US2659999A - Control for model airplanes - Google Patents

Description

Filed May 2, 1952 Nov. 24, 1953 E. E. TURNER 2,659,999

CONTROL FOR MODEL AIRPLANES 2 Sheets-Sheet l INVENTOR BY yaw/ AW ATTORNEYS.

E- E- TURNER CONTROL F'OR MODEL AIRPLANES Nov. 24, 1953.

2 Sheets-Sheet 2 Filed May 2, 1952 INVENTOR I .iQW/M .5 Zak/v52,

ATTORNEYS Patented Nov. 2 4, 1953 UNITED STATES PATENT OFFICE CONTROL FOR MODEL AIRPLANES. Edwin Turner, Oxford, Miss.

Application May 2, 1952, Serial No. 285,588

6 Claims.

This invention relates to controls for model airplanes and more particularly to a control assembly which extends from the model airplane toa person controlling the airplane so that the,

airplane can be caused to perform a controlled flight around a person standing on the ground and holding the corresponding end of the control assembly. i

It is among the objects of the invention to provide an improvedmodel airplane control system whereby an operator standing on the ground can control the action of a model airplane in circular flight around the operator; which permits the model airplane to roll freely about its longitudinal center line while in flight without loss of control; which independently controls the rolling and pitching action of the model airplane; which is tangle-proof and so arranged that the control strings will not wrap around the model airplane while the latter is in flight; and which is simple and durable in construction, and positive and sensitive in operation.

Other objects and advantages will become apparent from a consideration of the following description and the appended claims in conjunction with the accompanying drawings wherein:

Figure 1 is a perspective view of a model airplane and control assembly illustrative of the invention;

Figure 2 is a top plan view of the airplane and control assembly illustrated in Figure 1 with portions of the airplane brokenaway to better illustrate the control assembly;

Figure 3 is a fragmentary cross sectional View on an enlarged scale on the line 3--3 of Figure 1;

Figure 4 is a transverse cross sectional view on the line 44 of Figure 3; I

Figure 5 is a fragmentary perspective view the airplane frame; and

Figure 6 is a fragmentary perspective view of the frame and a portion of the control assembly mounted on the frame.

With continued reference to the drawings, the model airplane has a body or fuselage generally indicated at H], wings Hand 12 extending from respectively opposite sides of the fuselage intermediate the length of i the latter, an engine and propeller assembly I3 mounted on the front end of the fuselage, and a tail assembly mounted on the rear end of the fuselage and including a vertical tail fin M, a rudder l5, horizontal stabilizers I6 and I1 and elevators l8 and I9.

. While a particular form of airplane has been illustrated for the purpose of disclosing the inventiomit-is to be understood that the invention may 2 i be applied to model airplanes of other forms suc as those having two ormore engines or two rudders, without in any way exceeding the scope of the invention. i

Ailerons 20 and 2| are pivotally mounted on the wings H and I2 respectively at the trailing edges of the wings and near the outer ends thereof and these aileronsare interconnected bylink and lever mechanism including bell cranks .22 and 23 pivotally mounted in the wings ll and I2 respectively and connected each at one endone to the aileron 20 and one to the aileron 2| intermediate the lengths of the ailerons and links 24 and 25 extending from the bell cranks 22 and .23 respectively toward the longitudinal center line of the airplane and connected at the innerends to one end of a bell crank 26 pivotally mounted in the fuselage ID of the airplane. The connection between theailerons 29 and 21 is such that when the links 24 and 25 are moved longitudinally in one direction one of the ailerons is tilted upwardly and the other downwardly and when thelinks 24 and 25 are moved longitudinally in the other direction the ailerons are reversely operated. Y a Y The airplane fuselage if! has a frame including a tubular intermediate portion 28 which extends forwardly and rearwardly of the inner ends of the wings II and I2 and to which the wings are securedat their inner ends and lever carrying frame sections 29 and 30 disposed at the front and rear ends of the intermediate portion 28 and secured to the latter in end to end relationship thereto.

The engine and propeller assembly I3 is mount- The frame section 29 includes four inner mem bers 32, 33, 3E and 35 of substantially identical construction and each having two legs, as indicated at 35 and 37 for the member 32, of elon-' gated, rectangular shape, joined along common edges and disposed perpendicular to each other, a flange 38 extending perpendicularly from the edge of the leg 36 remote from the leg 3'! in'a pendicularly disposed legs of the several mem -O bers constitute an inner box formation of substantially square cross sectional; shape; the fianges extend two from each side of therec tangular box formation with each two adjacentflanges in parallel and spaced apart relationship to each other and the tongues projecting from the flanges are arranged in mutually opposedpairs of spaced apart and substantially parallel tongues, therebeing three pair of. tongues. spaced apart longitudinally. of. each side. of. the. box formation and spaced outwardly from. the cor.- responding sides of the box formationby. the width oflthecor'responding flanges.

' Onagrouppf tonguesisdispbsed at the. front end; oft-the frame section 29. and. arrangedin p'ai'rswhich are..spaced apart at. angular intervals of. 9.0 degrees'aroundthe. front endof the. frame. section. and. a v circular band. 43- extends. around the outer ends .of thisgroup of tongues. andrec'eivesthe rear .endof the engineand .p'ror pellensction oftheairplane to which the band is.attached.by. suitable. means, such asthe screw. fasteners. illustrated in Figure 3.

Another. group. of tongues including the tongue. 42tis .disposed. at. the. rear end. of the frame. sec: tionand. arranged ..in.. pairs of tongues. with the. pairslspaced apart at angular intervals of 90- degrees around therear end of the framesectionland .an. annular ..band or-.ring .45 surrounds thelouterendsof this groupof tongues ,andrer ceivescthelfrontiend :of the intermediate .frame sectionl28-to which. the bandi45 is secured :by suitable means such as the screw fasteners 45:, alsogillustrated in Figure 3..

The... intermediate .tongues are disposed sub.-.. stantiallyat .the midlength location of the frame section and. arearranged inpairs spaced apart atv angular. intervals of 90. degrees around"; the. frame section. and. these. intermediate. tongues. are.providedc'withapertures,.as indicated at 45. solarran'ged. that the .aperturesin each; adjacent. pair of tongues are in alignment with eachtother... Aniannular band. or ring .41 surrounds the outer ends of the intermediate tongues and isspacecL at its frontand rearend from the front'and. rear bands, 43 and45 respectively.

Rocker. levers, as indicatedat .50, of: triangular or T-shape are disposed one betweeneaclrpair of,

intermediate-tongues.4 I. and have straight. edges adjacent. the.. outer endsof the...tongues.. These ITQOKQnlQVers are each. provided with an aperture.

d a ent e midlength location of its .outer. straight. edge, and are .pivotally connected to the. corresponding intermediate tongueaby pivotpinsa as indicated at extending through registering apertures in each.rocker lever and inthe. associatedpair Ofintermediate tongues. These rocker let; S arepivotally movable aboutindividual axes. wh ch lie substantiallyiin a plane perpendicular to ;the longitudinal center line .of the .airplane tuselage. I 0. and, are disposed radially of. the, an-.

mm; .i ing .orpband, 41.; Rods; asindicated .at. 52;; are' conhected attheil forward ends one toeach: 75.--,the. horizontal bar J1: of the..:control stick while:

4 of the rocker levers adjacent the inner ends of these rocker levers and are connected at their rear ends to a plate 53 of triangular or T-shape at spaced apart locations transversely of the plate and adjacent one end of the latter. At its other end the plate is pivotally connected to the bell crank 26 at the end of this bell crank opposite that to which the links 24 and 25 are pivotally Q9enes2te i,

The plate. 53; isniovable in.a fore and aft direction upon rocking movements of the rocking levers 50 and upon fore or aft movement thereof imparts longitudinal movement in a corresponding, direction to .the links 24 and 25 which in turn impart tilting movement to the ailerons 20 and 2i; tilting one aileron upwardly and the other Aflat ring is disposed in the space between and bears on the outer edges of the rocker levers SS -at the correspondingside of the plane ofzthe pivotalaxes of these..rocker levers. A: similar. flat-ring 56:is. disposed in the. space between the annular ring. or. band 41 and the annular. ring and-bears upon theouteredges of the rocker. plates- 5!] .at the. corresponding rear sideof. the. plane-ofsthe pivotalzaxes ofthe rocker levers.

The rocker levers are connected together for simultaneous movementthrough the-rods 52 and the plate .53 andwhen one of the rings is moved inwardlyrelative to the frame sectionZQ the rockerlevers will be rocked in one direction-and when the other ringv is pulledinwardly-therockerleverswill'be rocked in the opposite. direction. In thearrangement illustrated, when thenringl55 is. pulledinwardly the rocker leverswill .berockedin a direction to impart-a rearward movement .to. the plate 53-anda consequent raising of the left aileronand lowering of the.right aileron of theairplanewhereas, when the rear ring 551s pulled inwardly therockerlevers will be moved in a-direction to impart aforward movement toth'e. p1ate. 53-vvith av consequent-lowering of the left aileron-and raising of: theright aileron oftheairplane Axcontrol string 51'is secured to thering 55 and extends therefrom andasimilar control string fiiltislsecured to. the ring 56 and extends from the latter.

As stated above; the rear frame section 30 is similar-in construction-and arrangement to thefront frame section -29- and this rear frame section has front and rearfixed rings or bands 60- and 61 and anintermediate fixed-ring or band 62 and alsohas movable- rings 63 and 64 riding on the outer straightedges-of rocker levers-corresponding to the rocker levers 50in the-front frame SBGtlOIkZBs- The rocker levers in the rear frame section are connected-by rods 65to'the front end=ofatriangularor T-shaped plate 66 the-rear end of which-is connected to the elev-a tors l8 and IQ of the modelairplane so that alternati-ve-movement o-f therings 63' -'and 64 inwardly of theframesection-30 causes the elevators-to tilt upwardly cr -downwardly;

Controlstrings -61 and 68 are connected to therings-63 wand -64. respectively and extend -'therefrom. At their ends-remote from the airplane the control stringsare connected to a control stickJ 0 .in the. form of across having a normally horizontallydisposed bar 1 I and a normallyvertically disposed bar 12w- Thecontrol strings 51 and.5B.-.are-connected at their ends-remote from theairplane to the respectively opposite ends of assayed the strings 61 and 68 are connected at their ends remote from the airplane to the respectively opposite ends of the vertically disposed bar 12 of the control stick, as illustrated in Figure 1.

With this arrangement, complete and sensitive controlis maintained by the operator over the ailerons and'elevators of the model airplane while the latter is in flight and the airplane can rotate freely in the control rings 55, 56, 60 and BI to do barrel rolls and other aerobatics without foulin lthe control lines or causing them to wrap around the fuselage of the airplane.

The invention may be embodied in other specificforms without departing from the spirit or essential characteristics thereof. The present embodimentis', therefore, to be considered in all respectsas illustrative and not restrictive, the scopeof the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the'jlmeaning and range of equivalency of the claims are, therefore, intended to be embraced thereini What is claimed is:

- 1.' A model airplane and control assembly comprising an elongated frame, wings extending to respectively opposite sides of said frame intermediate the length of the latter, ailerons pivotally mounted one on 'each of said wings at locations spacedfrom said frame, link means interconnecting said ailerons for movement of the ailerons in respectively opposite directions, elevators pivotally mounted on said frame at one end of the latter, a first set of rocking levers pivotally mounted 'on said frame at angular intervals around the latter for rocking movements about axes disposed in a plane perpendicular to the longitudinal centerline of said frame, means connecting said rocking levers to said link means for movement of said link means in opposite directions upon rocking movement of said rocking levers in respectively opposite directions about the axes of their pivotal connections with said frame, rings surrounding said first set of rocking levers one at eachopposite side of said plane, a second set ofrocking levers pivotally mounted on said'frame at angular intervals around the frame and at a location spaced longitudinally of said frame from said first set of rocking levers for rocking movement about axes disposed in a second plane perpendicular to the longitudinal center line of said frame, means connectingthe rocking levers of said second set to said elevators for movement of said elevators in opposite directions upon respectively opposite movements of the. rocking levers of said second set about the axes of their pivotal connections with said frame, rings surrounding said second set of rockinglevers one at each side of said second plane, and control strings extending one from each of saidirings, said frame and said sets of rocking levers being freely rotatable in said rings.

2.: A- model airplane and control assembly comprising an airplane frame including a tubular intermediate portion and frame sections disposed one at each end of said intermediate portion and each providing apertured ears disposed intermediate the length thereof and at substantially equal angular intervals therearound, rocking levers pivotally mounted on said ears and disposed at substantially equal angular intervals around the corresponding frame sections, each of said rocking levers extending radially of the corresponding frame section and having a substantially straight outer edge and said rocking levers extending longitudinally of said rrafiie'and being pivotally connected to the corresponding ears adjacent the midlength locations of their outer edges, wings extending from respectively opposite sides of said intermediate frame portion, ailerons mounted one on each wing at locations spaced from said frame, link and lever means interconnecting said ailerons for tilting movements in respectively opposite directions relative to said wings, means connecting the inner ends of all of the rocking levers mounted on one of said frame sections to said link and lever means for movement of the latter in response to rocking movements of the associated rocking levers, elevators carried by said frame at a location spaced from said wings and pivotally movable relative to said frame, means connecting the inner ends of all of the rocking levers carried by the other frame section to said elevators for tilting movement of said elevators in response to rocking movements of the associated rocking levers, the pivotal connections between said rocking levers and said frame sections being disposed in corresponding planes perpendicular to the longitudinal center line of said frame, rings surrounding said frame sections and said rocking levers and disposed one at each side of each plane of the pivotal connections between said rocking levers and said frame sections, and control strings extending one from each of said rings for selectively moving said rings transversely of said frame and thereby imparting rocking movements to said rocking levers.

3. A model airplane and control assembly comprising an airplane frame including a tubular intermediate portion and frame sections disposed one at each end of said intermediate portion and each providing apertured ears disposed intermediate the length thereof and at substantially equal angular intervals therearound, rocking levers pivotally mounted on said ears and disposed. at substantially equal angular intervals around the corresponding frame sections, each of saidi rocking levers extending radially of the corre sponding frame section and having a substan-- tially straight outer edge and said rocking levers extending longitudinally, of said frame and being; pivotally connected to the. corresponding ears; adjacent the midlength locations of their outeredges, wings extending from respectively opposite sides of said intermediate frame portion, ailerons; mounted one on each wing at locations spaced. from said frame, link and lever means interconnesting said ailerons for tilting movements in: respectively opposite directions relative to said. wings. means connecting the inner ends of all off the rocking leversmounted on one of said frame sections to said link and lever means for move-- ment of the latter in response to rocking movements of the associated rocking levers, elevatorscarried by said frame at a location spaced from: said-wings and pivotally movable relative'tosaid' frame, means connecting the inner ends of all of the rocking levers carried by the other frame section to said elevators for tilting movement of said elevators in response to rocking movementsof the associated rocking levers,'the pivotal connections between said rocking levers and said frame sections being disposed in corresponding planeslperpendicular to the longitudinal center line of said frame, rings surrounding said frame sections and said rocking levers and disposed one at each side of each plane of the pivotal connections between said rocking levers and said frame

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