US1284851A - Aeroplane. - Google Patents

Description

1. ASHWURTH.

AEROPLANE.

APPUCATION men ma. 18,. m17.

Patented Nov. 12, N18.

2 SHEETS-SHEET 1.

.Y @t LQ N5 /NVf/VTR w J. ASHWORTH.

AEHUPLANI.

APPLICATION FILED Aue le xsl? Patented Nov. l2, 1918 2 SHEETS-SHEET 2- UNITED .sTATEs PATENT oEEIoE. i

JOHN ASHWORTH, OF TORONTO, ONTARIO, CANADA.

AEROPLANE.

Application led August 18. 1917.

To all whom it may conce/m:

Be it known that I, JoHN Asiiwon'rn, of the city of Toronto, in the county of York, in the province of Ontario. Canada. have invented certain new and useful Improvements in Aeroplmies, of which the following is the specification. Q

M v invention relates to improvements in aeroplanes and the object of the invention is to provide an aeroplane having aV maximum active or movable flying surface, and a small passito or stationary surface, in which the angle of incidence oli' the plaines forming the aetive iyingr surface may be altered so that the direction of the slip stream and the resultant pressure may be directed either forward, imekward, downwnrd or upward. Automatic lateral stability is cansedby the equalization of pressures on the planes added to the gyroseopie effect of the rapidly7 rotating masses of the planes, in which automatic longitudinal stability'is provided, in which the steering 'muy be ellected b v adjnsiinent of the planes without the employment of n rudder or warp nnd b v which great weights can be carried at low speed and light weights at high speed and it consists essentially of the followingl arrangement and construction of parts as hereinafter more partieularlfyT eX- plained.

Figure 1. is a general of my aeroplane.

Fig. 2, is a side diagran'imatie elevation of one of the planes showingr approximately perspective view the various positions the plane assumes during one revolution ofits rotation.`

Fig. 3 is, an enlarged longitudinal section intermediately broken away of the. main portion of the mechanism forl adjusting the planes.

In the drawings like letters of reference indicate corresponding parts 'in the various figures.

1 indicates a central shaft, which is mounted in bearingr ortions 2 formed in the tubular shaft 3. 'libe central shaft 1 is divided into two members 1 and. 5 provided at their inner ends with bevel pinions 6 and 7 located in close proximity one to the other.

8 and 9 indicate tubular shafts mounted Specification of Letters Patent.

Patented Nov. 12, 1918.

Serial No. 186,986.

upon the tubular shaft 3. The iniier`ends ot' the shafts 8 :1nd 9 are provided with bevel gears l() and 11. 1Q indicates an oritiee formed in the lower peripheral p01 tion of the tubular shaft Il opposite the divided ends of the shaft members 4 and 5. 13 indicates a hanging shaft provided at its upper end with a bevel pin'ion 14 hanging in .mesh with the bevel pinions G and 7.

15 indicates a bevel gear also secured to the suspended shaft 13 and meshing Withi the. lower peripheral portions oi the gears 10 and l1. 1 indicates n gear easing suspended from the shalt 13 and 17 indicates n bevel pinion seeunnd to the lower end of the shaft 13 and l located within the casing. 18 indicates a steering shaft provided with a steering wheel 19 at. its outer end and a. bevel pinion .20 at its inner end meshing with the bevel pinion 17.

It will thus be seen that when the steering handle 1S) is turned in the direction of arrow (see Fig. l) that the shaft member l will be turned in the direction of arrow und the tubular shaft 8 turned in the Oppo .site direction to arrow and in the opposite direction to the shaft member 4. Simultaneously with this operation the shaftmernber 5 is turned in the opposite direction to the shaft member i and the tubular shaft 9 inthe opposite direction to the tubular shaft 8. When the steering Wheel 19 is lturned in the opposite direction of arrow the direction of rotation of4 the shaft members 4 and 5 and tubular shafts 8 and 9 is reversed.

21 indicates the body ofthe aeroplane,

swung upon the tubular shafts 8 and' beinr 9. y this means no metter in what direction the aeroplane is moving the body of the aeroplane is held in a horizontal" position suspended from the operative portions of the. plane. 4

.The tubular shaftS is provided with sprocket gears 82 and 8s at one end and sprocket, fears 8* and 8 at the opposite end. Thehubular shaft 9 is provided with .shaft 36 an mounted a. sprocket sprocket gears 9 and 92 at one end and spocket gears 9 and 9 at the opposite en 26 and 27 indicate arms extending dia inetrically from the tubular shaft 8 and provided interinediately of their len th with sleeve like portion 29 and 29x wiich are freely mounted uplin the shaft. 8 in prox imity to each end thereof. The sleeve portion 29t is provided with a gear 30 formed` integral therewith or rigidly secured thereto. l

firmly to them are placed similar shafts 39 :md 40. In (proximity to each end4 ofthe revolving thereon is freely"` to each end of the aft 37 and revolving thereon is freely mounted a s rocket ar 42 and in proximit to each en of the s aft 39 and revolving tliereon is freely mounted a sprocket gear 43 and in proximit to each end of the shaft 40 'and revolving thereon is v freely mounted a sprocket ear '44.

indicates a sprocket c, ain connecting each of the sprocket .sgears 41 respectively to the sprocket gears 5 and 8*. 46 indicate sproc (et chains connecting each of the gears y 37 respectively A`to theV spirocket gears 83 and' 8. 47 indicates a sproc et chain connecting each of the sprocket gears 43 respectively to the sprocket gears 91 and 9 and 48 indicates a sprocket vchain connecting each of the sprocket gears 44 respectively to the sprocket.k

- gears 92. and 9*.

,tend thereby swingilbly 4 supporting 49, 59, 51 and 52 indicate cainbered lanes. Each of the planes is provided with ugs 53 preferably located in proximity to each end thereof and through which the respective shafts 36,-37, 39, and 40 freely elixit e plane in position. order to resi ntly old the plane in its truc position each of the gears 41,` .42 48 and 44 is rovided with inwardly extendin pins (see ig. 2) 54 and 55.- To the pin `4 is secured two spiral springs 56 and 57 and to the pin 55 is secured two spiral springs 58 and 59. The springs 58 and 59 are secured to the lower face of the plane, and the springs 56 and 57 to the upper face of the plane.

When the plane is in th normal orhorizontal position such as shown byfull lines in Fig. 2 the springs 57 and 58 are under tension and the s'prings56 and 59 are under compression.

(SO and 61 'indicate supplemental planes 5pm' 41. In proximityrigidly secured to the ends'A of the divided members 4 und 5 of the central shaft l. 62 indicates the driving engine, the shaft 63 of which is provided at its ends with sprocketgears 64 and 65 connected by sprocket chains (i6 and 67 to the sprocket ears 30 and 33* mounted upon the sleeve ike poi-lions 3() and 34.

The aeroplane body is provided with axles 68 and 69 to which the lower ends of the inverted V-shaped hangers 22 and 23 are connected, the ends of the axles being provided with carrying wheels 68x and 69c of usual construction.

Having described the princi al parts involved in my invention I wil brieiiy describe the operation of the saine.

When the en ine shaft 63 is thrown into gear the sproc ets 30 and 33x are driven rom such engine shaft thereby rotating the arms 26 and 27, 31 and 32 mounted upon the tubular shafts 8 and 9 thereby carrying the planes-49, 50, 51 and 52 tlirou li a circular ath. The travel of each of t `e lanes 49, .0, E51 and 52 is approximately illustrated in Fig. 2.

It will thus be seen that as the plane travels forwardly in the direction of arrow and downwardly the sprin s 59 and 56 are held in compression until a er the osition C is assed when the spring 59 gra ually passes rom compression into tension, the spring 57 from tension into compression, the spring 56 from compression intotension and the spring 58 from tension into compression, t is action being produced by the rearward swing of the plane during its circular travel producing a pressure upon the back of the plane so as to swin it toward a vertical position, which position is indicated by dotted lines at A (Fig. 2*). As the plane gasses ii wardly from position A to position the p ane assumespractically a vertical position further com ressing the springs 57 and 58 and further rawing the springs 56 and 59 into tension.

As the plane travels forward and upward from position B it reverts rapidl back to norma osition4 shown by dottedy lines in Fig. 2, t e compression on the back of the plane being overcome by the pressure a ainst the lower side. The pressure on the ower face of the plane is directed downwardly and forwardly upon ythe air to produce a sustaining and propelling force while the resistance to the backward and'upward movement also upon their forward and downward movement will swing into such a position during part of their backward and upward morement as to experience little resistance ex cept friction.. I

The revolution of the planes creates a` resultant pressure in` one direction depending upon the angle of incidence of thc planes. By altering the angle of incidencey the pres- Snre may he exerted in an upward. fm'werd3 downward or backward or in any intermedia-te direction.

During Hight the planes act as supporting as Well as propelling members.

When it is desired to alter the angle of incidence ot the planes` so as to direct. the path of travel inan upward or downward inclined direction all that it is necessary to do is4 to force the sering handle 19 either forward or backwand longitudinally, of the body of the aeroplane thereby rotating the gears 10 and 11 by the interi'nesliing gear 15 carried by the shaft 13 in the sanne di.a rection and thereby through the gears 82, 8", and 85 and 9', 92, 95 and 9* and sprocket chains 45. 15:6` 47 and 48 rotate the e'eaxe 41 and 42, 43 and t4 thus causing the pianes 49.

0, 51 and 52 to rotate about their respective Shafts 36`y 3T, 39 and 40 and varying their angles of incidence to any desired extent.

lf it is desired to turn the plane in a curved path the shaft 13 is turned by means of the Steering shaft 18 and Steering wheel 19 so that the gears 10 and 11 are turned in opposite directions and thereby turning the gears 82; 83. 8t and 8 in one direction and the gears 9Y 92. 9 and 9* in the opposite di reetion ond thereby through the aforementioned Sprocket gear increasing the angle of incidence of the planes 49 and 50 and de` creasing the angle, of incidence of the planes 5() and 5l or rire Verna thereby increasing the forward propnlsive force on one side ol the machilnl and decreaeing it upon the other thus causing the one side to liy faster than the other so that a` turning` movement in produced.

To facilitate this movement and to connteraet the tendency of the retarded planes to rise I have provided supplemental planesl or ailerons 6l. The angle of ineidt-nec of these isiehanged simultaneously with the operi:1 tion of changingr the :ingle of incidence of the main planes but `in :in opposite direction to the direction oi' thc main plane so thnt on that side of the machine on which the angle of incidence of the main plnneniie` inrrensed the angle oi' incidence of the corresponding aileron is der-remoti and on the oppoe-ite, side of the machine. where the angle ol incidence olr the main planes1 derreaeed. the angle nl' iin-idoneiof the rorrrslnnnling aileron is inferir-led.

It will also he seenthat the longitudinal sti bility of the hody of the aeroplane is ontomatically maintained `by reason of the body heine suspended niovably` from a tubular Shaft and the conter ot gravity shifted backward or forward an the angle of incidence of the planes in changed, eo that no matter in what direction the propelling torce is carrying the machine the holly always hangs in the sinne directioin heilig; always held in a horizontal position and cannot he moved longitudinally ont of noch horizontal noniion hy any alteration in the course oli the lane.

lt 1will ale-o he seen. from the above denrription that hy altering the :ingle of incidence of the planes comprising the flying surf-are the direction ot the Slip Stream is changed so that the resultant pressure may he directed either forward, backward. downward or upward. This gives; the greatest possible speed Variation trono nothing to the highest speed attainable enabling the aeroplane lo rise practically perpendienlerly, lo hover over n given point to go forward at the higheei poeeihle speed to reverse the direction of progress and to descend perpendicnlarly and. therefore,y the danger of :ilighting on rough ground or ai` night is to a great extent oliviated.

lt will al o he seen that owing to the hei'ei gear connection lo hetnet-n the supple` mental tnlnilnr Shafts and it the total pressure on the planen on one side of the, central hotly et any time by reann of andden goeie of wind or otl'ierwise exceeds the total pressure on the plant-2 on the other side of the central body then the pull on the Sprocket chains actingr tlirougfh the bevel gear will canse the angle of incidence ot the planes haring greater pressure to he red need and the angle ot incif'lenco of the other planes to he eorrefqiondingrly increased until the preeenrea are eqnal on each sider` thus providing' automatic lateral Stability. Added to thie` ie ilre gyroseopic effect. of the masses of the rapidliT rotating planen about the central `Qhatt.

It will nlso he noticed that in the event of stoppage of engine all the plane?i will et once assume a horizontnl position automatically hy reneon of the air preferire on the ander surface and the aeroplane as a Whole will come to the ground ninch as a parachute. Uni-ing the iii-nennt the :ingle of incidence of the plane-1 een he changed as de- Hired.

What l claim as; my invention in:

l, An neroiiane con'lprifliing a centrnl holly and pinnen ircnteil at euch side of noch holly. menne. for revolving' the planes whole nhont a common trannre' horiz-foin tal axie. menne For retaining: the noi-:l planes; at any deeired anglo oi incidence with the lniriscontal. end :i Single menne whereby the angle of incidence of the planes may be adjusted in the same direction or the angle of incidence on one side of the machine changed in one direction and the angle of incidence of the plane on the opposite side of the machine changed in the opposite di rection.

An aeroplane comprising a central. body and planes located at each side of such body, means for revolvingr the planes as a whole about a connnon transverse horizontal axis, means for retaining the said planes at any desired angle ofincidence with the horizontal, means for adjusting the angle of incidence of the planes on one side of the machine in one direction and the angle of incidence of the planes on the opposite side of the machine in the opposite direc tion, and means for counteracting the lifting or depressingr action of the planes due to reversing the direction of the angle of incidence of the planes on each side of the cen tel' of the machine.

3. In an aeroplane, a main support,I an aeroplane body carried by the su port intermcdiately of its length, in e endent planes located upon each side of t e body on opposite sides of the supporting inember, a steering shaft locate in the center of the supporting member, and a shaft swingably mounted at its 'up er end and mechanism connecting the s aft to the planes whereby the backward and forward swing of the shaft alters the angle of inc dence in the same direction on both sides of the machine.

4. In an aeroplane, a main support, an aeroplane body carried by the support intermediately of its length, independent planes located on each side of the bodyY on opposite sides of the supporting member, a`

steering shaft swingably mounted at its npper end at the center of the supporting member, and means operated by the turning moveemnt of the shaft for increasing the glo of incidence of said planes on one side of the machine in one direction and decreasing the angle of incidence on the opposite side of the machine in the opposite direction, and means for rotating the planes around the main support.

5. In an aeroplane, a main support, an aeroplane body carried b v the support intermediately of its length,` independent, planes located on each side of the body on opposite sides of the supporting member, a shaft, swingably mounted at its upper end at. the center of the supporting member, mechanism operated thereby for simultaneously adjusting the angle of incidence of the planes on both sides of the machine, an aileron also carried by the supporting member at cach side of the center of the machine, and means operated by the swingably mounted shaft.

tation of the swingably mounted shaft on its own axis.

6. An aeroplane comprising a tubular shaft, au aeroplane body suspended from the shaft interniediately of its length, a pair of diametrically extending arms revoiubly mounted upon the tubular shaft, intermediately of their length, planes swingably carried upon the ends of the arms, resilient means for yieldably holding vthe planes in position, means for revolving the arms around the tubular shaft, a supplementalvtubular shaft carried by the aforesaid. tubular shaft on each side of the center of the machine, a sprocket gear connection between the supplemental tubular shaft and each of the planes, a stecrin shaft located above the body of the aerop ane, and means operated b v the turning of the shaft for rotating the supplemental tubular shaft to adjust the angle of incidence of the planes.

7. An aeroplane comprising a tubular shaft, an aeroplane bodv suspended from the shaft interinediately of its length, a pair of diametrically extending arms revolubly mounted upon the tubular shaft intermediately of their length` planes swingably curried upon the ends of the arms, resilient means for .vieldubly holdingr the planes in position? means for revolving the arms around the tubular shaft., a supplemental tubular shift carried bv the aforesaid tubular shaft on each side o the center of the machine, a sprocket gear connection between the. supplemental tubular shaft and each of the lanes, a steering shaft located above the indy of the aeroplane, and means operated by the movement of the steering shaft for turning the. supplemental tubular shafts either in the same direction or in opposite directions.

8. An aeroplane comprising a tubular shaft. an aeroplane body suspended from the shaft intermediatehr of its length, a pair of dametrically extending ,arms revolubly mounted upon the tabular shaft intermediately of their length, )lanes swingably carried upon the ends of the arms, resilient means for yieldebly holding the planes in position, means for revolving the arms around the tubular shaft, a supplemental tubular shaft carried by the aforesaid tubular shaft on each side of the center of the machine, a Sprocket gear connection between the supplemental tubular shaft and each of the planes, a steering shaft located above the body of the aeroplane, means o erated by the movement of the steering sha t for turning the supplemental tubular shafts either in the samedxrection or in opposite directions,

afsl

shaft members carried within the tubu'ar rons are turned in the opposite directions to shafts, ailerons carried at the outer ends of the corresponding shaftsil and planes oper' the shaft members, and means operated by ated from such tubular s afts.

the steering shaft whereby when the sup- JOHN ASHWORTH. 5 plemental tubular shafts are turned in oppo- Witnesses;

site directions to change the angle of inci- M. EGAN,

dence of the planes Vthe corresponding aile- H. LUCE.

Images