US2023760A

US2023760A - Rotor flying machine

Info

Publication number: US2023760A
Application number: US706090A
Authority: US
Inventors: Dornier Claude
Original assignee: Individual
Current assignee: Individual
Priority date: 1933-01-16
Filing date: 1934-01-10
Publication date: 1935-12-10
Anticipated expiration: 1952-12-10

Description

Dec. 1o, 1935. DORMER 2,023,760

ROTOR FLYING MACHINE Filed Jan. 1o, 1954 4 sheets-sheet 1 De.1, 1935. C, DORMER Y 2,023,160

ROTOR FLYING MACHINE Filed Jan. 10, 1934 4 Sheei-cs-Sheet 2 Dec. 10, 1935. c. DoRNlER 2,023,760

ROTOR FLYING MACHINE Dec. 10, 1935. D0RN|ER 2,023,760*

ROTOR FLYING MACHINE Filed Jan. 1o, 1954 4 sheets-snee; 4

72: Uren for azweoL-Zz'er Wwf/Ml filon-lacy;

essence oec. 1o, 193s PATENT oFFlcE 2,023,160 KOTOR FLYING MACHINE Claude Dornier, Friedrichshafen, Germany Application January 10, 1934, Serial No. 706,090 In Germany January 16, 1933 12 Claims.

This invention relates to a flying machine, more particularly to a dying machine having, instead of stationary wings mounted to the fuselage, a system of rotating hereinafter shortly called rotors adapted to move the machine horizontally, vertically or on an inclined course. Instead of one rotor, I can employ a plurality of rotors having parallel axes, e. g., in conneetion with large iiying machines. The rotors are vpower driven but can be disconnected from the source of power, e. g., when the machine descends.

An object of this invention resides in the provision'of a flying machine having only one power driven means for actively propelling the machine in a horizontal as well asin a vertical direction.

An object of this invention resides in the provision of a ying machine having only one means for lifting and propelling the machine, said means being arranged adjacent to the main body of the machine.

An object of this invention resides in the pro-V vision of a lifting and propelling rotor system for iiying machines assuring utmost ease in operation and air-cushioned vibrationless motion.

An. object of this invention resides in the provision of a ilying machine having an adjustable fuselage assuring a most convenient conguration of the fuselage for landing, loading and unloading purposes and the most emcient outside contour for dying.

An object of this invention resides in the provision of a collapsible fuselage for ying machines providing a contour and dimensions securing greatest flying eiiiciency and eiciency of the rudder and balancing apparatus and, at the same time, a most convenient form of the fuselage for landing, loading, unloading and hangaring.

An object of this invention resides in the provision of a flying machine having a telescoping fuselage adapted to assure best operating and maneuvering eiciency and also smallest and most suitable shape for landing, starting, loading, unloading and hangaring.

An object of Y this invention resides in the provision of a living machine of such comiguration as to assure best equilibrium and balancing conditions.

An'ohject of this invention resides in the provision of a flying machine having novel adjustable means for assuring best equilibrium and balancing conditicns.

Further and other objects of the present invention will be hereinafter set forth in the aoshape of companying specification and claims and shown in the drawings which, by way of illustration, show what I now consider to be a preferred embodiment of my invention.

In the drawings: Fig. 1 is a schematic side according to my invention.

Fig. 2 is a side view of a flying machine according to my invention with body for receiving passengers, load,l running gear and other details l. attached.

Fig. 3 is a front view of the machine illustrated by Fig. 2.

Fig.- 4 is a part cross sectional side view of a modification of a. flying machine according to my 1l invention;

Fig. 5 is an isometric illustration of a large seaplane according to my invention.

Fig. 6 is a longitudinal part cross sectional View of a wing system according to my invention show- 20 ing the mechanism for adjusting the wing control surfaces in particular.

Fig. 'l is a transverse part cross sectional view substantially along line 1--1 of Fig. 6.

Fig. 8 is a. top view of a rotating wing system according to my invention.

Figs. 9, 10 and 11 are part sectional side views of flying machines according to my invention illustrating certain details. v

I shall now proceed to generally describe the 30 underlying ideas of my invention with the assistance of the diagrammatic sketch Fig. 1. How these ideas can be can'ied out practically will be 'described later with the assistance of Figs. 2 to 11 which illustrate preferred embodiments of my 35 invention.

Fig. 1 diagrammatically illustrates a flying machine according to my invention omitting the showing of the motor drive, provisions for carrying passengers and freight and the undercarriage i0 o'r oats. At its front end, the body l has a system of rotating lift-producing wings 2 henceforth called rotor. At the lower rear end oi body i is the tail unit consisting of the tail n 3, the rudder l, a tail plane 5, and an elevator 45 When ying in horizontal direction the axis 00 around which rotor 2 rotates is inclined. It forms an angle a with the horizon which is open in'the direction of the night and is always larger than 0 and smaller than 90. Body I has the 50 a spindle the longitudinal axis of which substantially coincides with the rotating axis of wing system or rotor 2. In practice the shape of body I deviates more or less from that of a true spindle, as will be described later. Instead 0S view of the machine of one rotor, a plurality of co-axial and pairwise counterrotating rotors can be employed, as shown in my copending application Ser. No. 708,395. Large machines can be provided with outriggers each equipped with one or a plurality of rotating wing systems, wherein the axes of the individual rotors are parallel with respect to one another. 'Ihe tail unit which is at or near the rear end of spindle body I is preferably located in the air current discharged by the rotor; the stabilizers 5 constituting the elevator can be operated from the pilots seat, whereby the angle of attack can be changed at will. AThe connections required for this operation are not shown in the drawings because the mechanism is well known in the art. As is obvious from Fig. 1, the vertical component IOI of the force |02 generated by rotor 2 acts on the system at the small distance |03 from the center of gravity I 04 of the cording to my. invention and equipped with un- 20 system; while the vertical component |05 of the force |06 resulting from the elevator unit acts on the system at the much greater distance |01 from the center of gravity |04 of the system. The weight of the flying machine is thus chiefly carried by the rotor and only a small part of it is carried by the tail unit; the lift power of the tail unit can be adjusted by adjustment of the angle of attack in order to keep the machine balanced at various operating conditions. As will be described later, a disconnectable coupling is provided between rotor 2 and the motor driving it and not shown on Fig. 1; the rotor is of such dimensions that, when light running, i. e., when the before mentioned coupling is disconnected, it rotates by itself in such va direction and at such a speed as to assure a. descending speed suitable for landing. The wings of the rotor are adjustable in well known manner permitting an .adjustment of their power absorbing capacity in accordance with the change of the inclination of the revolving axis with respect to the horizontal. It is also advisable to provide flaps on the rear edges of the wings or auxiliary wings at the end of the main rotating wings, the position of said aps and/ or wings being automatically controlled so that the work of each rotating wing periodically changes during each revolution; the extent of this change can be adjusted, as will be described later. Rotary systems of this type greatly assist the tail unit at the rear end of the fuselage with respect to maintaining the ying machine in properly balanced condition. For the same purpose, particularly for counterbalancing the torque of the rotor, stationary and/or movable means may be provided at greatest possible distance from the axis of symmetry of the machine. 'I'hese means can be arranged on the undercarriage or the floats and can be adjustable during the night and of such conguration as to generate air pressure and/or currents to balance the torque of the motor and to serve forY other stabilizing purposes. Bodies acting in the aforesaid manner can, at the same time, be used for covering parts of the machine which must be protected from the ying wind such as, e. g., the wheels of the undercarriage. This will also be described later.

As already. stated, it is not always possible to design the fuselage in true spindle shape because of the necessity of providing room for passengers,

freight, motors etc. For this purpose 'I provide'a goiter-like body on the lower front side ofthe spindle, said body having the shape of a rightangled triangle the hypotenus'e of which is the ro-4 tating axis of the rotor, the bottom of said body being one cathetus of said triangle, the latter being in a substantially horizontal position before starting and when flying in a horizontal direction. The body has a streamline configuration which follows the air stream resulting from the forward movement of the machine'and the air current generated by the rotor. The goiter-like extension permits entirely free vision for the pilot forwards and downwards. The motor is disposed either in the rear part of said triangle-shaped body or adjacent to the rotor. 10

The rotor or rotors can be driven by one or a plurality of shafts connected to gears driven by the motor. These gears can be located either close to the rotor or to the motor. If a great ratio of transmission is required, instead of one gear, 15 several gears can be installed some of which are disposed near the motor or motors and others near the rotor or rotors. l

Fig. 2 is a side view of a flying machine acdercarriage and cabin for the passengers.

Fig. 3 is a front view of the same machine. The spindle shaped body 1 carries at its front end a rotor consisting of wings |01 and I 08 the revolving axis of which is inclined with respect to the 25 horizontal by the angle a. The ends of the wings |01 and |08 of the rotor are equipped with adjustable flaps 8 and 9. If they are so adjusted that they both project from.the same side of the planeof rotation of the wing system, they 30 aid in increasing the lift of the whole rotor. If one approjects on one side and the other flap on the other side of the plane of rotation of the wing system and if the position of the ilaps is periodically changed in known manner during 35 each revolution, the equilibrium of the flying machine can be affected. The motor driving the rotor is disposed adjacent to the rotor underneath an annular hood I0. The tail unit is attached to the rear end of the fuselage and con- 40 sists of the side n I I, the side rudder I2, the tail plane I3, the angle of attack of which can be adjusted during the ight, and the elevator Il. At the lower front side of the spindle-shaped body is the extension I5 serving as room for pas- 45 sengers and freight. The outside contour of the side view of this extension is substantially like a rightangled triangle. Body I5 has streamline configuration, particularly in the planes designated by the dotted lines I 09, I I0 and III which 50 are vertical with respect to the sheet of drawings and are in the direction of the air flow resultant from the forward movement of the machine and the air current discharged by the rotor. For resting on the ground the machine is provided 55 with a spur I6 and an undercarriage with wheels I1. Wheels I1 are covered by covers I8. These covers together with the streamlined bodies I9 which are revolvable around vertical axes II2 generate air forces by their form and/or adjust- 60 ment which counteract the torque of the rotor or produce other stabilizing effects.

Fig. 4 is a longitudinal section through a ilying machine using my invention in a modified way inasmuch as the motor 25 is arranged in 65 the rear of the rl om for the passengers and freight and stands on a plane common with the floor plane of said room. The body 20 carries the rotor 2| at its front end. The longitudinal axis I|3 of body 20 does not coincide with the 70 rotating shaft 28 of the rotor. In order to obtain the greatest distance possible between the tail unit and the rotor and in order to reduce the height of the flying machine, the longitudinal volvingaxis of the rotor, and the rear end of body 28 is slightly curved upwards resulting in a saddle-like configuration of the back of body 20. The wings of rotor 2l are provided at their ends with aps 22 which are movable and adjustable so that they may be projected from different sides of the plane of rotation of the rotor. They are adapted to periodically change their position in known manner during each revolution and to thereby periodically increase or decrease the lifting force of the individual wing. Other naps 23 are provided and located closer to the hub of the rotor; these flaps 23 both project from one side ofthe plane of rotation, and the degree of projection can be adjusted. This adjustment causes a change of the lifting power of the whole proy peller. These ilaps permit the adjustment of the work done by the rotor as required by a change of the angle a, i. e., the angle formed by the axis of the rotor and the horizon. Below body 20 is an extension `24 adapted to receive passengers or freight. The rotor is driven by motor 25 via gear 28 located adjacent to the motor, the disconnectable coupling 21 and shaft 28. Motor, coupling and gear are in`one chamber which is on the same plane as the room for the passengers. The ying machine as illustrated is built as a land plane and is provided with landing wheels.

Fig. 5 is a perspective illustration' of a flying machine differingv from the previously described machines in regard to its size and the provision of fioats 29 instead of landing wheels and the provision of two rotors instead of one. The floats are connected with the fuselage by a frame work in the usual and known manner. The motor is located in the lower part of body ||3 and in the rear of the passenger and/or freight room IM, as was the case in the machine shown by Fig. 4.

The power is transmitted by shaft ||5 to the front end of body I3 and therefrom over a bevel gear to shafts 3| and via further bevel gears covered by hub bodies IIB to the rotors 30. The reduction of speed of the motor to that required by the rotors can thus be conveniently distributed over a plurality of gears. The rotor wings are equipped with a system of flaps projectable from both sides of the plane of rotation and a system of ilaps projecting only from one side of the plane of rotation, as is done in the machine shown on Fig. 4. Streamlined bodies 32 are disposed on top of oats 29 and adapted to be rotated around the vertical shafts which serve at the same time to support the rotors 30. These bodies 32 can be adjusted as to -their position by the pilot by means of lever I|8 rigidly connected to the body and shafting H9 extending into the pilots cabin Hd. Bodies 32 serve by their configuration and position to stabilize the flying machine.'

Figs. 6, 7 and 8 illustrate in detail the mechanism for operating the

flaps

22 and 23 in the manner stated `in the foregoing paragraphs., I wish it to be understood that the mechanism shown is only one of the possible ways to materialize the object of providing the wings of a rotor with a system of flaps vadjustable While the rotor is in operation. and adapted to affect the lift power ofthe rotor and to act as balancing means whereby the balancing eiect can also be adjusted while the rotor is in operation. The system substan, tially consists of a pair of

flaps

22 and 23 in each wing 2|. Flaps 22 can be turned to project above main wing 2| or below it, as is obvious from Fig. 7. Flaps 22 are connected to s'hafts 88 which are provided with cranks 86 and 81 respectively. The

end of these cranks has the formation of claws |22 adapted to slidably engage disc which does not take part in the rotation of the rotor. As long as this disc is in a position parallel to shafts 88, the position of iiaps 22 with respect to wings 2| will 5 be maintained. The angle of the aps with respect to the wings can be changed by moving disc 85 up or down. If, however, the disc is held in an inclined position, the angle of aps 22 with respect to wings 2| will continually change during 10 each revolution of the rotor. This can be carried so far that the aps periodically project underneath and above wings 2|. The lift power of the wing will thus continually change during each revolution of the rotor, being largest at a certain 15 A position of the rotor and being smallest at the diametrically opposite position. The degree of the inclination of disc 85 can be adjusted while the whole system is in operation by manipulating lever 88. This rotates around fulcrum 8l carried 20 by support 82 which is located in the fuselage of the iiying machine. At equal distance from and at both sides of the fulcrum 8|,

rods

83 and 84 are linked to lever 88; the other end of these rods is linked to disc 85. All this can readily be seen 25 from Fig. 6 and also how disc 85 is adjusted by moving the handle of lever 80 up or down.

Flaps 23, which need not change their position during each revolution of the rotor, are mounted to the hollow shafts 90 and 9| which have cranks 30 82 and 93 respectively. Each crank has a claw |23 slidably cooperating with disc 94. 'I'his disc is rigidly connected to shaft and can be moved up and down by operating lever 91, swinging around fulcrum 96 and having on one end a fork 35 |24; this fork cooperates with projection 25 of shaft 95. For instance, by depressing the left end of lever 91, the fork end pushes shaft 85 and with it disc 94 and cranks 32 and 83' upwards; thereby shaft 9| is turned clockwise and shaft 38 40 counterclockwise, when observing this operation on Fig. 7, and both iiaps 23 are moved in such a Way as to further project from the bottom side of wings 2| and increase their lift power. Fig. 8, which is a top view of a rotor provided with ad 45 justable flaps, further assists to illustrate the foregoing. Like numerals on this gure and Figs. 6 and 7 indicate like parts and render Fig. 8 self-explanatory. v

To obtain an absolutely smooth operation of the 50 rotor and to eliminate percussions, a hollow rotor can be provided having apertures at the ends of the wings or near the ends, and the rotor can be driven by the reactive action of an air current flowing from the hollow hub of the rotor through 55' the hollow wings and said apertures or in opposite direction. This air current is generated by a blower driven by the motor which is arranged integral with the rotor, as will be more 'particularly described later. If such a pneumatic drive of the rotor is employed, provision of a. brake for the rotor is essential. The air current is also used for cooling the motor or motors directly or for `re cooling the cooling water.

Fig. 9 illustrates a flying machine of the same 65 type as illustrated by Fig. 4 but having a rotor operated by the reactive force of an air current. Rotor 33 is hollow and has at its ends apertures 34 and 35 through which air is eitherblown out of or taken into the interior of the rotor wings. 0

A motor 38 is located in the lower part of body 3l having a saddle-shaped concaveiy curved back and in the rear of extension 36. Via gear 38 and the disconnectable coupling 40, the motor drie-'es shaft M carrying the rotor I2 of the blower. 75

Shaft 4| is carried by the

bearings

43 and 44. With its ball-shaped end |20; blower 42 extends into the interior of rotor 33 which is equipped with a projecting part 45 of such configuration as to facilitate the air ow between the blower and the interior of the rotor. Rotor 33 is carried by the fuselage by the axial and radial bearing 46, The air is taken in through channel 41 provided ,within body 31 and is forced by blower 42 into the hollow rotor 33 and leaves this rotor through the apertures 34 and/or 35 which are placed at the rear edge of the rotor wings.'l The air flow can alsobe reversed and the air taken in through openings located near the edge of the rotor wings and discharged through channel 41. In this case, the openings must be arranged in the front edge of the wings. In both cases the air passesthrough a cooler.48 which is connected with the cooling jacket of motor 38 by conduits |26 and |21 and acts as cooler for the cooling agent of the motor.v

Fig. 10 illustrates an embodiment of my invention using the pneumatic reaction type rotor drive and an air cooled motor 54 driving the air pump 50 and located adjacent thereto. Blower 50 is rotatably carried by bearings 5I and 52. 'Ihe air taken in or exhausted by the blower passes through channel 53 in which the motor is located thereby directly cooling' the motor. A guide 55 for the air is provided in the interior of rotor 49.

'I'he fuselage of the machine illustrated by Fig. Hl consists of a front part B to which a rear part 58 carrying thetail unit is movablylinked by means of the hinge 51. During the flight rear part 58 is held in the position indicated by the dotted lines 58' by means of the spring member 59. When landing the spur wheel 60 at the rear end of part 58 rests on the ground thereby bending the rear end 53 upwards against the action of spring 59 and as far as the stop 6| permits. This arrangement provides that the main body of the fuselage is close to the ground when the vmachine is landed and that the tail unit is at an efficient distancefrom the center of. gravity of the'machine and the rotor when flying.

Fig. 11 illustrates a flying machine according to my invention having a motor driven rotor 64 the motor being adjacent to the rotor and under a hood 65 as is the case in the machine illustrated -by Fig. 2. The spindle-shaped part of the fuse--l lage consists of two

parts

62 and 63 concentrically arranged within one another. The front part 62 carries the rotor 64 driven by the air cooled motor located underneath the annular hood 65 which guides the cooling air and improves its cooling roller 68 mounted to and within part 62 to the ess, design and construction shown and described, for obvious modifications will occur to a person skilled in the art.

What I claim is:

1. A dying machine comprising a substantially 5 spindle-shaped body having two ends, a rotor producing lift and propelling power rotatably connected to one end of said body and a tail unit connected to the other end of said body, said body being inclined when ying in a substantially horizontal direction whereby the elevation of said rotor is greater than that of said tail unit, and a compartment protruding forwards and downwards from said b ody and adapted to receivel passengers and freight.

2. A fiying machine comprising a substantially spindle-shaped body having two ends, a rotor producing lift and propelling power rotatably connected to one end of said body, and a tail unit connected to the other end of said body, said body being inclined when fiying in a substantially horizontal direction whereby the elevation of said rotor is greater than that of said tail unit, and a compartment protruding downwards and forwards from said body and adapted to receive passengers and freight, said compartment having a bottom and a front wall, the longitudinal extension of said compartment having an outside contour forming a substantially rectangular triangle one cathetus of which is formed by the bottom of said compartment thc other cathetus by the front wall of said compartment, and the hypotenuse by said body.

3. A flying machine comprising a substani tially spindle-shaped body having two ends, a 3,-, rotor supplying lift and propelling power for said ying machine and rotatably connected to one end of said body, and a tail unit connected to the other end ofsaid body, said body being inclined when ying in a substantially horizontal direction, and a compartment protruding forwards and downwards from said body and adapted to receive passengers and freight, and outriggersprotruding from said compartment, said outriggers carrying running wheels.

4. A flying machine comprising a substantially spindle-shaped body having two ends, a rotor supplying lift and propelling power for said flying machine and rotatably connected to one end of said body, and a tail unit connected to the other end of said body, said body being inclined when flying in a substantially horizontal direction, and a'compartment protruding forwards and downwards from said body and adapted to receive passengers and freight, and outriggers protruding downwards and sidewards from said compartment, said outriggers carrying floats.

5. A flying machine consisting substantially of a plurality of lift and propelling power producing rotors, a substantially spindle-shaped body having a goiter-like extension protruding forwards and downwards from said body and adapted to receive passengers and freight, outriggers connected to and carried by said body, said outriggers carrying adjustable stabilizers and said 35 rotors.

6. A flying machine consisting .substantially of a plurality of lift and propelling power producing rotors, a substantially spindle-shaped body having a goiter-like extension protruding downwards and forwards from said body and adapted to receive passengers and freight, outriggers connected to and carried by said body, said outriggers carrying adjustable stabilizers and said rotors, apower plant located within said body,

and power transmitting means connecting said power plant and said rotors.

7. A flying machine comprising a substantially spindle-shaped body having two ends,` a rotor producing lift and propelling power rotatably connected to one end of said body, and a tail unit connected to the other end of saidbody, said bodybeing inclined when flying in a substantially horizontal direction, whereby the elevation of said rotor is greater than that of said tail unit, and a compartment protruding downwards from said body and adapted to receive passengers and freight.

8. A iiying machine comprising a substantially spindle-shaped body having two ends, a rotor producing lift and propelling power rotatably connected to one end of said body, a tail unit connected to the other end of said body, said body being inclined when flying in a substantially horizontal direction, whereby the elevation of said rotor is greater than that of said tail unit, and a compartment protruding forwards from -said body and adapted to receive passengers and freight.

9. A flying machine comprising a body being inclined when flying in a substantially horizontal direction, a rotor connected to and supplying lift and propelling power to said machine, a compartment protruding downwards from said body and being adapted to receive 'tal direction.. a rotor connected to and supplypassengers and freight, and outriggers protruding from said compartment and carrying-stabilizers. 1

10. A flying machine comprising a body being inclined when flying in a substantially horizoning litt and propelling power to said machine, a compartment protruding downwards from said body and being adapted to receive passengers and freight, and outriggers protruding downwards and sidewards from said compartment and carrying adjustable stabilizers.

11. A ilying machine comprising lift producing means, a body inclined when ying iny a substantially horizontal direction, a compartment protruding downwards from said body and 15 being adapted to receive passengers and freight, and outriggers protruding from said body and' compartment and carrying said lift producing means.

l2. A ying machine comprising supporting means, litt producing means, a body inclined when ying in a substantially horizontal direction, a compartment protruding downwards from said bo'dy and being adapted to receive freight and passengers, and outriggers protruding from said body, said outriggers carrying said supporting and lift producing means.

CLAUDE DORNIER. so