US1062116A - Aeroplane. - Google Patents

Description

E. J. & S. A. RANDALL.

AEROPLANE. 1 APPLICATION FILED AUG.16, 1910.

Patented May 20, 19 13;.

a SHEETS-SHEBTE.

E. J. 8; S. A. RANDALL.

AEROPLANE.

APPLICATION FILED AUG. 15, 1919.

Patented May20, 1913.

3 SHEETS-SHEET 2'.

Patented May 20, 1913.

AEROPLANE.

APPLICATION FILEL AUG.15, 1910.

E. J. & S. A. RANDALL.

UNITED STATES PATENT OFFICE.

EGBER'I. J. RANDALL, oFroNrmc, moment, AND snnmmn A. RANDALL, of

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Specification of letters Patent. I A' ncauonmea au ust 15,1910. Serial No. 577,202.

To all whom it may concern:

Be it known that we, EGBERT RAN- DALL, residing at Pontiac, county of vOakland, State of Michigan, and SHERMAN A. RANDALL, residing at Rochester, county of Monroe, State of New 'York, have invented a certain new and useful Improvement in- Aeroplanes, and declare the following to be a full, clear, and exact description of the same, such as will enable others skilled in the art to which it pertains to make and use the same, reference being had to the accompanying drawings, which form a part of this specification.

Our invention relates to an improvement in. aeroplanes, shown in the accompanying drawings and more particularly described in the following specification and claims.

The object of our invention is to provide means for automatically operating stabilizing planes or ailerons whereby the lateral balance of the aeroplane is maintained.

Other advantages and improvements will hereafter appear.

In the drawings accompanying this specification:-Figure 1 is a perspective view of an aeroplane, with parts broken away. Fig. 2 is a perspective view of a detail showing diagrammatically the manner of actuating the stabilizing planes. and rudder. Fig. 3 is a detail view with parts broken away and in section, showing the manner of engaging the slides control ing the operation of the stabilizing planes with the swinging motor platform. Fig. 4 is a plan view of the swinging platform and slides shown'in Fig. 3. Fig. 5 is a detail view indicating -the manner of locking the swinging platform in fixed relation to the frame of the aeroplane previous to operating the rudder and stabilizing planes manually. Fig. 6 is a similar view showing the swingin platform engaged by the dogs of the sli es controlling the automatic operation of the stabilizing planes. I

We will now denote the several parts by reference letters in which A indicates a biplane of the usu al type, though the inventiofi'is equally well adapted to a monoplane turned ends ings, B re resents an elevating plane, and C the rud er.

D, D, indicate stabilizing planes located at either end of the aeroplane for maintaining its lateral balance.

E is a swinging platform operating somewhat in the nature of a pendulum though it may be a sliding frame, on which the motor andother driving mechanism may be mounted. In the form, shown in the drawings, the platform E is pivoted at E'- to the upper spars A or framework of the aeroplane. Beneath the platform and adapted to slide in suitable guides or tracks supported by the lower spars or frame of the appa tus are slides F, and G, having upwardly f and 9. To the slide F are secured cables F and F passing around suitable sheaves or other supports and respectively engaging the rudder C. To the slide G are also secured similar cables G, and G suitably supported and guided and in turn respectively engaging the stabilizing planes D and D.

Carried by the slides F and G and pivoted thereon are dogs f and 9" provided with springs (not shown) or so weighted as to insure normally a locking engagement with the notched member E secured to the underside of the platform,-it being understood that any other suitable means of se' curing a locking engagement may be employed, the drawings merely indicating in this and other respects of like character, a working embodiment of the invention.

H is a locking dog adapted to secure the swinging platform E in a fixed position for purposes which will be hereafter explained. The locking dog H is pivoted at h to the frame and actuated by suitable lever mechanism H carried by the rock shaft H in turn operated by the foot lever I-I support ed by suitable hangers (not shown) to the frame. a

I and I are tripping bars actuated by suitable toggle mechanism I and I op- Patented May 20,1913.

erated by the rock shaft H wherebyupon operating the foot lever H the spring actuated dogs f and g are forced out of engagement with the notched member E J into engagement with the slide J between the plates j j, pivoted at 1', j, to the shde.

J and J are cables connected with the slide J and which pass through guides and around suitable sheaves and respectively connect with the stabilizing planes D, and D, but on the opposite side of the pivots d and d to that on which the cables G and G connect, whereby upon operating one set of cables the planes may be turned in one direction and in the opposite direction by operating the other set of cables. I

K is a lever adapted for manual operation,

supported in bearings mounted upon the rock shaft K to which is engaged the toggle arms K in turn connected with the slide F.

L is a guide bar secured to a fixed portion of the frame, and L', L, are rolls carried by the swinging iplatform adapted to bear upon each side 0' the bar L, to secure the swinging platform against lateral movement.

Having thus indicated the parts by reference letters, we will now describe the operation of our invention. Upon the aeroplane encountering air currents having a tendency to destroy its lateral balance and thus cause it to tilt in one direction or the other, the swinging or pendulum platform E,-on which we prefer to su port the driving mechanism or motor 0 the device? will have a tendency to swin in exact ratio to the degree of inclination o the aeroplane; or in other words, it will assume a vertical position. This act-ion of the movable or swinging platform serves to actuate the slides F and G,-they being normally connected with the platform by means of the dogs f and g,the cables on one side of the slides being under tension while those on the opposite side are free or slack, due to the movement of the slide in their direction. We will assume that the movable platform E has swung in the direction indicated by the arrow in Fig. 2 of the drawings. This would cause the slides F and G to move in that direction as indicated by dotted lines in the figure referred to. This action of the slides w1ll put the cable G under tension, thereby tilting the stabilizing plane D as indicated in dotted lines. The slide J being free to move, the cable J connected therewith and with the stabilizing plane D, will draw the slide J in the direction indicated by the dotted lines. The other end of the slide J being connected by the cable J 2 with the stabilizing plane D being thus put under tension, will serve to tilt the stabilizing plane D in the direction indicated in dotted lines. It will thus be seen that the stabilizing planes D and D will be tilted in opposite directions and in direct ratio with the lateral inclination of the aeroplane. Coincident with the movement of the stabilizing planes is the operation of the rudder C,

actuated by the cables F and F". As shown in Fig. 2, the cable F being under tension,-- as indicated by the dotted position of the slide F,will serve to move the rudder in the direction indicated by the dotted lines.

It may now be seen that the direction thus given to the stabilizing planes and rudder will serve to restore the lateral balance of the aeroplane, and should the aeroplane encounter aircurrents which have a tendency to tilt it in the opposite direction to that just described, the slides actuated by the platform tilting in the opposite direction, will operate the stabilizing planes and rudder ina like manner but in a reverse direction to that referred to. When it is desired to release the swinging'or movable platform from the slides, in order to manually steer the aeroplane, the pilot depresses the foot leven H which in turn actuates the rock shaft H and thereby operates the tripping bars I and I, which acting upon the dogs f and g force them out of locking engagement with the swinging platform at the same time forcing the long arm of the dog f into locking engagement with the slide J, being locked therewith by means of the plates j, y, pivoted to the slide ,the purpose being to provide a flexible abutment against which the end of the dog may bear should the operator throw the dog f out of engage ment when the platform is in such a position that the long arm of the dog would encounter the flexible plates before entering the spaced opening j between their ends provided for its reception. The relief thus afforded will permit the dog to find its seat between the contiguous ends of the flexible plates j, 7', through which it will be locked with the slide. Upon the operation of the tripping bars I and l by means of the foot lever H the locking dog H will be simultaneously actuated through its lever connection H with the rock shaft. This locking dog is designed to enter between two flexible members 6, e, secured to the rear end of the swinging platform on its underside, whereby the platform is locked in a fixed relation with the frame of the aeroplane.

We will now assume that the pilot desires to change the direction in which he is traveling. This is accomplished by grasping the manually operated lever K mounted upon the rock shaft K in turn connected by the toggle mechanism K with the slide F. The slide F being likewise connected with the rudder C by means of the cables F and F respectively, as previously explained. Upon operating the lever Ki'as indicatedindotted lines, the slide J will be forced to the 'posilines, while the end F, of the dog f, being;

now engaged with the slide J as previously tension wi noeana 1 opposite to that in mated by the dotted lines in that figure and opposite to that taken by the slide when the movable platform is engagedwith the slides F and G. 7

It may now be seen that the cables J and J 2 connected with the respective ends of the slide J, and inturn connected with the stabilizing planes D and D, will tilt the stabilizing planes D and D in a dlrection directly op site to that indicated by dotted lines in i 2. The cable J being under ii. tilt the plane D downward, thereby putting the cable G under; tension due to the lifting of the opposite side of the plane D,this action drawing the slide G and thereby puttin the cable Gr under tension, resulting in ti ting the plane D downward but in a direction directly opposite to that indicated in the dotted lines in the figure referred to. The inclination given to the stabilizing planes D and D is in accordance with the degree in which the rudder is turned, and is for the purpose of banking the aeroplane in making the turn.

When. it is desired to turn the aeroplane in the opposite direction, the lever K 1s forced to the left which action will cause the several slides, planes, and rudder to move in the opposite direction to that justdescribed, as will be understood.

While we have described the device as connected with a swinging or pendulum platform, it is apparent that the same re sults may be obtained by a sliding or rolling platform or element, connected with the stabilizing planes and rudder,-the construction being such that upon the lateral tilting of the aeroplane, the sliding element would be adapted to automatically actuate the stabilizing planes and rudder to restore the normal balance of the aeroplane.

Having thus described our invention, what we claim is 1. In an aeroplane, stabilizing planes, a rudder, a movable platform, slidable elements adapted to be engaged with said platform to move thereby, cables connecting the rudder with said slidable means, another set of cables connecting the stabilizing planes with said slidable means, whereby said stabilizing means and rudder are actuated to restore the normal balance of the aeroplane, and means whereby the platform and the slidable means may be thrown out .of cooperation so that the rudder and stabilizing planes, may be actuated manually. I

2. In an aeroplane, stabilizing planes, a rudder, a movable platform, a plurality of sliding elements, connections between one of the slidable elements and the rudder and other connections between the stabilizing planes and the other sliding elements, and means whereby upon swinging movement of the platform said sliding elements are actuated to manipulate the stabilizing planes and rudder to maintain the normalbalance of the aeroplane.

3. In" an aeroplane, stabilizing planes, :1 rudder, a movable platform, a plurality of sliding elements adapted to be engaged with said platform whereby they .mavmove with the platform, and cables connecting the rudder with one set of sliding elements, another set of cables connecting the stabilizing planes with the other sliding elements, for

the purpose described.

4. In an aeroplane, stabilizing planes, a rudder, a swinging platform, a plurality of sliding elements, means for interlocking said sliding elements with the platform, and cables connecting one of said sliding elements with the rudder and other cables connecting the stabilizing planes with the other sliding elements.

5. In an aeroplane, stabilizing planes, a rudder, a swinging platform, a plurality of sliding elements, a set of cables connecting one of said sliding elements with the rudder, another set of cables connecting the other sliding elements with the stabilizing planes, means for engaging said sliding elements with the swinging platform whereby they may move therewith, and means for tripping said engaging means, substantially as described.

6. In' an aeroplane, stabilizing planes, a rudder, a swinging platform, sliding elements adapted to be locked with said plat-- form, cables respectively connecting one of the sliding elements with the rudder and the other sliding elements with the stabilizing planes, means adapted to lock the swinging platform in fixed relation with the frame of the aeroplane and one of the sliding elements with another, and a manually op-,

erated lever adapted to operate the sliding elements whereby the stabilizing planes and rudder may be adjusted.

7. In an aeroplane, stabilizing planes, a rudder, a swinging platform, means connecting the stabilizing planes and rudder with the swinging platform, a guide bar secured to the fixed frame of the'aeroplane, and means secured to the swinging platform adapted to bear on either side of the guide bar whereby the swinging platform is secured against lateral displacement 8. In an aeroplane, stabilizing planes, a rudder, a swinging platform, sliding elements adapted to be locked to said platform, cables respectively connecting one of the sliding elements with the rudder and the other sliding elements with the'stabilizing planes and rudder, suitable dogs adapted to lock the swinging platform in fixed relation with the frame of the aeroplane and one of the sliding elements with another, and a manually operated lever adapted to operate the slidin elements whereby the stabilizing planes an rudder "may be adjusted.

9. In an aeroplane, adjustable stabilizing planes, a rudder, a swinging platform adapted to be operated by the inclination of the aeroplane, a plurality of sliding elements, means connecting the stabilizing planes and rudder with said sliding elements, and suitable locking dogs adapted to engage the swinging platform with'the sliding e ements.

10. In an aeroplane, a frame, stabilizing planes each mounted on a central axis, a rudder, a swinging platform, and means connecting the platform and the stabilizing planes and rudder whereby upon swinging movement of the platform under the influence of tilting action of aeroplane in flight the stabilizing planes and rudder will be adjusted automatically to maintain a normal balance of the aeroplane, and means constructed and arranged whereby the swinging platform may be locked against movement.

11. In an aeroplane, a frame, stabilizing planes each mounted on a central axis, a rudder, a swinging platform, and means connecting the platform and the stabilizing planes and rudder whereby upon swinging movement of the platform under the infiuence of tilting action of the aeroplane in flight the stabilizing planes and rudder will be adjusted automatically to maintain a normal balance of the aeroplane, means constructed and arranged whereby the swinging platform may be locked against movement, and means whereby, when the platform has been locked against movement, the stabilizing planes and rudder may be manually operated. j

12. In an aeroplane, stabilizing planes, a rudder, a movable platform, cables connect ed to the rudder, cables connected to the stabilizing planes, and movable mechanism operable under the influence of the movable platform 'to actuate the cables and thereby adjust the stabilizing lanes and rudder to maintain a balance of the aeroplane, said cables being independent of the movable platform.

13. In an aeroplane, stabilizing planes, a

rudder, a movable platform, cables connect- I ed to the rudder, cables connected to the stabilizing planes, and movable mechanism operable under the influence of the movable platform to actuate the cables and thereby adjust the stabilizing planes and rudder to maintain a balance of the aeroplane, and means whereby the movable platform and said movable means which cooperates with the platform may be thrown out of cooperative relation.

14. In an aeroplane, stabilizing planes, a rudder, a movable platform, cables connected to the rudder, cables connected to the stabilizing planes, and movable mechanism operable under the influence of the movable platform to actuate the cables and thereby adjust the stabilizing planes and rudder to maintain a balance of the aeroplane, and means whereby the movable platform and said movable means which cooperates with o the platform may be thrown out of cooperative relation, and means whereby, after said movable platform and said movable means are thrown out of cooperative relation, the aeroplane may be operated manually.

In testimony whereof, we sign this specification in the presence of two witnesses.

EGBERT J. RANDALL. Witnesses:

GRACE E. WYNKOOP, SAMUEL E. THOMAS.

SHERMAN A. RANDALL. Witnesses:

ROY C. WEBsTnR, SAMUEL L. CRABBE.

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