US1776733A

US1776733A - Combined brake and auxiliary wing mechanism for aeroplanes

Info

Publication number: US1776733A
Application number: US384759A
Authority: US
Inventors: Clement B Kasuboski; D F Breed
Original assignee: ROY H MORRIS
Current assignee: ROY H MORRIS
Priority date: 1929-08-09
Filing date: 1929-08-09
Publication date: 1930-09-23
Anticipated expiration: 1947-09-23

Description

Sept. 23, 1930. c. B. KASUBOSKI 1,776,733

COMBINED BRAKE AND AUXILIARY WING MECHANISM FOR ABROPLANES Filed Aug. 9, 1929 2 Sheets-Sheet 1 INVEN'I'ORr pt 1930- c. B. kAsuaosxl 1,776,733

COIBINED BRAKE AND AUXILIARY WING MECHANISM FOIi AEROPLANES Filed Aug. 9. 1 929 2 Shets-Sheet 2 "4' m J 9 77, e

. I14 ag 20 1 5169.41 g 1 1a a 9 9 Q 27 256 l \l E: v 1 2a 2f 17 1 I IN VEN TOR.

A TO may be selectively locked by the pilot in Patented Sept. 23, 1930 T NirsD STATES PAT CLEMENT n. KASUBOSKI, or CLINTONVILL SAID CLEMENT B. Knsnnosnr, A MINGR HALF TO. noY n. MORRIS,

nssienonsor ONE- 1 COMBINED BRAKEAND AUxrnrARY Wine MECHANISM non AERoPLnNEs 'Application filed August 3, 1929. Serial No. 384,759;

This invention relates to a combined brake and auxiliary WIIIgIHBChZUHSHI for aeroplanes and has for one of its ob ects to provide, in

a manner as hereinafter set forth, a device 1 of thecharacter aforesaid, by means of which a heavily loaded plane can taker-off from a. comparatively short run-way.

A further object of the invention is to pro vide a device of the character aforesaid by means of which an aeroplane of any type whichzis equipped with the device can more quickly gain altitude and can gain a higher altitude.

A further object of-the invention is to provide a device of the character means of which-the speed of a plane when gliding can be materially reduced, thereby facilitating the landing of a plane in a field of small area. Y

A further object of the invention is toprovide a device. of the character aforesaid by means of Which'a plane can be brought to a stop in a relatively short distance after touching the ground.

A further object of the invention is to pro vide a device of the character aforesaid which may be used as a brake when desired to check plane, and which, in such use,

the speed of a gradual apple automatically provides for the cation of the brake. I

Afurther object of the invention is'to pro-' vide a device of the character aforesaid which position to act as a brake, or in a position to aid the wings in lifting aplane, or in a neutral position. to permit the plane to function as though it were not equippedwiththe de vice.

ment of the invention, but it is to be understood that such description and drawings are to be taken as illustrative and that the invention is intended to be limited only by the scope of the claims hereunto appended.

aforesaid by numeral 1 indicates l/Vith the foregoing and other objects, in View, the invention consists of the novel construction, combination and arrangement of parts as hereinafter more particularly dc Inthe accompanyingdrawings in which ENT KS n, Wisconsin; 1). F. Bnnnn, GuARDIAN OF ANDSAID KASUBOSKI, or oLIn'ronvILLE, WISCONSIN like numerals are employed to designate like it partsthroughout the same: 1 7 V Figure 1 is a front elevation of a monoplane: showinganembodiment of my invention in association therewith; q 1 Figure 2 is a side elevation thereof. 7

Figure 3 is a fragmentary sectional. plan thereof. a l a Figure 4 is an enlarged vertical section taken at a point indicated at line 4-4 of F ure 3. V a

Figure 5 is a section taken online 5-5 of Figure 4.

Figure 6 is a sectiontaken on line 6+6 of Figure 4.

Figure/7 Figure :4. s

Figure 8 is" a fragmentary View similar to Figure 6 showing the unlocked position of the handle member for thelocking mechanism.

Figure 9 is a section taken on line 9-9 of Figure 8. 7

Referring to the drawings in detail, the generally 7 an vaeroplane of the monoplane type having its wing 2 ex tending over the body 3, although it is to-be' understood that my invention may be applied, to an aeroplane of any type desired. Posi+ tioned beneath the wing'2 is a pair of auxil-- iary wing and brake elements 4, one of'which is a section taken on line 77-17 of Figure2 one of the elements 4 is shown in" neutral position, in which position the upper face 5 of the element 4 is flat while the lower face 6 thereof is curved. The leading edge portion 7 of the'element 4 is of materially less thickness than the follower edge portion 8. The element lis preferably of hollow construction and adapted to befilledwith helium gas in order to eliminate any added weight to the plane and toprovide a means for float-1 ing the latter should it be forced to land onv a body of water. i

Extending through each of the elements 4 is a shaft 9', the inner end portion of Which is journaled in a side 10 of the body 3,- and to the outer end of which is pivotally' connected a pair of adjustable struts 11. The struts 11 extend at opposite inclinations and are pivoted at their upper ends to a pairiof breakets 12 secured to the lower face of the wing 2. The inner end portions of the shafts 9 extend through the sides 10 of the body 3 and are inserted within a sleeve 13 upon which is fixedlymounted a ring gear 14. The shafts 9 are adjustably secured to the sleeve 13 to rotate therewith as indicated at 15, and each of the shafts 9 has fixedly secured thereto one of the elements 4. I 7

Extending between the sides 10 of the body 3 is a brace 16, through which extends a shaft 17 which is provided on its forward end with a worm 18in mesh with the ring gear 14. The rearward end portion of the shaft 17 extends through a sleeve 19 which extends through and is fixedly secured to the instrument board 20 of the plane. The sleeve 19 further extends through and is fixedly secured to a panel brace 21 which is preferably diamond shaped and which is secured to the instrument board 20. I The rearward end of the shaft 17 projects from the sleeve 19 and is provided with a crank 22 having a handle member 23. Fixedly mounted on the shaft 17 is a gear 24, which is in mesh with a similar gear 25 fixedly mounted on a stub-shaft 26 rotatably mounted within a sleeve 27 which extends through and is fixedly secured to the instrument board 20 and panel brace 21. The stubshaft 26 extends into'a dial casing indicated generally by the numeral 28 which is mounted on the sleeve 19 by means of a clamp 29. Fixedly mounted on the'stub-shaft26 is a gear 30 which is disposed within the casing 28 and which'is in mesh with a dial gear 31 r0- tatably mounted within the casing 28. The outer face 32 of the casing 28 is provided with an opening 33 in order that suitable indicia on the outer face of the dial gear 31 may be read when such indicia is brought into alignment with the opening 33. It is essential that he dial gear 31 be provided with suitable indicia to indicate to the pilot the position of the elements 4. .By way of example such indicia is illustrated by an arcuate row of Bs so disposed as to be successively brought into alignment with the opening 33 upon the rotation of the dial gear, and by asimilar row of As arranged in spaced relation to the row row of Be. The row of Bs is designated by the numeral 34 and when visible through the opening 33 indicate to the pilot that the elements 4 are positioned to act as a brake to the plane; The row of As is designated by the numeral 35 and when visible through the opening 33 indicate to the pilot that the elements 4 are positioned at an angle to the direction of motion of the plane in order to aid the wing 2 in lifting the plane. Preferably a legend such as D. M. is interposed between the indicia indicated by the

numerals

34 and 35 on the dial. The legend D. M. is designated bythe numeral 36 and when visiible throughthe opening 33 indicates to the pilot that the elements 4 are disposed edgewise in the direction of motion of the plane, in which position the elements 4 have no effect on the operation of the plane. Y

Preferably the indicia designated by the numeral 34 has associated therewith'spaced legends such as On, and A, to indicate to the pilot whether the elements 4 are in full braking position or in partially braking position. Preferably a row of suc- 'cessive numerals is associated with the indicia designated by the numeral 35 in order to indicate to the pilot the extent of the angle between the elements 4 and the direction of motion of the plane. In Figure 4 one of the elements 4 is illustrated in full braking position and in Figure 5, the legend B on is visible through the opening 33 which indicates to the pilot that the elements 4 are in full braking position. An elongated stop 37 projects from the inner face of thedial gear 31 for coaction with a stop 38 projecting inwardly from the rear wall of the casing 28 in order to limit the rotating movement of the dial gear 31 in opposite directions. The stop 37 is so arranged with respect to the

indicia

34 and 35 and to the stop 38 that the extreme limit of movement of the dial gear 31in one direction will bring the legend B on in alignment with the opening 33 while the extreme movement of the dial gear 31 in the opposite direction will bring the highest unit of measure ofthe angle between the elements 4 and the direction of motion of the plane into alignment with the opening 33.

Fixedly mounted on the shaft 17, forwardly of the brace 16, is a disk 40 which is provided with an annular row of perforations 41. Secured to the brace 16 is a U-shaped bracket 42 through which a rod 43 slidably extends. The rod 43 further extends through the brace 16 and projects therebeyond for selective engagement with the perforations 41 on the disk 40. Encircling the rod 43 is a coiled spring 44, the respective ends of which abut against the inner face of the bracket 42 and a stop 45 fixedly secured to the shaft 43.

Extending through the instrument board 20 and panel brace 21 and fixedly secured thereto is a sleeve 46 which is formed with a longitudinally extending opening 47 substantially oval in cross section. Slidably mounted within the sleeve 46 is a'plunger 48, the shape of which in cross section corresponds to the shape of the opening 47 and which is connected by means of a connecting rod 49 with the rod 43. Extending into the sleeve 46 is a plunger 50, the cross sectional shape of which corresponds to that of the plunger 48 and which is connected with the plunger 48 by means of a threaded stem 51. The plunger 50 loosely engages the stem 51 in order that the same may be rotated with respect thereto. The rearward end of the plunger 50 projects from the panel brace 21 and formed on such projecting end is a hantained against movement by the operationof the handle 23 of the crank 22. 1

If it'is desired to rotate theshaft 17, the rod 43 may be withdrawn from engagement with the disk 40 by exerting a rearward pull on the handle member 52 and may be locked against the action of the spring 44 by rotating the plunger 50 a quarter turn when the plunger 50 clears the sleeve 46. In this position the greater cross sectionaldimension of the plunger 50 will be disposed at a right angle to the greater dimension of the opening 47 whereby the plunger 5O will be prevented from entering the opening 47.

When it is desired to adjust the positions of the elements 4, this may be accomplished by releasing the rod 43 from engagement with the disk 40 as heretofore described. then rotating the shaft 17 by means of the handle,

member 23. The rotation. of the shaft 17 also causes the dial-gear 31. to rotate and when the indicia indicated by the numeral 35 is brought into a position to be visible through the opening 33, the elements 4 will be set to. aid the wing 2 to lift the plane. In this position of the elements 4, the latter may be used also to check the speed of a plane when gliding towards a landing field.

It is not necessary that the speed of the plane be checked when gliding towards a landing field, as the elements 4 may be set in neutral position and the plane brought down in the usual manner if desired. I11 either case, the plane may be brought to a stop in a relatively short distance after its wheels touch the ground by rotating the shaft 17 in a direction to turn the elements 4 into braking position. Owing to the resistance of the air against the elements 4, a gradual tilting of the latter into braking position is assured regardless of the abrupt-ness of the operation of the handle member 23 by the pilot.

It is thought that the many advantages of a mechanism in accordance with this invention will be readily apparent, and although the preferred embodiment of the invention is as illustrated and described, it is to be understood that various changes may be made in the size, shape and arrangement of parts, so

long as such changes fall within the scope of the invention as defined in the appended claims.

What I claim is:

1. An attachment for aeroplanes comprising, a combined brake and auxiliary wing element, means for tiltably mounting said element on a plane, means for selectively tilting said element at an acute angle to the direction of motiono'f the plane to aid .in lifting thelatter and at a right angle to the direction of motion to'cheok the speed of the plane, a locking mechanism to maintain said element in.-- selected positions, a rotatable dial operatively connected with the means for tilting the combined brake and auxiliary Wing element and having arcuate rows of indicia thereon, and a casing for said dial, said casinghaving an opening through which successive portions of said indicia are visible when the dial is rotated.

2. An attachment for aeroplanes comprising, a combined brake and auxiliary wing element, a rotatable shaft for tiltably mountingsaid element on a plane, an operating shaft operatively connected with the first named shaft-to provide forthe rotation of theslatter, means for rotating. said operating shaft in opposite directions to selectively tilt said element at an acute angle to the direction of motion of'the plane to aid in lifting the latter and at a right angle to the direction of I110i3l0111l10 check the speed of. the plane, a locking mechanism to maintain said element in selected position, a rotatabledial operatively. connected with said operating shaft and having arcuate rows of indicia thereon, and a casing for the dial, said casing having an opening through which successive portions of said indicia are visible when the dial 'iswrotated.

3. An attachment for aeroplanes'comprising, a combined brake. and auxiliarywing element, a rotatable shaft for tiltably mounting said element on a plane, an operating shaft operatively connected with the first named shaft to provide for the rotation of the latter, means for rotating said operating shaft in opposite directions to selective-- ly tilt said element at an acute angle to the direction of motion of the plane to aid in lifting the latter and at a right angle to the direction of motion to check the speed. of the plane, a perforated disk fixedly mounted on the operating shaft, a spring actuated rod for selectively engaging the perforations in said disk, and means for selectively locking said rod in engagement and out of engagement with said disk.

4. An attachment for aeroplanes comprising, a combined brake and auxiliary wing element, a rotatable shaft for tiltably 1 mounting said element on a plane, an operating shaft operatively connected with the first named shaft to provide for the rotation of the latter, means for rotating said operating shaft in opposite directions to selectively tiltsaid element at an acute angle to the direction of motion of the plane to aid in lifting the latter and at a right angle to the direction of motion to check the speed of the plane, a perforated disk fixedly mounted on the operating shaft, a spring actuated rod for selectively engaging the perforations in said disk, a stationary sleeve having a longitudinally-extending opening of non-circular cross section, a plunger 5 slidablein said opening and'corresponding thereto in cross sectional shape, means rotatable With respect to said plunger for connecting it with said rod, and a handle member for-Withdrawing said plunger from said sleeve.

5. An attachment for aeroplanes comprising, a combined brake and auxiliary Wing element, means for tiltably'mountingsaid element on a plane, means for selectively tilting said element at an acute angle to the direction of motion of the plane to aid in lifting the latter and at a right angle to the direction of motion to check the speed of the plane, a locking mechanism to maintain said element in selected positions, a rotatable dial operatively connected with the means for tilting the combined brake and auxiliary wing element and having arcuate rows of indicia thereon, a casing for said dial, said casing having an opening through Which successive portions of said indicia are visible When the dial is rotated, a stop projecting from the dial, and a stop provided on the casing and projecting into the path of travel of the stop projecting from the dial to limit the rotative movement of the latter in opposite directions.

Intestimony whereof, I aifix my signature hereto.

g IOLEMEN' I B. KASUBOSKI.