CA1160612A - Flying craft - Google Patents
Flying craftInfo
- Publication number
- CA1160612A CA1160612A CA000373698A CA373698A CA1160612A CA 1160612 A CA1160612 A CA 1160612A CA 000373698 A CA000373698 A CA 000373698A CA 373698 A CA373698 A CA 373698A CA 1160612 A CA1160612 A CA 1160612A
- Authority
- CA
- Canada
- Prior art keywords
- vanes
- steering
- supporting
- flying craft
- supporting means
- 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.)
- Expired
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
- B64C39/062—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings
- B64C39/064—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings with radial airflow
Abstract
ABSTRACT OF THE DISCLOSURE
The invention relates to flying craft having an outer supporting means and at least one inner driving unit and a cabin or steering means, in which an annular gap is provided between the supporting means and the driving unit, through which an air stream is guided downwards, characterized in that two steering flap rims having at least two steering flaps are spacially arranged within the annular gap or immediately above said gap.
The invention relates to flying craft having an outer supporting means and at least one inner driving unit and a cabin or steering means, in which an annular gap is provided between the supporting means and the driving unit, through which an air stream is guided downwards, characterized in that two steering flap rims having at least two steering flaps are spacially arranged within the annular gap or immediately above said gap.
Description
PREAMBLE TO ~ISCLOSURE
======================
BE IT KNOI~N that Heinz Jordan, whose full post address is Poppichl 21, A-9061 Wolfnitz bei Klagenfurt (Federal Province of Carinthia), Austria, having made an invention entitled "Flying Craft", the following disclosure contains a correct and full description of the invention and of the best ~lode known to the Inventor of taking advantage of same.
.
The invention relates to a flying craft having an outer supporting means and at least one inner driving unit and a cabin or steering means~ in which an annular gap is provided between the supporting means and the driving means through which an air stream is guided do~nwards.
In a flying craft of prior art, the driving unit is rotatably mounted within the supporting means and the steering means or cabin is rotatably mounted in relation to the supporting means and the driving unit in particular by means of a ball-bearing-supported shaft. The supporting means, which in cross section preferably has the shape of an air-foil profile~ is dri-ven in a direction of counter rotation in relation to the direction of rotation of the driving unit itself generating a counter torque (AT-PS 353 105).
It is the first object of the invention to pro~ide an improved flying craft of stronger aerodynamic lift and reduced mechanical effort.
It is the second ofject of the invention to pro~ide a flying craft in which the supporting means does not carry out a rotating motion around its a~is during flight~
The fir~t object is achieved in a flying craft of the type i~itially mentioned by providing at least two steering flap rims with two or more steering flaps in the annular gap or immediately above it, -the s-teering flap rims being spacially arranged one above the other.
According to the invention, the supporting means is driven by the air stream generated by the driving means and not by the oounter -torque of the driving unit. Vepending upon the position of the steering flaps, the supporting means can be driven in the same direction of rotation as the driving unit or in a direction counter to the rotating direction of the driving unit. It is essential that the cou~ter torque by neutralized by the upper steering flap rim and the air stream be partially alignad and directed downwards and that subsequently a substantially laminar, downwardly directed air stream be generated by the lower steering flap rim.rThe cabin for receîving load or the steering means of the flying craft remain stationary in air space during flight.
According to an embodim~nt of the invention, the s-teering flaps of each steering flap rim are pivotable, preferably together, around their essentially horizontally extending axis. This permits variation of the rate of rotation of the supporting means and thus an increase or decrease of the gyroqcopic e*fect of the supporting means a~ desired, in order to influence the stability of the flying craft.
Since the cabin for receiving load or the steering means of the flying craft remain stationary in air space during flight, it is possible to rigidly connect the driving unit and the cabin or steering means to one another, in particular by means of a shaft. This results in a particularly simple and stable construction.
A preferred construction of the flying craft consists in that the upper steerlng flap rim is attached to the driving unit only and that the lower steering flap rim is attached to the supporting means, on the one hand, and to a supporting plate for the driving unit, on the other hand, the s~pporting plate being rotatably mounted in relation to the driving unit.
~6(~
It is also possible to provide the supporting means with a separate additional drive. By means of this additional drive, which is not absolutely necessary, steering of the flying craft can be f`urther improved.
This second object of the invention is achieved in the flying craft mentioned above by providing the flying craft and/or the driving unit with at least one means for displacing the center of gravity of the flying craft.
In this embodiment, -the supporting means receives its aerodynamic lift from the air stream genera-ted by the dri~ing unit and not from the counter torque generated by the driving unit. l`he supporting means can be so steered by the means for dis-placing the center of gravity that it remains stationary in air space during flight, i.e. that it does not carry out a rotating motion around its axis. The upper steering flap rim neutralizes the counter torque and partially aligns the air stream and directs it downwards, while the lower steering flap rim subsequently generates a largely laminar, downward-directed air stream. The cabin for receiving load or the steering means of the flying craft remain stationary in air space during flight.
The means for displacing the center of gravity can be a gyroscopic means rotatably mounted in relation ot the driving unit.
It is also possible, however, to provide the means for displacing the center of gravity in the form of two or more steering nozzles arranged on the supporting means.
The invention is explained in detail under reference to the drawing showing embodi~ments of the object of the invention.
Fig. 1 shows a diagrammatic sectional view of a flying craft according to the invention;
Fig. 2 shows a top view of Fig. l;
Fig. 3 shows a top view of a flying craft according to the invention and Fig. 4 a section along line IV-IV in Fig. 3 in enlarged scale.
The flying craft according to Fig. 1 and 2 comprises a ring-shaped supporting means 1, presenting rotation symmetry, as an airfoil, and an inner driving unit 2 with a propeller 3.
The driving unit 2 is arranged coaxially within the supporting means 1, an annular gap 4 being formed between the supporting means 1 and the driving unit 2. The supporting means 1 viewed in cross section has the form of an airfoil profile, but could be of any other given shape. The driving unit 2 could also have the form of a double propeller or of a radial-flow turbine, it could be arranged outside the shaft of the support-ing means 1. Connected to the driving unit 2 is a cabin 5 for receiving load having a landing gear 6 or a steering means for the Plying craft~ This connection is effected by means of a shaft 7 extending essentially perpendicularly and piercing a supporting plate 8 for the driving unit 2. The supporting plate 8 is arranged below the driving unit 2 and rotatable in relation to the driving unit and forms the inner circum-ference in the lower part of -the annular gap 4. The propeller 3 is arranged spacially above the upper side of the supporti~g means 1.
A ~irst steering flap rim 9 is arranged immediately above the annular gap 4 and a second steering flap rim lO is arranged ~, ~6~
below the first steering flap rim 9 within the annular gap 4.
The upper steering flap rim 9 is attached to the dri~ing unit
======================
BE IT KNOI~N that Heinz Jordan, whose full post address is Poppichl 21, A-9061 Wolfnitz bei Klagenfurt (Federal Province of Carinthia), Austria, having made an invention entitled "Flying Craft", the following disclosure contains a correct and full description of the invention and of the best ~lode known to the Inventor of taking advantage of same.
.
The invention relates to a flying craft having an outer supporting means and at least one inner driving unit and a cabin or steering means~ in which an annular gap is provided between the supporting means and the driving means through which an air stream is guided do~nwards.
In a flying craft of prior art, the driving unit is rotatably mounted within the supporting means and the steering means or cabin is rotatably mounted in relation to the supporting means and the driving unit in particular by means of a ball-bearing-supported shaft. The supporting means, which in cross section preferably has the shape of an air-foil profile~ is dri-ven in a direction of counter rotation in relation to the direction of rotation of the driving unit itself generating a counter torque (AT-PS 353 105).
It is the first object of the invention to pro~ide an improved flying craft of stronger aerodynamic lift and reduced mechanical effort.
It is the second ofject of the invention to pro~ide a flying craft in which the supporting means does not carry out a rotating motion around its a~is during flight~
The fir~t object is achieved in a flying craft of the type i~itially mentioned by providing at least two steering flap rims with two or more steering flaps in the annular gap or immediately above it, -the s-teering flap rims being spacially arranged one above the other.
According to the invention, the supporting means is driven by the air stream generated by the driving means and not by the oounter -torque of the driving unit. Vepending upon the position of the steering flaps, the supporting means can be driven in the same direction of rotation as the driving unit or in a direction counter to the rotating direction of the driving unit. It is essential that the cou~ter torque by neutralized by the upper steering flap rim and the air stream be partially alignad and directed downwards and that subsequently a substantially laminar, downwardly directed air stream be generated by the lower steering flap rim.rThe cabin for receîving load or the steering means of the flying craft remain stationary in air space during flight.
According to an embodim~nt of the invention, the s-teering flaps of each steering flap rim are pivotable, preferably together, around their essentially horizontally extending axis. This permits variation of the rate of rotation of the supporting means and thus an increase or decrease of the gyroqcopic e*fect of the supporting means a~ desired, in order to influence the stability of the flying craft.
Since the cabin for receiving load or the steering means of the flying craft remain stationary in air space during flight, it is possible to rigidly connect the driving unit and the cabin or steering means to one another, in particular by means of a shaft. This results in a particularly simple and stable construction.
A preferred construction of the flying craft consists in that the upper steerlng flap rim is attached to the driving unit only and that the lower steering flap rim is attached to the supporting means, on the one hand, and to a supporting plate for the driving unit, on the other hand, the s~pporting plate being rotatably mounted in relation to the driving unit.
~6(~
It is also possible to provide the supporting means with a separate additional drive. By means of this additional drive, which is not absolutely necessary, steering of the flying craft can be f`urther improved.
This second object of the invention is achieved in the flying craft mentioned above by providing the flying craft and/or the driving unit with at least one means for displacing the center of gravity of the flying craft.
In this embodiment, -the supporting means receives its aerodynamic lift from the air stream genera-ted by the dri~ing unit and not from the counter torque generated by the driving unit. l`he supporting means can be so steered by the means for dis-placing the center of gravity that it remains stationary in air space during flight, i.e. that it does not carry out a rotating motion around its axis. The upper steering flap rim neutralizes the counter torque and partially aligns the air stream and directs it downwards, while the lower steering flap rim subsequently generates a largely laminar, downward-directed air stream. The cabin for receiving load or the steering means of the flying craft remain stationary in air space during flight.
The means for displacing the center of gravity can be a gyroscopic means rotatably mounted in relation ot the driving unit.
It is also possible, however, to provide the means for displacing the center of gravity in the form of two or more steering nozzles arranged on the supporting means.
The invention is explained in detail under reference to the drawing showing embodi~ments of the object of the invention.
Fig. 1 shows a diagrammatic sectional view of a flying craft according to the invention;
Fig. 2 shows a top view of Fig. l;
Fig. 3 shows a top view of a flying craft according to the invention and Fig. 4 a section along line IV-IV in Fig. 3 in enlarged scale.
The flying craft according to Fig. 1 and 2 comprises a ring-shaped supporting means 1, presenting rotation symmetry, as an airfoil, and an inner driving unit 2 with a propeller 3.
The driving unit 2 is arranged coaxially within the supporting means 1, an annular gap 4 being formed between the supporting means 1 and the driving unit 2. The supporting means 1 viewed in cross section has the form of an airfoil profile, but could be of any other given shape. The driving unit 2 could also have the form of a double propeller or of a radial-flow turbine, it could be arranged outside the shaft of the support-ing means 1. Connected to the driving unit 2 is a cabin 5 for receiving load having a landing gear 6 or a steering means for the Plying craft~ This connection is effected by means of a shaft 7 extending essentially perpendicularly and piercing a supporting plate 8 for the driving unit 2. The supporting plate 8 is arranged below the driving unit 2 and rotatable in relation to the driving unit and forms the inner circum-ference in the lower part of -the annular gap 4. The propeller 3 is arranged spacially above the upper side of the supporti~g means 1.
A ~irst steering flap rim 9 is arranged immediately above the annular gap 4 and a second steering flap rim lO is arranged ~, ~6~
below the first steering flap rim 9 within the annular gap 4.
The upper steering flap rim 9 is attached to the dri~ing unit
2 on its inner circumference only, while the lower steering flap rim 10 is attached to (and supported on) the supporting means 1, on the one hand, and the supporting plate 8 of the driving unit 2, on the other hand. Each steering flap rim 9, 10 consists of a plurality of steering flaps or steering baffles 11 pivotable around an essentially horizontal axis and adjustable joi~tiy or individually by means of an adjusting means (not shown in detail), for instance an electrically or hydraulically operated adjusting means~ the adjustment consisting in rotation around their a~es. In particular, the steering ~laps of each steering flap rim can be pivoted jointly. l`he upper steering flap rim 9 is of smaller outer diameter than the lower steering flap rim 10, but this is not essential~ The dimensions could be either reversed or equal, as well. It would also be pos~ible to use steering flap rims with rigidly attached steering flaps.
The supporting plate 8 could be replaced by any other type of supporting str~ture such as a frame,casing or the like.
It could be rotatably mounted on the shaft 7 by means of bearings.
The flying craft functions as follows:
Air is sucked off from the upper side of the supporting means 1 by means of the propeller 3. This genera-tes a circular motion of the air of high turbulence. The circular air stream is guided to the first, upper steering flap rim 9. Here, the torque is neutralized and partially guided downwards. The air stream now reaches the second, lower steering fla rim 10~ Here, an essentially perpendicular, downward-directed, largely laminar air stream is generated. This results in ~ery strong aerodynamic lift 7 as the airstream extends practically vertically.
The motor or drive 2 and the cabin 5, which are fixed to one ano-ther by means of the rigid shaft 7, are stationary.
The direction of rotation of the propeller is indicated by arrow 12, the direction of rotation of the supporting means 1, which rotates in the same rotating direction as the propeller or counter to this, depending upon the position of the steering flaps, is indicated by arrowO 13.
The steering flaps 11 fixed to the rotatably mounted supporting plate 8 for the supporting means 1 allow a variation of the number of revolutions of the supporting means 1 and an increase of the gyroscopic effect achie~ed by the number of revolutions of the supporting means 1 and thus an influence of the stability of the device.
~ uring flight, the cabin part including the steering remains completely stationary~ This feature is of particular importance in -the event the device is to be used for conveying passengers.
The transmission of the steering function is facilitated by the fast connection of the driving unit and the cabin to the steering means by means of the rigid shaft.
Since the alrfoil presenting rotation symmetry is rotatably mounted on this rigid shaft, the mechanical effort is negligible.
In Fig. 3 and 4, the same references are used for parts which correspond to parts already mentioned in Fig. 1 and 2.
The flying craft according to Fig. 3 and 4 comprises, i~
top ~iew, an arrow-shaped supporting means 1 with airfoils and an inner driving unit 2 with a propeller 3. The driving unit 2 is arranged centrically within the supporting mea~s 1, an annular gap/being formed between the supporting means 1 and the driving unit 2. The supporting means 1 can have any other given form. The driving means 2 could also have the form of a double propeller (coa~ial contra-rotating propellers) or a radial-flow turbine and could be arranged outside of the axis of the supporting means 1. Fixed to the driving means 2 i~ a cabin 5 for receiving load having a landing gear 6 or a steering means for the flying craft.
This connection is effected by means of an axis or shaft 7 which extends essentially perpendicularly and pierces a supporting plate 8 for the driving means 2. The supporting plate 8 is arranged below the driving unit 2 rotatably in relation to the driving means 2 and forms the inner circum-ference in the lot~er part of the annular gap 4. The propeller
The supporting plate 8 could be replaced by any other type of supporting str~ture such as a frame,casing or the like.
It could be rotatably mounted on the shaft 7 by means of bearings.
The flying craft functions as follows:
Air is sucked off from the upper side of the supporting means 1 by means of the propeller 3. This genera-tes a circular motion of the air of high turbulence. The circular air stream is guided to the first, upper steering flap rim 9. Here, the torque is neutralized and partially guided downwards. The air stream now reaches the second, lower steering fla rim 10~ Here, an essentially perpendicular, downward-directed, largely laminar air stream is generated. This results in ~ery strong aerodynamic lift 7 as the airstream extends practically vertically.
The motor or drive 2 and the cabin 5, which are fixed to one ano-ther by means of the rigid shaft 7, are stationary.
The direction of rotation of the propeller is indicated by arrow 12, the direction of rotation of the supporting means 1, which rotates in the same rotating direction as the propeller or counter to this, depending upon the position of the steering flaps, is indicated by arrowO 13.
The steering flaps 11 fixed to the rotatably mounted supporting plate 8 for the supporting means 1 allow a variation of the number of revolutions of the supporting means 1 and an increase of the gyroscopic effect achie~ed by the number of revolutions of the supporting means 1 and thus an influence of the stability of the device.
~ uring flight, the cabin part including the steering remains completely stationary~ This feature is of particular importance in -the event the device is to be used for conveying passengers.
The transmission of the steering function is facilitated by the fast connection of the driving unit and the cabin to the steering means by means of the rigid shaft.
Since the alrfoil presenting rotation symmetry is rotatably mounted on this rigid shaft, the mechanical effort is negligible.
In Fig. 3 and 4, the same references are used for parts which correspond to parts already mentioned in Fig. 1 and 2.
The flying craft according to Fig. 3 and 4 comprises, i~
top ~iew, an arrow-shaped supporting means 1 with airfoils and an inner driving unit 2 with a propeller 3. The driving unit 2 is arranged centrically within the supporting mea~s 1, an annular gap/being formed between the supporting means 1 and the driving unit 2. The supporting means 1 can have any other given form. The driving means 2 could also have the form of a double propeller (coa~ial contra-rotating propellers) or a radial-flow turbine and could be arranged outside of the axis of the supporting means 1. Fixed to the driving means 2 i~ a cabin 5 for receiving load having a landing gear 6 or a steering means for the flying craft.
This connection is effected by means of an axis or shaft 7 which extends essentially perpendicularly and pierces a supporting plate 8 for the driving means 2. The supporting plate 8 is arranged below the driving unit 2 rotatably in relation to the driving means 2 and forms the inner circum-ference in the lot~er part of the annular gap 4. The propeller
3 is positioned spacially above the upper side of the support-ing means 1.
Further connected to the driving unit 2 i9 a means for displacing the center of gravity in the ~orm of a gyroscopic mean 14. In addition, steering nozzles 15 could be arranged on the airfoils. These means are essentially equivalent and may optionally be employed jointly or separately. A further possibility for displacing the center of gravitr,consists in a pivoting device 16 which allows pivoting the cabin Dr rotor axis in relation to the supporting means, as shown in dotted lines in Fig. 2. The pivoting range is indicated by means of angle oC.
A first steering flap rim 9 is arranged immediately above the annular gap 4 and a second steering flap rim lO
is arranged within the annular gap 4 below the first steering flap rim 9. The upper steering flap rim 9 is attached to the ~n6~
driving unit 2 on its inner periphery only, while the lower steering flap rim 10 is supported on the supporting means 1, on the one hand and on the supporting plate 8 of the driving means 2, on the other hand. Each steering flap rim 9, 10 consists of a plurality of steering flaps pivotable around essentially horizontal axes which are pivotable, i.e. rotatable, around their a~es7 jointly or separately, by means of an adjusting means not shown in detail, such as an electrically or hydraulically operable adjusting means~ The upper steering flap rim 9 is of smaller diameter than the lower s*eering flap rim 10, although this feature is not indispensable.
The dimensions could also be reversed or both steering flap rims could be of equal diameter. It would also be possible to use steering flap rims with rigid steering flaps.
The supporting plate 8 could be replaced by another supporting structure such as, for instance, a frame, casing or the like. The supporting structure can be rotatably mounted on the shaft 7 by means of, for instance, bearings.
The flying craft according to Fig. 3 and 4 functions as follows:
Air i9 sucked off from the upper side of the supporting means 1 by means of the propeller 3. This generates a circular motion of the air of high turbulence. This circular air stream is guided to the first, upper steering flap rim 9. Here, the tor~ue is neutralized and partially directed downwards. The air stream then arrives at the second, lower steering flap rim 10. Here, a largely laminar air stream directed essentially perpendicularly downwards is generated. This results in a very strong aerodynamic li~t, as the air stream is directed practically vertically. The supporting means 1, the motor or g _ , ,,{ ~ ) : ' ~
~.`
drive 2 and the cabin 5, which are fixed to one another .
by the rigid shaft 7, remain sta-tionary in air space. The rotating direction of propeller 3 is indicated by means of arrow 12.
.
Further connected to the driving unit 2 i9 a means for displacing the center of gravity in the ~orm of a gyroscopic mean 14. In addition, steering nozzles 15 could be arranged on the airfoils. These means are essentially equivalent and may optionally be employed jointly or separately. A further possibility for displacing the center of gravitr,consists in a pivoting device 16 which allows pivoting the cabin Dr rotor axis in relation to the supporting means, as shown in dotted lines in Fig. 2. The pivoting range is indicated by means of angle oC.
A first steering flap rim 9 is arranged immediately above the annular gap 4 and a second steering flap rim lO
is arranged within the annular gap 4 below the first steering flap rim 9. The upper steering flap rim 9 is attached to the ~n6~
driving unit 2 on its inner periphery only, while the lower steering flap rim 10 is supported on the supporting means 1, on the one hand and on the supporting plate 8 of the driving means 2, on the other hand. Each steering flap rim 9, 10 consists of a plurality of steering flaps pivotable around essentially horizontal axes which are pivotable, i.e. rotatable, around their a~es7 jointly or separately, by means of an adjusting means not shown in detail, such as an electrically or hydraulically operable adjusting means~ The upper steering flap rim 9 is of smaller diameter than the lower s*eering flap rim 10, although this feature is not indispensable.
The dimensions could also be reversed or both steering flap rims could be of equal diameter. It would also be possible to use steering flap rims with rigid steering flaps.
The supporting plate 8 could be replaced by another supporting structure such as, for instance, a frame, casing or the like. The supporting structure can be rotatably mounted on the shaft 7 by means of, for instance, bearings.
The flying craft according to Fig. 3 and 4 functions as follows:
Air i9 sucked off from the upper side of the supporting means 1 by means of the propeller 3. This generates a circular motion of the air of high turbulence. This circular air stream is guided to the first, upper steering flap rim 9. Here, the tor~ue is neutralized and partially directed downwards. The air stream then arrives at the second, lower steering flap rim 10. Here, a largely laminar air stream directed essentially perpendicularly downwards is generated. This results in a very strong aerodynamic li~t, as the air stream is directed practically vertically. The supporting means 1, the motor or g _ , ,,{ ~ ) : ' ~
~.`
drive 2 and the cabin 5, which are fixed to one another .
by the rigid shaft 7, remain sta-tionary in air space. The rotating direction of propeller 3 is indicated by means of arrow 12.
.
Claims (5)
1. A flying craft, comprising, an outer supporting means which has an annular airflow opening extending vertically therethrough, at least one driving means supported on the supporting means for propelling a stream of air downwardly through the opening, a carrier supported by the supporting means, an upper set and a lower set of air deflecting vanes, each set of vanes having at least two adjustable pitch vanes, said sets of vanes being spaced apart and located in the stream of air produced by the driving means, and a supporting member, said driving means being mounted on the supporting member, said upper set of vanes being fixed only to the driving means, said lower set of vanes each having one end attached to the supporting means and one end attached to the supporting member, said support-ing member being rotatably mounted relative to the driving means.
2. A flying craft according to claim 1, wherein the vanes in each set are pivotable about subs-tantially horizontal axes.
3. A flying craft according to claim 1 or 2, having a shaft which fixes together the driving means and the carrier.
4. A flying craft according to claim 1 or claim 2 wherein the upper set of vanes has a smaller diameter than the lower set of vanes.
5. A flying craft according to claim 1 having means for tilting the craft, said tilting means comprising two or more steering nozzles which are arranged on the supporting means.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| AT344980 | 1980-07-02 | ||
| ATA3449/80 | 1980-07-02 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1160612A true CA1160612A (en) | 1984-01-17 |
Family
ID=3550671
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000373698A Expired CA1160612A (en) | 1980-07-02 | 1981-03-24 | Flying craft |
Country Status (6)
| Country | Link |
|---|---|
| JP (1) | JPS57138500A (en) |
| CA (1) | CA1160612A (en) |
| DE (1) | DE3124525A1 (en) |
| FR (1) | FR2486020B1 (en) |
| IT (1) | IT1142812B (en) |
| SE (1) | SE446966B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3328417A1 (en) * | 1982-08-24 | 1984-03-01 | Technische Geräte- u. Entwicklungsgesellschaft mbH, 9020 Klagenfurt, Kärnten | TURNING WING BODY |
| SE450480B (en) * | 1982-08-30 | 1987-06-29 | Tech Gerete Und Entwicklungsge | STUFFED FLIGHT BODY |
| WO1986004558A1 (en) * | 1985-02-01 | 1986-08-14 | Masaru Tsuda | Vertical take-off machine |
| DE102008063484B4 (en) * | 2008-12-17 | 2012-11-29 | Berthold Möller | Aircraft which allows vertical flight by reducing air pressure in a rotating air column |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE699228C (en) * | 1938-03-23 | 1940-11-25 | Ludwig Kort Dipl Ing | helicopter |
| DE1227779B (en) * | 1957-10-08 | 1966-10-27 | R L Cie De Rech S Et D Etudes | Flying platform with a stabilization and control device |
| CH634516A5 (en) * | 1977-10-31 | 1983-02-15 | Tech Geraete Entwicklung Ges | MISSILE. |
| EP0040636A1 (en) * | 1979-11-26 | 1981-12-02 | MESSINA, Gene | Gyro stabilized flying saucer model |
-
1981
- 1981-03-24 CA CA000373698A patent/CA1160612A/en not_active Expired
- 1981-06-23 DE DE19813124525 patent/DE3124525A1/en active Granted
- 1981-06-24 FR FR8112387A patent/FR2486020B1/en not_active Expired
- 1981-06-24 SE SE8103949A patent/SE446966B/en not_active IP Right Cessation
- 1981-06-30 IT IT48793/81A patent/IT1142812B/en active
- 1981-07-02 JP JP56103896A patent/JPS57138500A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| SE8103949L (en) | 1982-01-03 |
| DE3124525C2 (en) | 1987-03-26 |
| IT1142812B (en) | 1986-10-15 |
| IT8148793A0 (en) | 1981-06-30 |
| DE3124525A1 (en) | 1982-06-16 |
| JPS6140600B2 (en) | 1986-09-10 |
| JPS57138500A (en) | 1982-08-26 |
| FR2486020A1 (en) | 1982-01-08 |
| SE446966B (en) | 1986-10-20 |
| FR2486020B1 (en) | 1985-01-11 |
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