US1110355A

US1110355A - Aeroplane.

Info

Publication number: US1110355A
Application number: US79379013A
Authority: US
Inventors: Philip H Smith
Original assignee: Individual
Current assignee: Individual
Priority date: 1913-10-07
Filing date: 1913-10-07
Publication date: 1914-09-15
Anticipated expiration: 1931-09-15

Description

P. H. SMITH.

AEROPLANE.

APPLICATION FILED 00'1.7, 1913.

1, 1 1 0,355. Patented Sept. 15, 1914.

3 SHEETS-SHEET 1.

P. H. SMITH.

AEROPLANE.

APPLICATION FILED OQT.7, 1913.

1,1 1 0,355, Patented Sept. 15, 1914,-

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P. E. SMITH.

ABROPLANE.

APPLIGATION FILED 0c T.7, 1913.

1,1 10,355. Patented Sept. 15, 1914 3 SHEETS-SHEET 3.

UNITED STATES PATENT oFFIoE.

PHILIP H. SMITH, or PAWLING, NEW YORK.

AEROPLANE.

Specification of Letters Patent. Patented S t 15 1914 Application filed October '7, 1913. Serial No. 793,790.

To all whom it may concern:

Be it known that I, PHILIP H. SMITH, citizen of the United States, and a resident of Pawling, Dutchess county, State of New York, have invented certain new and useful Improvements in Aeroplanes, of which the following is a specification.

' The object of my inventionis to prevent the precipitate descentof an'aeroplane in W ing to my invention, and presumably travel ing a horizontal dlrection or substantially so; Fig. 2, a similar view showing the biplane tilted at an angle of'forty" fivedegrees and the auxiliary safety plane in independent;

action; Fig. 3, is a top view of my auxiliary safety plane; Fig. 4, is a'sectional elevation upona larger scale, of means for controlling my auxlhary safety-plane, the latter being represented 1n its lowest or normal positlon and adjacent parts only of the biplane being shown; Fi 5, is a section taken upon plane 5-'5 Fig. 4, looking downward; Fig. 6, is a top vlew of the auxillary safety plane rudder expanded; Fig. 7, 1s a view of the auxiliary safety plane released and at the top of the mast; Fig. 8, a like view illustrating the relocking of the auxiliary safety plane prior to its descent into normal position; Fig. 9, 1s a detail of means for limiting the play of the auxiliary safety plane; Fig. 10, a top view with the parts in the positions shown in Fig; S, partly broken away; Fig. 11, is a sectional elevation upon a larger scale of the upper extremity of the mast illustrating means for effecting the parallelismof the auxiliary safety plane withrelation to the fixed plane or planes, the lifting pawlbeing shown in its highest position; Fig. 12,'is a similar View showing the lifting tion. I

In Figs. 4, 7 and 8 the axis 8 of the auxpawl in its lowest posiiliary safety plane ss, is shown in section,-

the near half of the plane being omitted.

I have herein shown and described mv invention as applied to a biplane, although it is applicable to a monoplane or any conceivable form of aeroplane, as may be found most expedient, so that I do not limit myself to the identical form and construct1on of parts herein shown, since various modifications in detail may be resorted to without departing from the spirit and intent of my invention in this respect.

WVith this understanding A, represents symbolically an aeroplane of any ordinary or well known construction provided with the parallel planes at, a, and rear controla the motor, propellor'and other details being omitted.

M is a tubular mastsupported on the main frame-work of the apparatus at right angles to the fixed planes a a,said mast being positioned centrally and forward,preferably in close proximity and to the rear of the seat of theaviator.

1 Normally my auxiliary safety plane 8,8, occupies aposition parallel to and above the upper fixed plane a, as shown in'Figs. 1 and i and being normally locked in such position constitutes essentially a supplemental plane of maintenance acting in conjunction withthemain plane or planes below'to sus tain'the aeroplane in its flight." Hence, if

used on a biplane it practically gives the effect, under normal conditions, of a triplane; or if used on a monoplane it converts the latter in some respects, as for normal flying, into abip1ane,the superficial area of auxiliary safety plane 8, 8, being of course made relatively proportionate in order to attain the results desired' Under adverse conditions of flight however the main function of the auxiliary plane 8, s, is to render the aeroplane self-righting and safe in recovering or descent. Thus in case of motor failure,'-the breakage of other parts, or loss of control for any reason, the release of the auxiliary safety'planes, s, obviates all dan ger ofheadlong descent, turning over or collapse, by allowing said auxiliary plane to automatically adapt itself to the air pressure in such manner as to turn the aeroplane to face the wind pressure, thereby retarding descent and enabling the aviator to regain control of the apparatus. 4 I

To this end I secure my auxiliary safety plane 8, s, to apivotal axis 8, which is longitudinally parallel to the fixed plane a below, but which under certain conditions is free to turn within prescribed limits so that the said auxiliary safety plane 8, s, when free may adapt itself to wind pressure under the guidance and control of a fixed rudder 9, attached to the frame F. This frame F, comprises an upper sleeve f, and a lower sleeve f, both slidably and rotatably mounted upon the cylindrical mast M,said sleeves f, and f being connected with and affording support for the bracket members 7, f and 7' 7" respectively. Upon the bracket members f 7' the axis 3, of the auxiliary safety plane 8, s, is mounted in bearings s, 8, while the rear bracket mem-.

bers 7, f support the rudder r, and the rock lever b, which latter is pivotally attached'as at 7". A stop 6, on the bracket member f limits the motion of the rock lever b, in one direction; and a pressure spring 5 interposed between the lower part of said rock lever 12 and the sleeve f tends constantly to thrust and maintain said lever in contact with said stop Z), as shown in Figs. 7 and 8, in which position the shoulder 6* on the lever I), is adapted to engage with and support the end of the arm 8 attached rigidly to the axis 8 of the auxiliary plane .9, s. XV hen the auxiliary plane 8, s and frame F descend to the lower normal position the lower end of the lever 1) contacts with a cam surface 0, thereby rocking the lever Z) against the resistance of the pressure spring 5 as shown in Fig. 4 and thus releasing the arm 8 s is a bolt arm also rigidly secured to the axis 3' of the auxiliary plane .9, s, and

formed at its lower extremity with a shoulder 5*, for engagement with a spring bolt cl, when the frame F is in its lowest position as shown in Fig. &,the two armss and 5 extending at right angles to each other or substantially so.

A spring 8, attached at one end to the arm 8 and at the other to the sleeve f, tends constantly to depress the arm 8 and to release the arm 3 from the spring bolt (Z, and to counteract this tendency, and to lock the frame F in its lowest position, another spring bolt 6, or equivalent mechanical ex-v pedient is provided, to be retracted either manually as by the handle 6, or automatically when the aeroplane assumes a dangerous inclination'by means of the gravity re lease G. This gravity release G, consists of a weighted pendulum g, suspended from a universal joint g and provided with cross arms 9 connected by cords g or equivalent means, with the. retractor 9 as shown in Fig. l,the slack of the connections'g being suflicient, say, to allow ofythe inclination of the aeroplane to any degree less than 45,

the top of the mast.

without causing the gravity release G to retract the bolt 6.

The parts being in the normal positions shown in Fig. &, the withdrawal of the bolt 6, causes the spring .9 acting upon the arm 8 to incline the auxiliary safety plane 3, s, at an angle with relation to the fixed or main plane a, or planes a, a, and this degree of inclination may be limited, for instance, by a stop 71, consisting of a bent arm secured to the axis 5 and arranged to contact with a member f of the frame F, so as to limit the divergence of the auxiliary plane 5, s, to say, an angle of 45 as related to the main plane or planes. By making this stop arm h, adjustable upon the axis 8, as by a set screw it, as indicated in Fig. 9 it is obvious that this degree of divergence of the auxiliary plane s, s, may be regulated and limited as desired; and by the use of a similar stop if, the parallelism of the planes may be attained with accuracy.

The efiect of-the release of the auxiliary safety plane 8, s, is to cause it, under the control of the rudder 1", to present resistance to the air pressure, and this resistance causes the frame F to slide up the mast Muntil the upper collar f, contacts with the cap m, at Hence the auxiliary plane 8, s, acting through the mast as a lever, tends to deflect the aeroplane from itsdownward course and to bring its fixed main plane or planes again into action in alinement with the air pressure or substantially so, so as to sustain the apparatus more or less in its descent; if not to bring it again under the control of the aviator, for even if failing in this latter respect the auxiliary plane .9, 8, if made ofappropriate superficial area will divert the aeroplane sufficiently from a head-long vertical course to cause it to describe a curve and descend in comparative safety. The mast M not only thus acts as a lever to apply the resistance afforded by the released auxiliary plane s, s, but it also serves as a track or guide to remove the auxiliary plane from the immediate vicinity of the fixed plane below, to afford freedom of action and available air pressure or res stance. Furthermore the frame F,

-when released from the lower normal positlon shown in Fig. 4, 18 free to rotate upon all contingencies of accident and disaster,

and to counteract all possible tendency to fall backward or tail-on, I form the rear portion of the rudder 1', in two sections 1*,

1", hinged to the main portion 9, so that in case of back action or pressure the said rear sections 1", 1*, will be spread apart temporarily against the stops r W, as shown-in Fig. 6, thereby causing the frame F to swerve'to one side or the other and so to bring the auxiliary plane 8, 8,130, faceqthe wind and right the aeroplane.

When the auxiliary plane 3, s, is used temporarily. as an adjunct or supplementary I means of control, as during gliding, exhibiplane and its frame willsettle by gravity tion maneuvers 810., or where the'auxiliary plane has been usedto counteract unfavor able atmospheric conditions and it is desir: able to restore said auxiliary plane and its frame to the normal position and relationship shownin Figs. 1 and 4, this may be accomplished by again bringing said auxiliary plane .9, 8, into parallelismwithlthemain plane or planes, underwhich conditions the auxiliary into said normal position. To this end I provide a planessettingdevice in the upper part of the mast M consistingessentially of: a spring pawl or lifter i, pivotallymounted upon a traveling block'or carrieri', situated within the .mast. The alinement of this carrier a" maybe provided for in any suitable or-desired manner. Asshowniin the drawthe rotation of the. carrier z";

.12. Attached to the lifting pawl 2', isa cord or equivalent j, passingovena pulley 7" mounted in the upper end of the mast, and down through the latter to. a pulley 1 j mounted in an opening in the lower part of the mast belowthe fixed plane a, as shown in Fig. 4, from which opening and pulley j, the cord 7', may be led over anotherpulley 7' so mounted as to bring the handle j into convenient proximity to the aviator. Supposing the carrier 71 to be in the lowest position as in Fig.12 and the auxiliary plane s, 8, and its frame F to be at the top of the mast M and held thereby air pressure due to the inclination of the auxiliary plane 8, 8, if the cord 7', is pulled by means of-the handle it will turn the lifting pawl i, against the resistance of the spring 6 until the point i of saidlifting pawl projects through the slot 472/ and will raisethe carrier i into" the position shown in Fig. 11,the point i of the lifting pawl i,in its upward journey encountering the under sideof thearms and raising it into the position'shown in Fig. 8 against the resistance of the spring .9 As the arm 8", is thus raised its end encounters and pushes back the lever b,-against the resistance of the spring 6 which latter when safety." r

the end of theflever, has passed the shoulder 6 forces said shoulder?) under. the end of said arm 8 thereby locking the auxiliary plane s, s, parallel inposition to the fixedv plane at, below, and also bringing the arm 8 into position for engagement with the spring bolt d. The aeroplane being presumably,

sailing against and at rightanglesto-the wind pressure, the frame F under the guidance of the rudder 9, upon the release of the. pull cord 7', will descend by gravity in aline-.

ment or substantially so with the boltid, and cam 0, below, and to insure an accurate register and engagement of thepartsI pre fer to make the lower portion of the sleeve.

f -V shaped to contact with a correspond ingly formed seat o, as shown in Fig. 4, so

that any slight variation in alinement during descent will be corrected. At the completion of the descent of the frame F &c.,

the curved side of the shoulder s on the 'le-' ver 8 forces saidshoulder into-engagement with the spring bolt 03, and at the same-time the cam c, acting on :the lower end ofthe lever '17, releases the arm .9 from the latter, s0 that-upon the withdrawal .of the bolt e, the auxiliary safety plane 8, s, will be again released and free to adapt itself instantly to' wind pressure; and to act independently of the niain orfixed plane lor. planes as hereinbeforeset forthq fwl .I' i- 1 fiAs hereinbefore intimated 'I' do not" limit 'myself to the identical formand-Z construction ofgdetails and devices herein'shown, the isameflbeing-used to illustrate the, practical application 'of' my invention, and; being designed to cover iequiia-lent mechanical ex- 'pedients as well as modlficationswlthin the scope and intent of my invention.

It is to be noted that my auxiliary safety plane and'its connections'are entirely independent of, and do not interfere'with, the

ordinary control ofthe aeroplane; and that under normal fixed conditions the auxiliary plane adds to the sum total of the sustainings'urface, while the auxiliary rudder tends to stability of alinement and motion. Furthermore. a single movement of the hand of the aviator is s'uflicient to immediately release the auxiliary safety plane; and a single movement is likewise all that is necessary to reset the'auxiliary plane and restore it to its normal position. And'if the aviator is care less or incapacitated for any reason, in case of the dangerous lILClHIEItIOIL of the aeroplane my automatic release wvill insure" VVhile it may be desirable under ordinary conditions of use that the auxiliary plane be held by positive means normally parallel and inproximityito the main plane surface,

it is also capable of free use and play un-- restrictedly on the mast as automatic means forycounteracting the effects. .of suddengva riations in pressure or direction of air currents, to facilitate gliding &c., and as a constant safety medium not dependent on manual or mechanical release, in which case a coiled spring w, may be arranged in con-' hat I claim as my invention and desirev to secure by Letters Patent is, i

1. In combination, an aeroplane, a mast carried by said aeroplane, a frame slidably mounted on said mast, releasable means for locking said frame in normal position, an

auxiliary plane pivotally mounted onsaid frame, releasable means for locking saidauxiliary plane parallel to the main-plane surface, and a ruddermounted on .said frame. i

2. In combination, an aeroplane, 'a mast carried by said aeroplane, a frame slidably;

mounted on said mast, releasable means for lock ng said frame in normal position,-an auxiliary plane pivotally mounted on said frame, releasable means for locking; saidauxiliary plane parallel to the mainfplane surface, and a rudder mounted on said frame; said rudder being formed 'with.

hinged expandable rear sections, for the purpose described. a a

3. In combination, an aeroplane, a mast carried by said aeroplane, a slidableframe mounted on said mast, an auxiliary plane pivotally mounted on said frame, a rudder mounted on said frame, releasable means for retaining said frame in its normal position, and means for automatically releasing said frame consisting of a spring bolt, a gravity pendulum supported upon a universal joint formed with lateral arms, and flexible means connecting said arms with said spring'bo-lt whereby when the aeroplane is tilted at a prescribed angle the auxiliary plane will be released for the purpose described.

4. In combination, an aeroplane, a mast carried by said aeroplane, a frame slidably mounted on said mast, releasable means for.

locking said frame in normal position, an auxiliary plane pivotally mounted on' said frame, releasable means for locking said auxiliary plane parallel to the main plane surface, a rudder mounted upon said frame, and means for turning said auxiliary plane Copies of this patent may be obtained for into parallelism with the main plane surface after its release, for the purpose set forth.

'5. In combination, an aeroplane, a mast mounted thereon, a frame slidable on said Inast, releasable means for securing said frame in its normal position,an auxiliary plane mounted upon an axis pivotally supported on said frame, locking arms secured to said axis, and a spring bolt and cam releasearranged to act in conjunction with said arms. to lock one while releasing the other, thereby setting the parts in such manner that the auxiliary plane may be released by the withdrawing of a single bolt as and for the purpose set forth. V

6. In combination, an aeroplane, a mast carried thereby extending substantially at right angles to the fixed plane surface, a

frame slidably mounted on said mast, re-- leasable means for locking said frame in its normal position adjacent the fixed plane 'surfaceyan auxiliary plane pivotally mounted'on said frame, and means for automatically releasing said auxiliary plane axially upon'the release of the said frame.

7. Iii-combination, an aeroplane, a mast carried thereby; extending substantially at right angles to the fixed plane surface, a frame slidably mounted on said mast, releasable meansfor lockingsaid frame in its norm'al position'adjace'nt' the fixed plane surface, an auxiliary'plane pivotally mounted on said frame, means for automatically releaslng said auxihary plane axially upon the'releaseof the said frame, and means forbringing said auxiliary plane into par-,

allelism with the fixed plane surface, and automatically locking-it in such position, for

f ?the purpose-set forth.

8. In combination, an aeroplane, a mast carriedthereby, a frame slidably mounted on said mast, releasable means for locking :said frame in its normal position at the bot tom of said mast, an auxiliary plane pivotallymounted on said frame, and means for limiting the inclination of said auxiliary plane when released axially, for thepurpose described.

9. In combination, an aeroplane, a mast carried thereby, a frame slidably mounted on-said mast, releasable means for locking said frame in its normal position at the bottom of said mast, an auxiliary plane pivotally mounted on said frame, and adjustable means for regulating the prescribed inclination of said auxiliary plane when released forthe purpose described.

PHILIP E. SMITH.

five cents each, by addressing the Commissioner of Patents,

Washington,-D. O. i