US2404829A - Helicopter - Google Patents

Description

c. E. DARROW HELICOPTER Filed Sept. 3, 1943 4 Sheets-Sheet l- Inventor y 4 c. E. DAROW- ,4

HELICOPTER Filed Sept. 3, 1943 4 Sheets-Sheet 2 q q 1 N m 'm 1 :r

\H\ Inventor diiawelii'efi Farrow M July 39, 1946.

c. E. DARROW HELICOPTER Filed se i. 3, 1945 4 Sheets-Sheet 4 I jlm/entor hrence .zi'flar raw' B? yaw W3) 1 WIi Patented July 30, 1946 UNITED STATE HELICOPTER Clarence E. Darrow, Miami, Fla. 7 Application September 3, 1943, Serial No. 501,121

2 Claims. 1

The present invention relates to new and use- ,ful improvements in helicopters, and has for one of its important objects to provide a flying machine of this character comprising a unique arrangement of rotors driven in opposite directions through the medium of twin engines.

Another very important object of the invention is to provide a helicopter of the aforementioned character which embodies novel propulsion and control means.

Other objects of the invention are to provide a helicopter of the character described which will be comparatively simple in construction,-strong, durable, reliable in operation, and which may be manufactured at low cost.

All of the foregoing, and still further objects and advantages of the invention, will become apparent from a study of the following specifi cation, taken in connection with the accompanying drawing wherein like characters of reference designate corresponding parts throughout the several views, and wherein:

Figure 1 is a top plan view of a helicopter constructed in accordance with the present invention.

Figure 2 is a-view in front elevation thereof.

Figure 3 is a View in side elevation of the machine.

Figure 4 is a fragmentary view in vertical 1ongitudinal section, taken substantially on the line 44 of Figure 2.

Figure 5 is a view inside elevation of the elevator assembly.

Figure 6 is a top plan view of the rudder assembly with portions of the surfaces broken 1:

away in section, the elevator assembly shown in Figure 5 being omitted from the rear end of the fuselage.

Figure 7 is a fragmentary view in horizontal section showing, in top plan, the means for releasably securing the safety flaps in vertical or inoperative position.

Figur 8 is a view principally in horizontal section through the fuselage.

Figure 9 is a cross-sectional view through the forward portion of the fuselage.

Figure 10 is a view in horizontal section on an enlarged scale through the elevator assembly.

Referring now to the drawings in detail, it will be seen that the embodiment of the invention which has been illustrated comprises a fuselage of suitable dimensions and material which is designated generally by reference numeral I. Landing wheels 2 are provided beneath the fuselage I. Th forward portion of the fuselage I comprises a cabin 3. The forward portion of the fuselage I further includes an anti'clinal'top portion 4. Rising from the apex or peak of the top portion 4 of the fuselage I is a panel 5..

Mounted on the forward portion of the fuselage I is a frame structure 6; The frame structure 6 is transversely elongated and mounted for rotation in opposite directions-on the ends thereof is a pair of rotors I. Engines 8 in thefuselage I drive the rotors I in opposite directions by suitable means, such as shafts 9,'universal joints I0, gears I I, et cetera.

Safety flaps I2 are hingedly suspended from the upper portion of theframe structure 6 on opposite sides of the fuselage I.' In the embodiment shown, the safety'flaps I2 are releasably secured in vertical or inoperative position by means including shafts I3 which are journaled in bearings I4 on the frame structure 6 and which are operable from within the cabin 3. As best seen in Figure 7 of the drawings, the shafts I3 have fixed thereon pairs of spaced fingers I5 which receive the flaps lz'therebetween for releasably securing said flaps against swinging movement and in vertical position. j Mounted on top of theframe structure 6," beneath the inner portions of the rotors I, are pairs of inverted U frames I6. Series of slats I1 are journaled for vertical swinging adjustment between'the pairs of frames I6 for receiving the air blast or wash from the rotors "1. Bars I8 are pivotally connected to the upper ends of the series of slat I! for actuating said slats: in unison. ,Cables I9 fromhandleverslbinthe cabin 3 are connected to the ends of the bars IB'for adjusting the slats Il as desired. Two such levers 20 are provided, onefor eachset or series of the slats I1.

Built into the fuselage I is a pair of wind tunnels 2!. The tunnels 2| comprise, at their forward end portions, upwardly opening intakes 22 (see Fig. 9) on opposite sides of the anticlinal top portion 4 of the fuselage I. Thus, the tunnels 2| are adapted to receive the air blast or wash from the inner portions of the rotors I. The upstanding panel 5 prevents air turmoil between the rotors I and the oppositely inclined sides of the top portion 4 of the fuselage I direct the air into the intakes 22. At an intermediate point, the tunnels 2| merge into a single tunnel 23 (see Fig. 8) which extends to the rear end of the fuselage I.

Mounted on the rear end of the fuselage I is an elevator assembly 24. The assembly 24 inludes a pair of rearwardly projectin Substam 3 tially U-shaped brackets 25 which are fixed on V the upper portion of the fuselage l. Journaled in the cabin 3 for actuating the elevators 26.

Also mounted on the rear end of the fuselage I, beneath the elevator assembly 24, is a rudder assembly 30. The assembly 30 includes a pair' of substantially U-shaped brackets 3| which are It is believed that the many advantages ofa helicopter constructed in accordance with the present invention will be readily understood, and although a preferrred embodiment of the machine is as illustrated and described, it is to be understood that changes in the details of construction and in the combination and arrangement of parts may be resorted to which will fall within the .scopeof the invention as claimed.

What is claimed is: 1. A helicopter comprising a fuselage including o a forward part provided with an anticlinal roof mounted transversely on the rear end of the fuselage I. Pivotally mounted for horizonal swinging movement on the brackets 3| and extending rearwardly therefrom is a gang of spaced, parallel rudders 32. A- bar 33 is pivotally connected to the rudders '32 at intermediate points in said rudders for actuating same in unison. Cables '34 connect the bar 33 to therotatable wheel 35 on the swinging column 29 in the cabin 3 for actuating the rudders 32. a

It is thought that the operation of the machine will be readily apparent from a consideration of the foregoing. Briefly, the desired lift is had from the oppositely rotating rotors 1, said rotors being actuated by their respective enines 8. Forward or backwardmovementis had through the medium of the slats l1. With the slats l1 adjusted to the inclination shown in Figure 4 of the drawings, thewash or downward blast of air from the rotors '1 strikes said slats and drives the machine forwardly. The speed is governed by the inclination of the slats I1. With the slats IT in a vertical position, the machine will ascend or descend vertically or hover. Rearward tilting of the slats I! will'cause the machine to travel backward. As the series of slats are adjustable independently, said slats may, if desired, be utilized to turn or'as'sist in turning the machine. Air from the'rotors is directed into the intakes 22 of the tunnels 2| by the top portion 4 of the fuselage 'l. The air thus is caused to enter the tunnels under pressure. This blast of air emerges at the rear'end of the fuselage l and assists in propelling the machine forwardly. This air also strikes the surfaces 26 -and"32 in amanner to materially increase the effectiveness thereof. Should one of the engines fail, that-side of the machine will, of course, drop. When this oocurs,';the safety flaps l2 are released and said flaps swing upwardly to a horizontal positionbeneath the upper portion of the frame structure 6 where they are arrested and function asplane to assist thepilot in bringing the craft to a safe landing.

portion having a ridge extending longitudinally of said fuselage, a frame structure mounted on and extending laterally from opposite sides of the fuselage, rotors mounted on and disposed above said frame structure at opposite sides of the fuselage, means for actuating the rotors, a panel rising from and parallel with the ridge of the anticlinal roof portion of the fuselage, between'the rotors, longitudinal air tunnels in the fuselage, said air tunnels including upturned intakes opening at their upper ends at opposite sides of the anticlinal roof portion of the fuselage and below the inner portions of the rotors for receiving the air blasts therefrom, said tunnels opening through the rear end of the fuselage, and control surfaces mounted on said rear end of the fuselage for receiving the air fromthe tunnels.

2. A helicopter comprising a'fuselage including a forward part provided with an anticlinal roof portion having a ridge extending longitudil nally' of said fuselage, a frame structure mounted on and extending laterally from opposite sides of the fuselage, rotors mounted on and disposed above said frame structure at oppo ite sides of the fuselage, means for actuating the rotors, a panel rising from and parallel with thejridge of the anticlinal roof portion of the fuselage between the rotors, longitudinal air tunnels inthe fuselage, said air tunnels including upturned intakes opening at their upper ends at opposite sides of the anticlinal roof portion of the fuselage and below the inner portions of the rotors for receiving the air blasts therefrom, said tunnels opening through the rear end of the fuselage, a series of transverse slats mounted for vertical swinging adjustment on the frame sections 'beneath the inner portion of each rotor and directly above said intakes for receiving the air blasts from said rotors, and means for "actuating each series of said slats in unison.

CLARENCE E. DARR'OW.

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