US1080498A - Airship. - Google Patents

Description

AIRSHIP.

APPLIOAHTION FILED 13150.24. 1912.

Patented Dec. 2, 1913,

5 SHEET S-'SHEET l.

Elttwwq B. F. STONER, DECD.

n. v. sToNBR, .ADMINIBTRATRIL AIRSH'IP. APPLIUATION riLnD 1320.24, 1912.

1,080,498, Patented Dec. 2, 1913.

5 SHEETS-SHEET 2.

B. F. STONER, DEGD.

lE. V. STONER, ADMINISTRATRIX. AIRSHIP,

APPLICATION FILED DBU. 24, 1912.

Patented Dec. 2, 1913.

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53 ff d... CJMM d? B. F. STONER, DECD.

E. v. sToNBR, ADMINISTRATRIX.

AIRSHIP.

APPLIUATION Yum) DB0. 24, 1912.

1,080,498, y Patented Dec. 2., 1913.

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glwuafntoz B. F. STONER, DECD. 1m v. sToNER, ADMINISTRATRIX.

AIRSHIP.

APPLIGATION FILED 13,110.24, 1my

1,080,498. Patented Dec. 2, 1913.

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BENJAMIN FRANK STONER,

OF NEWARK, NEW JERSEY; ELLA V. STONER, ADMINIS- TBATRIX F SAID BENJAMIN F. STONER, DECEASED.

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Specification of Letters Patent.

latented Dee. 2,1913.

Application tiled December 24, 1912. Serial No. 738.444.

To all whom it may concern:

Beit known that I, BENJAMIN F. SroNnR, citizen of the United States, and resident of Newark, in the county of Essex and State of New Jersey, have invented certain new and useful improvements in Airships, of which the following is a specification.

rlhis invention relates to flying machines of the heavier-than-air class, and particularly to a machine combining the flying supported by principles of the aeroplane and orthopter, the object of the invention being to provide a combination machine of this type in which the gliding and iiapping surfaces act in a synchronized manner to give great supporting and flying efiiciency.`

A further object of the invention is to provide a machine which is inherently stable and otherwise capable of being safely oper ated, and which is adapted to be easily and sensitively controlled by the airman.

The invention consists of the features of construction, combination and arrangement of parts hereinafter fully described and claimed, reference being had to the accompanying drawings, in which Figure 1 is a top plan view of a fiying machine constructed in accordance with my invention. Fig. 2 is a side elevation of the machine. Fig. 3 is a-front elevation thereof. Fig. 4 is a vertical longitudinal section. Fig. 5 is a sectional plan view on the line 5--5 of Fig. 4. Fig. 6 is a vertical transverse section on the line 6-6 of Fig. 4. Fig. 7 is an enlarged sectional .view through one of the parachutes and its controlling means and showing the parachute spread for action.

In carrying my invention into practice, I provide a boat-shaped car 1, preferably of streamline form, and provided with a stabilizing tail piece 2. This car is supported by a main frame 3, which extends above and below the car and which supports front and rear launching and landing wheels 4, journaled in suitable bearing brackets the framework. Within the car are arranged the aviators seat 5, a pair of driving motors 6 and 7, and a steering shaft 8 provided with a hand wheel 9 disosed in proximity to the aviators seat.

he car may also contain the fuel carrying tanks, one or more passenger seats, and other parts of the equipment.

The main frame carries a gliding surface in the nature of an aeroplane of substan tially cruciform shape, and presenting headand tail portions 10 and 11 extending parallel with the line of flight and wings 12 and 13 projecting laterally in opposite directions at right angles to the line of Hight, the machine as thus constructed being adapted when propelled through the air to sustain itself after the principle of machines of the gliding type.

Arranged beneath the lateral projecting wings 12 and 13 of the aeroplane surface are laterally projecting wings 14 and 15, of bird-like contour, each of which wings preferably consists of a framework having a covering of fabric or other suitable material and including a longitudinal rod or shaft 16 reinforced from the frame proper by braces 17 and provided at its inner end with a ball or spherical member 18 journaled in the bearing socket 19. The two wings 14 and are thus universally jointed to the framework to swing or flap in a vertical plane and to tilt or swing vertically to a certain degree on a transverse axis, so that in operation they may closely simulate the action of the wings of flapping birds. It is found that this mode of operation of the wings 14 and 15 and their described relationship to the wings 12 and 13 of the cruciform aeroplane surface gives what may be called a synchronized action in the way of a dual supporting effect, whereby a struc ture of great carrying and iiying efficiency is produced.

The wings 14 and 15 carry eccentric straps 20, connected therewith by link rods 21, which eccentric straps coperate with eccentrics 22 upon the opposite ends of a horizon tal transversely extending shaft 23 journaled in the upper portion of the main frame, whereby in the rotation of said shaft the wings will be simultaneously and alternately swung upward and downward on their universal joints and at the same time permitted to rock to a certain degree in a fore and aft direction to give a pounding action on the air, whereby an aerodynamical supporting effect is obtained. The shaft 23 is driven by a sprocket chain 24 from the front motor 6, which chain passes around sprocket wheels 25 and 26 on the shaft 23 and the shaft of the motor, respectively.

A. forward driving or propelling action is preferably secured by the use of a propeller 27 mounted in rear of the tail piece 2 upon a longitudinally extending shaft 28 driven by the rear motor 29, the action of the propeller` 27 driving the machine ahead at a proper speed for a. guiding support through the medium of the aeroplane surface, while the action ofthe wings 14 and 15 at the Sametime gives a sustaining and driving impulse.

The aeroplane surfaces 10 and l1 are provided with openings 30 in which are arranged front and rear horizontal rudders, elevators or altitude planes 31 and 32, which arey respectively mounted to tilt vertically on horizontal transverse shafts 33 and These rudders are connected at their forward edges by links 35 to the upper arms of bell crank levers 36, the lower arms of which are coupled by links 37 to controlling levers 38, one for each elevator or altitudeplane,

ywhereby said elevators or altitude planes may be simultaneously adjusted by simultaneous manipulation of thelevers or independently adjusted by independent manipulation of the levers to steer the machine vertically or balance it sensitively upon its transverse axis7 the shape of the aeroplane surface and action of the flapping wings giving inherent lateral stability without the use of lateral balancing means, although such may be employed if desired. Arranged beneath the tail portion of the car is a vertical rudder lin 39 linged or pivoted at its upper edge to swing laterally on a longitudinal axis, which rudder fm is coupled by connections 40 to the control shaft 8, whereby it may be adjusted laterally at an angle to the line of flight in either direction to steer the machine laterally. This rudder fin may also be employed as a lateral balancing medium, and automatically operates to prevent skidding of the machine and to hold it against side draft in an intended line of flight.

A stability vane 39 may be provided and located below the body of the car. This vane is supported by suitably guided rack bars 40 meshing with pinions 39a on a shaft 40a connected by gears 40b with a vertical control shaft 40c disposed in proximity to the a viators seat and having an operating crank, whereby the vane may be raised and lowered.

The machine is preferably provided with one or more parachutes in order to insure safety in the event ofthe collapse of a portion of the machine structure or the failure of the motive power, especially under conditions where a gliding landing cannot be' made. 1n the present instance the use of two parachutes is disclosed, each of which conslsts of an upwardly extending rod or stai" 41 supporting a collapsible umbrella-shapedparachute 42, said staffs being preferably disposed one .in rear of the other and reinforced by a suitable connecting stay 43. The frame of each collapsible parachute includes stretchers 44 secured 'to a collar 45 ixed to the upper end of a sleeve 46 slidably mount.- cd on the staff, which sleeve is also provided at its lower end with a collar 47 connected by links 48 with one arm of a bell crank lever 49, the opposite arm of which is conf pled to a controlling lever 50. As shown the levers 38 and 50 are preferably mounted on a common fulcrum 51, and each is provided with a spring actuated dog or latch 52 for engagement with a toothed segment 53, whereby it may be locked in adjusted position. I

The sleeve 4G of each parachute is slidable. in a guide 54 and is adapted to be projected by the expansive action of a coil spring 55, which is normally held compressed when the parachute is collapsed and is adapted when released to project the sleeve upward and spread the parachute to open position. Chains or other flexible connections 56 connect the lower edges of the body of the parachute to the main frame or aeroplane surface, to limit the opening movement of said parachute and to stay it against the pressure of the air when in action.. lt will be observed that the paraehutcs may be normally held collapsed, to reduce their resistance to flight, and that they may be released at any time for' automatic opening movement to support the machine in its descent and adapt it to land safely.

From the foregoing description, taken in connection with the drawings, the construction and mode of use of my improved flying machine will be readily understood, and it will be seen that the invention provides a flying machine which, in an effective manner, combines the supporting principles of the aeroplane and helicopter, enabling a reliable and eiiicient supporting action to be obtained, and that, in addition to the other safety factors mentioned, such use of the two types of supporting surfaces disclosed gives greater security, as in the event of injury to the one the other will operate to sustain and maintain the machine in flight.

1t will, of course, be understood that the machine may be provided with a hydroplane surface of a suitable character for use on water as well as on land.

1 claim A 1. A flying machine including a main frame, a boat shaped car carried thereby and having an attenuated tail portion provided with a transverse portion carrying a transverse tail piece, an aeroplane surface of substantially cruciform shape supported by the frame, said surface presenting head and tail portions and transverse wing portions, flapping wings universally jointed to the frame and arranged beneath the transverse wing portions of the aeroplane surface, a propel 1er shaft extending longitudinally above the tail piece of the car, a propeller carried by said shaft, a motor for driving the propeller shaft, a second motor, and mechanism actuated by said second motor for vertically swinging and rocking the flapping wings.

2. A `flying machine comprising -a Vboat shaped car having an attenuated tail portion with a transverse tail piece, a frame rising from the car, an aeroplane surface of substantially cruciforrn shape supported by the frame, said surface presenting head and tail portions and transverse Wing portions flapping Wings universally jointed to the frame and arranged beneath the transverse Wing portions of the aeroplane surface, a propeller shaft extending longitudinally above the tail piece of the car, a propeller carried by said shaft, a motor for operating the propellershaft, a transverse transmission shaft on the frame, eccentric mechanism actuated by said shaft for vertically swinging and rocking the flapping wings, and a second motor for driving said transmission shaft.

In testimon whereof I affix my signature in presence o two Witnesses.

BENJAMIN FRANK STONER. Witnesses:

BENJAMIN KRAIZOFF, DUoIsER Porm.

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