US1005205A

US1005205A - Aeroplane.

Info

Publication number: US1005205A
Application number: US54086610A
Authority: US
Inventors: Carl Hartmann
Original assignee: Individual
Current assignee: Individual
Priority date: 1910-01-29
Filing date: 1910-01-29
Publication date: 1911-10-10
Anticipated expiration: 1928-10-10

Description

C. HARTMANN.

AEROPLANE.

APPLICATION FILED JAN;29, 1910.

1,005,205. Patented Oct. 10,1911.

3 SHEETS-SHEET 1.

Q X \J \J a? l/VVE/VTUR 0/1/91. HART/MANN G. HARTMANN.

AEROPLANB.

APPLICATION FILED JAN. 20, 1910.

Patented Oct. 10, 1911.

3 SHEETS-SHEET 2.

IN VEN TOR CARL HART/MANN WITNESSES:

WWW

A TTORNEYS G. HARTMANN.

AEROPLANE.

APPLICATION FILED JAN. 29, 1910.

Patented Oct. 10, 1911.

4 TOR WITNESSES 22 23 27 l/Vl/EN 7%9 CAI?!- HARZMA/V/V flaw U 7%3 ATTORNEYS CARL HAR'I'MANN, 0F WOODSIDE, NEW YORK.

AEROPLANE.

:eooaeoa.

Specification of Letters Patent.

Patented Oct. 10, 1911.

Application filed January 29, 1910. Serial No. 540,866.

To all whom it may concern:

Be it known that I, CARL HARTMANN, a citizen of the United States, and a resident of Woodside, Queens county, Long; Island,

'State of New 'York, have inventor. ce1tainnew and useful Improvements in Aeroplanes, of which the following is a specification.

My invention relates to aeroplanes, preferably, although not necessarily, arranged to be driven by an attached motor, and has for a principal object to provide a construction which shall have a maximum of stability while in flight and especially when it encounters sudden and erratic air currents from whatever direction; a further object of my invention is to provide such stability in combination with a maximum amount of sustaining surface; and a still further objeet, directly associated with the preceding two, is to provide a symmetri al arrangement of sustaining surface, and a construction, in which the center of gravity shall lie in a vertical axis situated symmetrically with reference to said surface, as well as below the mean plane of such surface.

A further and most important object of my invention is to provide an improved rudder systcm, by means of which very quick changes ofdirection may be effected. This same systen'i of rudders may also be so used as to aid in lifting or depressing one or both sides of the aeroplane, being thus of advantage not only when rising from or descend ing to the ground, but also as an aid in maintaining the equilibrium of the aeroplane in case of sudden gusts tending to overthrow the same.

Still another object of my invention is to provide an improved screw for use in pro pelling an aeroplane.

A further object of the invention is to provide an improved landing d cvi ip by means of whiph the aeroplane may drop to the surface of the ground gently and without jar; this "same device is of substantial assistance in enabling the aeroplane to take its preliminary run over the ground preparatory to a flight without unduly jarring the operator and the driving mechanism by reason of irregularities which may be met with upon the ground surface.

Other objects of the invention will appear as the specification proceeds.

Referring to the drawings, Figure 1 represents a side elevation of a preferred form of my invention; Fig. 2 is a horizontal sectional view taken along the line 2-2 of Fig. 1 and shows the operators cage and the landing device; Fig. 3 is a plan view of Fig. 1 taken from above; Fig. t is a front elevation of Fig. 1.; and Fig. 5 is :1V section, looking from the front, taken along the line 5 5 of Fig. 1.

Considering the sustaining surface of the aeroplane proper, this comprises a series of narrow individual planes 1 extending the full width of the aeroplane, said planes being placed parallel with one another and arranged in echelon or diamond-shaped outline; or the arrangement may be spoken of as similar to that of two equal wedges placed with their bases abutting. As to both a central longitudinal plane and a central transverse plane this diamond is substantially synnnctrical. The individual planes constituting the bottom of the diamond are, however, shorter than the corresponding planes constituting the top of the diamond; the area of the upper sustaining surface of the aeroplane is, therefore, greater than that of the lower.

Extending centrally forward of the aeroplane a shaft 2 carrying the propelling screw 3.

A cage t is attached to and hangs centrally below the aeroplane; it carries a motor 5 adapted to actuate, through a sprocket wheel (5, a sprocket chain 7 and a second sprocket wheel 8, the shaft 2; a lever 9 is used to control the engine. As the operator is seated in this cage his head and the upper portion of his body projects a little above the level of the lowest central pair of planes. All the lower planes in front of him are cut away within a determined angle so as to give an extended field of view for the proper guidance of the aeroplane. The lower planes to the rear of the operator are also preferably cut away for better balancing of the aeroplane.

At the rear of the aeroplane and hinged to the edge of the lower plane is a horizontal rudder 10 adapted to be shifted throu h a suitable angle (as c. g. 10' to 10 Fig. 1 by use of a cord 1.1, running over suitable pulleys, and a controlling lever 12.

Attached to two axially alined rotatable shafts 13 supported midway between the top and bottom systems of planes on each 1110 side is my improved steering rudder 14. Each rudder is fixed to its shaft and may be turned thereon so as to changeits angle with the horizontal through a lever 15 and the cord or belt 16. v

The operation of the aeroplane is as follows: When in the air and moving straight ahead the lateral rudders 14 are set in a horizontal position, as shown at the left, Fig. 4. The rear rudder 10 should'also be horizon tal. level, the rear rudder should be inclined up-. wardly as indicated at 10 A. quicker rise may be accomplished by simultaneously 1nclining the lateral rudders 14: so as to have an upper edge to the front as shown at 17 (dotted) 1. To descend, rear rudder 11 and lateral rudders 1s should be set uppositely as shown at 10 and 18. If desired the lateral rudders may be used alone, without the rear rudder.

To use the lateral rudders tor steering purposes without ascent or descent, one rudder should be placed in a horizontal position and the other in a vertical position; this is shown in Fig. 4:. Should one side of the aeroplane tend to tip up or down while making the turn the level may be restored and maintained by suitably adjusting the angle of either or both rudders 14.

Pivotally fixed by .a shaft 18' t0, brackets 19 extending centrally below the operators cage, is my improved landing device 20. This extends to anequal extent forwardly and to the rear and, preferably, at least to the limit of the sustaining surface. It consists of a pair of light and thin but still. strips 21 spaced apart at the center and brought together toward each end so as to iave the general outline of a boat or snowshoe; braces 22 suitably stiffen the structure. Wheels 23 are provided at each end of the landing device and a central wheel 24:.is

placed at each end of shaft 18. Preferably,

although, not so shown, the wheels 2 should either be smaller than wheels 23 or else the shaft 18 01": wheels 2 1 should be placed at higher level than those of 24. Similar springs 25 at each end of the operators cage, connect said cage and the landing device.

In rising from the ground, as the aeroplane is either pulled along the same or driven by its motor, the landing device will ride over all irregularities of surface without transferring any material change of po sition to the aeroplane. Any shock, or jar, also, will-be taken up by the springs 25. in the same way, in making a landing, the

front wheel 23 will meet the ground first,

but the shock of this landing will be largely taken up by the springs 25 and will, hence, not be transmitted to the engine and to the aeroplane.

along the ground, either in rising or descend- If it is desired to ascend to a higher- As the aeroplane runs,

ing,'one or the other of the middle wheels 24:, and sometimes both, will be upon the ground.

Referring to the screw 3 this has, as will be observed, a blade the radial width of which increases steadily as the length of said blade along its shaft increases. 1 have found by experiment that with this type of screw as distinguished from the orthodox screw having a uniform radial width of blade at all points, the velocity attained through the air for a given amount, of power is much greater.

Owing to the fact that the screw blade is constantly increasing in width and weight from the end of its shaft, it is necessary to provide upon said shaft a balancing element 26; this may be simply straight radially extended bar fixed to the shaft and ending, if desired, in a knob embodying any required balancing weight. I find that I am able to effect the balance inthisway with less addition of weight than if'a b; wheel were used.

Owing to the substantially greater sustaining surface of the upper system of anced-ah currents of any kind. By reason.

of its wedge like shape, alsomy aeroplane tends to split the air in front of it and to pass through the same with a minimum of friction.

The individual planes 1 may overlap somewhat or as drawn, the edges of neigh boring planes may be directly over one another.

Many changes of detail as e. 9., the use of more than one screw. instead of but one screw as described and shown; or the use of a rear rudder 10 of diilferent length or different width, or both, from the one shown,

may be made without departing from the spirit of my invention. I may also, within the scope of my invention, have the individual planes of the lower system the same in number and size as the upper system provided I retain the wedge shaped outline; or I may, by keeping the lower system of planes of smaller area than the upper system, depart from the wedge shaped outline. 01', instead of having the lower set of plane shorter than the upper set ll may, it I choos make them of the same length but narrower Taken with the foregoing description are the drawings the exact nature of my inven tion is set forth in the following claims.

I claim:

1. In an aeroplane an arrangementflot sustaining surfaces comprising two sets of per allel planes said sets being located one above the other and the planes of each set being in stepped relation to one another, corresponding planes of said stepped sets being, further, closest to one another at the ends of the aeroplane.

2. In an aeroplane an arrangement of sustaining surfaces comprising two sets of parallel planes said sets being located one above the othe and the planes of each set being in stepped relation to one another corresponding planes of said stepped sets being farthest apart at the middle and closest to one another at the ends of the aeroplane.

In an aeroplane an arrangement of sus' taining surfaces comprising two sets of parallel planes said sets being located one above the other and the planes of each set being in stepped relation to one another the planes of the upper set having a greater area than the planes of the lower set.

4. In an aeroplane the arrangement of sustaining surfaces comprising two sets of parallel planes said sets being located one above the other and the planes of each set being in stepped relation to one another the planes of the upper set extending laterally beyond the planes of the lower set.

In an aeroplane the combination of sustaining surfaces comprising two sets of parallel planes said sets being located one above the other and the planes of each set being in stepped relation to one another with the planes of the upper set extending laterally beyond the planes of the lower set and a laterally arranged rudder adapted to be ad justed about a transverse axis.

(3. In an aeroplane the combination of sustaining surfaces comprising two sets of parallel planes said sets being located one above the other and the planes of each set being ,in stepped relation to one another with the planes of the upper set extending laterally beyond the planes of the lower set and a pair of independent laterally arranged rudders each adapted to be adjusted about a transverse axis.

7. In an aeroplane an arrangement of sustaining surfaces comprising two sets of planes, said sets being located one above the other, and the planes of each set being in stepped relation to one another, with corresponding planes of said stepped sets closest to one another at the ends of the aeroplane, planes of the lower set being centrally cut away.

In testimony whereof I have hereunto set my hand in the presence of two subscribing witnesses.

CARL HARTMANN.

Witnesses: i

Emma G. \VILLYOUNG, JOHN A. Kminnmxnox.

Copies of this patent may be obtained for five cents each, by addressing the Commissioner of Patents, Washington, D. C.