• 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:
    - Removable auxiliary power device for aircraft and aircraft adapted to use at least one such device. - The auxiliary power device (1) is removably connectable externally to said aircraft (7) so as to increase the performance of the aircraft, especially at takeoff and landing. It comprises a propeller (or fan) (5) connected to an electric motor (4) powered by a power source (3).
    公开号:FR3030453A1
    申请号:FR1462893
    申请日:2014-12-19
    公开日:2016-06-24
    发明作者:Olivier Cazals；Thierry Druot；Julien Guillemaut
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a removable auxiliary power device for aircraft and an aircraft adapted to use or comprising at least one such auxiliary power device. Aircraft users are known to seek maximum flexibility for the aircraft they operate to obtain the most appropriate services. However, for reasons of construction costs and operating costs, the basic performance of these aircraft is generally best suited to the basic missions that these aircraft are required to perform and can not be increased if these aircraft are to be completed. missions requiring superior performance. The object of the present invention is to overcome these disadvantages by making it possible to improve, if necessary, the basic performance of an aircraft without increasing operating costs when said aircraft performs a basic mission that does not require increased performance. The present invention notably allows an aircraft to access airports whose tracks would be too short to ensure, with its basic performance, landings and takeoffs without difficulties. To this end, according to the invention, the auxiliary power device for aircraft is remarkable: in that it comprises at least one electric motor, a power source for said electric motor and a propeller (or fan) connected to said electric motor and capable of generating at least one of the following forces: a propulsive force, a reverse force opposed to the direction of the speed of the aircraft; and in that it is externally connectable detachably to said aircraft. Thus, by virtue of the present invention, when the mission to be performed by the aircraft requires performance that is superior to its basic performance, at least one auxiliary power device is connected to said aircraft that can provide the latter with the performance supplement delivered. by said propeller. On the other hand, as soon as this mission requiring superior performance is completed, the auxiliary power device can be dismantled, so that the aircraft regains its configuration and its basic performance.
    [0002] Since said propeller (or fan) can operate in propulsion mode or in reverse mode, it will be readily understood that, in case of takeoff on a track too short for the basic performance of the aircraft, it can receive, auxiliary device a power supply operating in propulsion mode, a power supply enabling it to take off unhindered and that, conversely, in the event of landing on such a runway, said auxiliary power device, operating in the opposite mode, generates a force opposite to the speed involved in braking said aircraft.
    [0003] In a simplified embodiment, the helix is configured to generate only a propulsive force. In addition, in another embodiment, the helix is configured to be able to generate one or the other of said forces (propulsion force, reverse force) as required.
    [0004] Such ability of the auxiliary power device to operate in the propulsion mode or in the reverse mode may result from the fact that the helix (or fan) can rotate in both directions of rotation or is equipped with a pitch variation device. The power supply source of the auxiliary power device according to the present invention may be formed by at least one battery or at least one supercapacitor. In particular in the particular case where the auxiliary power device is intended for a civil transport aircraft, the mass of the power supply source can be of the order of 100 kg to more than 1000 kg and the power supplied by the helix (or fan) can be of the order of 50 KVA to more than 1000 KVA. Preferably, the auxiliary power device comprises a nacelle enclosing at least said electric motor and said power supply source, and a pylon adapted to connect said nacelle to said aircraft. For this purpose, this auxiliary power device may comprise a removable coupling device disposed at the end of said pylon opposite said nacelle. In the auxiliary power device, said propeller (or fan) may be disposed upstream or downstream of said nacelle with respect to the aerodynamic flow around the aircraft.
    [0005] The present invention furthermore relates to an aircraft capable of using at least one auxiliary power device specified above, this aircraft being remarkable in that it comprises at least one removable connection device, accessible from the outside, able to receive said auxiliary power device, in particular by cooperating with a removable coupling device integral with said auxiliary power device. When said aircraft comprises two wings symmetrical with respect to its longitudinal axis, it may comprise at least two removable connecting devices carried by said wings and, for balancing reasons, arranged symmetrically with respect to said axis longitudinal. Advantageously, the device (s) of removable connection of said aircraft is (are) arranged (s) to the lower part thereof, so that said auxiliary power devices are suspended from said aircraft. These are then particularly accessible for maintenance purposes.
    [0006] Alternatively, the connection of the auxiliary power device or devices may be located at the fuselage, for example laterally at the rear part of the fuselage. The present invention further relates to an aircraft equipped with at least one auxiliary power device as specified above, said auxiliary power device being removably connected to said aircraft. The appended figures will make it clear how the invention can be realized. In these figures, identical references designate similar elements.
    [0007] Figure 1 illustrates, in schematic perspective, an embodiment of the auxiliary power device according to the present invention, mounted externally on an aircraft part. FIG. 2 is a schematic side view of the auxiliary power device of FIG. 1, with partial detachments.
    [0008] FIG. 3 illustrates, in a diagrammatic side view similar to FIG. 2, the auxiliary power device separated from the aircraft part. FIG. 4 shows, in perspective from the front and from the top, an aircraft equipped with two auxiliary power devices according to the present invention.
    [0009] FIG. 5 is a view from the front of the aircraft of FIG. 4.
    [0010] FIG. 6 shows, in perspective seen from the rear and the top, a variant of the aircraft of FIGS. 4 and 5. The auxiliary power device 1, making it possible to illustrate the present invention and represented in FIGS. 1, 2 and 3, comprises a nacelle 2 in which are contained at least one power source 3, such as at least one battery or a supercapacitor, an electric motor 4 and an associated control electronics. The power source 3 and the electric motor 4 are able to rotate a helix 5, possibly ducted, external to the nacelle 2 and rotatable in both directions or provided, in a known manner and not shown, a pitch variation device. The nacelle 2 is secured to a pylon 6, which can connect removably to an outer portion 7 of an aircraft. To this end, at its end opposite the nacelle 2, the tower 6 comprises a connecting device 8, adapted to cooperate detachably with a connecting device 9 provided on said outer part of the aircraft 7. In FIGS. 3, the cooperating coupling devices 8 and 9 are not shown in detail, because they can be of any known type, such as those used for the carriage of weapon systems by combat aircraft. As illustrated in FIGS. 2 and 3, the cooperating coupling devices 8 and 9 allow the removable attachment of the power device 1 on the outer part of the aircraft 7 (FIG. 2), as well as the separation of the power device from said outer part of aircraft 7 (Figure 3). FIGS. 4 and 5 show a civil aircraft 10, whose wings 11 and 12 each support a turbine engine 13 and 14 respectively. In addition, each of said wings supports, as described with reference to FIGS. 1 to 3. for the outer part of the aircraft 7, an auxiliary power device 1, the two auxiliary power devices 1 30 being symmetrical to each other with respect to the longitudinal axis LL of the civil aircraft 10. In this civil aircraft 10, it is assumed, as shown in FIGS. 4 and 5, that the propellers 5 of the auxiliary power devices 1 are disposed upstream of said nacelle 2 with respect to the aerodynamic flow around said aircraft 10.
    [0011] On the contrary, in the civil aircraft 20 with two wing motors 23 and 24, shown in FIG. 6, the wings 21 and 22 also carry two auxiliary power devices 1, symmetrical to each other with respect to the longitudinal axis XX of said aircraft 20, but the propellers 5 of the auxiliary power devices 1 are disposed downstream of said nacelle 2 with respect to the aerodynamic flow around said aircraft 20. The power delivered by the propeller 5 of each device 1 of the aircraft 10 and 20 can be of the order of 50 KVA to 1000 KVA or more, while the mass of the electrical source 3 can be of the order of 100 kg to 1000 kg or more. In a manner not shown in FIGS. 1 to 3, the nacelle 2 comprises opening hoods allowing access to its interior, in particular for maintenance purposes of the power source 3, the electric motor 4 and the associated electronics. .
    [0012] The maintenance operations are clearly facilitated when, as is illustrated in Figures 1 to 3, the auxiliary power device 1 is suspended under the outer part of aircraft 7 via its tower 6. However, this auxiliary device power can be arranged laterally relative to the fuselage of aircraft 10 and 20, for example in the rear part of this fuselage. From the foregoing description, it will be readily understood that the auxiliary power devices 1 can be used not only to allow take-offs or landings of the short-track aircraft 10 and 20 as indicated above, but also to move these aircraft to ground, especially when the turbine engines 13, 14 and 23, 24 are stopped. When the auxiliary power devices 1 are set up on an airplane and that it moves under the action of its turbine engines, the propellers of these auxiliary power devices 1 are rotated, thanks to the electrical energy from generators associated with the turboshaft engines, which makes it possible to improve the dilution ratio of the overall propulsion system of said aircraft. Moreover, as is generally the case for civil transport aircraft, when the aircraft 10, 20 comprises an auxiliary power unit APU intended to allow ground servitudes while the turbine engines are stopped, it is possible to supply the auxiliary power devices 1 at least partly from this APU unit. Thus, thanks to the present invention, the power produced by the latter can then be used to propel the aircraft. In addition, it will be noted that: - the power supply source 3 of a power auxiliary device 1 can not only be recharged on the ground during maintenance operations, but also in flight thanks to a reel operation of this device 1; that the positioning of the auxiliary power devices 1 outside the aircraft 10, 20 not only allows easy access to the elements 3, 4 they contain, but also an effective cooling thereof, in particular by convection which increases security; and - that the connection device or devices 9 provided on the aircraft 7, 10, 20 can receive different auxiliary power devices that are different and adapted to different needs, so as to allow the replacement of the following auxiliary power device (1) the need.
    权利要求:
    Claims (12)
    [0001]
    REVENDICATIONS1. Auxiliary power device (1) for aircraft (7, 10, 20) characterized in that it comprises at least one electric motor (4), a power supply source (3) for said electric motor and a propeller (5) connected to said electric motor (4) and capable of generating at least one of the following forces: a propulsive force, a reverse force opposed to the direction of the aircraft speed; and in that it is externally releasably connectable to said aircraft (7, 10, 20).
    [0002]
    2. auxiliary power device (1) according to claim 1, characterized in that said propeller (5) can rotate in both directions.
    [0003]
    3. Auxiliary power device (1) according to claim 1, characterized in that said propeller (5) is equipped with a pitch variation device.
    [0004]
    4. Auxiliary power device (1) according to one of claims 1 to 3, characterized in that the power delivered by said propeller (5) is of the order of 50 to more than 1000 KVA.
    [0005]
    5. Auxiliary power device (1) according to one of claims 1 to 4, characterized in that said power supply (3) is at least one battery or a supercapacitor and in that the mass of said source power supply is in the range of 100 to over 1000 kg.
    [0006]
    6. auxiliary power device (1) according to one of claims 1 to 5, characterized in that it comprises a nacelle (2) enclosing at least said electric motor (4) and said power source (3). ), and a pylon (6) adapted to connect said nacelle (2) to said aircraft (7, 10, 20).
    [0007]
    7. auxiliary power device (1) according to claim 6, characterized in that said propeller (5) is disposed upstream of said nacelle (2) relative to the aerodynamic flow. 35
    [0008]
    8. Auxiliary power device (1) according to claim 6, characterized in that said propeller (5) is disposed downstream of said nacelle (2) relative to the aerodynamic flow.
    [0009]
    9. Aircraft (10, 20) adapted to use at least one auxiliary power device (1) according to any one of claims 1 to 8, characterized in that it comprises at least one removable connection device (9) , accessible from the outside, adapted to receive said auxiliary power device (1).
    [0010]
    10. Aircraft (10, 20) according to claim 9, provided with two wings (11, 12; 21, 22) symmetrical with respect to the longitudinal axis (LL; XX) of said aircraft, characterized in that it comprises at least two removable coupling devices (9), carried by said wings and arranged symmetrically with respect to said longitudinal axis.
    [0011]
    11. Aircraft (10, 20) according to one of claims 9 or 10, characterized in that the device (s) of removable connection (9) of said aircraft is (are) arranged (s) at the bottom of the latter, so that the said auxiliary power device (s) (1) are suspended from the said aircraft (10, 20).
    [0012]
    Aircraft (10, 20), characterized in that it is equipped with at least one auxiliary power device (1) as specified in any one of claims 1 to 8, said auxiliary power device (1 ) being removably connected to said aircraft.
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    同族专利:
    公开号 | 公开日
    US20160176533A1|2016-06-23|
    FR3030453B1|2018-09-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US1791707A|1929-09-13|1931-02-10|Jr Joseph Botka|Attachment for aeroplanes|
    US3438304A|1966-05-18|1969-04-15|Matra Engins|Device for mounting a gun beneath the wing of an airplane|
    FR2316178A1|1975-07-03|1977-01-28|Alkan R & Cie|DEVICE FOR LIFTING LOADS ON AIRCRAFT, INCORPORATED IN THE CARRYING AND AUTOMATIC RELEASE SYSTEM|
    US20070145182A1|2005-12-16|2007-06-28|Page Gregory S|Electric motor assisted takeoff device for an air vehicle|
    FR2913935A1|2007-03-20|2008-09-26|Airbus France Sas|METHOD AND DEVICE FOR AERODYNAMIC BRAKING WITH ENERGY ACCUMULATION|
    US8814081B2|2010-12-27|2014-08-26|Rolls-Royce North American Technologies, Inc.|Aircraft and external pod for aircraft|FR3003845B1|2013-04-02|2016-04-15|Labinal|SYSTEM FOR RECOVERING AND CONVERTING KINETIC ENERGY AND POTENTIAL ENERGY IN ELECTRIC ENERGY FOR AIRCRAFT|
    RU2637277C1|2016-09-01|2017-12-01|Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" |Wing of aircraft with retracting air screw|
    EP3492386A1|2017-12-01|2019-06-05|Dietmar Posch|Aircraft with a power supply|
    GB201807773D0|2018-05-14|2018-06-27|Rolls Royce Plc|Aircraft propulsion system|
    RU2696681C1|2018-10-17|2019-08-05|Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" |Aircraft wing|
    WO2020142332A1|2018-12-31|2020-07-09|DZYNE Technologies Incorporated|Drag recovery scheme for nacelles|
    US20210070458A1|2019-09-06|2021-03-11|Hamilton Sundstrand Corporation|Vortex turbines for a hybrid-electric aircraft|
    EP3798129A1|2019-09-30|2021-03-31|Ratier-Figeac SAS|Electric motor for a propeller engine|
    WO2021157736A1|2020-02-06|2021-08-12|Hapsmobile Inc.|Aerodynamic electric motor nacelle|
    法律状态:
    2015-12-21| PLFP| Fee payment|Year of fee payment: 2 |
    2016-06-24| PLSC| Publication of the preliminary search report|Effective date: 20160624 |
    2016-12-22| PLFP| Fee payment|Year of fee payment: 3 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-12-19| PLFP| Fee payment|Year of fee payment: 5 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-12-23| PLFP| Fee payment|Year of fee payment: 7 |
    2021-12-24| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1462893|2014-12-19|
    FR1462893A|FR3030453B1|2014-12-19|2014-12-19|REMOVABLE AUXILIARY POWER DEVICE FOR AN AIRCRAFT AND AN AIRCRAFT SUITABLE FOR USE AT LEAST ONE SUCH DEVICE.|FR1462893A| FR3030453B1|2014-12-19|2014-12-19|REMOVABLE AUXILIARY POWER DEVICE FOR AN AIRCRAFT AND AN AIRCRAFT SUITABLE FOR USE AT LEAST ONE SUCH DEVICE.|
    US14/974,660| US20160176533A1|2014-12-19|2015-12-18|Removable auxiliary power device for aircraft and aircraft adapted to use at least one such device|
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