US2587104A - Apparatus of the gyroplane type - Google Patents

Description

Feb. 26, 1952 BREGUET 2,587,104

APPARATUS OF THE GYROPLANE TYRE Filed Aug. 13,1946 6 Sheets-Sheet 1 INVGNTQ Feb. 26, 1952 L. BREGUET 2,587,104

APPARATUS OF THE GYROPLANE TYPE Filed Aug. 13, 1946 e Sheets-Sheet 2 i X 02 m3 2/ 20 H I I I I 25-. 5 A l .9 8 5 1 v 6 H e HHLIII 1 in 7 Q I .6. a 12 2 12,

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121/9075! 1 l Y ma Feb. 26, 1952 BREGUET APPARATUS OF THE GYROPLANE TYPE 6 Shee1', et 5 Filed Aug. 13 946 L. BREGUET APPARATUS .OF THE GYROPLANE TYPE Feb. 2 1952 6 Sheets-Sheet 4 Filed Aug. 15, 1946 Feba 2Q, 1952 L. BREGUET APPARATUS OF THE GYROPLANE TYPE 6 Sheets-Sheet 5 Filed Aug. 13, 1946 Feb, 2%, 1952 E T 2,587,)4

APPARATUS OF THE GYROPLANE TYPE Filed Aug. 13, 1946 6 Sheets-Sheet 6 QNTOR Patented Feb. 26, 1952 oFric wi e 135%.? 95 F TFE t 'BQPk E .k q sl s erla i ees n i s i n Aus sm, mascot In France September 30, 1941 Section 1, Public Law 690, Angus ratenter rres sept sa esnn- .3 1.241

- For ensuring the control of apparatuses with rotary sails of the gyroplane type vboth loneltudinally and transversely and in order v.to provide for their equilibrium, it hasalready been proposed to use arrangements for increasing the angle of incidence of the blades when theypass in the meridian plane in whichv the pilot wishes to act while the angle of incidence ,of the diametrically opposed blades is simultaneously reduced.

These arrangements have an action equivalent to that obtained in Autogiros by inclining the hub of the propeller to which theblades are coupled through a free connection.

When in a gyroplane, the 'blades are freely pivoted to their hub in the usual"manner, for instance through a cardan joint and the like means, the control of inclination and warping obtained through the above disclosed n'ljeari's lacks efliciency, accuracy and instantaneousnes's. This defect is chiefly ascribable to the i vertical oscillations of the freeblades as produced 'by the operation and to the buffeting generating objectionable secondary oscillations as produced when the gyroplane is progressingin a straight line or when the pilot acts on the control' mfem bers,-by reason of' the rocking of the rotary plane of the arms and of the blades -If in order to remove these drawbacks, the blades are rigidly connected with their hubfltlie righting torque produced by the variations @in incidence may be considerable J and its action almost instantaneous, but other defectsmayappearwhich are particularly serious whenjthe gyroplane progresses translationally at consider-. able speeds, which results chiefly in an exaggerrated strain of the blades.

- My invention has for its object anarrangement adapted to reduce the strain ontthearms and blades in the gyroplane apparatuses includ ing a rigid or semi-rigid connection for the blades, said arrangement beingsuch that, when the machine progresses translationally, there is produced an automatic reductionin .the incidence of the blades under the actionofitheincreased thrust and an increase of this incidence under the action of a reduced thrust. j

The expression semi-rigid vconnection iota blade should be construed as meaning anonnection which allows only alimited displacement of the blade in the plane defined by its axis and by theaxis of rotation of the hub.

The improved arrangement is ,completednby a system ensuring a differential connection between the sails, or rotors, allowing in theease of two sails or rotors provided on the gyroplane in coaxial or non-coaxial relationship and adapted ttorotatein opposite directions, a mutual balancing of the variations in the aerodynamic .torque exerted on these two sails or rotors; there may .b'e 'provided moreover an automatic oompensated control acting through a general adjustment'of all the blades of each rotor in accordance with the very translational speed of the f'gyroplane. *flhe'jollowing description given out with refer'ence to the accompanying drawings by way of example andby no means in a limitative sense will allow my invention to be readily understood, the features appearingboth in the drawings andiin the specification formingobviouslyj part of said invention.

Fig: .-1' ,is van explanatory diagram showing in plan'yiew two coaxial rotors rotating in opposite directions.

.2.is ,an elevational view, partly in section, of an embodiment of the invention;

Fig. 2a is a diagrammatic perspective view of .the :control members of a gyropl ne fitted in accordance with my invention.

' Fig..-.3j is ,an elevational view of the differential connecting means in a particular thereto.

;Fig. A illustrates a ,modification of said mechanism Eigs. ;5 to 9 vareviews similar to Fig. 3 but at a; -redueed scale, said .diagrammatical views illustrating other positions of the connecting mech nisml0 shows diagrammatically in one of its iormsof execution, the automatic control SY 1 1 ;In, the arrangement shown in Fig. 1, it has been assumed that two opposite blades l-l' are mounted, lpiyotally. round their longitudinal axis $72], on. a hub .3 rotating clockwise round an axis perpendicular to .the plane of the drawing and that these blades are given no degree'of freedom with reference :to .the hub or may at the utmost move with a limited degree of freedom'in the plane...perpendicular to the plane of .thefigure, and passing through .the axis ::cy, said blades pivotingjhen round an axis perpendicular to said plane. Suchalimited freedom of movement is given to the blades in order to avoid vibrations,i;but,withoutallowing any flapping of said blade .It has. also beensupposed that between the blades; ofnthe same rotor'is provided a system position given lfondhijerential; connection of the type described in my prior U. S. Patent No. 1,919,089 and relating to a Method and means for stabilizing, controlling and propelling a flying machine with rotary sails of the gyroplane type said sails being power driven or rotating freely.

The mounting described in said prior patent provides through links connected with a rockin plate the balancing of the mean centrifugal and aerodynamic torques of two opposite blades of a same propeller or rotor or of two blades considered artificially as oppositein the case ofan odd number of blades, so that the aerodynamic incidences z" and i of these blades may vary differentially until the torques balance one another.

With such a mounting, it is practically useless when the degree of freedom of the blades is limited, as stated, to resort to a rising and sinking movement of the blades as disclosed in my prior abovementioned patent for producing variations in incidence of the rotor during one revolution.

According to my present invention, there is provided a periodical modification of the incidences during one revolution whereby the pivoting of the blade round its longitudinal axis is rendered automatic under the action of an increase or reduction in the aerodynamic torque when the blade advances against a relative wind or recedes in said wind; this is provided by giving the blades a symmetrical section or outline, i.e. an outline for which the thrust center is invariable or else an autostable outline, i. e. an outline for which the center of thrust is displaced towards the front of the outline for increasing the thrust, the center of thrust being located to the rear of the longitudinal pivotal axis of the blade, which reduces the amplitude of the variations in incidence of each blade per revolution. The automatic pivoting thus obtained is practically instantaneous by reason of the small momentum of inertia of the blades round their longitudinal axis.

If it is supposed that this gyroplane assumes a translational movement in the direction of the arrow F at a speed 11 and that for instance the point P of the blade I advancing in the relative wind progresses by reason of the rotation of the rotor at a speed V higher than 1), the

aerodynamic torque at P as the blade'passes in the plane perpendicular to v, as in the case illustrated, is proportional to the product of (V+'u) by the aerodynamic incidence; the corresponding torque at P on the opposite blade I is proportional to the product of the aerodynamic incidence by (V-'u) as this latter blade recedes with reference to the relative wind. It is immediately apparent that by given different values to the angles of incidence i and i", it is possible to obtain a balancing of the mean aerodynamic torques and at the same time of the mean centrifugal torques of the blades I and l as stated; this is made possible by reason of the freedom of pivoting round the axis m-y allowed for said blades.

In the case of symmetrical outlines, the thrusts which are proportional to the torques have a tendency to remain constant for each blade, which reduces the stresses to which said blades are submitted.

In the case of autostable outlines, i.e. of out-- lines of which the center of thrust advances when the incidences are reduced, said incidences will be reduced to a lesser extent than in the case of symmetrical outlines for blades advance 4 in the relative wind, which will allow within the limits authorized by the straining of the arms; thrusts which are more consistent with improved aerodynamic efiiciencies.

In practice instead of a single couple of blades .such as ll it is preferable to use two thereof; the second pair shown in dotted lines at 2-2 in Fig. 1, moves in a direction opposite to the preceding pair; it is illustrated in the position for which the axis .r-y of the blades is parallelto the translational speed c, in which case the incidences z of the blades are the same.

It should be noticed that it is possible to provide in each rotor any desired number of blades 'angularly shifted by a same amount. However by way of simplification and in order to keep to the-most frequent case, I will describe hereinafter the execution of my invention with rotors comprising only two diametrically opposed blades.

The above arrangement ensuring the cyclic arrangement of the incidences for each of the rotors mounted on the gyroplane will be advantageously completed in a gyroplane including two coaxial rotors rotating in opposite directions by an arrangement allowing the two primary rocking plates to assume opposite inclination.

The primary plates will be connected for this purpose by diiferential arrangements respecting their freedom of oscillation but allowing their simultaneous displacement or their angular relative shifting inside any meridian plane.

These automatic difierential arrangements form one of the chief characteristics of the present invention. For allowing an easy control of a gyroplane, it is in fact necessary while allowing a free adjustment of the incidence as required for translational movement to obtain the possibility at every moment.

(a) of increasing the incidence of one blade while reducing that of the opposed blade as it passes through any given meridian plane. With two rotors rotating in opposite directions, the operation should preferably be performed on both propellers together, whereby it is possible for the pilot to produce any restoring torque as required for the warping or handling of the machine, indifierently when the translational speed is zero or for any value of the translational speed.

(1)) of increasing or reducing in a general and permanent manner the incidences of all the blades for climbing or diving or for adjusting the pitch.

(0) of obtaining for two propellers rotating in opposite directions an incidence which is greater for one of the rotors than for the other, this forming in fact an easy manner of producing the giration or turning of the machine.

(d) lastly of automatically reducing the incidences of the blades when the throttle is being closed andconsequently the driving of the rotor is reduced, the self rotation being performed with very small pitches.

Fig. 2 gives by way of example a general dia grammatic showing of a form of execution of this arrangement.

The general axis of revolution of the rotors is given out by X-Y. A so-called primary plate 8 is mounted centrally on a rotula 9 which allows it to rock in all directions, the center of this rotula being arranged on the axis X-Y. At the periphery of the plate 8 is arranged a ballbearing 7 the outer ring 6 of which is. con- 'a-ssmoe n e throu h-a connect n roM with-the blade I in the vicinity .of its leading edge. The ends of the connecting rod 4 are pivotal-1y secured through rotulas '5 and to the ring 6 and to the blade I respectively. The other blade I of the rotor is coupled in a similar -,manner to the ring 6-.

.A similar connection is: established between the blades 2 and 2' of the other rotor and iaisimi lar ring 6 is located at the periphery of @anis other rocking plate 8. II-he members :corresponding to those illustrated with reference to the connection between :the blade I and the plate 8 have received the same refzerence numbers :accompanied by a dash.

I will refer hereinafter simultaneously to Fig. 2 and to the showin of Fig. 3 which 1 11315 been modified diagrammatically as :follows: in forder to allow the incidences of the blades to appear more clearly, I have shown, above the inner end of the connecting rod 4, :the connection of said rod with the corresponding blade cross-sectionally .ina plane perpendicular to the axis of the blade; furthermore, I have shown at 3 and 3' the portions of the rotary shafts or hubs to which are connected the blades I-'-I' and 22" respectively. As may be seen on Fig. 2, it is possible to figure in ones mind, these hubs are mounted for rotation in opposite directions on a stationary structure II6 borne by the frame III of the gyroplane having X-Y for an axissaid hubs are driven by known means comprising for instance a bevel gear I00, 2. central shaft IOI, pinions I02, I03 and I04 for hub 3 and a bevel-gear I00, a hollow shaft IOI' surrounding shaft IOI, pinlons I02, I03 and I04 for hub 3, bevel gears I00 and I00 being driven'by a common bevel pinion I05 secured to a motor shaft I06. Finally I have shown by way of example a link 2| with an axis perpendicular to the plane of the drawing through the agency of which each blade is adapted to pivot in a plane defined by its axis xy and the axis X-Y, the corresponding movements being braked and limited by elastic dampers 22 inserted between the blade and a collar 23 rigid with the hub 3; the same arrangement has been adopted for the other blades.

The plate 8 is rigid with a sleeve 24 adapted to slide with respect to the structure H6 and it carries a stud l0 engaging a. meridian slot II in the rotula 9; thus the plate is adapted to assume any angular position without being allowed any relative rotation. The system of a rotula and locking means preventing rotation may be replaced by any equivalent means such for instance as a cardan joint. Elastic dampers 25 are inserted between the plate 8 and a collar 26 rigid with the sleeve 24 for braking and limiting the movements of said plate.

The same arrangement is adopted for the primary plate 8' and the corresponding members receive the same reference numbers accompanied by dashes.

Between the primary plates 8-8" is arranged a central plate I4 mounted on a rotula I5; the latter is rigid with a column I6. As in the case of the primary plates a stud 28 rigid with said plate I4 engages a meridian slot 29 inthe rotula I5 and prevents any undesired rotation of said plate; in this case again a cardan joint may replace the system of the rotula and of :the device for locking the plate against rotation. On Fig.

supposed to be rigid with a-sleeve 21 secured to said column 1-6.

The primary plates8-8 andthe-central plate I4 are interconnected through connecting rods I'2-I 2,two connecting rods I-2I 2"being pivotally secured to a swing-bar I3 pivotally secured to the plate I4; it'is possible to provide for instance four sets of connecting :rods at 90 from one another or else three sets at 120. By Way of a modification (Fig. 14), .it is possible to replace the iswing-bars I3 .by toothed wheels I3 meshing with racks provided atthe ends of the rods I2"-I2 playing the same :part as the corresponding rods :I2--I 2 Reverting now more particularly to Fig. 2, it will be appreciated in order to make the showing clearer and the understanding easier that the column I6 is hollow and that it may rise and sink without rotating .round the axis ,X-Y.

In the cockpit of the gyroplane are provided (Fig. 2d) two levers and a rudder bar which are within reach of the pilot for executing the different control operations.- The lever 30 is mounted on a cardan joint at -:41 and "controls through a transmission illustrated under the form of a rod 3I, a bell crank 32 and a rod 33, the angular setting of the central plate I4 which is caused to pivot round an axis perpendicular to the plane defined b'ythe axis X-Y and the longitudinal axis of thegyroplane; this same lever 30 controls through a cardan shaft 34, an arm 35 and a rod 36 the angular setting'of the central plate I4 by "pivoting round a second axis perpendicular to the preceding axis.

The-second control lever 31 ispivotally secured at 38 and provides through a rod 39 the end of which forms a rack 40 the rising and sinking movement of the column Iii; to this end the column shows helical teeth 4I meshing with a 3, the hubs 3 and 3' and sleeves 24 and 24' have.

been diagrammatically shown as slidably 111011111]- ed on column I6, whereas therotula I5 has been pinion 42 provided with a corresponding tapping and with an outer series of teeth meshing with the rack 40.

The rudder bar 43 is pivotally secured at 44 and through the agency of a bell crank 45 and of a rod 46 it controls the rising and sinking movements of the primary plate 8.

The operation of the above described members and the manner of controlling the gyroplane thus equipped will be now disclosed, reference being made; more particularly to Fig. 2 considered in succession in combination with each of Figs.

It will be first noticed that when the control levers 303'I and the rudder-bar-43 occupy fixed positions and the primary plates 8-6' are capable of rocking in opposite directions round their I rotulas :99 through the agency of the connecting rods I2.I2' and of the swing-bars i3, this produces during flight the automatic and cyclic adjustment of theincidences; the incidence of the blades advancing against the relative wind is reduced while that of the blades receding in said wind increases. By reason of the differential equilibrium between the actions exerted on the primary rocking plates 6-8, no reaction is exerted on the central plate -14 and thereby no reaction is exerted either on the control levers and rudder bar.

Fig. 3 shows the plates 8-8 and I4 in their mean position perpendicular to the column I6, the condi-tions'being then those ofrest or of stationaryfiight'for 'the'gyroplane. In Fig. 5 which corresponds to Fig. 3 for the position of the levers and-' rudd'er-bar is shown clearly the inclination in opposite directions of the plates 88' under the conditions defined in the preceding paragraph, the thrust on the blades I and I and on the blades 2 and 2' compensating one another.

Fig. 6 corresponds to the case where the pilot has caused the control lever 3'! to rock in the direction of the arrow fl so as to produce a rise of the central plate I4 and therewith of the two primary plates 8--B; in this case, the incidence of all the blades has increased which corresponds to rising position. If conversely, (Fig. '7) the pilot causes the lever 31 to pivot in the direction of the arrow f2 the incidences of all the blades are reduced; the position obtained corresponds therefore to downward flight.

If. the pilot rocks the control lever 30 in the direction of the arrow 13 for instance, the blades are submitted on the left hand side to an increase in incidence (Fig. 8) and to a reduction in incidence on the right hand side, when they pass through the .plane containing the axis XY and perpendicular to the longitudinal axis of the gyroplane. If the inclination is provided in the opposite direction f4 the incidence increases on the right hand side and is reduced on the left hand side. A similar disclosure is applicable if the lever is inclined either in the direction of the arrow f5 or in the direction of the arrow f6 and generally speaking in any direction. This provides thus for warping action.

In the case where the pilot pushes the rudder bar 43 in the direction of the arrow I! this raises the plate 8 and as the plate I 4 remains stationary, the plate 8 is lowered. The incidences of the upper rotor ll' increases and those of the lower rotor 2--2' are reduced (Fig. 9). If the pilot urges the rudder-bar in the opposite direction, given out by the arrow f8 the opposite action is obtained. This produces thus a giratory torque in ither desired direction.

In brief, the conditions of operation of my improved apparatus are as follows:

(a) in the automatic cyclic adjustment of the incidences, the two primary plates rock in opposed directions on their ro-tulas. Th swingbars assume a periodical inclination while their centers remain motionless on the central plate.

By reason of the differential balancing of the actions exerted on the two primary oscillating ipla-tes, no reaction is exerted on the central plate and therefore on the pilots hand.

(b) If the central plate is inclined in any azimuthal direction, this modifies the mean positions of the two primary plates. According to the direction of inclination, of said plate, the incidence of the blades is increased or reduced in the two rotors, when they pass through the azimuthal direction considered. This produces thus a torque which rightens the apparatus in a direction which may be selected as desired.

(0) It is possible by making the cylindrical support carrying the rotulas of the plates slide upwardly to increase in a general and permanent manner the incidences of all the blades. These incidences are reduced by displacing the cylindrical sup-port downwardly.

(d) by spacing away from one another the rotulas of the primary plates I increase in a permanent manner the incidence of the upper rotor, while they are reduced for the lower rotor. The reverse action is obtained by moving towards one another the rotulas of the two primary plates. This produces thus a giratory torque in one direction or the other.

It is apparent from the preceding disclosure 8 that by reason of the arrangement disclosed, the pilot may execute all desired operations.

In practice, it is of interest to complete the above described mechanism by an automatic control arrangement which in case of a reduction of the speedo-f the engine and consequently of a reduction or cancellation of the driving torque acting on the rotors, reduces the incidences of the blades. It is sufficient therefore that the arrangement considered, controlled directly or indirectly by the motor may be connected to the plates 88' in a manner such as will modify their spacing. The adjustment should preferably be such that if the engines are slowed down, the rotors assume of their own a pitch near zero without the pilot having to interfere.

This automatic control arrangement may becentrifugal or hydraulic and its pressure in this case should depend on the torque of the engine or else it may be constituted by a system controlled by the depression at the admission into the engine.

Lastly, the arrangements of the control memhere may be advantageously completed by an arrangement controlled by the very speed of translation of the apparatus forming a speed compensation system operating automatically on the incidences of the blades.

This arrangement may be executed as illustrated in Fig. 10. It includes a driving piston 56 controlling through connecting rods the different swing bars I3 of which only one is shown for illustrating the control means; said piston 56 is adapted to move inside the cylinder 48; a Venturi tube 89 is connected with the distributor 56, thedouble piston 5! in which is connected with the swing-bar 52 which is also connected with the piston 56 and with a manometric capsule 53; said inanometric capsule is submitted to the depression produced at the restricted part of a.

Venturi sleeve 5% arranged in the relative wind, As the distributor 58 is balanced through its being submitted to the depression from 49 at both ends and to normal atmospheric pressure in its center through the pipe 55, the capsule 53 easily produces the displacements of the piston- 5! therein. Of course the control througha Venturi tube and a capsule may be replaced by any othersuitable control means such as gliding and perpendicular surfaces, a Pitot tube, blade anemometers and the like, or else it is possible to act otherwise on the swing bars [3, for instance directly or through the agency of an auxiliary motor different from that described such as a fluid operated auxiliary motor, a hydraulic auxiliary motor and the like. It is also possible to act no longer on the swing bars, but on one of the primary plates 8 or 8.

Obviously many detail modifications may be brought to the apparatuses which have been described without widening thereby the scope of the invention.

What I claim is:

1. In a gyroplane or the like flying machine of the kind having two rotors rotating coaxially in opposite directions and carried by a nonrotating column, the blades of said rotor being allowed of taking variable incidences and of affecting at the utmost limited flapping displacements, the combination of two primary toggle plates non-rotatably supported from saidof the kind having two rotors rotating coaxially c in opposite directions and carried by a nonrotating column, the blades of said rotor being allowed of taking variable incidences and of efiecting at the utmost limited flying flapping displacements, the combination of two primarytoggle plates non-rotatably supported from said column, two ring members rotatably mounted around said toggle plates respectively, two sets of connecting rods, the rods of one set being connected each to a blade of one of the rotors and to one of said ring members whereas the rods of the other set are connected each to a blade of the other rotor and to the other of said ring members, a balancing third toggle plate non-rotatably supported from said column, swing bars pivotally secured to said third plate, two sets of connecting rods, the rods of one set being pivotally connected each to one of the primary plates and to one end of one of said swing bars whereas the rods of the other set are connected each to the other primary plate and to the other end of one of said swing bars.

3. In a gyroplane or the like flying machine of the kind having two rotors rotating coaxially in opposite directions and carried by a non-rotating column, the blades of said rotor being allowed of taking variable incidences and of effecting at the utmost limited flapping displacements, the combination of two primary toggle plates nonrotatably supported from said column, two ring members rotatably mounted around said toggle plates respectively, two sets of connecting rods, the rods of one set being connected each to a blade of one of the rotors and to one of said ring members whereas the rods of the other set are connected each to a blade of the other rotor and to the other of said ring members, a balancing third toggle plate non-rotatably supported from said column, pinions pivotally secured to said third plate, two sets of rack members, each member of one set being pivotally secured at one of its ends to one of said primary plates and meshing with one of said pinions whereas each 10 member of the other set is pivotally secured to the second of said primary plates and meshes with one of said pinions.

4. In a gyroplane or the like flying machine of the kind having two rotors rotating coaxially in opposite directions and carried by a non-rotating column, the blades of said rotor being allowed of taking variable incidences and of efiecting at the utmost limited fiapp-ing displacements, the combination of two primary toggle plates nonrotatably but slidably supported from said column, two ring members rotatably mounted around said toggle plates respectively, two sets of connecting rods, the rods of one set being connected each to a blade of one of the rotors and to one of said ring members whereas the rods of the other set are connected each to a. blade of the other rotor and to the other of said ring members, a balancing third toggle plate non-rotatably supported from said column, differential means supported by said third toggle plate and connecting together said primary plates," a control linkage supported by said column and adapted to control the angular setting of said third toggle plate under the action of a control lever, means for adjusting the longitudinal position of the third toggle plate and thereby of the primary plates with respect to said rotors, a second lever for controlling said last-mentioned means, means supported by said column for controlling the relative spacing between said primary plates and said third plate and a rudder bar for controlling said last-mentioned means.

LOUIS BRE'GUET.

REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS Number Name Date 1,800,470 Oehmichen Apr. 14, 1931 1,836,351 Wike Dec. 15, 1931 1,919,089 Brguet et a1 July 18, 1933 2,041,789 Stalker May 26, 1936 2,389,170 Stalker Nov. 20, 1945 2,397,489 Jenkins et a1 Apr. 2, 1946 FOREIGN PATENTS Number Country Date 488,111 Great Britain Nov. 12, 1935

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