• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    An active lift propellant (100) includes an annular flange (110) and a propeller propulsion assembly (120) within the annular flange (110). The propulsion assembly (120) includes first and second propellers (122, 123) collinearly positioned within the annular flange. The first and second propellers (122, 123) are counter-rotating.
    公开号:FR3049575A1
    申请号:FR1652781
    申请日:2016-03-31
    公开日:2017-10-06
    发明作者:Nicolas Autrusson；Julien Castex；Philippe Lopez
    申请人:Herakles SA；
    IPC主号:
    专利说明:

    Background of the invention
    The present invention relates to propellant devices of the active lift type.
    In a context of increased mobility, while road infrastructures are increasingly congested in large cities, intra-urban air mobility represents an interesting solution.
    Aerial devices adapted for the transport of persons and / or goods must be able to take off and land on distances or small surfaces such as roofs of buildings.
    Document FR 1 412 382 describes a propulsion device of the type comprising channel or channel wings ("Custer Channel Wing") which make it possible to obtain very short take-off distances. The principle of this technology is to provide the wings with a concave profile defining a channel or a gutter in which is disposed a propeller motor, the propeller being designed to rotate in the vicinity of the trailing edge of the channel in which it is mounted . This creates a lift on each wing not by the speed of movement of the latter in the air but by the speed of the air around the wing induced by the propeller. The propeller placed in the channel of the wing creates a flow and, consequently, a depression above the wing which, although immobile, undergoes lift allowing a takeoff over a short distance. However, if such a technical solution can significantly reduce the take-off distances, it does not provide sufficiently compact devices to be able to evolve in urban environments where the circulation space is limited.
    Object and brief description of the invention
    The present invention aims to provide a solution for propellant devices capable of taking off over short distances and which have a small footprint. The invention also aims to provide such devices with a reduction of noise at the propulsion system.
    According to the present invention, this object is achieved by means of an active lift propulsion device comprising an annular wing and a propulsion propulsion assembly present inside the annular wing, the propulsion assembly comprising first and second helices placed in a collinear or coplanar manner within the annular flange, the first and second propellers being contra-rotating. The use of two contra-rotating propellers inside the annular flange makes it possible to eliminate the torsion torque of the device around its roll axis so that it is not necessary to provide a stabilizing rotor. This greatly optimizes the compactness of the propulsion device. The use of two counter-rotating propellers also makes it possible to straighten the air flow for the control surfaces (control surfaces) downstream in the propeller.
    Moreover, the two propellers being keeled inside the annular wing significantly reduces the noise generated by the propulsion system by canceling the vortex at the end of the propeller which are usually a source of significant noise on unveined propellers .
    According to one embodiment of the propulsion device of the invention, the first and second propellers are arranged coaxially inside the annular flange.
    According to a particular feature of this embodiment, the annular wing has in cross section a circular shape extending around a longitudinal central axis, the annular wing comprising an upper portion extending downstream of a plane of reference perpendicular to the longitudinal central axis and a lower portion extending upstream of said reference plane, the first helix extending in the vicinity of the trailing edge of the annular wing at the bottom of the annular wing and in the vicinity of the leading edge of the annular flange at the upper portion of said annular flange.
    This arrangement creates a vacuum on the upper surface of the lower part of the annular flange and an overpressure on the lower surface of the upper part. This increases the lift of the annular wing.
    According to another particular characteristic, the first propeller is placed upstream of the second propeller with respect to the leading edge of the annular wing.
    According to yet another particular characteristic, the lower and upper portions of the annular flange have a curved bearing profile while the lateral parts of the annular flange have a symmetrical straight profile.
    According to another embodiment of the propulsion device of the invention, the two propellers are arranged next to each other inside the annular wing, the two propellers being aligned along a reference plane perpendicular to a longitudinal axis of the annular wing.
    According to a particular characteristic of this embodiment, the annular wing has in cross section an oval shape extending around a longitudinal axis, the annular wing comprising an upper portion extending downstream from a reference plane. perpendicular to the longitudinal axis and a lower portion extending upstream of said reference plane, the two helices extending in the vicinity of the trailing edge of the annular flange at the bottom of the annular flange and at the adjacent the leading edge of the annular wing at the upper part of said annular flange. With an annular wing having an oval cross-section in cross-section, the ratio between the bearing surface (upper and lower portions of the annular flange) and the non-bearing symmetrical surface (side portions of the annular flange connecting the lower and upper parts) is increased. .
    This arrangement creates a vacuum on the upper surface of the lower part of the annular flange and an overpressure on the lower surface of the upper part. This increases the lift of the annular wing.
    According to another characteristic, the lower and upper parts of the annular wing have a cambered profile while the lateral portions of the annular wing have a symmetrical straight profile.
    BRIEF DESCRIPTION OF THE DRAWINGS Other characteristics and advantages of the invention will emerge from the following description of particular embodiments of the invention, given by way of non-limiting examples, with reference to the appended drawings, in which: FIGS. and 2 are very schematic views respectively front and rear of a propulsion device according to an embodiment of the invention, Figure 3 is a vertical radial sectional view along the section plane III indicated on the FIG. 2 is a horizontal radial sectional view along the sectional plane IV shown in FIG. 3; FIG. 5 is a cross section of the annular wing of the propulsion device of FIG. 3 along the section plane V; indicated in FIG. 3, FIGS. 6 and 7 are very schematic views respectively of front and rear views of a propulsion device according to another embodiment of FIG. embodiment of the invention, Figure 8 is a vertical radial sectional view along the sectional plane VIII shown in Figure 7, Figure 9 is a horizontal radial sectional view along the section plane IX shown in Figure 8, FIG. 10 is a cross-section of the annular wing of the propulsion device of FIG. 8 along the section plane X indicated in FIG. 8.
    DETAILED DESCRIPTION OF THE EMBODIMENTS OF THE INVENTION
    Figures 1, 2 and 5 schematically illustrate a propellant device or aircraft 100 of active lift type according to a first embodiment of the invention. The propulsion device 100 comprises an annular flange 110 having in cross section a circular shape extending around a longitudinal central axis Xcno so as to define a duct 101 (Figure 3). The annular flange 110 has a leading edge 111 upstream and a trailing edge 112 downstream.
    The propulsion device 100 also comprises a propulsion assembly 120 housed inside the annular flange 110. The propulsion assembly 120 here comprises a rotary motor 121 connected to the inner wall of the annular flange by two arms 1210 and 1211 having an aerodynamic profile. The propulsion assembly further comprises a first helix 122 and a second helix 123 mounted coaxially along the longitudinal central axis Xcno, the first propeller 122 being placed upstream of the second propeller 123 relative to the edge of the propeller. attack 111 of the annular wing 110. In the context of the present description, the term "upstream" and "downstream" the directions respectively upstream and downstream of the flow of a propellant fluid through the two propellers indicated by arrow F in FIGS. 1 and 2. In the example described here, the first and second propellers each comprise two blades.
    The first and second propellers 122 and 123 are contra-rotating or counter-rotating propellers in that the first propeller 122 rotates in a first direction, for example the clockwise direction, while the second propeller 123 rotates in a second opposite direction, for example the counterclockwise direction. In the example described here, the first and second propellers 122 and 123 are driven by the same rotary motor 121, the propellers being well known per se, each connected to the rotary motor 121 via a mechanical gearbox. (Not shown in Figures 1 and 2) and an independent shaft (not shown in Figures 1 and 2) connected to the output of the corresponding gearbox. According to an alternative embodiment, the propulsion system may comprise two rotary engines each directly rotating one of the two propellers. The use of two counter-rotating propellers inside the annular wing makes it possible to eliminate the reversal torque of the propulsion device around its roll axis so that it is not necessary to provide a stabilizing rotor on the device. This greatly optimizes the compactness of the device while reducing noise thanks to the fairing of the propellers. The fairing of the propellers also improves the safety of people near the propulsion device.
    An empennage 130 is attached downstream of the annular wing 110 by two arms 131 and 132. The empennage 130 has here an inverted cap or V shape to ensure the steering pitch, roll and yaw of the propulsion device. The propulsion device 100 further comprises a cockpit 140 placed upstream of the propulsion assembly 120, the cockpit 140 being intended to carry at least one passenger and / or goods to be transported. The annular flange 110 is formed of four parts: a lower part 1100, an upper part 1101 and two lateral parts 1102 and 1103 connecting the lower part 1100 to the upper part 1101. As illustrated in FIGS. 3 and 4, the lower part 1100 and the upper part 1101 have a curved profile that is to say bearing, for example of the NACA 2412 or Clark Y type, while the side portions 1102 and 1103 have a symmetrical profile, that is to say not for example of NACA 0012 type. If one traverses the annular wing in its circumferential direction, it thus has an evolutionary aerodynamic profile which alternates between arched profile, on the lower and upper parts of the wing, and symmetrical profile, on the lateral parts of the wing. The symmetrical side portions 1102 and 1103 make it possible to connect the lower and upper portions 1100 and 1101 of the annular flange while minimizing the drag.
    Furthermore, the lower part 1100 and the upper part 1101 of the annular flange 110 are offset along the longitudinal central axis Xcno. More precisely and as shown in FIG. 3, the upper part 1101 of the flange 110 extends downstream from a reference plane Pri perpendicular to the longitudinal central axis Xcno while the lower part 1100 from the flange 110 extends upstream of the reference plane Pri. The reference plane Pri intersects the annular wing 110 at both the leading edge 111 in its upper part 1101 and at the trailing edge 112 in its lower part so that the leading edge 111 of the annular flange 110 at the top 1101 is substantially perpendicular to the trailing edge 112 at the lower portion 1100. This provision creates a vacuum on the upper surface of the lower part 1100 of the wing annular 110 and an overpressure on the lower surface of the upper part 1101, which increases the lift of the annular wing.
    The first propeller 122 extends substantially at the reference plane Pri while the second propeller 123 is placed downstream of the first propeller. The first and second propellers 122 and 123 each preferably have a diameter close to the inside diameter of the annular flange 110 so as to minimize the space between the ends of the propellers and the annular flange.
    Figures 6, 7 and 10 schematically illustrate a propellant device or aircraft 200 of active lift type according to another embodiment of the invention. The propulsion device 200 comprises an annular wing 210 having in cross section an oval shape extending around a longitudinal axis Χαιο so as to define a conduit 201 (Figure 10). The annular flange 210 comprises upstream a leading edge 211 and downstream a trailing edge 212.
    The propulsion device 200 also comprises a propulsion assembly 220 housed inside the annular flange 210. The propulsion assembly 220 here comprises a first and a second rotary engine 221 and 222, the first motor 221 being connected to the propulsion unit 220. inner wall of the annular flange by a first arm 2210 and the fuselage 202 of the propulsion device by a second arm 2211 each having an airfoil while the second motor 222 is connected to the inner wall of the annular flange by a first arm 2220 and the fuselage 202 of the propulsion device by a second arm 2221 each having an aerodynamic profile. The propulsion assembly further comprises a first propeller 223 mounted on the first rotary engine 221 and a second propeller 224 mounted on the second rotary engine 222, the first and second propellers 223 and 224 being coplanar, that is to say aligned along a reference plane Pr2 (FIG. 8). In the context of the present description, "upstream" and "downstream" mean the directions respectively upstream and downstream of the flow of a propulsive fluid through the two propellers indicated by the arrow F in FIGS. 6 and 7. In the example described here, the first and second propellers each comprise two blades.
    The first and second propellers 223 and 224 are contra-rotating or counter-rotating propellers in that the first propeller 223 rotates in a first direction, for example the clockwise direction, while the second propeller 224 rotates in a second opposite direction, by example counterclockwise. The use of two counter-rotating propellers inside the annular wing makes it possible to eliminate the reversal torque of the propulsion device around its roll axis so that it is not necessary to provide a stabilizing rotor on the device. This greatly optimizes the compactness of the propulsion device while reducing noise thanks to the fairing of the propellers. The fairing of the propellers also improves the safety of people near the propulsion device.
    In the example described here, the aircraft 200 comprises a tail V or butterfly 230 comprising two flaps 231 and 232 serving both as elevators and steering (steering pitch and yaw). The empennage 230 is here fixed on the fuselage 202 of the propulsion device downstream of the annular wing 110.
    The fuselage 202 of the aircraft 100 further comprises a cockpit 240 placed upstream of the propulsion assembly 220, the cockpit 240 being intended to carry at least one passenger and / or goods to be transported. The annular flange 210 is formed of four parts: a substantially planar lower portion 2100, a substantially planar upper portion 2101 and two curved side portions 2102 and 2103 connecting the lower portion 2100 to the upper portion 2101. As illustrated in FIGS. 9, the lower part 2100 and the upper part 2101 have a curved profile that is to say carrying, for example of the NACA 2412 or Clark Y type, while the lateral parts 2102 and 2103 have a symmetrical profile, it is ie non-bearing, for example of the NACA 0012 type. If the annular wing is traversed in its circumferential direction, this latter therefore has an evolutionary aerodynamic profile which alternates between arched profile, on the low and high parts of the the wing, and symmetrical profile, on the lateral parts of the wing.
    The symmetrical side portions 2102 and 2103 make it possible to connect the lower and upper portions 2100 and 2101 of the annular flange while minimizing the drag.
    Furthermore, the lower portion 2100 and the upper portion 2101 of the annular flange 210 are offset along the longitudinal central axis Χαιο. More precisely, and as shown in FIG. 8, the upper portion 2101 of the wing 210 extends downstream from a reference plane Pr2 perpendicular to the longitudinal central axis Xc210 while the lower portion 2100 of the wing 210 extends upstream of the reference plane Pr2. The reference plane Pr2 intersects the annular flange 210 at both the leading edge 211 in its upper part 2101 and at the trailing edge 212 in its lower part so that the leading edge 211 of the annular flange 210 at the upper portion 2101 is substantially plumb with the trailing edge 212 at the bottom 2100. This provision creates a vacuum on the upper surface of the lower part 2100 of the wing annular 210 and an overpressure on the lower surface of the upper part 2101.
    The propellers 223 and 224 extend substantially at the reference plane Pr2.
    The drive of the propulsion device can be automatic and performed in a manner known per se by a programmable automatic system (not shown in the figures) or semi-automatic, that is to say with the possibility for the passenger to manually take orders where applicable.
    The propellers used in the propulsion device according to the invention may comprise two blades as described above or more.
    The motor (s) used in the propulsion assembly of the propulsion device according to the invention are preferably electric motors powered by batteries or fuel cells.
    The batteries or fuel cells as well as any inert mass of the propulsion device are preferably arranged in a balanced manner on or in the side portions 1102 and 1103 of the annular flange 110 so as not to disturb the control of the device.
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    An active lift propellant device (100) comprising an annular flange (110) and a propeller propulsion assembly (120) within the annular flange (110), the propulsion assembly (120) comprising first and second propellers (122, 123) placed colinearly or coplanarly within the annular flange, the first and second propellers (122, 123) being counter-rotating.
    [2" id="c-fr-0002]
    2. Device according to claim 1, wherein the first and second propellers (122, 123) are arranged coaxially inside the annular flange (110).
    [3" id="c-fr-0003]
    3. Device according to claim 2, wherein the annular flange (110) has in cross section a circular shape extending around a central longitudinal axis (Xcno), the annular flange (110) having an upper portion ( 1101) extending downstream from a reference plane (Pri) perpendicular to the longitudinal central axis (Xcuo) and a lower portion (1100) extending upstream of said reference plane (Pri) and in which the first helix (122) extends in the vicinity of the trailing edge (112) of the annular wing at the lower portion (1100) of the annular wing (110) and in the vicinity of the leading edge (122) of the annular flange at the top (1101) of said annular flange.
    [4" id="c-fr-0004]
    4. Device according to claim 3, wherein the first propeller is placed upstream of the second propeller with respect to the leading edge of the annular flange.
    [5" id="c-fr-0005]
    5. Device according to any one of claims 2 to 4, wherein lower and upper portions (1200, 1201) of the annular flange (110) have a bearing arch profile while side portions (1202, 1203) of the annular flange (110) has a symmetrical straight profile.
    [6" id="c-fr-0006]
    6. Device according to claim 1, wherein the two propellers (223, 224) are arranged next to each other inside the annular flange (210), the two propellers being aligned in a plane reference plane (Pr2) perpendicular to a longitudinal axis (Xc2io) of the annular wing.
    [7" id="c-fr-0007]
    7. Device according to claim 6, wherein the annular flange (210) has in cross section an oval shape extending around the longitudinal axis (Xcno), the annular wing having an upper portion (2101) s'. extending downstream of the reference plane (Pr2) perpendicular to the longitudinal axis (Xc2io) and a lower part (2100) extending upstream of said reference plane and in which the two propellers (223, 224) extend at adjacent the trailing edge (212) of the annular wing at the lower portion (2100) of the annular wing (210) and in the vicinity of the leading edge (211) of the annular wing at the level of the upper portion (2101) of said annular flange.
    [8" id="c-fr-0008]
    8. Device according to claim 6 or 7, wherein lower and upper portions (2200, 2201) of the annular flange (210) have a bearing arch profile while side portions (2202, 2203) of the annular wing. (210) have a symmetrical straight profile.
    类似技术:
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    同族专利:
    公开号 | 公开日
    WO2017168088A1|2017-10-05|
    FR3049575B1|2019-08-16|
    WO2017168089A1|2017-10-05|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR893866A|1943-05-24|1944-11-08|Aerodyne|
    US2879957A|1954-08-02|1959-03-31|Collins Radio Co|Fluid sustained aircraft|
    GB865524A|1956-07-02|1961-04-19|Snecma|Improvements in or relating to annular-wing aircraft|
    US3017139A|1959-02-02|1962-01-16|Binder Wilhelm|Ring airfoil aircraft|
    FR2871136A1|2004-06-04|2005-12-09|Bertin Technologies Soc Par Ac|MINIATURIZED DRONE WITH LANDING AND VERTICAL TAKE-OFF|US10604237B2|2011-02-11|2020-03-31|Andreas Voss|Aircraft with a weight element controlling the center of gravity thereof|
    US11014669B2|2018-09-17|2021-05-25|Amazon Technologies, Inc.|Six degree of freedom aerial vehicle having pivoting wing sections|FR1412382A|1963-12-30|1965-10-01|Custer Channel Wing Corp|Winged airplane in canal|US11249477B2|2018-09-17|2022-02-15|Amazon Technologies, Inc.|Six degree of freedom aerial vehicle having reconfigurable propellers|
    US11136119B2|2018-09-17|2021-10-05|Amazon Technologies, Inc.|Six degree of freedom aerial vehicle having reconfigurable motors|
    法律状态:
    2017-02-10| PLFP| Fee payment|Year of fee payment: 2 |
    2017-10-06| PLSC| Search report ready|Effective date: 20171006 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 3 |
    2018-07-27| CD| Change of name or company name|Owner name: ARIANEGROUP SAS, FR Effective date: 20180621 |
    2018-07-27| TP| Transmission of property|Owner name: ARIANEGROUP SAS, FR Effective date: 20180621 |
    2019-03-21| PLFP| Fee payment|Year of fee payment: 4 |
    2020-03-13| PLFP| Fee payment|Year of fee payment: 5 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1652781|2016-03-31|
    FR1652781A|FR3049575B1|2016-03-31|2016-03-31|PROPULSIVE DEVICE WITH ACTIVE PORTABILITY|FR1652781A| FR3049575B1|2016-03-31|2016-03-31|PROPULSIVE DEVICE WITH ACTIVE PORTABILITY|
    PCT/FR2017/050710| WO2017168089A1|2016-03-31|2017-03-28|Active lift propulsion device having coplanar propellers|
    PCT/FR2017/050709| WO2017168088A1|2016-03-31|2017-03-28|Propulsion device with active lift|
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