US1663302A

US1663302A - Mark hehzl

Info

Publication number: US1663302A
Authority: US
Publication date: 1928-03-20
Anticipated expiration: 1945-03-20

Description

M. HERZL AUXILIARY POWER SYSTEM FOR AERIAL VESSELS Filed 061;. 27. 1927 Mim A r I III/ IN V EN TOR.

ATTORN s.

Patented Mar. 20, 1928.

UNITED STATES MARK HERZL, OF NEW YORK, N. Y.

AUXILIARY POWER SYSTEM FOR AERIAL VESSELS.

Application filed October 27, 1927. Serial No. 229,126.

The present invention relates to improvements in aerial Vessels, and more part1cularly to an auxiliary power system therefor.

The main object of the invention is to provide an aerial vessel, provided, in addition to the motor-driven propeller or propellers, with one or more propellers which are driven independently of the motor of the aerial vessel, more particularly by a rotary internal combustion engine in which a charge of gun powder or other explosive substance 1s exploded and the resulting gases allowed to I act upon the working piston of the engine.

Another object of the invention is to provide an auxiliary power system of the charactor described which is simple in construc tion, efficient in operation, and which may be conveniently installed in aerial vessels Without necessitating material changes in the construction of the latter.

A further object of the invention is to produce an auxiliary power system of the character mentioned, which, when applied to aeroplanes, will sustain the same in flight for a considerable time even after the main motor thereof comes to a full stop, thereby avoiding accidents due to the sudden stoppage of the said motor.

With these and other objects in View, which will more fully appear as the nature of the invention is better understood, the same consists in the combination, arrangement and construction of parts hereinafter described, pointed out in the appended claim and illustrated in the accompanying drawings, it being understood that many changes may be made in the size and proportion of the several parts and details of construction within the scope of the appended claim, without departing from the spirit or sacrificing any of the advantages of the invention.

One of the many possible embodiments of the invention is illustrated in the accompanying drawings, in which igure 1 is a side elevation of the front portion of an aeroplane, provided with ,an auxiliary power system constructed in accordance with the present invention; Fig. 2 is a transverse section taken through one of the aerofoils of the aeroplane, on a larger scale, showing in elevation the auxiliary power system; Fig. 3 is a central vertical section, partly in elevation, taken through the firing device of the power system; Fig. 4 is a side elevation of a portion of said firing device; Fig. 5 is a section taken through one of the cartridges used in the internal-com- I bustion motor; and Fig, 6 is a plan view of a band of the cartridges.

In the drawings, the numeral 10 indicates an aeroplane, which may be of any suitable type and construction. In the case illustrat ed the said aeroplane includes an upperaerofoil 11, a lower aerofoil 12, and a screw propeller 13 mounted on a horizontal shaft 14, the said shaft being driven by a power plant, not shown. The construction and operation of the elements are well known, so that a further detailed description thereof seems to be unnecessary.

The auxiliary power plant comprises a rotary internal combustion engine 15 of any suitable type, preferably mounted within. the upper aerofoil 11, and provided with a vertical driven shaft 16, to which is attached an auxiliary propeller 17, disposed above the aerofoil 11. This motor is, preferably, of the turbine type, its runner being actuated by charges of un powder of other explosive substances, w ich are exploded within a chamber 18, provided with a, nozzle 19, the latter directing the resultant gases to the said runner which is thus rotated, thereby actuating the auxiliary propeller 17. The

On diagonally opposite portions of this head are provided apertures 22, to allow of the insertion of cartridges, as will hereinafter appear, said apertures being adapted to be closed by a cap 23, which is slidably arranged on the said head, springs 24 being adapted to keep the said can in its outer position in which the said apertures are open, as clearly shown in Fig. 4 of the drawings. The head and cap are provided with registering

openings

25 and 26, respectively, through which a firing pin 27 is adapted to protude. This pin. slides in guides 28 and carries a collar 29, adapted to bear against the outer face of the cap 23. On'the pin is provided a further collar 30, between which and one of the guides 28 is inserted an actuating spring 31.

The cartridges consist each of a shallow ,open container 32, having projections 33.

33. The cartridges are supplied to the chamber 18 through the apertures 22, by a bell-crank lever 37, which is fulcrumed at 37' adjacent the said chamber. The arm 38 of this bell-crank lever is in engagement with a flexible means 39 such as a cord, which leads over a sheave 40 down to within reach of the operator on a seat on the body of the aeroplane. The other arm 41 of the said bell-crank lever is. adapted to engage projections 33 on the cartridges, drawing them, in a manner hereinafter to be described, through the apertures 22 above mentioned to an abutment 42, which is carried by the head 21. Adjacent its fulcrum, the bell-crank lever is provided with a finger 43, adapted to engage a lug 44 of a lever 45, which is fulcrumed at 46 adjacent the firing pin and engages a recess 47 in said firing pin.

The operation of this device is as follows: Normally the aeroplane is propelled through the air by the main propcller'l3.- The auxiliary propeller 17 is then at rest and the elements ofthe cartridge supplying and firing pin setting device and also the firing pin are in the positions shown in Fig. 3 of the drawings. In these positions the arm 41 of the bell-crank lever 37 engages an already fired cartridge, that is in contact with the abutment 42. If the main power plant of the propeller, by accident or otherwise, comes to a full stop, the rotary'internal combustion engine 15 is set to motion. For this purpose, the operator takes hold of the cord 39 and pulls the same in the direction of the arrow shown in Fig. 1 of the drawings, whereby the finger 43 of the bell-crank lever engages the lug 44 of the ever 45,

whereby compressing the spring31 of the firing pin 27. At the same time thecap 23,-

under the tension of the springs 24, moves outwards, thereby allowing of the insertion of a new cartridge into the chamber 18. As

soon as the apertures 22 are uncovered, the

bell-crank lever 37 supplies a new cartridge to the chamber by engaging the already fired cartridge, in contact with the abutment 42, and'drawing the said cartridge downwards, whereby a new cartridge is inserted into the chamber 18. When now, in the further swinging movement of the bell-crank lever 37, the finger 43 is disengaged from the lug 44, the spring 31 is allowed to act, whereby the firing pin is projected into the chamber cord 39, the auxiliary propeller is kept in,

motion until a safe landing is made.

What I claim is An auxiliary propelling mechanism for aeroplanes, including arotary internal combustion engine having a vertical driven shaft extending through the top aerofoil of the aeroplane, a propeller attached to said shaft above said aerofoil rotatable in a horizontal plane, means associated with said engine for exploding solid explosivecharges and permitting the resulting gases to act upon the rotor of said engine, and means within the reach of the operators'seat in the body of said aeroplane forfeeding explosive charges to said first-mentioned means and for actuating the charge explosion means.

Signed at New York, in the county of New York, and State of New York, this 22nd day of September, A. D. 1927.

MARK HERZL.