US1938171A - Aeroplane - Google Patents

Description

Dec. 5, 1933, A. A. BRALEY 1,938,171

AEROPLANE Filed Jan. 29, 1952 Patented Dec. 1933 UNITED STA-'ras PATENT OFFICE 5 Claims. (Cl. 244-14) The present invention relates to aeroplanes, and speciflcally to that type of aeroplane capable of vertical lift or hovering.

I am aware that an enormous amount of work 5 has been done in the put in an attempt to produce aeroplanes of the conventional type requiring a preliminary run along the ground before rising, particularly in attempt to make them safer to operate. Considerable work has also been l done in attempting to produce satisfactory aeroplanes of the conventional vertical lift type. Of the vertical lift type of aeroplanes there are two distinct groups, namely, those depending upon the use of a vertically directed propeller, and those l depending upon the use ofv opposing propellers which are so arranged in relation to iixed wings, as shown for instance in United States Patent No. 1,368,891, thata downwardly directed blast of air acts to lift the aeroplane in a vertical direction. The present invention relates to the lat- Lter type of vertical lift aeroplane in that such lift is derived through the reaction of the air (deected from its course as defined by the propellers) upon fore and ait adjustable wings and vstabilizing blades especially adapted to that purpose; the propellers meantime rotating about substantially horizontal axes or in approximately vertical planes. This downward reaction of the air may be secured in several ways. The aeroplane wings, for instance, may be pivoted and the wings in consequence given a very large angle of incidence or, if desired, the wings may be heavily cambered and given a iiexible or pivoted trailing edge portion. The result in each instance is identical, i. e. the propelling force realized from the propellers is converted into vertical lift by the deflection of the propeller air blast in an approximate downward direction through its reaction on the biased or deeply cambered wings.

Among the objects of the present invention accordingly is the provision of an aeroplane capable of rising or landing in vertical manner. A further object is the provision of an aeroplane capable of hovering" as well as flying forward, backward, sidewse, or of rotating in a horizontal plane. Further objects and advantages will appearvas the description proceeds. v

To the accomplishment of the foregoing and 0 related ends, the invention, then, consists of the means hereinafter fully described and particularly pointed out inthe claims, the annexed drawing and the following description setting forth in detail certain means for carrying out the invention, such disclosed means illustrating, however,

but one of the various ways in which the principle of the invention may be used.

In said annexed drawing:-

Fig. 1 shows in diagrammatic manner a sectional side elevation of my improved aeroplane; Fig.A 2 is a top view of the aeroplane.

My improved aeroplane, which may take oi or land with a preliminary run in accordance with common practice, is especially well adapted for rising vertically, which would be particularly desirable, for instance, where the starting or landing area was very small. The vertical lift is obtained by means of fore and aft propellers which may be driven so as to produce opposing air blasts which may be directed downwardly by means of fore and aft wings adjustable for that purpose. After the aeroplane has risen a suitable distance above ground, the propellers, wings, and stabilizing blades can be adjusted for forward flight or otherwise as desired.

Referring more particularly to the drawing, a tractor helix 1 or forepropeller is mounted on the front end of the fuselage 2, while an aft propeller 3 is mounted on the rear end thereof. The aeroplane is mounted on ground wheels 4 by 80 means of framework 5 in the usual and well lmown manner.

Adjustable wings are mounted at the fore and aft ends of the fuselage. The fore upper wing 6 extends crosswise of the fuselage, as is shown in Fig. 2. Said upper wing may be pivotally mounted on hinge 'I and framework 8 in conventional manner. Directly below upper wing 6 are mounted two wings 9a and 9b, said wings `preferably being arranged on opposite sides of the aeroplane cabin so as to be freely adjustable up and down alongside thereof about pivot 10. The upper wing 6' and lower wings 9a and 9b are preferably fastened together, for instance, by means of a connecting link mechanism 11 on opposite sides of 95 the aeroplane cabin. This connecting link is to be considered as showing in diagrammatic manner any of the many equvalent ways that the wings can be fastened together so as to work in unison. It is to be noted in this connection that it is not essential that upper wing 6 be fastened to lower wings 9a and 9b since obviously these wings could all be independently operated without departing from the spirit of my invention, and, moreover, the lower wings 9a and 9b may be 105 separately controlled so as to act as stabilizing wings in conventional manner. The fore wings may be tilted in any convenient manner as, for instance, by lever 35 and connecting mechanism 3G, The aft or rear end of the aeroplane in simi- 110 lar manner to the front end thereof is equipped with upper wing 12 preferably pivotally mounted at 13 on fuselage attached framework 14 in conventional manner. Lower wings 15a and 15b are likewise preferably pivotally attached at 16 to the fuselage in such manner that they can be freely adjusted up and down along side the aeroplane cabin, but closely approaching same. Upper wing 12 may be connected to lower wings 15a and 15b by a connecting link mechanism 23 or its equivalent, on opposite sides of the aeroplane cabin, in such manner that they function as described in connection with wings 6, 9a, and 9b. The aft wings may be tilted in any convenient manner as, for instance, by lever 37 and connecting mechanism 38. The aeroplane is further equipped with fore balancing wings or stabilizing blades 17a and 17b. Said stabilizing blades are pivotally mounted respectively on pivot posts 18 and 19, the stabilizing blades preferably being adjustably mounted as shown in the figures, so that they will also serve to extend the reactive lifting area during the rising orl lowering of the aeroplane as well as to function as balancing wings while same is under motion. The stabilizing wing 17a may be controlled by any suitable means such as lever 47, and balancing wing l'lb may be controlled in similar manner. Balancing wings or stabilizing blades 20a and 20h pivotally mounted respectively on pivot posts 21 and 22 act in similar manner at the rear or aft end of the aeroplane as does balancing wings 17a and 17h at the fore end thereof. The aft stabilizing wing 20a may be controlled by any suitable means such as lever 48 and connecting linkage 49. stabilizing wing 20h may be controlled in similar manner.

The fore and aft underfaces and 51, respectively, of the cabin or fuselage 2 are 'preferably built With a fiat or wing-like surface which aids in presenting a greater reactive area for vertical lift and hovering. During forward flight the fore undersurface acts to provide an upward lift component similar to the wings, and at the same time the aft undersurface 51 offers a low resistance to the air flowing past the aeroplane. For high speed flying, the fore and aft undersurfaces of the cabin are preferably constructed with a very gradual inclination to present a minimum Wind resistance, while with slower speed machines especially adapted to hauling freight, etc., the fore and aft underfaces of the cabin are preferably made somewhat steeper to increase the lifting power during all phases of operation.

Fore propeller 1 mounted on shaft 24 is connected by any suitable means, such as by shafts with bevel gears, to motor 25. A clutch 30 mounted on the shaftv connecting motor 2,5 and propeller shaft 24 is operated by means of control lever 31. The aft propeller 3, suitably mounted on shaft 26, is connected to motor 27 by any suitable means, for instance, as by shafts with bevel gears. Between said motor 27 and propeller 3 are interposed any suitable means for reversing the slip stream of the aft propeller, for instance as diagrammatically shown, a clutch 28 and a reversible gear transmission 29, both of which are controlled 'from the pilots seat 52 by means of levers 32 and 33. respectively. To aid in controlling and reversing the rear propeller, a brake 53 controlled by lever 54 is preferably installed between said reversible gear transmission 29 and rear propeller 3. The use of separate motors for driving hthe fore and aft propellers, wherein a reversible transmission is utilized in connection with the aft propeller, permits the propellers to be driven in opposition for taking 0E vertically, hovering, or landing vertically, and at the same time permits them to operate in conjunction for driving the aeroplane forward. While the two motors can be operated independently at all times, the use of a clutch 34 permits them to be connected together for operation at like speed which simplifies the control of the aeroplane while under forward motion.

Fore rudder 39, mounted on pivot post 40, is controlled from the pilots seat 52 by means of controller 41 and a connecting mechanism such as a cable 42. The rear or aft rudder 43, mounted on pivot post 44, is operated by means of controller 45 and a connecting mechanism such as a cable 46.

The operation of the aeroplane is as follows:- the operator seats himself in seat 52, adjusts wings 6, 9a, 9b, 12, 15a, and 15b to the position shown in heavy lines in Fig. 1. The stabilizing or balancing wings 17a, 17h, 20a, and 2Gb are also set as shown by heavy lines in Fig. 1. Motors 25 and 27 are started and clutches 28 and 30 engaged so as to rotate fore propeller or tractor helix 1 in a 100 forward pulling direction and rear propeller 3 in a backward pulling direction. Propellers 1 and 3 are then speeded up so that the flow of air or slip stream is directed respectively against the underfaces of the fore and aft wings, fore and 105 aft stabilizing blades, and fore and aft under faces of the cabin. The slip streams of the two propellers, diverted downwardly by the wing surface etc., produces a vertical lifting component which increases as the propellers are speeded up until this reactive. force exceeds the pull of gravity on the aeroplane. The aeroplane will then rise from the ground in a vertical direction. While rising vertically the aeroplane may be maintained in a substantially 115 horizontal position and in satisfactory ying attitude by manipulating the angle of inclination of the wings and stabilizing blades with or without change in propeller speed. 'I'he aeroplane in any event is quite stable since'its center of gravity 120 is well below the center line of the propellers. After reaching a desired elevation the aeroplane may be caused to hover at that point by slightly slowing down the propellers or decreasing the slope of the wings. It may be caused to fly sidewise by adjusting rudders 39 and 43 slightly in opposite directions, and it may likewise be made to rotate by turning the rudders slightly in the same direction. When it is desired to fly forward the fore propeller or tractor helix 1 is speeded up to start the aeroplane moving in a forward direction, the slope of the fore wings and stabilizing blades being gradually decreased at the same time. Wings 12, 15a, and 15b, as well as stabilizing blades 20a and 2Gb, are then gradu- 1 ally changed to the position shown in dotted lines as the forward speed of the aeroplane increases. The rear propeller 3 is likewise slowed down and by means of brake 53, clutch 28, and reversible transmission 29, controlled respectively 140 by levers 54, 32, and 33. is reversed in its direction of rotation so as to coincide with the direction of pull of fore propeller 1. 'I'he front wings 6, 9a, and 9b are likewise adjusted to the position shown in dotted lines. The aeroplane is then in 145 forward flight wherein all of the wing surface acts to support same, and the stabilizing blades to keep it in balance. It is thus to be seen that there are no parts corresponding, for instance, to

ythe vertically directed propeller nl' an nim-em 1c which acts to produce an undesired wind resistance during forward flight. In'landing vertically the reverse procedure is followed in that the forward flight of the aeroplane is gradually decreased and the wings and rear propeller adjusted to hovering position, following which it is a simple matter to slow up the propellers to a point where the reactive force of the opposed slip streams on the wings and balancing blades is just short of equalling the pull of gravity. The aeroplane will then settle down and land in a vertical direction.

While the present improved aerial apparatus has been described in terms of rising and landing vertically, it is not limited to any such procedure since obviously the wings can be adjusted, for instance, as is shown in dotted lines in Fig. l. Rear propeller 3 can be adjusted to produce a slip stream in the same direction as propeller l, under which conditions the aeroplane can be caused to rise in the conventional manner wherein a preliminary short run is necessary to produce suicient wind reaction on the wings to cause the aeroplane to take on. The aeroplane can likewise land in the conventional manner wherein a short run along the ground precedes the stopping thereof.

Other modes of applying the principle of my invention may be employed instead of the one explained. change being made as regards the mechanism herein disclosed, provided the means stated by any of the following claims or the equivalent of such stated means be employed.

I therefore particularly point out and distinctly claim as my invention:-

1. In an aeroplane, the combination of fore and aft propellers operating in substantially vertical planes, means for reversing the direction of rotation of the aft propeller, means to drive said propellers, adjustable fore and aft wings, each comprising a plurality of superposed separately mounted planes, adjacent but between said propellers, means for adjusting said fore and aft wings from a vertical lift position to a forward ying position, fore and aft balancing Wings on each side of the aeroplane, means for operating said balancing wings, steering means including fore and aft vertically mounted rudders, and means to operate said rudders.

2. In an aeroplane, the combination of fore and aft propellers operating in substantially vertical planes, means for reversing the direction of rotation of the aft propeller, means to drive said propellers, adjustable fore and aft wings, adjacent but between said propellers, means for adjusting said fore and aft wings from a vertical lift position to a forward flying position, fore and aft balancing means, mechanism for operating said balancing means, fore and aft vertically mounted rudders between said propellers, the fore rudder being mounted in the slip stream from the fore propeller and adjacent to said propeller, the aft rudder being mounted in front of the aft propeller and adjacent thereto, said fore and aft rudders being arranged adjacent to said fore and aft adjustable wings in manner permitting free adjustment of either, and means to operate said rudders.

3. In an aeroplane, the combination of a fuselage having fore and aft substantially flat underfaces which slope downward and toward each other at an angle with the horizontal axis of the aeroplane that is substantially greater than the corresponding slope of the fore and aft upperfaces of the fuselage, fore and aft propellers operating substantially perpendicular to the longitudinal axis of the aeroplane, means for reversing the slip stream of the aft propeller, means to drive said propellers, adjustable fore and aft wings, each comprising a plurality of superposed separately mounted planes, adjacent but between said propellers, means for adjusting said fore and aft wings, fore and aft balancing wings on each side of the aeroplane, means for operating said balancing wings, steering means including fore and -a'ft rudders mounted vertically above the fuselage, and means to operate said rudders.

4. In an aeroplane, the combination of a fuselage having fore and aft substantially nat winglike underfaces which slope toward each other at an angle with the horizontal axis of the aeroplane that is substantially greater than that of the fore and aft upperfaces of the fuselage, fore and aft propellers operating substantially perpendicular to the longitudinal axis of the aeroplane, means for reversing the slip stream of the aft propeller, means to drive said propellers, fore and aft wings, each comprising a plurality of superposed separately mounted planes, adjacent but between said propellers, and so mounted that the lower planes form in combination with the substantially at wing-like underfaces of the fuselage, when adjusted to vertical lift position, substantially continuous wings, means for adjusting said wings, fore and aft balancing wings on each side of the aeroplane, means for operating said balancing wings, steering means including fore and aft vertically mounted rudders. and means to operate said rudders.

5. In an aeroplane, the combination of a fuselage having fore and aft wing-like underfaces which slope toward each other at an angle with the horizontal axis of the aeroplane that is substantially greater than that of the fore and aft upper faces of the fuselage, fore and aft propellers operating substantially perpendicular to the longitudinal axis of the aeroplane, means for reversing the slip stream of the aft propeller, means to drive said propellers, fore and aft wings, each comprising a plurality of superposed 4separately mounted planes, adjacent but between said propellers, and so mounted that the lower planes form in combination with the substantially fiat wing-like under faces of the fuselage, when adjusted to vertical lift position, substantially continuous wings, means for adjusting said wings, fore and aft balancing Wings on each side of the aeroplane, means for operating said balancing wings, steering means including fore and aft vertically mounted rudders, the fore rudder being mounted below the fore upper wing and at an elevation above the fore lower wings, the aft rudder being mounted below the aft upper wing and at an elevation above the aft lower Wings, and means to operate said rudders.

ALFRED A. BRALEY.`

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