US1443567A - Flying-machine propulsion - Google Patents

Description

2 SHEETS-SHEET 1 Jan. 30, 1923.

' C DORNIER FLYING MACHINE PROPULSION- F| LED MAR. 31 1921 INVETOR;

' C. DORNIER.

Jan. 30, 1923. 1,443,567

FLYING MACHINE PROPULSION.

Fl LED MAR. 31'. I921 2 SHEETSSHEET 2 INVENTUR M MM.

Patented Jan. 30 1923.

CLAUDIUS DORNIER, OF FRIEDRICHSHAFEN, GERMANY, ASSIGNOR, BY MESNE ASSIGNMENTS, T0 HIMSELF AN D DORNIEB, METALLBAUTEN GESELLSC HAFT MIT BESCHRANKTE HAFTUNG.

FLYING-MACHINE PROPULSION.

Application filed March 31, 1921. Serial K0 4 51542.

To all whom it may concern:

Be it known that I, OLAUDIUS D'ORNIER, a citizen of. the German Empire, residing at Friedrichshafen, Germany, have invented certain new and useful Improvements in Flying-Machine Propulsion, of which the following is a specification,

My invention relates to flyingmachines and its particular object is to render flying machines capable of varying their speed within wide limits. Ever since the beginning of high speed flying, one of the objects aimed at has been to increase the difference between the maximum and the minimum fly ing speed. The only means which has hitherto been found practicable, and which consisted in increasing the size of the supporting planes while at the same time lessenlng the objectionable resistance, however, only solved the problem within very narrow limits, whereas, on the other hand, the helicopters, which had been proposed in great numbers, and whichpromised a more satisfactory solution of the problem involved, all failed on account of insurmountable difliculties of construction.

It.is with due regard to these facts that my invention will be found to cover a form of flying machine construction, which may be readily realized practically and which allows of the speed of flight to'be varied within wide limits, and thi by means of a flying machine the traction propeller of which is firmly lodged, together with the respecial advantage to so dispose their pivot,

that the weights of the said propelling sets will be either entirely,-or at least partially balanced relatively to their pivots; Itwill be found that for purpose of securing the aforesaid balancing use may also be made with much advantage of the receptacles of fuel, oil or other running material, and that I was PTNT are.

by suitably positioning them within the machine.

Generally speaking, the propelling sets will be rotated about their points only into two positions, i. e., a horizontal for high speeds, and a vertical one for low speeds. However, by suitable means the said propelling sets may also be rotated into intermediate positions. I

In th drawings affixed to this specification and forming part thereof a flying machine embodying my invention is illustrated by way of example. In the drawing- Fig. 1 is a side elevation Fig. 2 a plan view, and

Fig. 3 a front elevation of a monoplane, in which the lateral motor sets are adapted to be rotated, separately, about a horizontal axls.

,Referring to the drawing, the stationarymotor 1 (Fig. 1), disposed in the forward end of the flying machine serves to drive a traction propeller 2. The side motors 3 are lodged to rotate, together with their respective propellers 4 about a pivot 5. If high speed be required, then the propellers i operate, with the drivingvshaft in horizontal position, as pressure propellers. If now the speed is to be reduced, then the moto 3 and propellers t are rotated into thepos'tions 3' and a, respectively, in the direction indicated by the arrow 6, so that the propellers 4 will now come to act as lifting propellers.

The invention is mainly intended for monoplanes with self supporting wings requiring no special staying means, since it is in connection with this particular form of construction that the advantages peculiar to my invention may be fully utilized. However, there is no fundamental'objection to applying my invention also to other forms 0 flying machines, and in the same way, the invention may be successfully realized in the case of flying machine having more than three motors.

I claim: I

In an aeroplane incombination, a hull and a supporting plane connected with said hull, a stationary motor on said 'hull and a trac-' tion propeller operatively connected with said motor and disposed in front of said supporting plane, a motor pivotally suspended on either side of said hull, immediately below said supporting plane and adapted to rock through an angle of 90 about a horizontal axis extending trans versely to said hull and a pressure propeller operatively associated to each rookable m0- tor in such a way as to press the air rear- Wards, Whenever its shaft extends horizontally, or downwards, When its shaft is di rected vertically. V

lntestiinony, whereof I aflix my signature.

- CLAUDIUS DORNIER.

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