US1906764A

US1906764A - Aeroplane rotor

Info

Publication number: US1906764A
Application number: US596001A
Authority: US
Inventors: Fritz F Petersen
Original assignee: Individual
Current assignee: Individual
Priority date: 1932-03-01
Filing date: 1932-03-01
Publication date: 1933-05-02
Anticipated expiration: 1950-05-02

Description

May 2, 1933- i. F. FQ PETERSEN 1,906,764

AEROPLANE ROTOR Filed March l, 1952 `2 Sheets-Sheet 1 FRITZ F. 'PETERSEN afm- Arrow/iff May 2, 1933. l F. F. PETERSEN 1,906,764

AEROPLANE ROTOR Filed March 1, 1932 2' sheetvg-snee: 2

l/W/V. Franz F; PETERSEN.

@354% ATTO/NFK Patented May, 2', 1933 FRITZ F. PETERBEN, F SAN FRANCISCO, GALIFOBCN'IA manana Boron.

application mea umn i, im. semi 110.596.001.

This invention relates to a .construction of an improved rotor employed' to impart non-stalling support and lift to an aeroplane. 'In certain respects this invention comprises certain specific improvements over that inventionY disclosed in my copend` Y ing application Serial No. 589,660, filed January 29, 1932, and in other' respects' this linvention is eneric thereto.

It is an object of the present invention to provide a. new and improved rotor for an aeroplane. f

Another object of is to devisea rotor the present invention support for an aeroplane, which can be controlled and manipulated to vary selectively operative portions of the rotor.`

' A further object of the present invention' is to provide' an aeroplane rotor which can be manipulated during flight to provide. nonstalling lift and support to an aeroplane during maneuvering. of the aeroplane... l

A further' object of the present invention is to provide a rotor mechanism for an aeroplane, a portion of which can be varied se lectively to change the degree of effective use of the rotor in providing lift and non-stalling support during maneuvering of the laeroplane upon which it is employed.

A still further object of the present invention is to provide means for selectively varying the ailerons provided on a rotating blade during'rotation.

I 'accomplish these means of the improved device disclosed in the drawings forming a part of the present application wherein like characters of lreference 'are used to designate similar parts thruout4 the specification and drawings, an in which Fig. 1A is a plan view of a preferred form of aeroplane rotor of my invention. v

Fig. 2. is a section along the line 22 of Fig. 1 showing the contour of the blade and aileron and means for varying the aileron relative to the blade. a

, Fig. 3 is a view, the left hand lportion of which is in section and the right hand portion of which is an elevation Of the aileron control means.

vide a plurality of blades 1 for providing lift and.

.rim members 4 and 5 w positioned along the trailing edge of the l and other objects by -p Fig. 4 is a view along the line .4--4 in Fig. 3v showing the construction of the means for varying. selectively the ailerons.v

his invention, Il prowhich extend radially from thecommon icenterof hub'2 to which they are fixed.` Intermediate-the ends of the blades I position an annular wing 3 -which is preferably discontinuous adjacent each blade. Thus, outer and inner r-ing members 4 and 5 are extended between adjacent `blades to join them. to ether and to provide a support upon whic the win 3 can be fabricated or. mounted. The length' of each blade is thus free to engage the ai'r to act thereon.

Each blade has a leading edge 6 and a trailing edge 7, the blades' being suitabl In accordance with contoured. At' each blade trailing edge 7 Ailerons 8 are preferably ositioned between ile ailerons 9 are blades between inner ring member 5-v and hub 2. The outline and contour of the anthe blades andv the ailerons are nular wing, such that a self-rotating, balanced rotor 1s available to supply lift and non-stalling supabout shaft12 which supports hub 2.

Means are provided for selectively varythe cables are connected to the control stick. i

ort to an aeroplane as the rotor rotates ing the ailerons and for moving them automatically durin rotation. of the rotor. Cables 13'exten from each aileron 9 thru slots 10 inthe blades to bell cranks '14 which are mounted forhinged movement in recesses 16 in the blades.

Since the ailerons 8 and, 9 aresecured to rotatable shaft `11, 'y f movement of a cable 13 is eective to move 9. Each bell crank'14 includes a crank arm 17 whichengages agroove 18 in a ring 19.

ioo' v simultaneousl and an equal amount, both V ailerons 8 an mounted for hinge movement by pins 23 in move universally. Ring 19 carries eyes 26 `from which cables 27 extend to a suitable control mechanism as stick 28 located inthe aeroplane convenient to the pilot. Stick 28 fis mounted for 4universal movement byA ball and socket 29. Cables 27 are-passed over guides 30 and are attached to cross 3l on i stick 28 so that when stick 28 is moved, the

ring 19 is moved likewise. and the ailerons are moved relative to the blades durin rotation of the rotor. Pins 32 extending rom iing 19 into grooves 33 in ring 22 limit movement of ring 19 .relative to ring 2 2 while pins 34 extending' into grooves 35 in shaft 12 limit movement between ring 22 and shaft 12. The'total free universal movement of the ring 19 is thus limited.

While the rotor is capable of self-rotation when moved relative to the air, I preferably include means for rotating vthe rotor positively. Ring gearI 36 is secured to blades l and hub 2 by bolts .37. A pinion gear 38 drives the ring gear from a shaft39 upon which the pinion gear is mounted in a supporting casing 41. Shaft 39 carries universal 42 connected to shaft 43 which extends to a suitable source of power and is ldriven therefrom selectivel when desired, as

I have disclosed in my a orementioned copending application.

Shaft 12 ishinged about. pin 44 which is I carried by a suitable supporting structure 46 on the aeroplane. Arms 47 extend from casin 41 and carry cables 49 which extend to suitable control mechanism so that shaftv 2, and the rotor carried thereby, can be ad- The ailerons are selectively operated when I o the aeroplane is to be banked by the stick 28 to make a turn or when a climb isto be undertaken or a descent made. The rotor l provides non-stalling support so flexible in character and ofsuch an'amount that the stub wing, usual to aeroplanes ofthis type, can b'e dispensed with and the controls of the aeroplane simplified. 'I-he rotor is capable of hinge movement about pin 44 so that the rotor can be moved relative'to the directaken.

tion of flight of theaeroplane to cause autogiration, if desired, vquickly and without positive driving when 'a -take-oifis under- The ailerons are the only exible elements in the structure, thus simplifying the construction. The centrifugal forces'- arising rality of bla center, an annular Wing, joining said upon rotation are counterbalanced aga-inst each other, and are taken up thru a relatively solid structure, thereby making the .operation of the rotor smooth and with greater efficiency. v

Having thus described myi invention what I claim as new and desire to secure by Letters Patent is- 1. An aeroplane rotor comprising a] plurality of blades4 extending from a common center, and an annular wing joining said plu-` rality of blades, said Wing being discontinuous adjacent each of said blades.

2. An aeroplane rotor comprising a plurality of blades extending from a common center, an annular Wing joiningsaid plurality of blades, said wing being discontinuous adjacent each of said blades, and a movable aileron on each of said blades.

3. An aeroplane rotor comprising a plurality of blades extending from a common center, an annular wing joining each of said blades and an aileron trailing each of said blades;

4. An aeroplane rotor comprising a plurality of blades extending from a common center, an annular Wing joiningeach of said blades, saidwing'bcing discontinuous adjacent each of said blades, and an' aileron trail- -ing each of said blades adjacent said discontinuous wing.

An aeroplane rotor comprising a plurality of blades extending from a common center, an annular wing joining each of said blades, said Wing being discontinuous adjacent each of said blades, an aileron trailing each of said blades adjacent said discontinuous wing, and another aileron trailing each ofsaid blades between said wing and said center.

6. An aeroplane rotor comprising a plurality of blades extending from a common center, an annular wing joining each of said blades, said wing being discontinuous adjacent each of said blades, an aileron trailing each of said blades adjacent said discontinuous wing, and means to vary selectively the position of each of said ailerons to each of said blades.

' 7. An aeroplane rotorcomprising aplurality of blades extending from a common center, an annular wing joining each of said blades, said wing being discontinuous adja- .cent each of said blades, an aileron trailing each of said blades adjacent said discontinuous wing, another aileron trailing each of said 4 blades between said Wing and said center, and means to vary selectively the position of each of said ailerons to veach of said blades.

8. An aeroplane rotor comprising a plues extending from a common rality ofblades. said wing being discontinuvary selectively the position of each of said ailerons to each of said blades. 9. An aeroplane rotor comprising a plurality of blades extending from a common 5 center, an annular wing joining said pluraliy of blades, said wing` being discontinuous a jacent'each of said blades, a movable aileron on each of said blades, and means to vary selectively the position of each of said ailerons 10 to each of said blades in a predetermined manner upon rotation of said rotor.

10.l An aeroplane rotor comprising a plurality of radial blades, an annular wm joining said blades and discontinuous a jacent y' 15 each of said blades, a first aileron trailing each Aof said blades adjacent said discontinuous wing, a second ailerontrailing each of said blades inside of said wing, andmeans to vary selectively said ailerons. 20 11. An aeroplane rotor com rising a plurality of radial blades, an annu ar win joining said blades` and discontinuous a ]acent each of said blades, a first aileron trailingeach l of said blades adjacent said discontinuous 25 wing, a second aileron trailing each of said blades inside of said wing, and means to vary selectivel said ailerons in a predetermined s manner uring rotation of said rotor.

2. An aeroplane rotor comprising a hub,

y o a shaft for supporting said h'ub for rotation, a

plurality of blades extending from said hub, an aileron on each of said blades, a grooved ring mounted for universal movement on said shaft, means for moving said rin and 5 means connecting saidring to said a' erons,

including a. bell crank engaging said grooved ring, whereby said vmoving means control said ailerons.

PETERSEN.