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Publication numberUS1761053 A
Publication typeGrant
Publication dateJun 3, 1930
Filing dateJun 11, 1928
Priority dateJun 11, 1928
Publication numberUS 1761053 A, US 1761053A, US-A-1761053, US1761053 A, US1761053A
InventorsRystedt Ingemar K
Original AssigneeRystedt Ingemar K
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Airplane
US 1761053 A
Abstract  available in
Images(5)
Previous page
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Claims  available in
Description  (OCR text may contain errors)

I. K. RYSTEDT June 3, 1930.

AIRPLANE 5 Sheets-Sheet Filed June 11, 1928 v I \I. a v 3% ATTORNEY 5 Sheets-Sheet 2 l. K. RYSTEDT AIRPLANE Filed June 11, 1928 June 3, 1930.

Jun; 3,1950.

I. K. RYSTE DT AIRPLANE Filed Jux xe 1 1, 1928 5 Sheets-Sheet 3 June 3,1930. K, RYST DT 1,761,053

AIRPLANE Filed June 11, 1928 5 Sheets-Sheet 4 Patented June 3, 1930 fumrso STA-res rA'raun or Flou- INGEMAR-K. RYS'IEDT, OF DAYTON, OHIO AIRPLANE Application filed June 11,

ther development of the fundamental principle embodied in the airplane construction set forth in United States Letters Patent No.

1,075,863, issued to me on October 14, 1913.

The invention is directed to a solution of the problem of applying to airplane construction certain principles of construction I for accomplishing natural flight, that is to say, the provision of nature in the bodies of birds which enables flight'with far greater perfection than has been so' far attained in mechanical flight.

The particular objects of the invention consist in the provision of added means for lifting the plane into the air more directly, for

attaining elevation in shorter time and for sustaining the airplane in the air at slower forward speed than is possible with airplanes of the usual construction; the ,samemeans serving also for maklng a more direct descent, at slower speed and landing within a smaller prescribed arean Incidental improvements to the main features of the invention consist in applying a parachute attachment in a novel manner to the air plane as an element of safety for effecting a forced launching; in providing means for preventing or minimizing the .accumula tion of ice on vital portions of the planes and rudder as a measure of safety in making a continuous flight over long distances; in providing means for retracting the landing gear within the body of the airplane; a novel construction of the rudder which has a wider range of movements and more responsive in function than the usual type of rudder; also a wider range of adjustment is provided for the laterally extended planes which increases the effectiveness of the planes for maneuvering the airplane.

The improved airplane is also capable of taking off and landing on the water and to be otherwise operated as ahydroplane.

In the preferred construct-ion the airplane is provided with a forward driving propeller and a plurality of rotatable lifting planes,

rangements for effecting mechanical flight 1928; Serial No. 284,585.

the propeller and the planes being operated by separate motors, the distribution of weight of the structure as a whole being such that the equilibrium of the airplane will be maintained with one or the other of the motors inoperative.

To the end of attaining these objects of the invention the structureof the airplane consists of various novel mechanisms and arwith the added range in: maneuvering the plane and increased safety herein claimed.

In the accompanying drawings which servefor illustrating the invention in a preferred construction:

Fig. 1 is a View in perspective of the airplane;

Fig. 2 is a view in side elevation with the body of. the plane shown in section;

Fig. 3 is a cross sectional view on line 3--3 of F ig.-2, including a modification;

Fig. 4 is a detail view in end elevation of a double unit of the rotatable planes and mo, tor;

Fig. 5 is a detail view in elevation of the controls for the lateral planes;

Figs. '6, 7 and 8 are detail views of the rudder;

Fig. 9 is a detail in side elevation of the rotatable planes and motor;

Fig. 10 is a detail view of one of the lateral planes and controlling mechanism Fig. 11 is a cross sectional View of one of the lateral planes taken on line 1111 of Fig. 5;

Fig 12 is a detail sectional view of a feature of the exhaust system taken on line 1212 of Fig, 5.

As shown in the drawings, the body or fuselage'of the airplane consists of a hullshaped metal housing 1 including various frame structures 2 for supporting the oper able parts. At the front a propeller 3 and motor 4 of well known construction are arranged in the usual manner in airplane construction.

The pilots compartment is glass enclosed as indicated at 5 and is entered at the side 'means of a door 6; which also servesas an entrance to the interior of the plane, other" glass covered portions 7 being provided for 00 fuselage at the rear being glass covered also for affording a wide range of view rearward.

The landing ear consists of front and rear trucks, there being preferably two pneumatic wheels 9 to each truck which are supportedon pivoted frames 10 operable by a lever 11 adjacent the pilots seat, rods 12-13 and arms 141516 which connect the rods to the respective trucks, the connections serving for projecting and retracting the landing gear.

in the operation of the plane. The dotted outlines 17 indicate water-tight walls over the landing gear for adapting the plane for taking off and landing on water. When the plane is adjusted for continued flight the landing gear is in retracted position as indicated in Fig. 2.

The lateral planes 18 may be of any suitable construction. As here shown, the planes are of hollow metal formation being cambered on their under side and convexed on their upper side, the front edge of the wings being formed on a suitable radius to give the desired depth to the planes, the upper and lower walls being tapered rearwards. The planes are supported ,pivotally' forward of their inner edges on hollow journals 19 operable in bearings 20 on the frame structure 2, and are connected by interposed links 21'22'23 to a manual control for each plane consisting of a hand wheel 24 forwardly adjacent the pilots seat and a worm and gear connection 25-26enclosed inacasing 27 which serves for giving a highly responsive, wide range angular adjustment of each plane on its journal 19 independently of the other plane which increases the effect of the lateral planes in controlling the airplane in other than straight away flying, as in maneuvering the plane in turning, changing the direction of flight, or for retarding the speed for landing.

The airplane as here shown is provided with two sets of horizontally disposed, ro-

tatable planes in axial alignment one plane with another of the opposite sets, the planes being interposed axially between the pilots compartment and the rear end of the fuselage and confined generally laterally and vertically to the stream lines of the over-all structure of the airplane.

Each unit of the rotatable planes consists of a plurality of planes 28 constructed of any suitable material, as wood or hollow metal,

the planes being convex on their u per surface, cambered or concavical wit a pronounced curve on their under side and inclined at a suitable angle rearward for effecting the required tangential lifting force or torque of the planes. The planes are supported in relatively fixed relation on opposite spoked ends 29, the open cylindrical structure as a whole being rotatable on shafts ing the drive shaft to shaft 30 upon which the plane is mounted. The planes of each set are driven in inverse direction one to the other, each plane rotating around a semicircular hollow body 35 supported on shaft 30 and extended between the ends 29, the greater portion of the body being-below the cen- 'ter of rotation of the. planes. The lower portion of each unit of the plane's is enclosed in a semi-circular casing 36, there being the required clearance between the bodies 35 and the covering casings 36 for the free movement of the' planes.

Operation of the rotatable planes produces an upward lift on the airplane of sufficient force to take all or part of the load off the lateral planes 18 and the forward driving propeller 3 in ascending or descending regardless of the forward speed, the rotatable planes having the further effect of stabilizing the plane fore and aft and maintaining its equilibrium at relativtly lower speeds than is possible with airplanes of the usual construction.

Both motors 4 and 31 are suitably connected to fuel supply tanks 37 supported in shock absorbing material 38 and enclosed between asbestos covered walls 39 adjacent the passenger compartment and the casings 36.

The rudder 40 of the airplane, as here shown, is flat, generally rectangular-shaped and is connected to the rudder shaft 41 by a universal joint 42, the shaft 41'bein connect ed to therudder control lever 42 ad acent the pilots seat by interposed rods 43-44 and levers 4546 and compensating joints 47-48 so arranged that universal an thereon when flying in wet and freezing.

weather, thus to provide a further safeguard to the operation of v the airplane. The connections for conducting the exhaust to the lateral planes consist of a pipe line 51 leading from the motor to the opposite planes, the lines leading to chambers 52 which discharge through the hollow journals 19 upon whichthe lar adjust- -ments of the rudder can be e ected, within planes are-mounted into the forward portion of the planes, the journals bein suitably apertured as indicated at 53 for distributing the heat in the planes, the exhaust from the planes being through a series of ports 54 along the rear edge of the planes. The discharge to the rudder is into a jacket 55 which encloses the universal joint 42 circumferentially, and thence through a series of ports 56 over the adjacent surfaces of the rudder.

Opposite parachute structures 57 may be attached, as shown in Fig. 3, along the opposite sides of the airplane below the plane of the lateral planes 18-, the parachutes as collapsed being arranged in plural folds extending fore and aft and conforming to the adjoining surface of the airplane, the parachutes being spaced one from another on fold.

lines 58 to provide clearance for the landing gear 9. Wire cables or struts 59 are suitably arranged in the folds for supporting the parachutes when the same are released and opened for effecting a landing, the parachutes serving more especially for sustaining the airplane for making a gradual descent in an emergency when a normal landing cannot be accomplished. Any suitable releasing devices as the clasps 60 releasable by pulling a cord 61 adjacent the pilots seat may serve for supporting the folded parachutes and for releasing the same for emergency use.

Certain of the detail structure of the airplane as herein shown and described is shown more or less conventially for illustrative purposes, my invention relating more especially to fundamentals or principles of construction as embodied in the rotatable lifting planes in their correlation to the forward driving propellerand the lateral planes, and the wide range of adjustments of the lateral planes and the rudder for overning the movements of the airplane. is far as I am aware the principles of airplane construction set forth in my issued patent herein referred to and the further amplification of new principles and improvements of the earlier constructions are broadly new in the art. I desire to claim the same broadly therefore, as to the new principles and as to new structure herein presented and defined and comprehended in the appended claims.

I claim as my invention:

1. An airplane including a forward driving propeller, a stream line fusela e, a semicylindrical housing, open upwar intermediate the ends ofthe fuselage substantially within the plane thereof, and a rotatable plane operable in the housing, and opposite laterally extended stationary planes intermediate the ends of the rotatable plane.

2. An airplane including a forward driving propeller, a stream line fuselage, a semicylindrical housing, closed at its ends and under side and open upward, intermediate the ends of the fuselage substantially within the plane thereof, and a plurality of planes rotata le as a unit in a suction relation in said housing, and opposite laterally extended stationary planes intermediate the ends of the rotatable plane.

3. Anairplane including a forward'driving propeller, a stream line fuselage, a plurality of opposite semi-cylindrical housings, closed at their ends and under sides and open upward, intermediate the ends of the fuselage onopposite sides of its axial center substantially within the plane thereof, and. a plurality of planes rotatable as a unit in each housing in synchronized operation one plane with another, and opposite laterally extended stationary planes intermediate the ends of the rotatable plane. r

4. An airplane including a forward driving propeller, a stream line'fuselage, a hollow, closed housing intermediate the ends of the fuselage substantially within the plane thereof, a semi-cylindrical housing arranged under, spaced from and enclosing thehollow housing, a plurality of planes rotatable as a unit through said space between the housings in suction relation therewith, and opposite laterally extended stationar planes intermediate the ends of the rotatab e plane.

In testimon whereof I 'aflix m signature.

KNGEMAR K. R STEDT.

Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2459470 *Apr 5, 1944Jan 18, 1949Swennes Benjamin AMotor vehicle fuel tank
US2469106 *Jan 28, 1944May 3, 1949United Aircraft CorpLanding gear for aircraft
US2561291 *Jun 26, 1947Jul 17, 1951Rethorst Scott CRoadable aircraft
US3801047 *Feb 4, 1972Apr 2, 1974Wendros CoOmnidirectional aircraft
US4390148 *Mar 6, 1978Jun 28, 1983Wave-Rider, Inc.Rotary wing device
US5954295 *Feb 17, 1998Sep 21, 1999Olson; Virgil DaleLift generation by counter-rotating line vortices
US6007021 *Nov 18, 1997Dec 28, 1999Tsepenyuk; MikhailFlying apparatus for a vertical take off and landing
US7370828May 4, 2005May 13, 2008X Blade Systems LpRotary wing aircraft
US8727265 *Apr 5, 2012May 20, 2014Airbus Helicopters Deutschland GmbHHelicopter with cycloidal rotor system
US20120256042 *Apr 5, 2012Oct 11, 2012Eurocopter Deutschland GmbhHelicopter with cycloidal rotor system
CN1738743BDec 18, 2003Oct 27, 2010Iat21创新航空技术有限公司飞行器
EP2511177A1 *Apr 11, 2011Oct 17, 2012Eurocopter Deutschland GmbHHelicopter with cycloidal rotor system
WO2004054875A1 *Dec 18, 2003Jul 1, 2004Amx Automation Technologies GmAircraft
WO2005049422A2 *Nov 15, 2004Jun 2, 2005Joerg ArnoldAircraft
Classifications
U.S. Classification244/9, 244/102.00R, 280/832, 244/135.00R
International ClassificationB64C39/00
Cooperative ClassificationB64C39/008
European ClassificationB64C39/00C3