US1902813A - Aeroplane - Google Patents

Description

March 28, 1933 A G. cRoMPToN, JR

AEROPLANE f Filed April, 19:50 zsheers-sheet 1 Marh 28, 1933 G CR'OMPTON, JR vAE'ROPLANE 2 sheets-sheet 2 FileAd April 9. 1930 Patented Mar. 28,.` 1933 GEORGE CRMPTON, IR., I@ YORK, N. Y.

.AEBUPLASNE Application filed April .9,

The invention relates to aeroplanes, particularly of the type disclosed in my prior Patent No. 1,716,116, granted June 4.-, 1929. According to the invention therein disclosed,

the main plane is rotatable on a transverse axis, and is allowed to freely rotate when the aeroplane is landing, being held rigid at other times, however, for normal flight. The machine of the aforesaid patent provides `a differentially controllable rudder, the separate parts of which can be moved separately or in unison, thus constituting means vfor laterally stabilizing the aeroplane, this means being undisturbed when the main plane is allowed to rotate.

The differential rudder control of my prior invention is not as sensitive Vas the usual aileron. control, because for [a given pressure, the couple is smaller, and the main object of the present invention is to provide an aileron system of control for aeroplanes of Vthis class. Such a system of control should be automatically connected and disconnected when the wings are locked in position and allowed to rotate, respectively. and

this is another object of the present invention;

It is very desirable that the standard system of controlfor aeroplanes be maintained.

In practically all aeroplanes now'built the elevating rudder andthe ailerons are controlled from a single member, which is either a wheel or a stick. Further objects of the invention reside in the specific actuating mechanism for the lateral stabilizing means,

'f which controls not only the wing ailerons, but also the differential rudder control. I still make use, preferably of the dii'erential rudder system of control, in order that the 0 aeroplane may be guided when the main plane is revolving, and the coordination of these two lateral stabilizing mechanisms constitutes still another object of the invention.

The above and other objects ofthe inven- 45 tion will hereinafter more fully appear from 1930.- senai im 442,931.

the following detailed description, taken in connection with the accompanying drawings, in which Fig. `1 is a side elevation of an aeroplane constructed in accordance with my inven- 5o tion.

Fig. 2 is an enlarged fragmentary vertical sectional view showing the control mechanism inside the fuselage.-

`Fig. 3 is an isometric view, partly dia- 55 grammatic, of the aeroplane, taken from above.

Fig. 4 is avertical sectional view taken on the line 4-4 of Fig. 2, but on a smaller scale.

Fig. 5 is a view similar to Fig. 4, taken on 50 the line 5 5 of Fig. 2. y

Fig. 6 is an isometric view of part of the control mechanism in the fuselage.

Fig. 7 .is a detailed fragmentary sectional 6 yview of the rotating wing bearings.

Like reference characters refer to like parts in the different fi res. f

Referring to all the gures, the aeroplane of the invention provides a fuselage 1 of common type, and a pair of wings 2, 2 that 70 are formed on a shaft 3. The shaft 3 is `fastened to disc members 4, 4 which-are journalled in bearings 5, 5and 6, 6 provided by stationary annular members 7, 7 attached Ato 1 the fuselage. F or a complete description of the supports vfor the rotatable wings, refer'- ence should be had to the aforesaid atent.

As set forth in vmy -prior patent, ook and brake means are provided to normally hold the wings 2, 2 from rotation. This lock and 8 brake means is actuated by means of a hand lever 8. Preferably I employ the specific type of mechanism shown 1n` my co-pending application Serial No. 417,445, wherein the releasing of Vthe brake procures partial rotation`of the wings. As best shown in Figs. 2 and 6, the lever 8 is fastened to a shaft 9; a dependening portion 10 of the lever 8 on one side of thefuselage, and an arm 11 on the other side are connected to a pair of links 12, 9

Jla

the top and 12, the other ends of which arek connected to brake members 13, 13. The brake members 13, 13 provide shoes 14, which t in depressions 15u termed in brake drum portions 15 formed integrally with the members 4, see Fig.. 4. llhen the pilot draws the lever 8 towards him, the brake members 13, 13 are projectedA forwardly, starting the wings 2, 2 in rotation, and releasing them for conn tinued rotation..`

The tail ci the aeroplane provides the usual vertical rudder 16 (Figs. 1 and 3) which may be operated from a rudder bar 16a, Fig. 2, in the usual manner. rlhe tail also pro vides a pair of horizontal rudders 17, 17 which are independently mounted as shown in my aforesaid patent. l preferably make use of he mechanism described in a patent to Coakley, No. 1,110,895, dated September 15, 1914, to actuate these rudders separately or in unison. When the rudders are actuated in unison they act as elevators, and when actuated separately they constitute lateral stabilizing means, as full? set orth in my own prior patent. Instea of providing a wheel control, according to the patent to Coakley, I'pr'efer to employ a stick control, and the. modification of the Coakley mechanism `for this purpose is part of the present invention.

Referring now particularly to Fig. 2, a control stickf 18 is fastened to a member 19 whose lower end is pivotally mounted en a stud 20 provided by a member 21 that 1s 1n turn journalled on the horizontal shaft 9. A

lshaft 22, which normally extends vertically, for rotation about its axis in,

is journalled the same member 21. The member 19 and the shaft 22 each provide segments of bevel gears, which mesh withpeach other and are designated byI the numerals 23 and 24, respectively. It will now be seen that when the stickl 18 with the member 19 is moved to one side or the other, the shaft 22 will be turned, in one direction or the other, while forward or rearward movement of the stick 18 with member 19 will impart corresponding movement to the shaft 22.

As best shown in Figs. 2, 5 and 6, the shaft 22 is provided with cross bars 25 and 26 at bottom respectively. Flexible connections 27, 28, 29 and 30 connect the four endsof these two cross bars to horns 27a,1

28a, 29a, and 30a respectively, provided by the horizontal rudders 17. The right hand side of the top cross bar 25 is connected to the left hand lower horn 27a; the left hand side of the top cross bar 25 is connected to the right hand lower horn 28a.; the right hand side ot the lower cross-bar 26 is connected to -the right hand upper horn29a; and the left hand side of the lower cross bar 26 is connectedto the left hand upper horn 30a. It will be seen at once that since movement to the left of the stick 18 and the member 19 Leonora will be lowered, and this will cause the aero-l plane to incline on its longitudinal 4axis to the left. It will 4also be seen that forward motion of the stick 18 will depress both rudders 17, 17, which will cause the aeroplane to nose down, and thus the aeroplane will respond to movement of ythe stick in the usual manner.

According to the present invention, ailerons are provided in the wings 2, 2 in order to more easily stabilize the aeroplane in normal Hight. These ailerons are preferably actuated by the same control stick 18 that actuates the rudders 17, 17. rlfhe connection between the means in the cockpit to control these ailerons and the said ailerons must,

however, be disconnectible, in order to allowk versal joint `31 to a member 32, whlch may comprise a pair of parallel bars connected rigidly by clamps 33, 33, 33. A space is left between the bars of the member 32, the front end of said member the two bars and at t extend on opposite sides of a bolt 34 which extends through a stationary cross bar 35 fastened to rigid members 36, 36. A spring 37 urges the bolt 34 downwardly, and as the head ofthe bolt extends over the top of the member 32, it follows that the member 32 can move forward and rearward, can swing from side to side, and can rise. and fall slightly, but the locus of a variable point of said mem'- ber 32 is always located at the pin 34.

A cross member 38 is held in position by forked brackets 39, 39 attached to a stationarycross member 40. The member 38 is rectangular in cross section., and therefore can not turn, but it can move sideways of the aeroplane, and can move to a limited extent up 4 and down. A pin 41 carried by the member 38 iits between the bars of the member 32, and thus swinging movement of the member 32is i transmitted to the member 38, being transformed into lateral movement ofthe latter.

It will now be seen that as the stick 18 is moved from side to side, the member 38 will move correspondingly, while forward and rearward movement of the stick will have no effect upon the member 38..

The member 38' is connected at each end by a universal joint 42 to one of two members 43, 43, which inV turn are connected by universal joints 44, 44 to the brake operating connectors 12, 12. Between the universal Joints l on each member 43 is a cam member 45 which actuates the ailerons 46, 46 in the wings. During normal flight the universal joints 44, 44 have a tixed position, and the upper universal ist . 45, 45 move laterally only as the stick moves laterally. When, however, the lever 8 is moved, the connectors 12, 12 are moved forwardly, and this carries the cam members 45, 45 forwardly for a limited distance.

Portions 47, 47 provided by the discs 4, 4 slidingly support members 48, 48, which are in position to be pushed by the cam members 45 when the wings 2, 2 are not rotating. Re-

ferring now to Fig. 3, the members 48 are connected to levers 49, 49 which actuate the ailerons 46, 46. Pushing of the left hand member 48 must depress the right hand ail leron 46, so that the right wing 2 will be raised, and vice versa. Consequently the forward end of the left hand lever 49 is connected to a cord or the like 50a which vruns to the extreme left hand edge of the left -hand wing 2, then through the hollow shaft 3, and finally to a horn 51a connected to the right hand aileron 46. Similarly the forward end of the right hand lever 49v is connected to a cord or the like 50h which runs to the extreme right hand edge of the right hand wing 2, then through the hollow shaft 3, and finally to a horn 51h connected to the left hand aileron 46. Suitable pulleys may be provided for the cords as shown in Fig. 3.

The ailerons 46, vas shown in Fig. 2, are resiliently urged into the wings 2 by springs 52. Of course, when one of the cords 50a or 50?) is actuated, the ailerons can move downwardly against the spring. The `springs insure t e proper seating of the ailerons when the wings revolve. a

The aeroplane takes ofi' and flies in the usualmanner, but when aboutto land the pilot may pull the lever 8 and cause the wings to revolve. The wings when revolving act as an'aerodynamic brake, and bring the aeroplane to a stop quickly without any danger of nosing over. The aeroplane is under com plete control at all times by reason of the several sets of stabilizing mechanism provided by the invention.

Use of the stick 18 in normal flight actuates the stabilizing means at the rear of the aeroplane, and also actuates the ailerons 46. Movement of the lever 8 to allow the wings to rotate, however, disconnects the ailerons 46, 46 from the stick, by reason of the movingorWard Vof the cam members 45 as described. The cam members are called such because they are shaped to come into proper position automatically when the lever 8 is restored to the position shown in the drawings, if the stick is to the right or the left of centre, one of said members 45 having at that time a wedge action upon one of the members- 48 to push it inwardly as thecam member comes' into position. The apparatus is so formed that the members 48 can revolve with the discs 4 when the cam members' are forward without interfering with anything.

I claim,

1. In an aeroplane, a. main plane mounted to rotate freely on an horizontal axis, and ailerons provided by said main plane.

2. In an aeroplane, a main plane mounted to rotate freely on an horizontal axis, ailerons provided on said main plane, and means to actuate said ailerons when the, main plane is not rotating. i a l ,Y

3. In an aeroplane, a mair'i,v planmonted to rotate freely `on anvhori-'zontal axis, lateral.

stabilizing means provided at the tail of said aeroplane, land allerons on .the said main plane. V

4. In an aeroplane, a main plane mounted to rotate freely on an horizontalv axis, a controlling lever to allow said plane to revolve, ailerons provided on the said main plane, and disconnectible mechanism to actuate said ailerons, the mechanism being disconnected by movement of said controlling lever.

Q 5. In an aeroplane, a maln plane freely rotatable on a transverse axls, ailerons on sald ymain plane, and means to maintain said ailerons in position of no-lift when the plane is rotating.

6. In an aeroplane, a main plane freely rotatable on a transverse axis, a universally journalled stick to control said plane, a member in the form of an H connected to move forwards and backwards with said stick, and to oscillate as said stick is moved from side to side, a member mounted to move from side to side, connections between said stick and said last named member to move it as said stick is moved, brake means to hold the plane normally stationary, connec-l tions to actuate said brake means, a pair of members connecting the member that moves from side to side with the connections to actuate the brake means, a pair of ailerons in the plane, and connections between the last named members and the ailerons, adapted to be disconnected by movement of the connections to actuate the brake means.

7. In an aeroplane, a main plane mounted vto rotate freely on an horizontal axis, lateral stabilizing means provided at the tail of said aeroplane, ailerons onsaidmain plane and a common control for said ailerons an said lateral stabilizing means.

8. In an aeroplane, a main plane mounted i stabilizing means provided at the tail of said aeroplano, ailerons onsaid main ane a comma@ control for said ailerons on ssi afml stabilizing means, a control o0 pei'- mi?J said main plana to rotate, and moans op @rated by said mso-named oontro to discomnect-tiio connection between si sa-momniomad oonto and said aiorom's.,

x10.' n an aoiopsme, a Iusolagos a. main pmie mounted on said fuselage ibo fotoos freely on an horizoiia mis, ailerons piovisd on said main piane, and means im said iiselsge to @Chiaia said ailerons when the main piana is not rooing.

GERGE CREWTN, Jia.

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