US1053619A - Aeroplane. - Google Patents

Description

W. L. MARR.

AEROPLANE.

APPLICATION FILED JULY 2,1910.

1,053,619, Patented Feb. 18, 1913.

2 SKBETB-BHIIET 1.

a 7%dA7 Mmm Y 1 g h M WALTER L. MARE, OF FLINT, MICHIGAN.

AEROPLANE.

Specification of Letters Patent.

Patented Feb. 18,1913.

Application filed July 2, 1910. Serial No. 570,134.

To all whom it may concern:

lie it known that I. \VALTER L. Mann, a citizen of the United States of America, residing at Flint, inthe county of Genesee and State of Michigan, have invented certain new and useful Improvements in Aeroplanes, of which the'following is a specification, reference being had therein to the accompanying drawings.

In the construetimi and operation of aeroplanes it is found that one of the chief ditliculties of controlling lies in the fact that when the sustaining planes become tilted for any reason transversely to the line of flight. the machine is liable to fall as there is but little resistance afforded by the planes to this movement. Or if there be stability planes, they are so arranged that they offer as much resistance to the movement of'the lower part of the machine as they do to the upper part so that while the sidewise movement of the machine due to its tilting may be resisted by these planes, the machine does not tend to right itself.

This invent-ion relates to aeroplanes and to an arran ement thereof whereby any tendency in die machine to sidewise movement due to the lateral tilting of the main planes is so resisted that the lower portion of the machine tends to swing under the uper portion as a parachute tends to right itself when falling, and thereby to cause the machine to automatically resume a horizontal position. 7

Another feature of the invention is the provision of auxiliary balance steering planes so disposed that either end of the machine may be raised at will to avoid an obstacle when in flight whereby the aeroplane may be turned in its course, even if the main steering plane or rudder of the machine becomes disabled, the operator still having complete control of the apparatus and directing its flight without the use of the main rudder plane.

The invention consists of the matters hereinafter set forth, and more particularly pointed out in the appended claims.

In the drawings, Figure 1 is a view in elevation of an aeroplane that embodies features of the invention; Fig. 2 is a plan view thereof; Fig. 3 is a view in detail of a balance steering plane.

As shown 1n the drawings as one preferred form of construction of the bi-plane type, the main frame 1, preferably rhomboidal in figure, is formed of suitable materials 1n proportion to combine the necessary strength with lightness. The frame is sup-V ported when on the ground in the usual manner on a wheel truck 2. The main frame is disposed longitudinally to the line of llight of the machine and has suitable lateral extensions 3.

A pair of main planes 4 are supported by the frame and extensions and are preferably secured in sections to the frame work, being inclined to the line of light of the machine at the proper sustaining angle. 7

Forward lifting planes 5 preferably disposed in parallel horizontal pairs, are pivotally secured at the forward end of the frame with a tilting bar 6 or other suitable controlling mechanism extending back to the operators station at the middle of the main body whereby their angle of incidence to the line of flight may be varied as desired.

A rear balance plane 7 is secured at the proper angle to the rear end of the main frame and a main rudder plane 8 that is split to lear the balance plane is pivotally secured to the frame to swing transversely to the line of flight through suitable controlling mechanism of any preferred type extending forward to the operators station.

A. balance steering plane 9 is pivotally mounted on each extension of the main frame preferably adjacent to and between the outer sections of the main planes. In preferred form, each consists of a rudder member 10 pivoted at its forward edge to swing on an axis substantially perpendicular to the sustaining or main planes and a balance member split to embrace the rudder plane and pivoted at its forward edge to swing on an axis that intersects the secondary rudder axis at right angles thereto. As herein shown the members swing together on the rudder axis while the balance memher is free to be tilted on its own axis independent of theangular position of the rudder member relative to the line of [light of the machine. if the rudder axis is at the forward nun-gin of the main plane. the front edge of the balance plane is slightly curved so that it does not project beyond the main planes when swung with the rudder. The balance plane need not swing in which case proper provision is made to afford movement of the rudder plane. The members are controlled separately through suitable connections running to the operators station where levers, handles or other devices which may be of any preferred type and arej chine is well below the upper main plane and preterablyis also below thelower main plane. At each end of the lateral extensions of the main frame, stability planes 14: are.

secured to the upright members of the frame, substantially perpendicular to the "under face ofthe upper main plane. C ne or more of these planes is placed at each endoi" the machine with its lower margin at a considerable distance above the upper face of the lower main plane and above the center of gravity of the machine. Preferably the stability planes are disposed in pairs on either side of the auxiliary balance steering planes, as indicated herein. By this arrangement of the balance steering planes, the operator may tilt them toaugmcnt the lifting power of the main planes or to oil'- set their effect dependent on the angle he gives the balance members. if he wishes to cause either end of the machine to momentarily rise or fall he accomplishes this by depressing or raising the rear edge ot'the' balance member at that end. The auxiliary planes are preferably pivotally secured to the main frame at as proximately the same'distance from its center as the main steering plane, and by defiection of the auxiliary rudder members, the machine is made to swing on one end as on a pivot- If any one of the steering planes, either auxiliary or main, become disabled, the operator can control the direction of his flight by proper manipulation of the other two. By simultaneously deflecting the steering planes and depressing the outer balance plane, the outer end of the machine as it wheels, tends to rise, thereby overcoming its inertia which would otherwise rock it the other way.

Another feature is the self-righting character oi the machine due to the position of u the stability planes. It for any reason the main planes are tilted laterally, the stability planes aiford such resistance to the air as to prevent the sidewise movement of the ma- 1 es which would otherwise occur and as t e center of gravity of the machine is-well below the upper main plane, and as the stability planesextend only a short distance below the upper plane, the movement of the latter siilewise is retarded while the under' plane and the motor swing into place below it with he same motion as that of a loaded parachute. Thus the machiiie tends to mainta 11 its equilibrium under ordinary conditibns and rights itself when swervingj or decreased as the case'may be to meet;

from a direct line of flight. Obviously the stability planes may extend above the upper main plane it so desired. 7

The pivotal supports of the auxiliary rudders enables the operator to hold the membore in line with the path of motion of the machineif desired,-so as to afford as little resistance as possible to its forward motion compatible with their lifting or sustaining effect. This reduces the power necessary to drive the aeroplane below that required by aeroplanes of ordinary type.

The planes may be multiplied in imnibegr fer ent requirements of service and the tion offthe several parts may be varied without materially affecting their ellici'ency. Y

Obviously, changes in. the details of construction may be made without departing from the spiritof the invention and I do not care to limitmyself to any-particular form or arrangement of parts.

I claim as my invention 1. In an aeroplane, a main frame disposed longitudinallly in the line of flight of the machine, main planes secured transversely on the main frame at a fixed angle. to the line of flight, lifting planes angularly ad-i justable 'on the forward end of the main frame, a rear balance plane on the back end of the main frame, a main steering plane pivotally secured to the back end of the main frame to swing in a plane transverse to the main plane, balance steering planes adjacent the main planes swinging on an axis perpendicular to the main planes, balance members each angularly adjustable on an axis interseating a balance steering plane axis, and stability planes perpendicular to the main planes parallel to the line of flight adjacent to the upper main plane.

2. In an aeroplane, a main frame disposed longitudinally in the line of flight of the machine, main planes secured transversely on the main frame at a fixed angle to the line of flight, lifting planes singularly adjustable on the forward end of the main frame, a rear balance plane on the back end of the main frame, a main steering plane pivotally secured to the back end of the main frame to swing in a plane transverse .to the main plane, balance steering planes adjacent the main planes, each pivoted to swing on anaxis substantially perpendicular to'the main planes and provided with a balance member angularly adjustable on an axis intersecting: the steering plane axis, and stability planes substantially perpendicular to the main plane secured parallel to the line of flight adjacent to the upper main plane and at an interval from the lower main plane. I

3. In an aeroplane, a main frame disposed longitudinally in the line of flight of the machine, lateral extensions therefrom, main planes secured on the main frame and extensions at a fixed angle to the line of flight, forward lifting planes angular-1y adjnstahle on the main frame a rear halam'e plane on the ba k end e-t' the main frame, a main steering plane pivetally serured to the l aelc end of the main frame to swing in a plane transverse tn the main planes and divided to embrace the rear balance plane. halance steering planes each pivtnallv secured near the extremities of the main plane to swing on an axis at right anglea therete and previded with a halanee member tiltahle on an axig at rightangles to said lllvwl axis. and means for n'ianipulat-itng the several steering and balance planes independently.

:1. 1n anaereplane, a main frame disposed longitudinally in the line of flight 01' the machine. lateral extensiens tlteret.mn main planes secured on the main frame and extensio-ns at a fixed angle to the line of flight, forward li'l'tinn' planes angularly adjustable 0n the main frame, a rear balance plane on the back end of the main frame, a main steering plane pivotally secured to the baelt end of the main frame to swing: in a plane. transverse to the main plane and divided to embrace the rear balanee plane, stability planes Substantially perpendicular tn the main planes seeured parallel to the line (Fl light adjarent to the upper main plane and at an interval from the lower main plnntn balance steering plant-H eat-h pivetally eured near the extremities of the main plane in swing on an axis at right; anglesthereto and provided with a balance member till'able en an axis at right angles to said first ax and means i'nr manipulating the several steering and balance planes independently.

Witnesses U'r'rn l. .lLurrnnL, Anna lt'l. Donn.

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