DE2050929C3 - Propeller assembly - Google Patents

Description

With the second flow device, all three rotor areas rotate in the same ₄ o meaningfully and at the same angular speed. It is therefore only a rotor in which the rotor blades in the inner area are independent of

ih ihe ^ gen

the rotor blades inside

The invention relates to a Luftsehrau- those in the middle of their respective ben arrangement, especially for rotary wing flight longitudinal axes "rfrehtar smd κ ^ that the rotor, with two coaxially arranged, opposing 45 optionally in ^ ⁵ ^^^ _η 3 ° 5 _3ηη "u ^ m _{t the} rotating rotors, of which the rapid a rotor we found lung can en ^rf and then nu, with AEM slide, to the rotor axis within the other rotor ^

Α German patent specification 128658 is a dcm'e, in this ^^^ 1 dchÄ propeller arrangement of the ₅ o sam revolving Roto, ^ ™ ^ha ™ ^ See "3 type known, in which two coaxial rotors in two de torques uncountable levels are arranged one above the other ^ In ^^ ^d ^ S _h ^ _ln ^ of this known propeller arrangement, seeing ^lu "^{> ine} " = ^cn ^ ' ^e _{... the} rotor blades are constricted by the middle area sucked in by the upper, outer rotor tew between the Ro orWat air flow after passing through the rotor 55 tem of the middle *? ^Kl £ * ™ ** ™ ^e £ ** t ™ t? _ together and thereby at least hits the au- Bcre.chs have be. ^ * ^ ™ ^^ ™ _ά ^ ßcren areas of the underlying, inner rotor, d.e_ Turbinens nonlung von J " ^S lromung through tors. The middle rotor area sucked in by the lower, inner rotor and this " ^m ^ ⁿ 8 ^v ™ S.rönunm is therefore largely influenced by the upper flow through the inner rotor to the outer rotor and in an unfavorable manner 60 separate, and not de task £ ™ J £ "i ^ affected. In the known Luftschraubenan- separate rotors to re fu _ß ^ ^. therefore, this order does not bc arbeilen the two rotors as known flight Gera, cmc ^ nipcnsation desvom Ko

iriichti-t. With the known Luflschraubcnanord- not achievable.

The invention is based on the object of designing a rotatable wing aircraft that can be used in a harmful manner.

The propeller arrangement explained at the beginning is suitable.

Way to create, soft a structurally simple. The propeller arrangement is advantageous.

and secure mounting of the outer rotor ensure the invention is designed so that the struts

Constantly and as kotoranordnunp in inherently stable, precision 5 are designed as flexible connecting means that

.sion-controlled rotary wing aircraft are usable under such low voltage that they are at the

is. Rotation of the outer rotor practically no centri-

According to the invention, this task will have to absorb the structural forces of the rotor. The triggers that the inner and the outer rotor in a design of the struts as flexible connecting means Eb nc and the outer rotor over the inner io is possible because the boundary wall the Rotor to both ropes of the rotor level encompassing centrifugal forces occurring during the rotation of the rotors is suspended on the rotor hub and that galkriven the individual rotor blades in itself Blades of the outer rotor in itself known takes, so that these centrifugal forces do not have the Way must be derived from at least one ring-shaped limiting strut towards the axis of rotation, tongue wall are attached. 15 The struts can then be particularly small

The propeller arrangement according to the invention can be rened. An advantageous development of the eifin-

has a propeller arrangement according to the present invention which is essential compared to the state of the art.

Advantages c. In the case of the propeller according to the invention, achieved that the connecting means made of wire

The inner rotor and the outer ropes are approximate.

Rotor in one plane. This ensures that a stable and robust structure of the

The currents of the two rotors do not result in the propeller arrangement in accordance with the

harmful way affect each other and in their development is also achieved in that

can affect the efficiency. The struts are designed as rods,

the arrangement of the two rotors in one plane A particularly advantageous embodiment of a

if the two rotors result in an air screw arrangement lying in one plane,

Gendes gyro system, which is achieved in its behavior that the struts of the outer rotor on

like a single top lying in this plane on one side of the rotor plane with the drive shaft

behaves. The propeller assembly according to the invention and the struts on the other side of the rotor

tion can therefore be used, for example, for a plane connected to a freely rotatable turntable

the, in the area of the common axis of the rotors 30 are.

and the center of gravity of a car in the rotor plane. In the following, exemplary embodiments of the bine are to be provided and the car to be arranged in this area of the invention in conjunction with the drawing. In this way, if the letters,
bine via a support ring arrangement triaxial carda- It shows

niche suspended in the propeller assembly 35 F i g. 1 an aircraft with two rotors one

will create an aircraft that in flight, like a propeller arrangement, is located in its center

inherently stable gyro behaves and encircle the housing in its flight positions,

can be controlled by the precession of the gyro, where F i g. 2 shows a similar missile in axial direction

the cabin is kept stable in its position, viewing direction,

can. In the known airborne vehicle discussed at the beginning, a missile with the two rotors,

This is not possible with screw arrangements because the gimbal mounted inside the housing

dorl the two rotors in different levels is a suspended cabin.

gene and thus torques from the two rotors. According to FIG. 1, the aircraft shown here the common rotor axis (which at the same time gyro through a housing I with an inner rotor 2 and axis is), the vector components 45 an outer rotor 3 is formed. The inner rotor th have perpendicular to the rotor axis. This consists of the two boundary walls 4 and 5, In the case of such an aircraft, there would be a running precision between which the blades 6 lie. The welcome Caused, and there would be an unstable tongue walls 4 and 5 are cylindrical and Flight behavior. The propellers according to the invention have such a height that they the blades 6 somewhat arrangement combines the favorable properties so protrude, whereby a rotation of the rotor 2 a complete torque compensation with ho pressure compensation on the sides of the blades 6 is practical hem efficiency and precisely controllable gyro is prevented. The inner rotor is via arms 7 behavior. The support members of the outer rotor are connected to the housing 1, which is connected to the Rosind rotates with the air screw assembly 2 according to the invention and is designed as a body of revolution tion designed as struts, which is the inner rotor 55. In the axial direction of the housing 1 is on the encompass. These struts can, for example, each have a pivot bearing 8 and 9 on wire ropes as the upper and lower side be designed or as thin rods. Brought in, which by one inside the Geiiäujedem In the case of these struts only the drive motor located in the opposite direction to the drive motor record the weight of the outer rotor in the stillland Rotation of the housing 1 and thus of the rotor 2 in and the torque of the drive is shifted to the ßn rotation. On the two pivot bearings 8 Can transfer rotor. This thinly dimensioned and 9 hangs over the inner rotor 2 encompassing th struts interfere with a rotation of the outer strut of the rotor 3. The struts are here as wire rotors the slrosing ropes 11 and 12 flowing towards the inner rotor are formed. The wire ropes 11 and muiig practically not, because these thin struts offer practically no air resistance and have only 12 have very little air resistance. All in 65 only to exert a pull on the rotor 3 in order to Above all, the air screw arrangement according to the invention is to be set in rotation. The rotation of the With a simple structure, it is light in weight, but rotors3 has to cope with centrifugal forces high efficiency and is therefore aiifue-

took. Between these boundary walls so that these frictional forces are now balanced the sheets 15. The possibly considerable can or ' optionally the cabin 20 in a covering as a result of centrifugal forces it can be turned from the right direction the rotors 2 and 3 withstood themselves, so that the hcrausragenden from the outer ring 27 downwards Wire ropes ίΐ and 12 and the arms 7 in this regard 5 axis 31 a fixed magnetically connected with this are unencumbered. The wire ropes 11 and 12 shear driver 32 is provided, which serves on and the arms 7 only have a corresponding torque from the shaft 31 1 and the Drchlagem 8 and 9 outgoing to exercise when the axis 31 by frictional forces in To transmit torques as well as when floating-undesirably carried along or when the aircraft set the io maneuvering acting on the housing 1 in a certain direction Balance gravity. In the case of flight it is supposed to be grain. The magnetic driver 32 is made In addition, there are forces due to the air resistance made of magnetizable material. electrical not shown for reasons of clarity

If now the two rotors 2 and 3 in the one coils more magnetic and acts with the relevant

arrow direction drawn are rotated, so he 15 housing part 10 or the turntable 37 together,

Every rotor produces for itself a lift that is completely Here it should only be pointed out that the

regardless of the buoyancy of the other outer ring 27 upwards against the housing 1

The rotor is, with the roller bearing 33 being supported in each case. The housing 10 is still

Practically do not disturb air currents. The buoyancy is each supported by the roller bearing 34 on the axle 31.

The rotor adds up to that of the other -: <i The inner rotor 2 is placed here directly on the housing

Ren. By the opposite direction of rotation and the choice 10, so that this is its inner boundary wall

a corresponding angle of attack of the blades 6 forms.

and 15 can thereby be used on the two rotors 2 The rotor 3 is sound via the wire ropes 35 and 36 10 torques exerted equal, both with the hub 30 and with one below that the plate 37 located in the interior of the housing 1 is connected to 25 of the housing 10, the counter torques cancel each other out. This part 37 is on the roller bearing 38 on the

Fig. 2 shows a similar construction, mounted on the axle 31. The axis 31 is normally

only a slightly different type of suspension of the still, if not the cabin 20 in a different direction

both rotors is selected. The outer rotor 10 device is to be rotated. There is still on axis 31

The take-off and landing gear hangs here on six upper wire ropes 16 and six 30 at their lower end

lower wire ropes 17. The inner rotor 2 is also attached 39.

if suspended from the housing 1 by wire ropes, when the two rotors 2 and 3 rotate in opposite directions via six wire rope pairs 18, 19. In the current sense, the aircraft receives the necessary lift function of the aircraft shown in FIG. the housing 10 about the axis corresponds completely to that according to FIG. 1. 35 ^se B rotates, but with the outer ring 27 and you

Of course, instead of the wire ropes, I cannot take the car 20 with it, since the outer ring struts are also used, which essentially 27, as I said, borrowed from the roller bearings 33 and 34 represent a rigid connection. the housing 1 is supported.

In FIG. 3, an aircraft is shown in which the aircraft according to FIG.

can fly in a gimbal 40 different directions inside the housing 10, i.e. thus ma

suspended cabin 20 is attached. The cabin 20 rests can be navigated, in this case the precession is de _; .

exploited over the two stub axles 21 and 22 in Drehia gyroscope. The two rotors 2 and 3 sim:

like 23 and 24 of an inner ring 25, which in turn is dimensioned so that their counter-torque

has stub axles 26 offset by 90 'therefrom, which largely or completely compensate. Independent

in corresponding rotary bearings of an outer ring 27 45 depending on it, however, it is possible, above all, by

are stored. Due to the mutually perpendicular mass distribution on the two Ro

axes A and C in connection with the ϊη- Ioren2 and 3 a resulting gyroscopic effect / u

nenring 25 and the outer ring 27 results in a achieve. This gyroscopic effect is now used to control

Cardanic suspension used for the inside of the aircraft. This is done because

the rings located cabin 20, so that this of 50 by that perpendicular to the axis B a torque

Following gravity, the ro- ment is also exerted at an inclination, which therefore strives to reduce the axis

always to tilt tationsachse B in vertical position comparable se B. According to the known gyroscopic

remains. kung then gives way to the axis B perpendicular to the

The outer ring 27 is now in the axis of rotation they acting torque from what the known

of the two rotors 2 and 3 rotatably mounted, so that 55 th effect of the gyroscope corresponds. The movement,

with the rotation of the outer ring 27, the cabin 20 into which the missile acting as a gyro moves

can be rotated in any direction. is then the precession of the top. Takes

On the upper side of the rotatable around the axis B the aircraft, as a result of this precession with the housing 10, is seated a drive motor 28, from which the axis B is inclined in the air so that the drive shaft 29 protrudes upwards, which protrudes into the 60 acts in addition to the lifting forces of the roto hub 30. By the motor 28 both ren 2 and 3 a force component in a horizontal torque on the housing 1 as well as in the ent direction, namely the direction in which the opposite direction of rotation on the drive shaft 29, the axis B is inclined, so that the missile in and thus the hub 30 exerted so that the rotor moves this direction forward. The aircraft ren 2 and 3 are rotated in opposite directions. 65 remains inherently stable in this position and moves.The aircraft thus receives its lift without moving continuously in the relevant direction that a torque is exerted on the outer ring 27 until a new rotation acting on the axis B , apart from occurring frictional forces. moment a corresponding reversal takes place.

In order to bring such a torque into effect on the axis B , one can, for example, shift weight in the outer ring 27 or the inner ring 25, which would otherwise express itself as a torque on the axis B due to gravity. However, this requires weights that would unnecessarily load the aircraft. Another possibility for generating such a torque is to be seen in the arrangement of flaps in the rotor blades, the flaps of diametrically opposite blades being controlled cyclically in opposite directions during the rotation of the rotor, whereby a stronger lift on one side of the rotor than on the opposite

Page is generated, which acts in a corresponding torque on the axis B , namely in a direction on the axis B, which runs as a connection via the actuated flaps. As a result of the precession, the axis B then deviates perpendicularly to the torque, i.e. perpendicular to the connection between the actuated flaps. The collapses are adjusted cyclically as their angle of rotation is reached, until the resulting effect of the torque on the axis results in a corresponding inclination of this axis, so that the missile is in a corresponding direction of flight occupies.

1 sheet of drawings

Claims (5)

The individual rotor blades are now seated on radial arms attached to the shaft. These patent claims: S en A me rn ^ fen bd a rotation of the Roto- racidieu «■■ c ^ £ otor leaves produced _{1. Propeller arrangement} , in particular for the entire ^ ^. ^ Απηβ ^^ rotary wing aircraft, with two coaxially arranged 5 Fhehkratte f " ¹ " ⁶ "" _who ionized and received, gceensinnig rotating rotors, from which therefore senr ^swll \ Weight In addition, the nen of one rotor is arranged radially to the rotor axis inside an unfavorable non ^ ^ _{due to its} necessary half of the other rotor, that arms dei; ot> er ^ ^ ^^ ^ ^ characterized by that the inner strong dimension «fe _{under Ro {or} ^ (2) and the outer (3) rotor lie in one plane Roto, s the flow« ^^ _wiedcrum gene and the outer rotor (3) on the inner current forming air £ »™ 'environmentally _{R and (j} rotor (2) on both sides of the rotor plane of ^{w' rkun} £ ^ ^d ^ is deteriorated. Ins.egreifende struts ( 11, 12; 16, 17; 35, 36) on the entire _ekannte ^ro ^ ^ ™ _c ^V _b ^e Luftschraubenän-Rotornabc is suspended and that the sheets including seen "* this De ^. (15) of both rotors (2, 3) in a known 15 order by, ihan. ^ Use in business At least on a ring-shaped ^boundary "? ¥" nt / hiren rotary wing aircraft not zuaswand (13, 14) are attached. Shank part usable urine _B Bb 2. Propeller assembly according to claim 1, suitable. Ausiceschrift 1 288 924 is characterized in that the struts (11, 12; from the dcutsJ en AxMc ^ 16, 17; 35. 36) as a flexible connecting device *> Rotary flights -Flugg rat got, ^. ^ are formed, which under such low tension au shows, ^ r three kon * nt fc ^ b ^. ^ ^ ^ stand that it has at the rotation of the outer Ro-. ° he utterly Bern _t ors (3) practically no centrifugal forces of the Ro- auScn protrudeJ "Turb" cnsch ^ ^ ^ ^ tors have to take. am ^AuL f, ⁿ TU; ' get sleepy. This turbine 3. Propeller arrangement according to claim 2, = 5 mungsm.tte du η btau ^ ^chIa S ^l ; . _{nd bcfcsti} characterized in that the connection look e> η! nd ^^ f ^^^ chsc run, medium made of wire ropes. ^ l ^ r snezS ^ Form of the rotor di, - 4. Propeller arrangement according to claim 1, at e.ner specicl en α e circular ring wall, characterized in that the struts (11, 12; ™ ^^^^% M * nns ™ d with gerin-16, 17; 35, 36) designed as rods s.nd. 30 ° ^k "f _R ™ _by rotor provided that the in- 5. Propeller arrangement according to one of the like radius in atm mn t, Rotorbe claims I to 4, characterized in that «first Rotorberc.ch ν £ ^" ¹ J; the struts (11, .16 35) of the outer rotor (3 ) smelled ^ enn ^ the ^ Ic ™ ^ tortarcj * be ^ ^ ^ on one side of the rotor plane with the on rotor blades, mc ^{ZWI!> 1} - "^ Drive shaft (29) and the struts (12, 17, 36) mounted on 35 neren Krcisringwand the other side of the rotor plane with a free gate area consists of κοιογ rotatable turntable (37) are connected. de "