Search Images Maps Play YouTube News Gmail Drive More »
Sign in
Screen reader users: click this link for accessible mode. Accessible mode has the same essential features but works better with your reader.

Patents

  1. Advanced Patent Search
Publication numberUS1827438 A
Publication typeGrant
Publication dateOct 13, 1931
Filing dateSep 10, 1928
Priority dateSep 10, 1928
Publication numberUS 1827438 A, US 1827438A, US-A-1827438, US1827438 A, US1827438A
InventorsRauch John D
Original AssigneeRauch John D
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Airplane
US 1827438 A
Images(2)
Previous page
Next page
Description  (OCR text may contain errors)

Oct; 13, 1931. J. D. RAUCH 1,827,433

' AIRPLANE Filed Sept. 10, 19 28 2 Sheets-Sheet l F, iwewto/j Wws John, D.

J. D. RAUCH Oct. 13, 1931.

AIRPLANE Filed Sept. 10, 1928 2 Sheets-Sheet 2 5% NQW .KN)

Patented 0.1. 13, 1931 1 1,827,438

UNITED STATES PATENT OFFICE JOHN D. moon, or 11111, OHIO AIRPLANE Application filed September 10, 1928. Serial No. 305,061.

This invention relates to improvements in as shown in Figures 1 and 2. This pressure alrplanes, and more particularly to propul- Valve may be of any well known form to autosion devices therefor, and has for its princimatically maintain a predetermined pressure pal ob ect to provide an improved system of in the high pressure line 30, such as illus- 5 airplane propulsion mechanism utilizing hytrated in detail in my copending application so draulic power transmission wherein a single bearing SerialNumber 189,849, filed May 9, driving motor may be utilized in connection 1927. Such valves are well known in the art wlth a plurality of propellers which can be and details need not be herein shown or deoutin and out individually or collectively as scribed. The arrangement is such that upon des red excess pressure produced in the manifold 31, 60

Other objects of the invention will appear the pressure will be relieved through the from time to,-time as the following descrippressure valve 32 and permit the liquid to tion proceeds. escape through the relief manifold 33 and The invention may best be understood by from thence to a low pressure'pipe 34. The reference to the accompanying drawings in low pressure pipe returns rearwardly and up- 66 which wardly to a low pressure tank 35 preferably Figure 1 is a skeletonized view of an airarranged in a relatively high position, as for plane to which my improved form of propulinstance, near the upper wing 12, as shown in slon device has been applied. Figure 1 so that the tank is at or above the Figure 2 is an'enlarg'ed side view of the normal level of all of the hydraulically oper-- main pump and motor and supply lines conated control members. A supply pipe 36 nected to one of the propeller motors. leads from the supply tank 35 to the inlet Figure 3 is a vertical section of one form port 23 of the main hydraulic motor 17. Of hydraulic pump or motor which may be Connected with the pressure manifold 31 utilized as the main pressure pump or as one and in parallel between said pressure mani- 7 of the motors for actuating the propellers. fold and the relief manifold 33, I provide a Figure .4 is ahorizontal section of the pump plurality of pipes 40, 41 and 42, respectively or motor shown in Figure 3. having a control valve 40a, 41a and 42a there- Figure 5 is a detail sectional view of a fourin arranged to supply circuits to respective Way valve of the type used for controlling propeller motors b, 41b and 42?). Each of the pressure to the propellers. these motors referred to may be similar in Referring now to the details shown in the construction to thepump 17 but are now utidrawings, the airplane shown in skeletonizedlized as motors and are connected respecform -'in Figure 1 comprises a fuselage 10 tively by supply pipes 400, 4011, 410, 41d and 35 with atailpiece 11 and upper and lower wings 420, 42d to their control valves 40a, 41a and 12 and ,13, respectively. In my improved 42a. These valves are of the four-way type construction a single engine or prime mover, as shown in detail in Figure 5, and arrange herein of the internal combustion type, is inso that pressure may be applied to either pipe dicated at 15 and is arranged to drive a hy- 400 or 40d from the pressure pipe line draulic pressure pump indicated at 17 as for connected to the pressure manifold 31, de-. 9 instance, directly through suitabledrive shaft pending upon the position of the control han- 16. The pump herein illustrated is of the dle 45. It will be understood that when the well known rotor type shown in detail in valve is arranged so as to supply pressure to Figures 3 and 4 and consists of a pair of one of the pipes, as for instance 400 or 40d, the meshed rotors 20 and 21 in casing 22 having other pipewill be connected through the fourinlet and outlet ports 23 and 24 arranged in way valve to the relief or low pressure side the usual manner to produce a pressure on a of the connecting pipe 41, and vice versa. liquid, such as oil, when the rotors are driven. Furthermore, each of the valve handles may An outlet or high pressure pipe 30 leads to a be moved to an ofi position.

manifold 31 and through a pressure valve 32, With the construction above'described, the- 0 mamas 1 several propellers 50, 51 and 52 may be controlled at will, and the number of such propellers may be increased or decreased as desired. In all cases, the propellers can be operated at full or varying speeds, or entirely turned off by manipulation of their valves.

Furthermore, the propellers are capable of being reversed, as for instance, for retarding the movement of the airplane during landing. m A further advantage of my improved transmission device is that it permits the placing of the gasoline engine or prime mover 15 at a most advantageous posltion toward the rear of the plane, which, under some con- 15 ditions, gives better weight distribution of the heavy parts and at all events does not confine the motor to the front forward end of the body of the fuselage as in present con structions. It also permits the use of a sin- 30 gle motor with a plurality of propellers to reduce the motor weight now necessary when a motor is required for each propeller.

I claim:

1. In an airplane having laterally extending wings, a plurality of propellers each pro vided with a hydraulic motor supported in laterally spaced relation on said wings and hydraulic transmission system for said propeller motors including a centrally disposed 50 motor and a pump driven thereby, a high pressure line, a pressure valve, a low pressure line, and independent control means operatively connected with each of said propeller motors and interposed in parallel between 35 said high and low pressure lines.

2. In an airplane, a motor, a plurality of propellers each provided with a hydraulic motor, hydraulic transmission system for said propeller motors including a pump M driven by said motor, a high pressure line, a

pressure valve, a low pressure line, and independent control means operatively connected with each of said propeller motors and in terposed in parallel between said high and 415 low pressure lines, said control means includ ing a four-way valve for reversing one or more of said propeller motors at will.

In an airplane having a centrally disposed fuselage and laterally extending wings, 5 a plurality of propellers each provided with a hydraulic motor supported on said Wings remote from said fuselage, and a hydraulic transmission system for said propeller motors, including a centrally disposed pump and as a driving motor, a high pressure line, a low pressure line and pressure valve, and independent control means in said fuselage operatively connected with each of said propeller members and interposed in parallel between to saidhigh and low pressure lines.

Signed at Lima, 0., this 30 day of Aug.

1928. I JOHN D. RAUCH.

Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2445446 *Mar 14, 1947Jul 20, 1948Antonio MasPropeller transmission means
US2454138 *Oct 25, 1944Nov 16, 1948Reinhold DelzerEngine driven pump
US2514822 *Aug 19, 1949Jul 11, 1950Jr Frank H WolfeHelicopter automobile
US2621001 *May 10, 1948Dec 9, 1952Roman Alfred IConverti-plane
US2771255 *Feb 28, 1952Nov 20, 1956Young Raymond AMounting and drive for helicopter rotor
US2868476 *Jun 25, 1956Jan 13, 1959Schlieben Ernest WConvertiplane with tiltable cylindrical wing
US3002484 *Apr 24, 1958Oct 3, 1961Alfred T DubeBoat
US3037223 *Nov 16, 1955Jun 5, 1962George V LovseyApparatus for treating the finish of automobiles
US3405890 *May 24, 1966Oct 15, 1968Karl EickmannControl means in fluid-power driven, fluid-borne vehicles
US3497162 *May 24, 1966Feb 24, 1970Karl EickmannHydraulically controlled,propeller-driven fluidborne vehicle
US3503574 *May 27, 1966Mar 31, 1970Karl EickmannFluid power operated vehicle groups
US3614029 *Jun 12, 1970Oct 19, 1971Eickmann KarlAdded fluidflow control means for governing the attitude of fluidborne vehicles
US3790105 *Apr 6, 1971Feb 5, 1974K EickmanHydraulically controlled fluid stream driven vehicle
US3801046 *Apr 11, 1972Apr 2, 1974Eickmann KFluid borne craft driven by hydrostatically operated propellers governed by an accident peventing automatic control device
US3823898 *Mar 8, 1971Jul 16, 1974K EickmannHydraulically controlled fluidstream-driven aircraft
US3861623 *Sep 11, 1973Jan 21, 1975Fruechte Vernon DPower transfer system in a multi-engine propeller driven aircraft
US4009849 *Jul 10, 1974Mar 1, 1977Karl EickmannFluid-stream driven aircraft
US4086768 *Sep 8, 1975May 2, 1978Karl EickmannDriving and controlling unit
US7811150Apr 26, 2007Oct 12, 2010Mattel, Inc.Modular toy aircraft
US7918707Mar 31, 2008Apr 5, 2011Mattel, Inc.Toy aircraft with modular power systems and wheels
US8133089Apr 25, 2007Mar 13, 2012Mattel, Inc.Modular toy aircraft with capacitor power sources
Classifications
U.S. Classification244/60, 440/5, 244/53.00R
International ClassificationB64C11/00
Cooperative ClassificationB64C11/00, B64D2700/62701
European ClassificationB64C11/00