US1359590A

US1359590A - Airplane

Info

Publication number: US1359590A
Application number: US252205A
Authority: US
Inventors: George C Gillespie; Frederick W Barker
Original assignee: Individual
Current assignee: Individual
Priority date: 1918-08-31
Filing date: 1918-08-31
Publication date: 1920-11-23
Anticipated expiration: 1937-11-23

Description

G. C. GILLESPIE AND F. W. BARKER.

AIRPLANE.

APPLICATION FILED AUG.31 1918. 1,359,590. Patented Nov. 23, 1920.

2 SHEETS-SHEET1- G. C GILLESPIE AND F. W. BARKER.

AIRPLANE.

APPLICATION FILED AUG. 31. 1918.

Patented Nov. 23, 1920.

2 SHEETS-SHEET 2- til i may he effected with greater seiety then LS, AN

l) FREDERICK "W. Bel

31,359,5ttlh Application tiled August 31,

England, respectively, residents of Great Hills and New Dorp, both in the county of Richmond end State of New York, have invented certain new and useful improvements in Airplanes, of which the following is o, specification.

This invention relates to airplanes, and our improvement is porticulerlv directed to broking or speed retarding means, as tor nose dives or when tolling, end whereby lendings heretofore; also whereby on he brought to it hslt otter e releti surtece run,

The high powered eirplenes Whose flying speed lroin 100 to 150 m l s an hour, and which in lending; under it tions touch the ground from oil condo n to at) iniles en hour reouire even sur'ioced runway 0 o J Y M o h v J2 or 3% to 300 rest to assure ireedon'i accidents. These surfece conch; ore not always evsileble, especially uh forced lending hes be .i e c. J desireble that the speed or too nioclnne should be retorded, hoth when gliding to "Word the lending piece, end When, under moment-urn, it is rolling along" the surface.

Therefore our invention. co.,.isists o1 pres sure or broking venes, normally closed against the sides of the fuselage, and adapted to be swung; outwardly to present e large increase in one or heed resistance ol the airplane, thereby causing o diminution in its speed oi movement.

Two pairs of these broking vetoes, oil of the some area, may be employed, operating, respectively, at the opposite sides of the fuse loge, and at the top end loottoni thereof, Thus the increased pressure may be opplied equally in lines of force exerted in pore-ullelisin With and about the longitudinal oi? the eirplane, and thereby no tendency is created to very the directional control of the machine Further, seid broking venes rosy he loceted reervverdly ol the center Oil grovitv of the machine, Where they have the effect of stabilizing the machine in its controlled direction of movement.

Appreciating the necessity of minimising the amount of energy to he Specification. of Letters Eetent.

lfi lei. Serial 330. 252,205.

forth by the pilot in operating the braking vanes, to apply them, and also to assure their smooth and cosy svorlring, We have devised a sliding carriage, mounted Within the fuseloge, and operable through a lever'un'der the control of the pilot; and e systeni'of con1- pound leverage between the sliding frame and the braking vanes, the letter being belonced or nearly balanced, whereby said vones may he moved out or in with the exercise oi relatively little effort by the pilot.

Uther lectures and sdvunteges ot our invention will hereinafter sppeer.

in the drawings Figure 1 is plon view of e po fuselage broken away, one, shoving provement. in. 2 is a perspective view 0 i "ie poi non of e tussle-gs, with the veneeextended therefrom,

Fig, 3 is o cross-sectional view of the tr loge frame, hnv-ing the guide broclrets the sliding cerrie l ig. at is e deb tion of the fuseloge, loving on one lever mounted therein, toil perspective view showing the connected z rrongenient of the hrelting venes.

in carrying;- out our invention we provide means whereby the pressure venes, loceted respectively the top, bottom end sides of the fuselage, ore pivotolly mounted upon at single carrizwe or frame which is adopted to slide longitudinally Within the luseloge, the engaging iulcro between the venes end cotriege being thus inoveble. A separate guide arm for each vane is pivoted thereto, eten outward portion thereof, and also heslizred pivotal engagement with the fuselage, to thus cause the vane to turn out or in concurrently With the rearward or torivord slid inp; movements ot the carriage.

ln the drawings We have shown on air plene fuselage Whose frame is composed of the longerons l endtrensverse members Mounted in the angles of said frame are brackets 3, having guide orifices t, to receive slidoble rods 5, which letter comprise the longitudinal members of the ven e operating carriage or frame. in the present example of our invention, wherein the fuselage is shown as equipped with tour pressure vanes 6, four of the rods 5 are required, since each vane 6 is carried by e pair of rods The hinge portions the vsnes, es Y,

nonof s it lt tl each extend rearwardly from said vanes and extend through slots 8 in the fuselage covering, and engage with pintles 9 carried by a bushing 10 on a rod 5. Each bushing 10 may obviously have hinge connection for two right-angularly pivoted vanes 6, when four of said vanes are employed.

The slidable frame is produced by connecting the rods 5 with transverse rods 11, and diagonally extended, crossed bracing rods 12, which latter be connected,at their points of intersection 13, to comprise a strong and rigid structure.

Guide arms 14, of which a pair may be used for each vane '6, are pivoted .each at one end to a fixed point in the fuselage frame, as at 15, and, at their opposite ends are pivoted to said vanes, toward the outer portion of the latter, as at 16, to cause said vanes to swing outwardly through' a flattened arc during the rearward sliding move ment of the carriage. llt will be obvious that the pivoted connection 16 between arms 14 and a vane 6 should be located in the most effective portion relatively to the chord of the vane, and we prefer to locate these pivotal points toward the outer edge, in order to attain a pressure balancing effect upon the vane for facilitating its outward turning movement.

As the carriage is moved rearwardly the rods 5 carry with them the inner hinged portions of the vanes, and the vanes being held at their outward portions by arms it, thus swing outwardly to the desired bralting positions,

The carriage may be actuated as by a lever It' l, mounted in the cockpit, under the con.- trol of the pilot, and connecting by rod 18 with said carriage. it. raclr 19 or the lilre may be employed to hold the lever 17' in a desired operative position.

in order to absorb the shoclrs resulting from the sudden impact of the sliding carupon reaching the limit of its movement, we provide cushions, as 20, which may be composed of cork or other resilient material. These cushions may be mounted upon the fuselageframe in positions to serve as stops for the carriage at the limit of its movement in operating the vanes to their full extended openine",

Variations may be resorted to within the spirit and scope of our invention, and thereof used without other we claim 1.. Speed retarding means for airplanes comprising vanes normally closed against the four sides of the fuselage, and manually controlled means to synchronously extend said vanes for balanced pressure resistance offered in directions parallel to the longitudinal axis of the airplane, said vanes presenting their pressure surfaces at increasing, rearwardly outward inclinations relatively to the longitudinal axis of the airplane, as said vanes are being extended.

2. The combination, with an airplane having a fuselage, of braking vanes normally closed against opposite sides thereof, and having longitudinal slidable engagement with said fuselage, and means for turning said vanes outwardly. to offer ressure resistance surfaces in the line of fl1ght,

while said vanes are outward.

3. The combination, with an airplane, having a fuselage, of braking vanes movable from and to said fuselage, means slidable upon the fuselage to move said vanes longitudinally, and guide means to turn said vanes outwardly, the guide means engaging the vanes in intermediate positions along their chords, whereby said vanes are pressure balanced in turning outwardly.

4t. The combination, with an airplane, having a fuselage, of bralring vanes movable from and to said fuselage, means slidable upon the fuselage to move said vanes longitudinally, 1. id guide means, in fixed pivotal engagement, respectively, with the fuselage and said vanes, accord outward turning movement to said vanes during their longitudinal motion,

1 The combination, with an airplane. a fuselage, or carriage sli-dably mounted upon said fuselage, control means for said carriage, bralre vanes mounted on said carriage, and means co-acting with said. sliding carriage to turn vanes outwardly or inwardly according to the direction of movement of said carr .ge,

feigned the boroue'h of l nhattan in the city, county andldtate of New Ybrh this 80th day of August, A. D. 1918.

GEQlEtGE GlLLldEtPlTE. lt lithlDEPtlQltl "W. ldllltlliER.

Witnesses