four wings mounted on said structure, means for adjusting the angle of incidence of said wings between two limits once during each revolution of each wing, means for changing said limits at any instant during rotation of the wings, each of said wings having an upper curved surface extending over the entire upper portion of the wing, a lower surface extending from the front edge of the wing to approximately the central longitudinal axis of the wing thereby forming an aperture extending longitudinally through the front portion of the wing between said surfaces, transverse ribs on the under side of the wing extending from the rear edge of the wing to approximately the central longitudinal axis of the wing thereby forming enclosures and said wing formed with openings connecting said aperture with the enclosures formed by said ribs.

5. An aeroplane comprising a stationary structure on the under surface of the fuselage, a rotatable structure mounted for rotation around said stationary structure on bearings at the upper portion of said stationary structure and on bearings on said fuselage, four wings, a shaft for each wing, means for rotatably mounting said shafts on said rotatable structure, a lever at the free end of each shaft, a ring surrounding said stationary structure, a bar, means for mounting said bar in a vertically slidable position in said stationary structure, a member having four arms, means for mounting said member at. its centre in said bar for movement within certain limits in any direction, means for connecting said ring to the outer ends of said arms, means for adjusting said member in any position within said limits in relation to said bar, a clamp shaped member for each lever slidably mounted on said ring, a universal link structure for connecting each clamp shaped member to a particular lever so arranged that when the ring is adjusted to a certain position in relation to the bar and the rotatable structure is rotated around the stationary structure said clamp shaped members will travel around the ring and transmit through their respective links and levers rocking movements'to the associated shafts, each shaft participating during each rotation of the rotatable structure of a rocking or turning movement consisting of a movement in one direction followed by an equal movement in the opposite direction.

6. An aeroplane wing having an upper curved surface extending over the entire upper portion of the wing, at lower surface extending from the front edge of the wing to approximately the central longitudinal axis of the wing thereby forming an aperture extending longitudinally through the front portion of the wing between said surfaces, transgerse ribs on the under side of the wing extend ng from the rear edge of the wing to approximately the central longitudinal axis of the wing, thereby forming enclosures and said wing formed with openings connecting said aperture with the enclosures formed by said ribs.

7. An aeroplane wing having an upper curved surface extending over the entire upper portion of the wing, a lower surface extending from the front edge of the wing to approximately the central longitudinal axis of the wing thereby forming an aperture extending longitudinally through the front portion of the wing between said surfaces, ribs on the under side of the wing extending diagonally across the wing from the rear edge of the wing to approximately the central longitudinal axis of the wing thereby forming enclosures and said wing. formed with openings connecting said aperture with the enclosures formed by said ribs.

HAKON G. LINIVJ.

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