CA1151130A - Unmanned remotely piloted aircraft - Google Patents
Unmanned remotely piloted aircraftInfo
- Publication number
- CA1151130A CA1151130A CA000377951A CA377951A CA1151130A CA 1151130 A CA1151130 A CA 1151130A CA 000377951 A CA000377951 A CA 000377951A CA 377951 A CA377951 A CA 377951A CA 1151130 A CA1151130 A CA 1151130A
- Authority
- CA
- Canada
- Prior art keywords
- remotely piloted
- aircraft
- piloted aircraft
- propellers
- control
- 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
- 238000001514 detection method Methods 0.000 claims description 6
- 125000004122 cyclic group Chemical group 0.000 claims description 5
- 238000006243 chemical reaction Methods 0.000 claims 1
- 239000002828 fuel tank Substances 0.000 claims 1
- 238000000926 separation method Methods 0.000 claims 1
- 230000000875 corresponding effect Effects 0.000 description 6
- 230000007246 mechanism Effects 0.000 description 4
- 238000006073 displacement reaction Methods 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical group C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 229940000425 combination drug Drugs 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/10—Constructional aspects of UAVs for stealth, e.g. reduction of cross-section detectable by radars
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
- B64U2201/202—Remote controls using tethers for connecting to ground station
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Toys (AREA)
- Manipulator (AREA)
Abstract
UNMANNED REMOTELY PILOTED AIRCRAFT
ABSTRACT OF THE DISCLOSURE
An unmanned aircraft of the remotely piloted type that is characterized by its configuration and outline using rigid counter rotating propellers, positioned substantially at the height of its center of mass or slightly below to allow producing a suffi-ciently large control moment to use a tether line for landing the aircraft and to allow using two substantial-ly spheroidal surfaces at the top and bottom respecti-vely rather than a single one relatively larger and more detectable surface as when the propellers are at the top.
ABSTRACT OF THE DISCLOSURE
An unmanned aircraft of the remotely piloted type that is characterized by its configuration and outline using rigid counter rotating propellers, positioned substantially at the height of its center of mass or slightly below to allow producing a suffi-ciently large control moment to use a tether line for landing the aircraft and to allow using two substantial-ly spheroidal surfaces at the top and bottom respecti-vely rather than a single one relatively larger and more detectable surface as when the propellers are at the top.
Description
FIEID QF THE I~VE~TION
This invention relates to an unmanned aircraft more particularly of the remotely piloted type.
DESCRIPTION OF THE PRIOR ART
There have been conceived and/or produces many unmanned aircraft of the above type. So far, the efforts have produced workable units in particular concerning the flight and stability controls. In the known unmanned aircraft of the above type that have been conceived so fa~, the propul-sion is achieved by helicopter like propellers positioned atthe top of the aircraft and using non-rigid propellers to achieve the desired flight and attitute controls and in particular using differential collective pitch control. Such propellers produce a relatively small control output resulting in an undesirable limitation against strong moments on the aircraft such as when a tether line is attached to hold it captive.
The unmanned aircraft of the above type are more commonly conceived for warfare use on the battlefield and for that purpose they must be as difficult as possible to detect by the enemy; visually, by radar, or by infra red~
It is a general object of the present invention to provide an unmanned remotely piloted aircraft that includes active flight and stability controls producing relatively large moments sufficient ~o ~ounter the large moment produced on the aircraft by a tether line holdi~ it captive.
~.
~S~
It is another general object of the present inven-tion to provide an unmanned remotely piloted aircraft that is made with an appropriate configuration combination and outline of its major components one relative to another to minimize the possibility of its detection such as by the enemy.
It is a more specific object of the present invent-ion to provide an unmanned remotely piloted aircraft combina tion that is made with counter rotating propellers positioned substantially at the height of the center of mass of the combination and to thus achieve the above mentioned general ob j ects of the present invention.
It is a still more specific object of the present invention to provide an unmanned remotely piloted aircraft combination that uses rigid counter rotating propellers positioned substantially at the height of the center of mass of the combination to allow larger control moments which thus cope with large unbalance moments such as produced by a tether line holding the aircraft captive.
It is a still more specific object of the present invention to provide an unmanned remotely piloted aircraft that allows to have a configuration with counter rotating propellers positioned at intermediate hei~ht between the top and bottom thereof and also with two generally spheroidal surfaces above and below the propellers for minimum exposure to detection by radar reflection and the like due to the inherent dispersive nature of such surfaces.
BRIEF DESCRIPTION OF THE DRAWINGS
The above and other objects and advantages of the present invention will be bet-ter understood with refer-ence to the following detailed description of a preferred embodiment thereof which is illustrated, by way of example, in the accompanying drawings; in which:
Figure 1 is a cross-sectional view in elevation of an unmanned aircraft according to the present invention;
Figure 2 is an exploded elevation view of the lQ same aircraft to illustrate its modular concept;
Figure 3 is an elevation view partly in cross section of the propellers, blades and swashplate intercon-nection shown in a larger scale and in a slightly different embodiment than in Figure l; and Figure 4 is an elevation view as seen in the direction of the arrows 4-4 in Figure 3.
The illustrated remotely piloted unmanned air-craft comprises a body that is symmetrical about a vertical axis. That aircraft body comprises vertically superposed sections including an uppermost section 1, an intermediate section 2, and a lowermGst section 3. Each of these sections constitutes a separable module constructed and arranged to be readily disconnected for maintenance or replacement.
., The uppermost module or section 1 includes a rotary internal combustion engine or turbine 4 fixedly mount-ed on a supporting bracket 5. A generally annular or dough-nut shaped gas tank is positioned around the engine 4 and ~.~5~3~
is thus used to shield the hot parts of the engine against infra-red detection. The outside of the body is provided with a housing or shell 7 having a generally spheroidal out-line to be the least susceptible to radar detection. This iS 50 due to the inherent high dispersive nature of spheroid-al surfaces to radar waves or reflections. The exhaust out-let 8 for the engin~ 4 is positioned at the top of the upper-most section and thus also of the whole body of the aircraft and is upwardly directed to be concealed against infra-red detection from the ground, down below, The lowermost section or module 3 is also provided with a housing or shell 9 of generally s~heroidal outline in which is housed the necessary flight control units. The control units do not form part of the present invention and therefore will not be described in the present disclosure.
Suspension brackets 11 are fixedly secured at their upper end, inside the lowermost body section. These suspension brackets are constructed and arranged to releasably support a payload 12 that is pivotally suspended by the brackets, in any well known manner. The payload 12 in this case consti-tutes a data acquisition package for remote control of the vehicle and for surveillance of ground sites such as for enemy surveillance on a battlefield, for traffic surveillan-ce, or for other civil uses. A shielding hood 13 is provi-ded over and around the data acquis~tion payload 12.
A landing gear l~ is attached to the exterior of the lowermost section 3 and includes a landing ring 15. The latter is connected to the lowermost body section 3 by means of three legs 16 each in the form of a shock absorbing strut that is pivotally connected at its opposite ends to the lowermost body section and to the landing ring respectively.
The intermediate body section 2 includes a pair of counterrotating propellers 17 and 18 and the associated control mechanisms shown in greater details in Figure 3. A
gearbox 19 is centrally mounted at the top of the intermedia-te body section, and through appropriate shaft and gearing arr~ngement, not shown, it drives the top propeller hub 20 in one direction and the bottom propeller hub 21 in the opposite direction. Each propeller 17, 18 includes 3 blades 22 having each a hub portion 23, as shown in Figure 1 rotatively mounted in its corresponding propeller hub 20 or 21.
The collective and cyclic pitch control mechanisms illustrated in Figures 1 and 3 are essential;y the same with only some secondary differences. The embodiment of Figure 1 will first be described in details. As shown in Figure 1, the collective and cyclic pitch control mechanism is connect-ed to the blades 22 to selectively vary the pitch angle ofeach blade around its blade pitch control axis defined by the corresponding blade hub 23. A swash plate 24 is mounted between the two counterrotating propellers and is tiltable by any appropriate means, not shown in two orthogonal directions corresponding to the selected pitch an roll directions of the aircraft. A pair of rings 25 are rotably attached to the swashplate to rotate coaxially around it in well known manner. A blade pitch actuator arm 26 is pivotal-ly connected, for each blade 22, at one end to the correspond-ing blade hub ~3 and at the other end to the corresponding ring 25 to vary the bl~de pitch in relation with bodily tilting of the swashplate and rings for cyclic pitch control or in xelation with bodily up or downi displacement of the swashplate and rings for collective pitch control, all as is well known in the art.
The collective and cyclic pitch control mechanism illustrated in Figure 3 represents a slightly different embo-diment compared to the embodiment in Figure 1 and morespecifically defines how the propeller hubs 20, 21 and the swashplate 25 are mounted in the vehicle or aircraft body.
The latter is provided with a fixed central shaft 27 having fixedly secured thereto spoked wheels 28 around which are rotatably mounted the propeller hubs 20 and 21 respectively.
Each of the propeller hub 20, 21 carries a ring gear 29 that is driven by the engine 4 through appropria~e pinion and shaft drive, not shown. In this embodiment, each blade 22 has a hub portion 30 rotatably engaged in a radial projection 31 of the corresponding propeller hub. A lever 32 is fixed to each blade hub 30, as in the embodiment of Figure 1, for connection of the blade pitch actuation arm 26 to it;
In this embodiment of Figure 3, the swashplate 24 is shown tiltably mounted on a ball joint 33 fixed to a spool shape support 34 that is slidable along the shaft 27. Thus the ~ertical sliding of the support 3~ produces the same displacement of the swashplate 24 and collecti~e control of the blade pitch angles.
A tether line 35 is attached to the lower end of the aircraft more particularly by one of its ends attached to a ring 36 that is mounted on bal bearings to freely rotate relative to the body of aircraft. The tether line is coiled on a spool 37 that is releasably carried by the aircraft during a flight. Any remote controlled releasable latch system is provided to releasably hoid the spool onboard during flight. When desired for landing, the spool 37 is remotely unlatched or released to allow it to fall to the ground where the tether line is then pulled on to safely and guidably land the aircraft independently of adverse weather conditions and excessively accurate control performance.
This invention relates to an unmanned aircraft more particularly of the remotely piloted type.
DESCRIPTION OF THE PRIOR ART
There have been conceived and/or produces many unmanned aircraft of the above type. So far, the efforts have produced workable units in particular concerning the flight and stability controls. In the known unmanned aircraft of the above type that have been conceived so fa~, the propul-sion is achieved by helicopter like propellers positioned atthe top of the aircraft and using non-rigid propellers to achieve the desired flight and attitute controls and in particular using differential collective pitch control. Such propellers produce a relatively small control output resulting in an undesirable limitation against strong moments on the aircraft such as when a tether line is attached to hold it captive.
The unmanned aircraft of the above type are more commonly conceived for warfare use on the battlefield and for that purpose they must be as difficult as possible to detect by the enemy; visually, by radar, or by infra red~
It is a general object of the present invention to provide an unmanned remotely piloted aircraft that includes active flight and stability controls producing relatively large moments sufficient ~o ~ounter the large moment produced on the aircraft by a tether line holdi~ it captive.
~.
~S~
It is another general object of the present inven-tion to provide an unmanned remotely piloted aircraft that is made with an appropriate configuration combination and outline of its major components one relative to another to minimize the possibility of its detection such as by the enemy.
It is a more specific object of the present invent-ion to provide an unmanned remotely piloted aircraft combina tion that is made with counter rotating propellers positioned substantially at the height of the center of mass of the combination and to thus achieve the above mentioned general ob j ects of the present invention.
It is a still more specific object of the present invention to provide an unmanned remotely piloted aircraft combination that uses rigid counter rotating propellers positioned substantially at the height of the center of mass of the combination to allow larger control moments which thus cope with large unbalance moments such as produced by a tether line holding the aircraft captive.
It is a still more specific object of the present invention to provide an unmanned remotely piloted aircraft that allows to have a configuration with counter rotating propellers positioned at intermediate hei~ht between the top and bottom thereof and also with two generally spheroidal surfaces above and below the propellers for minimum exposure to detection by radar reflection and the like due to the inherent dispersive nature of such surfaces.
BRIEF DESCRIPTION OF THE DRAWINGS
The above and other objects and advantages of the present invention will be bet-ter understood with refer-ence to the following detailed description of a preferred embodiment thereof which is illustrated, by way of example, in the accompanying drawings; in which:
Figure 1 is a cross-sectional view in elevation of an unmanned aircraft according to the present invention;
Figure 2 is an exploded elevation view of the lQ same aircraft to illustrate its modular concept;
Figure 3 is an elevation view partly in cross section of the propellers, blades and swashplate intercon-nection shown in a larger scale and in a slightly different embodiment than in Figure l; and Figure 4 is an elevation view as seen in the direction of the arrows 4-4 in Figure 3.
The illustrated remotely piloted unmanned air-craft comprises a body that is symmetrical about a vertical axis. That aircraft body comprises vertically superposed sections including an uppermost section 1, an intermediate section 2, and a lowermGst section 3. Each of these sections constitutes a separable module constructed and arranged to be readily disconnected for maintenance or replacement.
., The uppermost module or section 1 includes a rotary internal combustion engine or turbine 4 fixedly mount-ed on a supporting bracket 5. A generally annular or dough-nut shaped gas tank is positioned around the engine 4 and ~.~5~3~
is thus used to shield the hot parts of the engine against infra-red detection. The outside of the body is provided with a housing or shell 7 having a generally spheroidal out-line to be the least susceptible to radar detection. This iS 50 due to the inherent high dispersive nature of spheroid-al surfaces to radar waves or reflections. The exhaust out-let 8 for the engin~ 4 is positioned at the top of the upper-most section and thus also of the whole body of the aircraft and is upwardly directed to be concealed against infra-red detection from the ground, down below, The lowermost section or module 3 is also provided with a housing or shell 9 of generally s~heroidal outline in which is housed the necessary flight control units. The control units do not form part of the present invention and therefore will not be described in the present disclosure.
Suspension brackets 11 are fixedly secured at their upper end, inside the lowermost body section. These suspension brackets are constructed and arranged to releasably support a payload 12 that is pivotally suspended by the brackets, in any well known manner. The payload 12 in this case consti-tutes a data acquisition package for remote control of the vehicle and for surveillance of ground sites such as for enemy surveillance on a battlefield, for traffic surveillan-ce, or for other civil uses. A shielding hood 13 is provi-ded over and around the data acquis~tion payload 12.
A landing gear l~ is attached to the exterior of the lowermost section 3 and includes a landing ring 15. The latter is connected to the lowermost body section 3 by means of three legs 16 each in the form of a shock absorbing strut that is pivotally connected at its opposite ends to the lowermost body section and to the landing ring respectively.
The intermediate body section 2 includes a pair of counterrotating propellers 17 and 18 and the associated control mechanisms shown in greater details in Figure 3. A
gearbox 19 is centrally mounted at the top of the intermedia-te body section, and through appropriate shaft and gearing arr~ngement, not shown, it drives the top propeller hub 20 in one direction and the bottom propeller hub 21 in the opposite direction. Each propeller 17, 18 includes 3 blades 22 having each a hub portion 23, as shown in Figure 1 rotatively mounted in its corresponding propeller hub 20 or 21.
The collective and cyclic pitch control mechanisms illustrated in Figures 1 and 3 are essential;y the same with only some secondary differences. The embodiment of Figure 1 will first be described in details. As shown in Figure 1, the collective and cyclic pitch control mechanism is connect-ed to the blades 22 to selectively vary the pitch angle ofeach blade around its blade pitch control axis defined by the corresponding blade hub 23. A swash plate 24 is mounted between the two counterrotating propellers and is tiltable by any appropriate means, not shown in two orthogonal directions corresponding to the selected pitch an roll directions of the aircraft. A pair of rings 25 are rotably attached to the swashplate to rotate coaxially around it in well known manner. A blade pitch actuator arm 26 is pivotal-ly connected, for each blade 22, at one end to the correspond-ing blade hub ~3 and at the other end to the corresponding ring 25 to vary the bl~de pitch in relation with bodily tilting of the swashplate and rings for cyclic pitch control or in xelation with bodily up or downi displacement of the swashplate and rings for collective pitch control, all as is well known in the art.
The collective and cyclic pitch control mechanism illustrated in Figure 3 represents a slightly different embo-diment compared to the embodiment in Figure 1 and morespecifically defines how the propeller hubs 20, 21 and the swashplate 25 are mounted in the vehicle or aircraft body.
The latter is provided with a fixed central shaft 27 having fixedly secured thereto spoked wheels 28 around which are rotatably mounted the propeller hubs 20 and 21 respectively.
Each of the propeller hub 20, 21 carries a ring gear 29 that is driven by the engine 4 through appropria~e pinion and shaft drive, not shown. In this embodiment, each blade 22 has a hub portion 30 rotatably engaged in a radial projection 31 of the corresponding propeller hub. A lever 32 is fixed to each blade hub 30, as in the embodiment of Figure 1, for connection of the blade pitch actuation arm 26 to it;
In this embodiment of Figure 3, the swashplate 24 is shown tiltably mounted on a ball joint 33 fixed to a spool shape support 34 that is slidable along the shaft 27. Thus the ~ertical sliding of the support 3~ produces the same displacement of the swashplate 24 and collecti~e control of the blade pitch angles.
A tether line 35 is attached to the lower end of the aircraft more particularly by one of its ends attached to a ring 36 that is mounted on bal bearings to freely rotate relative to the body of aircraft. The tether line is coiled on a spool 37 that is releasably carried by the aircraft during a flight. Any remote controlled releasable latch system is provided to releasably hoid the spool onboard during flight. When desired for landing, the spool 37 is remotely unlatched or released to allow it to fall to the ground where the tether line is then pulled on to safely and guidably land the aircraft independently of adverse weather conditions and excessively accurate control performance.
Claims (8)
1. An unmmanned remotely piloted aircraft comprising, in combination, - a body that is substantially symmetrical about a vertical axis, - a pair of counterrotating propellers vertically positioned substantially at the height of the center of mass of the combination, fixedly posi-tioned and rotatable about the vertical axis of symmetry of the body, and including each at least three blades, and propeller hub means opera-tively carrying the three blades, - each of the blades including a blade hub portion rigidly integral therewith, defining a blade pitch control axis, and fixedly positioned relative to the propeller hub means and rotatable about the corresponding blade pitch control axis, and means to collectively and cyclically control the blade pitch angles of the propellers and construc-ted and arranged to exclusively provide thrust and pitch and roll moments.
2. An unmanned remotely piloted aircraft as defined in claim 1, wherein - said body comprises separable sections defining - an uppermost section including an engine laterally shielded by a fuel tank, - an intermediate section including the counterrota-ting propellers, and - a lowermost section including a payload.
3. An unmanned remotely piloted aircraft as defined in claim 2, wherein a quick connect-disconnect connection joins each of the uppermost and lowermost sections to the intermediate section and is constructed and arranged for quick separation of either section from the other sections.
4. An unmanned remotely piloted aircraft as defined in claim 3, wherein the intermediate section includes a gear-box openly accessible at the top thereof and the quick connect-disconnect connection joining the intermediate sec-tion to the uppermost section is operatively connected to the gearbox and firmly joins the intermediate section to the uppermost section.
5. An unmanned remotely piloted aircraft as defined in claim 4, wherein the uppermost section includes an exhaust outlet connected to the engine and outwardly opening at the top of said body in substantial concealment from infra red detection from the ground.
6, An unmanned remotely piloted aircraft as defined in claim 1, 2 or 5, further comprising control means constructed and arranged to produce cyclic change of the propeller blade pitch angles to generate moments to control and stabilize the attitude of the body axis of symmetry with respect to verti-cal, control means constructed and arranged to produce col-lective change of the propeller blade pitch angles to control the level of thrust produced by the propellers and control means constructed and arranged to produce differential speed of the two propellers to generate torque reactions on the body to control and stabilize the orientation of the body around the axis of symmetry.
7. An unmanned remotely piloted aircraft as defined in claim 1, 2 or 5, further comprising a tether line including a coil releasably deployable from said body, having one end remaining operatively connected onboard; and being construct-ed and arranged for captive landing of the aircraft upon pulling on the released tether line.
8. An unmanned remotely piloted aircraft as defined in claim 1, 2, or 5 wherein said uppermost and lowermost sections are of generally spheroidal outline.
Priority Applications (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA000377951A CA1151130A (en) | 1981-05-20 | 1981-05-20 | Unmanned remotely piloted aircraft |
| FR8205012A FR2506256B1 (en) | 1981-05-20 | 1982-03-24 | REMOTE PILOT ROBOT AIRCRAFT |
| DE3211039A DE3211039C2 (en) | 1981-05-20 | 1982-03-25 | Unmanned remote controlled aircraft |
| GB08208931A GB2103167B (en) | 1981-05-20 | 1982-03-26 | Unmanned remotely piloted aircraft |
| IT67536/82A IT1191190B (en) | 1981-05-20 | 1982-04-22 | REMOTE CONTROLLED AIRCRAFT ROBOT |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA000377951A CA1151130A (en) | 1981-05-20 | 1981-05-20 | Unmanned remotely piloted aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1151130A true CA1151130A (en) | 1983-08-02 |
Family
ID=4119996
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000377951A Expired CA1151130A (en) | 1981-05-20 | 1981-05-20 | Unmanned remotely piloted aircraft |
Country Status (5)
| Country | Link |
|---|---|
| CA (1) | CA1151130A (en) |
| DE (1) | DE3211039C2 (en) |
| FR (1) | FR2506256B1 (en) |
| GB (1) | GB2103167B (en) |
| IT (1) | IT1191190B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2581613B1 (en) * | 1985-05-07 | 1987-12-11 | Durand Roger | DEVICE FOR TRANSPORTING AND LIFTING LOADS FOR THEIR MOVEMENT BY AIR PROPULSION |
| US6981844B2 (en) * | 2003-10-08 | 2006-01-03 | Hamilton Sundstrand | Cyclic actuation system for a controllable pitch propeller and a method of providing aircraft control therewith |
| RU2371354C2 (en) | 2007-12-28 | 2009-10-27 | Зубков Сергей Геннадьевич | Method to control flight in expanded range of speeds with controlled thrust-vector rotors |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB568548A (en) * | 1943-06-28 | 1945-04-10 | James Robert Anderson | Improvements in aircraft |
| US3149803A (en) * | 1961-07-19 | 1964-09-22 | Us Industries Inc | Tethered hovering platform |
| DE2434042C3 (en) * | 1974-07-16 | 1979-04-26 | Dornier Gmbh, 7990 Friedrichshafen | Vertical flying aircraft |
| US4123018A (en) * | 1976-01-12 | 1978-10-31 | Tassin De Montaigu Rene C A | Helicopters with coaxial rotors, of convertible type in particular |
-
1981
- 1981-05-20 CA CA000377951A patent/CA1151130A/en not_active Expired
-
1982
- 1982-03-24 FR FR8205012A patent/FR2506256B1/en not_active Expired
- 1982-03-25 DE DE3211039A patent/DE3211039C2/en not_active Expired - Lifetime
- 1982-03-26 GB GB08208931A patent/GB2103167B/en not_active Expired
- 1982-04-22 IT IT67536/82A patent/IT1191190B/en active
Also Published As
| Publication number | Publication date |
|---|---|
| IT1191190B (en) | 1988-02-24 |
| DE3211039A1 (en) | 1982-12-09 |
| FR2506256A1 (en) | 1982-11-26 |
| GB2103167A (en) | 1983-02-16 |
| FR2506256B1 (en) | 1985-12-06 |
| IT8267536A0 (en) | 1982-04-22 |
| DE3211039C2 (en) | 1993-10-21 |
| GB2103167B (en) | 1984-12-12 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKEX | Expiry |