SE446966B

SE446966B - FLYING MACHINE

Info

Publication number: SE446966B
Application number: SE8103949A
Authority: SE
Inventors: H Jordan
Original assignee: Tech Geraete Entwicklung Ges
Priority date: 1980-07-02
Filing date: 1981-06-24
Publication date: 1986-10-20
Also published as: FR2486020A1; JPS6140600B2; FR2486020B1; DE3124525A1; SE8103949L; CA1160612A; JPS57138500A; IT8148793A0; DE3124525C2; IT1142812B

Description

44s 966 ett styrorgan för flygmaskinen. Anslutningen åstadkommas via en i huvudsak vertikal axel 7, vilken passerar genom en bär- platta 8 för drivenheten 2. Bärplattan 8 ligger under driven- heten 2, är roterbar relativt denna drivenhet och bildar den inre omkretsen i den ringformiga öppningens 4 nedre del. Pro- pellern 3 befinner sig på avstånd över bärorganets 1 övre sida. 44s 966 a control means for the aircraft. The connection is made via a substantially vertical shaft 7, which passes through a support plate 8 for the drive unit 2. The support plate 8 lies below the drive unit 2, is rotatable relative to this drive unit and forms the inner circumference in the lower part of the annular opening 4. The propeller 3 is spaced above the upper side of the support member 1.

Ett första styrklafforgan 9 är anordnat omedelbart över den ringformiga öppningen 4 och ett andra styrklafforgan 10 är an- ordnat inom den ringformiga öppningen 4 under det första styr- klafforganet 9. Det övre styrklafforganet 9 är anslutet till drivenheten 2 endast vid sin inre periferi, medan det undre styrklafforganet 10 är anslutet till (samt uppbärs av) å ena sidan bärorganet 1, och å andra sidan drivenhetens 2 bärplat- ta 8. Varje styrklafforgan 9, 10 består av ett flertal styr- klaffar eller styrskovlar 11 som är vridbara kring en i huvud- sak horisontell axellinje och som, med hjälp av icke i detalj visade reglerorgan, såsom elektriskt eller hydrauliskt manöv- rerade styrdon,kan inställas var för sig eller gemensamt. In- ställningen består i en vridning kring respektive axellinjer och i synnerhet kan styrklaffarna i varje styrklafforgan regleras gemensamt. Styrklaffarna eller -skovlarna i de kransformiga styr- klafforganen förlöper radiellt relativt den ringformiga öppningen.A first guide flap means 9 is arranged immediately above the annular opening 4 and a second guide flap means 10 is arranged inside the annular opening 4 below the first guide flap means 9. The upper guide flap means 9 is connected to the drive unit 2 only at its inner periphery, while the lower guide flap member 10 is connected to (and supported by) on the one hand the support member 1, and on the other hand the support plate 8 of the drive unit 2. Each guide flap member 9, 10 consists of a plurality of guide flaps or guide vanes 11 which are rotatable about a mainly horizontal axis and which, by means of control means not shown in detail, such as electrically or hydraulically operated controls, can be adjusted individually or jointly. The setting consists of a rotation about the respective axis lines and in particular the guide flaps in each guide flap member can be adjusted jointly. The guide flaps or vanes in the ring-shaped guide flap members extend radially relative to the annular opening.

Det övre styrklafforganet 9 har mindre ytterdiameter än det nedre, men detta är inte avgörande. Dimensionerna kan likaväl vara identiska, eller förhållandet omvänt. Också styrklaffor- gan med styvt anslutna styrklaffar kan användas.The upper guide flap member 9 has a smaller outer diameter than the lower one, but this is not decisive. The dimensions can still be identical, or the relationship reversed. The control flaps with rigidly connected control flaps can also be used.

Bärplattan 8 kan ersättas av vilken som helst annan bärkon- struktion, såsom en ram, ett hölje e.d., och den kan med hjälp av lager vara roterbart monterad på axeln 7.The support plate 8 can be replaced by any other support structure, such as a frame, a housing or the like, and it can be rotatably mounted on the shaft 7 by means of bearings.

Flygmaskinen fungerar på följande sätt: Luften sugs bort från bärorganets 1 övre sida av propellern 3. »v Därigenom uppstår en cirkelformig luftrörelse med stor turbu- lens. Den cirkulära luftströmmen ledes till det första, övre ¿ styrklafforganet 9. Där neutraliseras vridmomentet och delvis ledes nedåt. Luftströmmen träffar nu det andra, undre styr- 446 966 klafforganet 10. Där uppstår en-i huvudsak vertikal, nedåt rik- tad och i hög grad laminär luftström. Detta medför mycket kraf- tig aerodynamisk lyftkraft, eftersom luftströmmen praktiskt ta- get förlöper vertikalt. Motorn eller drivdonet 2 samt hytten 5, som är fästa till varandra via den styva axeln 7, är stationära.The airplane operates as follows: The air is sucked away from the upper side of the propeller 1 by the propeller 3. »v This creates a circular air movement with a large turbulence. The circular air flow is led to the first, upper ¿control flap member 9. There the torque is neutralized and partly led downwards. The air flow now hits the second, lower control member 10. There arises a - mainly vertical, downwardly directed and highly laminar air flow. This results in very powerful aerodynamic lifting force, as the air flow practically runs vertically. The motor or drive unit 2 and the cab 5, which are attached to each other via the rigid shaft 7, are stationary.

Propellerns rotationsriktning visas av pilen 12 och bärorganets 1 rotationsriktning, som i beroende av styrklaffarnas läge kan vara samstämmig med propellerns eller motsatt därtill, visas av pilarna 13.The direction of rotation of the propeller is indicated by the arrow 12 and the direction of rotation of the support member 1, which depending on the position of the guide flaps may be consistent with the propeller or opposite thereto, is indicated by the arrows 13.

De till bärorganet 1 och till den roterbart anordnade bärplat- ta 8 anslutna styrklaffarna 11 medger att variera bärorganets 1 varvtal och att öka den på detta varvtal avhängiga gyrosko- piska effekten, varigenom flygmaskinens stabilitet kan påver- kas.The control flaps 11 connected to the support member 1 and to the rotatably arranged support plate 8 allow to vary the speed of the support member 1 and to increase the gyroscopic effect dependent on this speed, whereby the stability of the aircraft can be affected.

Under flygningen förblir hyttdelen inklusive styrningen allde- les stationär. Denna omständighet är speciellt viktig när flyg- maskinen skall användas för transport av passagerare. Överföring av styrfunktionen underlättas av drivenhetens och hyttens fasta förbindelse med styrorganet medelst den styva axeln.During the flight, the cabin part, including the steering, remains completely stationary. This circumstance is especially important when the aircraft is to be used for the transport of passengers. Transmission of the control function is facilitated by the fixed connection of the drive unit and the cab to the control means by means of the rigid shaft.

Eftersom den rotationssymmetriska bärytan är roterbart monte- rad på denna styva axel, är den mekaniska ansträngningen för- sumbar.Since the rotationally symmetrical bearing surface is rotatably mounted on this rigid shaft, the mechanical effort is negligible.

I fig. 3 och 4 används identiska referensbeteckningar för de- lar motsvarande de i fig. 1 och 2 redan beskrivna delarna.In Figs. 3 and 4, identical reference numerals are used for parts corresponding to the parts already described in Figs. 1 and 2.

Flygmaskinen enligt fig. 3 och 4 innefattar, sett i planvy, ett pilformigt bärorgan 1 med bärytor, och en inre drivenhet 2 med en propeller 3. Drivenheten är centriskt anordnad inom bärorganet 1 och en ringformig öppning 4 förefinnes mellan bärorganet 1 och drivenheten 2. Bärorganet 1 kan också ha vilken annan form som helst. Drivenheten 2 kan också innefatta en dubbel propeller (koaxiella, i motsatta riktningar roteran- de propellrar) eller den kan bildas av en radialflödesturbin och kan vara anordnad utanför bärorganets 1 axellinje. Till 446 966 drivdonet 2 är en hytt 5 för upptagning av lasten ansluten som har ett landningsställ 6 eller ett styrorgan för flygmaskinen.The aircraft according to Figs. 3 and 4 comprises, seen in plan view, an arrow-shaped support member 1 with support surfaces, and an inner drive unit 2 with a propeller 3. The drive unit is centrally arranged within the support member 1 and an annular opening 4 is present between the support member 1 and the drive unit 2. The support member 1 can also have any other shape. The drive unit 2 may also comprise a double propeller (coaxial, rotating propellers in opposite directions) or it may be formed by a radial flow turbine and may be arranged outside the axis of the support member 1. Connected to the 446 966 propulsion device 2 is a cab 5 for receiving the load which has a landing gear 6 or a control means for the aircraft.

Förbindelsen åstadkommas med hjälp av en i huvudsak vertikal axel 7 som passerar genom en bärplatta 8 för drivdonet 2. Bär- plattan är anordnad under drivenheten 2, roterbart relativt detta drivdon 2, och den bildar den inre omkretsen i den ring- formiqa öppningens 4 nedre del. Propellern 3 är anordnad på avstånd över bärorganets 1 övre sida.The connection is effected by means of a substantially vertical shaft 7 which passes through a support plate 8 for the drive device 2. The support plate is arranged below the drive unit 2, rotatable relative to this drive device 2, and it forms the inner circumference in the lower ring of the annular opening 4. part. The propeller 3 is arranged at a distance over the upper side of the support member 1.

Till drivenheten 2 är vidare anslutet ett organ för flyttning av tyngdpunkten vilket har formen av ett gyroskopdon 14. Dess- utom kan styrmunstycken 15 anordnas vid bärytorna. Dessa organ är i princip ekvivalenta och de kan användas tillsammans eller separat. Ännu en möjlig lösning för att flytta tyngdpunkten ut- görs av en vridanordning 16 som medger att vrida hytten eller rotoraxeln relativt bärorganet, som det visas med_streckpricka- de linjer i fig. 4. Vridområdet ligger härvid inom vinkeln u.A means for moving the center of gravity is further connected to the drive unit 2, which is in the form of a gyroscope device 14. In addition, guide nozzles 15 can be arranged at the bearing surfaces. These bodies are in principle equivalent and can be used together or separately. Another possible solution for moving the center of gravity is constituted by a rotating device 16 which allows the cab or rotor shaft to be rotated relative to the support member, as shown by dash-dotted lines in Fig. 4. The rotational area here lies within the angle u.

Ett första styrklafforgan 9 är anordnat omedelbart över den ringformiga öppningen 4 och ett andra styrklafforgan 10 är an- ordnat inom den ringformiga öppningen 4, under det första styr- klafforganet 9. Det övre styrklafforganet 9 är anslutet till drivenheten 2 endast vid sin inre periferi, medan det nedre styrklafforganet 10 uppbärs dels av bärorganet 1, dels av driv- enhetens 2 bärplatta 8. Varje styrklafforgan 9, 10 består av ett flertal styrklaffar vilka med hjälp av ett ej i äetalj visat, exempelvis elektriskt eller hydrauliskt styrt reglerdon är vridbara kring i huvudsak horisontella axlar (separat eller gemensamt).A first guide flap means 9 is arranged immediately above the annular opening 4 and a second guide flap means 10 is arranged inside the annular opening 4, below the first guide flap means 9. The upper guide flap means 9 is connected to the drive unit 2 only at its inner periphery, while the lower control flap member 10 is supported partly by the support member 1 and partly by the support plate 8 of the drive unit 2. Each control flap member 9, 10 consists of a plurality of control flaps which by means of a control device not shown in detail, for example electrically or hydraulically controlled, are rotatable about mainly horizontal axes (separately or jointly).

Styrklaffarna eller -skovlarna i de kransformiga styrklaffor- ganen förlöper radiellt relativt den ringformiga öppningen.The guide flaps or vanes in the ring-shaped guide flaps extend radially relative to the annular opening.

Det övre styrklafforganet 9 har mindre diameter än det nedre, fastän detta särdrag inte är obligatoriskt. Dimensionerna kan också vara omvända eller båda styrklafforganen kan ha lika diameterÄ Även styrklafforgan med fasta.styrklaffar kan an- vändas.- Bärplattan 8 kan ersättas av någon annan bärkonstruktion så- som exempelvis en ram, ett hölje e.d. Bärkonstruktionen kan, V.)The upper guide flap member 9 has a smaller diameter than the lower one, although this feature is not mandatory. The dimensions can also be inverted or both guide flap members can have the same diameter. Guide flap members with fixed guide flaps can also be used. The support structure can, V.)

Claims

1,446,966 e.g. by means of the law be rotatably arranged on the shaft 7. The plowing machine according to Figs. 3 and 4 operates in the following manner: The air is sucked away from the upper side of the support member 1 by the action of the propeller 3. This creates a circular trachea with great turbulence. The circular air flow is led to the act first, upper control flap member 9. There, the rotation is neutralized and partly directed downwards. The air flow then hits the second, lower guide flap member 10, where a highly laminar air flow arises which is directed substantially vertically downwards. This results in a very large lifting force, since the air flow practically runs vertically. The support member 1, the motor or drive unit 2 and the cab 5, which are connected to each other by means of the rigid shaft 7, remain stationary in the air space. The direction of rotation of the propeller 3 is indicated by the arrow 12. Claim 1 Airplane with a substantially non-rational and in particular rotationally symmetrical support body (1) and with at least one preferably coaxially arranged relative to the support body (2), for example dzivmotor, with a propeller (3), and with a cab (5) arranged below the support body corresponds to a guide part, wherein between the support body and the control unit or, its support structure there is an annular gap (4) through which an air flow is led downwards, and wherein in the annular gap there are resistance surfaces for compensation of the torque provided by the drive assembly, characterized in that at least two guide vane rings (9, 10) are spaced apart in the annular gap or immediately above each, each comprising two or more, in particular adjustable guide vanes (11). ), the upper guide vane ring (9) being arranged only at the drive unit and the lower guide vane ring (10) being a mounted partly at the support body and partly at a support plate e d (8) for the drive unit, which support plate ß d is rotatably mounted relative to the drive unit. 446 966 2 E '- An aircraft according to claim 1, characterized in that the guide vanes (11) in each vane ring are preferably jointly pivotable about their substantially horizontally extending axes. 3 1 1 _ g Flying machine according to one of claims 1 or 2, characterized by the drive unit and the cab resp. the guide part is firmly connected to each other, in particular by means of a shaft (7). 4 Airplane according to one of the patent knees P6, characterized in that the upper guide vane ring has a smaller diameter than the lower one. An airplane according to any one of claims 1-4, characterized in that the support body is provided with a separate additional drive device. An airplane according to any one of claims 1-5, characterized in that the support body and / or the propulsion unit are provided with at least one device for tilting the airplane. An airplane according to claim 6, characterized in that said device consists of a gyroscope device (14) which is rotatably mounted relative to the drive unit. An aircraft according to claim 6, characterized in that said device consists of two or more guide nozzles (15) arranged on the carrier body.