US1960141A

US1960141A - Helicopter

Info

Publication number: US1960141A
Application number: US426153A
Authority: US
Inventors: D Ascanio Corradino
Original assignee: Individual
Current assignee: Individual
Priority date: 1929-02-09
Filing date: 1930-02-05
Publication date: 1934-05-22
Anticipated expiration: 1951-05-22

Description

May 22, 1934.

C DASCANIO HELICOPTER 2 Sheets-Sheet 1' Original File d Feb. 5, 1930 152 are nror:

.w n a x 6 WWW d 0 L, w WI y 4- c. DASCANIO 1,960,141

' HELICOPTER w Original Filed Feb. 5, 1930 2 Sheets-Sheet 2 In v'entoi'v bCorradz'nO d'fiscarzz'o 1 4; w W 7 I. 5:943

- Patentecl May 22, 1934 {UNITED sures HELICOPTER Corradino dAscanio, Rome, Italy asai or to Pietro TroianLRomeJtaly m I Application February 5,

Renewed October 31, 9, 1929 Claims.

\ The invention relates to helicopters and its ob.- Ject is to construct a helicopter which is substantially characterized by the fact that the blades of its two or more coaxial horizontal propellers revolving in opposite directions and provided with tail wings or horizontal rudders, are tiltable about their longitudinal axis of gravity and -are also freely movable about an axis which is perpendicular to. and passes through the axis of rotation ofj'the propellers. The axis of gravity of the blades, about which they are tiltable, passes through the axis of rotation of the propellers and extends in proximity of the centres of aerodynamic pressure of the combined blades and rudders.

When the propellers are rotating each blade takes up a longitudinal position in accordance with the resultant of the aerodynamic thrust and of the centrifugal force, and a transverse position which depends on the action of the horizontal rudders. Further, when the motor is stopped, the said rudders cause the blades to take up automatically a position in accordance with the optimum angle of incidence of a gliding flight, and they thus sustain the machine while continuing to rotate, so that the machine will descend with a small speed which depends on the load and on the aerodynamic features of the blades and the rudders.

The tail wing of the blades of the propellers is provided with movable parts which may be operated by the pilot and which control the vertical movements of the machine, so that through a movement of the said movable parts the angle of incidence of the blades respecting the wind and therefore the movement of the machine in a vertical direction are being controlled.

When using two propellers revolving in opposite directions, they may be driven by means of an epicyclic gear whose driving wheel is rotated with a high angular speed by the motor, the propellers following respectively the rotation of the planet wheels and therotation of the crown wheel ofthe epicyclic gear, so that an automatic equilibrium of the couples of reaction of the two propellers revolving in opposite directions is set up.

' In this latter case, in order to control the vertical movements of the machine, only the tail wings of the lower propeller may be provided with movable parts under the control of the pilot,

while the tail wings of the upper propeller are immovable and its blades therefore move with a constant angle of incidence. The vertical movements of the machine are then controlled 1930, Serial No.

428,153. 1933. In Italy February by varying the angle of incidence of the blades of the lower propeller through manmuvring the movable parts of its tail wing so that the upward thrust of the two propellers will be altered through a variation of the angle of incidence of --the blades of the lower propeller and through an automatic increase ordecrease of the angular speed of the blades of the upper propeller produced by the variations of reaction of the lower propeller.

One or more additional smaller propellers whose blades may be operated by the pilot and which are driven by the motor and rotate about axes which are substantially at right angles respecting the axis of rotation of the main propellers and far apart therefrom, render it possible, when their pitch is being altered, to create a lateral thrust adapted to compensate the couple of differential reaction of the-main shaft which rotates at a high angular speed, and thus capable of steering the apparatus in the desired direction.

One or more other additional propellers whose blades may be controlled by the pilot and which are driven fromthe motor and rotate about axes 89 which are substantially parallel with the axis of rotation of the main propellers, render it possible, when their pitch is being altered, tocreate a vertical thrust which produces an inclination of the axis of the machine and thus creates a horizontal 8 component of the thrust due to the main propellers, which said component produces the forward flight of the whole machine.

There are also provided devices, such as will hereafter be described, for automatically con- 9o trolling the horizontal rudder when the longitudinal axis of the blade inclines beyond a preestablished limit above the horizontal, for automatically causing; the blades to tilt about their longitudinal axis in order to increase their incidence during landing, for elastically or rigidly connecting between them the blades of each propeller, for allowing the blades to continue to rotate freely even when the motor has been stopped, and for damping abrupt movements of the blades of the propellers about their longitudinal axes.

The'invention is shown by way of example in the accompanying drawings wherein Fig.1 is a side view, partly in section, of the helicopter,

Fig. 2 is a plan view thereof, the blade porting arms being shown in section,

Fig. 3 shows a blade of the propellers seen in the direction of its longitudinal axis,

sup-

Fig. 4 shows a form ofcshock absorber upon the various blades, and.

Fig. 5 shows schematically the controlling apparatus of the machine.

The helicopter as illustrated in Figures 1 and 2 comprises a fuselage l which is mounted on a resilient landing gear. The fuselage contains the cockpit and the necessary spaces-for the gears, the tanks andso on, and also a motor 2 which through a friction gear 3 adapted to be operated by the pilot, and through a bevel gearing 4 transmits its motion to a vertically arranged shaft 5 which rotates with a high angular speed. This shaft 5 is connected at its upper end to the driving wheel'B of anepicyclic gear. The planet pinions '7 of this gear are mounted on the upper end of a tubular shaft 8 which surrounds the shaft 5 and is coaxial therewith. The shaft 8 is secured to the fuselageby, and rotates in, bearings 9 and 10. Its upper end carries on suitable bearings the crown wheel 11 of the epicyclic gear.

The sets of blades of the two propellers of the helicopter are respectively secured to the crownv wheel 11 of the epicycliegear and to the shaft 8. Each blade comprises an arm 13- and a wing element or blade proper 12. The blade 12 is secured with its prolongation 14 to the respective arm 13, for example-with the interposition of suitable bearings, so that the blade is capable of tilting on the arm about a longitudinal axis of gravity 15 which extends in proximity of the centres of aerodynamic pressure of the various sections of the blade. The arms 13 are pivoted to the shaft 8 and to the crown wheel 11 respectively by means of

pins

17 and 16 arranged respectively in pairs on an axis which is perpendicular to the axis of rotation of the propeller and crosses this axis. Each blade is provided with a stabilizing sur face arranged at a suitable distance from its exit edge towards its outer end. this surface being thus in the zone of the maximum circumferential speed. The stabilizing surface like the horizontal wing of a common airplane, consists of two members, of which the member 18 is secured rigidly to the blade, while the member 19 is hinged to the first member and may be operated by the pilot after the manner of the horizontal rudder of an airplane.

The fuselage carries at a suitable distance from the central vertical axis two small propellers 20 and 21, of which the'propeller 20 is arranged at the tail end of the fuselage, its axis being parallel to the shaft 8, while the propeller 21 is ,arranged laterally of. the fuselage with itsaxis in a horizontal position. The propeller 20 is driven by the motor through a shaft 22 arranged in line with the driven shaft of the friction gear, and

through a small bevel gearing 23, or in any other suitable way, while the propeller 21 is driven by means of two sets of bevel gears of which one set 24 is arranged in the carter of the bevel gear 4 and is concentric therewith, while the other set 25 is arranged on the end of the driving shaft 28. The blades both of the propeller 20 and of the propeller 21 may be controlled by the pilot. For stabilizing purposes two propellers 21 may be arranged symmetrically respecting the axis 0 the helicopter.

The machine works in the following way. On the motor being thrown into gear and the movement being transmitted to the epicyclic gear, by means of the friction gear or in other ways, the two main propellers which are respectively con- ,nectedto the crown-wheel 11 and to theshaft 8,

start to rotate in opposite directions with such angular speeds asto set up an equilibrium between the two couples of reaction of the two propellers. In this way, the machine is influenced only by the couple of reaction due to the secondary shaft 5, which couple however is very small in view of the high angular speed of the secondary shaft, and may thus readily be compensated by the small lateral propeller which with its horizontally arranged blades serves also for steering the machine which will deviate in one direction or the other or will not deviate at all according to whether the moment of the thrust of the lateral propeller respecting the central axis of the machine is greater or smaller than, or equal to, the couple of reaction of the shaft 5.

When the main propellers are in motion, each blade will ,take up under the action of its tail wing a certain angle of incidence respecting the wind and thus produce a thrust which will raise the machine. Abrupt movements of the blades of the main propellers about their longitudinal axis are clamped by shock-absorbers, for example of the hydraulic type, not shown in the drawings. -As further the blade is pivoted through the intermediary of its arm either to the crown wheel of the epicyelic gear or to the central shaft 8, it will take up a longitudinal position in accordance with the force resulting from the centrifugal force and the thrust.

By operating the horizontal rudders of the blades their angle of incidence respecting the wind and therefore the vertical thrust of the two propellers may be varied. It will thus be easily understood that with the arrangement described a perfect stability of the machine is assured. A gust of wind which invests the blades unequally cannot produce a canting of the apparatus, as the centre of pressure of the two sets of blades remains unaltered and passes always through the pivots and thus through the central axis of the machine. On the other hand, the controls for raising the machine are Just as easily managed and act quite as semi-automatically as in ordinary airplanes, as they are realized in a quite similar manner.

For the forward drive of the machine it is sufficient to act on the tail propeller which through a suitable manoeuvre of its blades will produce an upward thrust which tends to'incline the central shaft forward and thus creates a horizontal component of the thrust of the main propellers, which will cause the machine to advance. Through an inverse manmuvre the machine may be braked during its horizontal flight or its direction of flight may be inverted.

It will also be evident that it is also possible to control the rise of the machine by acting only on the blades of the lower propeller, in which case only these blades will be provided with the horizontal rudder 19, while the blades 12 ofthe upper propeller will be provided only with the fixed wing 18 and thus rotate with a constant angle of incidence. When varying the incidence of the blades of the lower propeller by means of a mameuvre of the horizontal rudder 19. a variation of the upward thrust of the two propellers will be obtained through the said variation of the angle of incidence of the blades of the lower propeller and through an increase'or a decrease of the angular speed of the upper propeller due to the variations of the reaction of the lower propeller.

shaft may also be obtained in other ways, for

example in the way shown in Figure 4. The

blades 12 during their rotation about their own axes are clamped by means of a shock absorber which acts between an arm 28 secured to each of the said axes and a point 32 upon the blade. The shock absorber comprises a piston 29 which slides in a cylinder 30 containing oil or the like and which is pivoted at 31 to the arm 28, while the cylinder 30 is pivoted at 32. The sets of the blades are again pivoted respectively to the cen tral shaft 8 and to the crownwheel 11 and if the propeller has two blades a pivot like the one above described will be employed, while if the propeller has more than two blades a universal Joint will be used. Thus, while the resultant of an aerodynamic action on the blades passes always through the pivot of the set on the central shaft 8, the angular speed of this shaft may be reduced at will, as it is no longer necessary that a given centrifugal force should be generated on the blades to maintain their longitudinal axis suitably inclined.

By the described arrangement the machine is rendered capable of descending slowly even if the motor has been stopped. The single blades working as elementary airplanes, will then automatically take up a position corresponding to the optimum angle of gliding flight, and will continue to rotate under the action of the horizontal components of the gravity. The speed of descent depends on the shape of the blades, on the load and on the aerodynamic features of the combined blades and wings, and the various members may thus be constructed so as to reduce the said speed to a preestablished, limit in accordance with the capacity of the landing gear of absorbing the kinetic energy.

The transmission between the motor and the blades may have inserted in it a free wheel or several free wheels (not shown in the drawings) which when the motor stops permit the blades to rotate freely without their having to trail heavy moving parts or Without it being necessary to operate the friction gear.

Suitable elastic ties 2'7 sustain the blades in a given position of rest. These ties are secured to the blades in a point slightly in front of the longitudinal axis of the blades so that the shock imparted to the whole arrangement when the machine lands, will cause the various blades to be automatically tilted so as to increase their angle of incidence, whereby the shock will be damped and the propellers be braked.

The whole machine is controlled by the aid of one single hand-wheel arranged within reach of the pilot. A perspective view of the control is shown in Figure 5 wherein dotted lines indicate the central shaft 8 with two bladearms secured thereto, in order to illustrate the position of the control respecting said shaft.

Two brackets 33 are rigidly secured to the fuse-- lage and carry a double-forked lever 35 adapted to rock about an axis 34 at right angles respecting the central shaft 8. To the rear end of this lever meets the axis 36. A chain 41 passes round the said sprocket and round a sprocket 42 secured by means of a universal Joint to the upper end of a small shaft 43 and arranged at the point where the axis 34 meets the longitudinal axis of the lever 35. The lower end of the shaft 43 carries a pulley 44 on which trains a small cable 45 which transmits the rotation of the pulley 44 to a pulley 46 whose movements produce variations of the pitch of the lateral propeller by the aid of one of the usual devices.

The axis 34 has pivoted to it a lever 47 which is connected by means of a rod 48 with the lever 37 and is also connected by means of a rod 49 with one arm of a bell crank lever 50 adapted to rock about an axis 51 which is parallel to the axis 34, while the other arm of the said lever 50 is connected with a small cable 52 which passes round two pulleys 53 and 54. The rotation of the pulley 54 causes variations of the pitch of the tail propeller in a manner similar to the pulley 46.

The ends of the front fork of the lever 35 enter a groove of a collar 55 which is coaxial with the shaft 8. This collar rotates together with the shaft 8 and may be displaced in an axial direction. The collar is connected by means of small rods 56 with the forked end of a bell crank lever 57 adapted to rock about an axis 58 which is carried by the shaft 8 at right angles thereto. The upper end of the lever 57 carries a spindle 59 which is parallel with the axis 58 and has pivoted to it two bell crank levers 60. The horizontal arms of these levers are provided with grooves which slide on two pins 61 secured to rods 62 which may be displaced in a parallel direction respecting the axis of the shaft 8 and are guided by sleeves 63 secured to the shaft 8. The rods 62 are normally maintained in their lower position by means of springs 64.

The ends of the vertical arms of the levers are connected by means of small rods 65 to bell crank levers 66 which rock on the axes 67 on the blade supporting arms. These levers 66 are further connected by means of rods 68 arranged inside the blades, of a bell crank lever 69 and of a small rod. 70 with the lever '71 of the horizontal rudder 19 of the tail wing on each blade.

The lower ends of the rods 62 are fastened by means of cables 72 of a certain length to points on the blade supporting arms at a suitable distance from the axis of rotation-of the said arms.

The devices now described work as follows.

The machine is controlled in a vertical direction through moving the hand wheel 39 axially in the direction of the arrow 74, whereby the lever 35 is caused to rock about the axis 34 and produces by means of the described transmissions of rods and levers a movement of the horizontal rudder of the tail wing of each blade, the angle of incidence of the blade and its'vertical thrust being thus altered.

The forward flight of the machine is controlled by moving the hand wheel in the direction of the arrow 75, viz. in the direction of the longitudinal axis of the fuselage. In this case the lever 37 rocks about the axis 36 and produces by means of the rod 48, the lever 4'7, the rod 49 and the lever 50 a movement of the cable 52 in one direction or the other and thus a rotation of the pulley 54, whereby the thrust of the tail propeller will be altered and the axis of the machine will be given the inclination which is required to create the forward thrust.

For steering the machine in the desired direction it is necessary to turn the hand wheel about its own axis, as this rotation produces by means of the chain 41 and the cable 45 a rotation of the add lie

lot)

pulley 46 and thus a variation of the thrust of the laterally arranged propeller.

As above said, the blade supporting arms which are pivoted to the shaft, take up automatically a certain inclination above the horizontal, this inclination being the resultant of the centrifugal force and the vertical thrust. The cables 72 have such a length that they become tight when the arms surpass the said normal inclination, while they are slack when the arms move downward. If on account of a sudden gust of wind or of a larger speed of the blade moving against the wind during the forward flight, or on account of a false manoeuvre, the vertical thrust surpasses a certain limit and the inclination of the arms thus surpasses their normal inclination, the rise of the arms produces an upward movement of the rods 62, which by means of the pins 61 displace the levers 60 and the movable tail surface 19 so as to increase the angle of incidence of the respective blade and thus its vertical thrust.

What I claim is: 1. A helicopter comprising a rotation shaft, a propeller, the blades of said propeller being hinged to said shaft to vary the dihedral angle, said blades also being rotatably mounted to vary 'the angle of incidence, a fixed stabilizing plane upon each blade, a movable controlling plane upon each blade and means for controlling said controlling planes. I

2. A helicopter comprising a rotation shaft, a propeller, the blades of said propeller being hinged to said shaft to vary the dihedral angle, said blades also being rotatably mounted to vary the angle of incidence, a fixed stabilizing plane upon each blade, a movable controlling plane upon each blade, means for controllingsaid controlling planes, and means for varying the direction of the thrust of said propeller.

,3. A helicopter comprising a rotation shaft, arms pivotally mounted upon said shaft, propeller blades rotatably mounted in said arms, a fixed stabilizing plane upon each blade, a movable controlling plane upon each blade and means for controlling said controlling planes.

4. A helicopter comprising a rotation shaft, arms pivotally mounted upon said shaft, propeller blades rotatably mounted in said arms, a fixed stabilizing plane upon each blade, a movable controlling plane upon each. blade, means for controlling said controlling planes and means for varying the direction of the thrust of said propeller blades.

5. A helicopter comprising a rotation shaft, arms pivotally mounted upon said shaft, propeller blades rotatably mounted in said arms, a fixed stabilizing plane upon each blade, a movable con trolling plane upon each blade, means for controlling said controlling planes and a second propeller for varying the direction of the thrust of said propeller blades. I

6. A helicopter comprising a rotation shaft, arms pivotally mounted upon said shaft, propeller blades rotatably mounted in said arms, a tubular shaft encircling said rotation shaft, means rotating said tubular shaft in counter direction to said rotation shaft, arms pivotally mounted upon said tubular shaft, propeller blades mounted on said last-named arms and a propeller offset from said rotation shaft for equalizing the difference in torque set .up by said rotation shaft and said tubular shaft.

'7. A helicopter comprising a rotation shaft, arms pivotally mounted upon said shaft, propeller blades rotatably mounted in said arms, a

fixed stabilizing plane upon each blade, 9. movable controlling plane upon each blade, a tubular shaft encircling said rotationv shaft, means ro tating said tubular shaft in counter direction to said rotation shaft, arms pivotally mounted upon said tubular shaft; and propeller blades mounted on said last-namedarms.

8. A helicopter comprising a rotation shaft, arms pivotally mounted upon said shaft, propeller blades rotatably mounted in said arms, a fixed stabilizing plane upon each blade, a movable controlling plane upon each blade, a tubular shaft encircling said rotation shaft, means rotating said tubular shaft in counter direction to said rotation shaft, arms pivotally mounted upon said tubular shaft and propeller blades rotatably mounted on said last-named arms,

9. A helicopter comprising a rotation shaft, arms pivotally mounted upon said shaft, propeller blades rotatably mounted in said arms, a fixed stabilizing plane upon each blade, a movable controlling plane upon each blade, a tubular shaft encircling said rotation shaft, means rotating said tubular shaft in counter direction to said rotation shaft, arms pivotally mounted upon said tubular shaft, propeller blades mounted on said last-named arms and means for varying the direction of the thrustof said propellers.

10. A helicopter comprising a rotation shaft,

1 arms pivotally mounted upon said shaft, propeller blades rotatably mounted in said arms, a fixed stabilizing plane upon each blade, a movable controlling plane upon each blade, a tubular shaft encircling said rotation shaft, means rotating said tubular shaft in counter direction to said rotation shaft, arms pivotally mounted upon said tubular shaft, propeller blades mounted on said last-named arms and means for equalizing the difference in torque set up by said rotation shaft and said tubular shaft.

11. A helicopter comprising a rotation shaft, arms pivotally mounted upon said shaft, propeller blades rotatably mounted in said arms, a fixed stabilizing planeupon each blade, a movable controlling plane upon each blade, a tubular shaft encircling said rotation shaft, means rotating said tubular shaft in counterdirection to said rotation shaft, arms pivotally mounted upon said tubular shaft, propeller blades mounted on said last-named arms and a propeller offset from said rotation shaft for equalizing the difference in torque set up by said'rotation shaft and said tubular shaft.

12. A helicopter comprising a rotation shaft, arms pivotally mounted upon said shaft, propeller blades rotatably mounted in said arms, a fixed stabilizing plane upon each blade, a movable controlling plane upon each blade, a tubular shaft encircling said rotation shaft, means rotating said tubular shaft in counter direction to said rotation shaft, arms pivotally mounted upon said tubular shaft, propeller blades mounted on said last-named arms and means'for damping the rotative movement of said blades in said arms.

13. A helicopter comprising a rotation shaft, arms pivotally mounted upon said shaft, propeller blades rotatably mounted in said arms, a fixed stabilizing plane upon each blade, a movable controlling plane upon each blade, means for controlling said controlling planes and means for 140 lar shaft encircling said rotation shaft, means rotating said tubular shaft in counter direction to said rotation shaft, arms pivotally mounted upon said tubular shaft, propeller blades mounted on said last-named arms and means for damping the rotative movement of said blades in said arms.

15. A helicopter comprising a rotation shaft, arms pivotally mounted upon said shaft, propeller blades rotatably mounted in said arms, a fixed stabilizing plane upon each blade, a movable controlling plane upon each blade, means for controlling said controlling planes and means for automatically increasing the angle of incidence of said. blades upon landing.

16. A helicopter comprising a rotation shaft, arms pivotally mounted upon said shaft, propeller blades rotatably mounted in said arms, a tubular shaft encircling said rotation shaft, means rotating said tubular shaft in counter direction to said rotation shaft, arms pivotally mounted upon said tubular shaft, propeller blades mounted on said last-named arms and means for automatically increasing the angle of incidence of said blades upon landing.

17. A helicopter comprising a rotation shaft. arms pivotally mounted upon said shaft, propeller blades rotatably mounted in said arms, a fixed stabilizing plane upon each blade, a movable controlling plane upon each blade, a tubular shaft encircling said rotation shaft, means rotating said tubular shaft in counter direction to said rotation shaft, arms pivotally mounted upon said tubular shaft, propeller blades mounted on said lastnamedarms and means for automatically increasing the angle of incidence of said blades upon landing.

bular shaft encircling said rotation shafts, meansrotating said tubular shaft in counter direction to said rotation shaft, arms pivotally mounted upon said tubular shaft, propeller blades mounted on said last-named arms and elastic ties secured to said blades slightly in front of their longitudinal axes so as to increase automatically the angle of incidence of saidblades upon landing.

20. A helicopter comprising a rotation shaft, a propeller, the blades of said propeller being hinged to said shaft to vary the dihedral angle, said blades also being rotatably mounted to vary the angle of incidence, a fixed stabilizing plane upon each blade, a movable controlling plane upon each blade, means for controlling said controlling planes and elastic ties secured to said blades slightly in front of their longitudinal axes so as to increase automatically the angle of incidence of said blades upon landing.

'CORRADINO DASCANIO.