DE3400006A1 - Aircraft - Google Patents
AircraftInfo
- Publication number
- DE3400006A1 DE3400006A1 DE19843400006 DE3400006A DE3400006A1 DE 3400006 A1 DE3400006 A1 DE 3400006A1 DE 19843400006 DE19843400006 DE 19843400006 DE 3400006 A DE3400006 A DE 3400006A DE 3400006 A1 DE3400006 A1 DE 3400006A1
- Authority
- DE
- Germany
- Prior art keywords
- machine according
- flying machine
- aircraft
- turbine wheel
- missile
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Ceased
Links
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 3
- 230000005540 biological transmission Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/001—Flying saucers
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
Description
" F 1 u g m a s c h i n e " "F 1 u g m a s c h i n e"
Die Erfindung betrifft eine Weiterentwicklung des der Patentanmeldung Akz. P 33 44 740.3 zugrunde liegenden Erfindungsgedankens.The invention relates to a further development of the patent application Acc. P 33 44 740.3 underlying inventive idea.
Während bei der Voranmeldung der Antrieb der Flug maschine mittels einzelner Triebwerke erfolgt,die entwedsermit einem Motor kombiniert sind, odervoit einem im Flugkörper angeordneten Motor mittels Über= tragungselemente, ist bei der Erfindung eiii den Flugkörper umkreisendes Turbinenrad vorgesehen von einem im Flugkörper vorgesehenen Motor in kreisende Bewegung versetzt wird. Diese Turbinenrad ist in einem den Flugkörper umgebenden Gehäuse angeord= net, das nach oben und unten offen ist zur Luft= ansaugung und Abstoßung.While with the pre-registration the drive of the flying machine by means of individual engines, which are either combined with an engine, or voit a motor arranged in the missile by means of transmission elements, is at the Invention eiii the missile orbiting turbine wheel provided from a motor provided in the missile is set in circular motion. These The turbine wheel is arranged in a housing that surrounds the missile and that after above and below it is open to air = suction and repulsion.
Durch diese Maßnahme erfolgt ein Antrieb rundum den Flugkärper, also kein Einzelantrieb von diversen Einzelaggregaten. Der Antrieb erfolgt so gleich= mäßiger als bei Einzelaggregaten und die Leistung ist wesentlich verbessert.This measure results in a drive all around the missile, that is no individual drive from various individual units. The drive takes place in the same way = more moderate than with single units and the performance is significantly improved.
Die Zeichnung veranschaulicht die Flugmaschine nebs Antrieb in beispielsweiser Ausführung. Es zeigen: Fig.l eine Seitenansicht der Flugmaschine, Fig.2 eine Draufsicht dazu.The drawing illustrates the flying machine and its propulsion system as an example Execution. They show: FIG. 1 a side view of the flying machine, FIG. 2 a plan view to.
Der kugelförmige Körper der Flugmaschine besteht aus zwei Hälften 1 und 2, die mittels der Gehäuse= ringteile 3, 4 miteinander verbunden sind. Inner= halb des Gehäuses 3, 4 ist das mit Schaufeln ver= seh-ene Turbinenrad 5, 6 gelagert, das mit seiner Nabe auf der Welle 7 des Motores 8 befestigt ist, der seinerseits auf einer Grundplatte 9 im Oberteil 1 des Kugelkörpers verankert ist.The spherical body of the flying machine consists of two halves 1 and 2, which are connected to one another by means of the housing = ring parts 3, 4. Inner = half of the housing 3, 4, the turbine wheel 5, 6 provided with blades is mounted, which is attached with its hub on the shaft 7 of the motor 8, which in turn is anchored on a base plate 9 in the upper part 1 of the spherical body.
An der Unterseite des Kugelkörpers 2 ist das Lande= gestell 10 angebbacht, dessen Beine automatisch aus fahrbar sind. Oben und unten sind an Körper 1, 2 Radar 15 vorgesehen. Oben und seitlich der Kugel hälfte 1 sind Fallschirme 16 vorgesehen, deren An= zahl sich nach der Anzahl der Flugpersonen richtet.The landing = frame 10 is attached to the underside of the spherical body 2, whose legs can be automatically extended. Above and below are radars on body 1, 2 15 provided. Above and to the side of the ball half 1 parachutes 16 are provided, the number of which depends on the number of passengers.
Die Steuerung erfolgt mittels der Steuerungsklappen 11, zweckmäßig auf elektronischem Wege.The control takes place by means of the control flaps 11, expediently electronically.
Im Kugelunterteil 2 sind Sitze 12 vorgesehen, die als Hängsitze ausgebildet sind. Fenster 13 er Kugelhälfte 1 bieten bieten genügend Ausblick nach allen Seiten. Eine Türe 14 dient zum Ein- und Aus steigen.In the lower ball part 2 seats 12 are provided, which are designed as hanging seats are. Windows 13 he spherical half 1 offer sufficient views on all sides. A door 14 is used to get in and out.
Zum Landen und Starten auf dem Wasser kann ein auf= blasbares Luftkissen vorgesehen sein.An inflatable air cushion can be used to land and take off on the water be provided.
Die Flugmaschine kann bei entsprechend eingestellten Steuerklappen 11 senkrecht stARTEN und Landen und auch horizontal fliegen.The flying machine can with appropriately set control flaps 11 Take off and land vertically and fly horizontally.
Zu dem Rundum-Turbinenrad-Antrieb sei noch gesagt, daß rundum den Kugelkörper 1, 2 die Luft obeji nm Gehäuse 3 angesaugt und unten am Gehäusetei1 4 i1U;-gestoßen wird, Es erfolgt also ein ununterbrochener Kreisantrieb rundum die Flugmaschine. Die Schaufeln des Turhinenrades können evtl. elektronisch v er stellt werden.Regarding the all-round turbine wheel drive, it should be said that all around the Spherical body 1, 2 sucked in the air obeji nm housing 3 and below at the housing part 4 i1U; is pushed, so there is an uninterrupted circular drive around the Flying machine. The blades of the turbine wheel can possibly be adjusted electronically will.
- Leerseite -- blank page -
Claims (8)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19843400006 DE3400006A1 (en) | 1983-12-10 | 1984-01-02 | Aircraft |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19833344740 DE3344740A1 (en) | 1983-12-10 | 1983-12-10 | Aircraft |
DE19843400006 DE3400006A1 (en) | 1983-12-10 | 1984-01-02 | Aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
DE3400006A1 true DE3400006A1 (en) | 1985-07-11 |
Family
ID=25816337
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE19843400006 Ceased DE3400006A1 (en) | 1983-12-10 | 1984-01-02 | Aircraft |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE3400006A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2001064512A1 (en) * | 2000-03-02 | 2001-09-07 | Pier Luigi Rivolta | Vertical takeoff aircraft |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2939654A (en) * | 1956-09-13 | 1960-06-07 | Sebac Nouvelle Sa | Device for the simultaneous control of lifting and directional elements |
US3199809A (en) * | 1963-08-12 | 1965-08-10 | James N Modesti | Circular wing flying craft |
US3465989A (en) * | 1966-07-14 | 1969-09-09 | Saucercraft Inc | Circular vtol aircraft |
US3633849A (en) * | 1969-02-25 | 1972-01-11 | Alberto Kling | Flying craft |
US3640489A (en) * | 1968-07-26 | 1972-02-08 | Karl Jaeger | Vertical takeoff and landing aircraft |
DE2105287A1 (en) * | 1971-02-04 | 1972-08-17 | Pender, David Raymond, Columbia, S.C. (V.StA.) | Aircraft and flight procedures for vertical takeoff and landing |
US3750980A (en) * | 1970-06-30 | 1973-08-07 | S Edwards | Aircraft with vertical take off and landing capability |
US3946970A (en) * | 1974-12-16 | 1976-03-30 | Blankenship Ben F | Gyroscopically stabilized, vertical takeoff and landing aircraft |
-
1984
- 1984-01-02 DE DE19843400006 patent/DE3400006A1/en not_active Ceased
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2939654A (en) * | 1956-09-13 | 1960-06-07 | Sebac Nouvelle Sa | Device for the simultaneous control of lifting and directional elements |
US3199809A (en) * | 1963-08-12 | 1965-08-10 | James N Modesti | Circular wing flying craft |
US3465989A (en) * | 1966-07-14 | 1969-09-09 | Saucercraft Inc | Circular vtol aircraft |
US3640489A (en) * | 1968-07-26 | 1972-02-08 | Karl Jaeger | Vertical takeoff and landing aircraft |
US3633849A (en) * | 1969-02-25 | 1972-01-11 | Alberto Kling | Flying craft |
US3750980A (en) * | 1970-06-30 | 1973-08-07 | S Edwards | Aircraft with vertical take off and landing capability |
DE2105287A1 (en) * | 1971-02-04 | 1972-08-17 | Pender, David Raymond, Columbia, S.C. (V.StA.) | Aircraft and flight procedures for vertical takeoff and landing |
US3946970A (en) * | 1974-12-16 | 1976-03-30 | Blankenship Ben F | Gyroscopically stabilized, vertical takeoff and landing aircraft |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2001064512A1 (en) * | 2000-03-02 | 2001-09-07 | Pier Luigi Rivolta | Vertical takeoff aircraft |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
AF | Is addition to no. |
Ref country code: DE Ref document number: 3344740 Format of ref document f/p: P |
|
8141 | Disposal/no request for examination | ||
8110 | Request for examination paragraph 44 | ||
8131 | Rejection |