• 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:
    The invention relates to a device for assisting a propulsion system of a single-engined helicopter comprising a motor connected to a transmission transmission box (15) adapted to rotate a rotor of the helicopter, characterized in that it comprises: a turbine (18) rotational drive of an output shaft (34) mechanically connected to said transmission box (15); and means (16) for supplying said pressurized fluid drive turbine (18) to enable said turbine (18) to transform the energy of said pressurized fluid into rotational mechanical energy of said shaft (34) Release.
    公开号:FR3019588A1
    申请号:FR1453123
    申请日:2014-04-08
    公开日:2015-10-09
    发明作者:Romain Thiriet；Camel Serghine；Patrick Marconi；Jean-Louis Besse；Pascal Guillemet；Guillaume Demezon；Philippe Barrat；Francois Danguy；Jean-Michel Sannino；De Chanaud Nicolas Marucheau
    申请人:Turbomeca SA；SNECMA SAS；Herakles SA；
    IPC主号:
    专利说明:

    [0001] DEVICE FOR ASSISTING A SOLID PROPERGOL PROPULSIVE SYSTEM OF A MONOMOTOR HELICOPTER, MONOMOTOR HELICOPTER COMPRISING SUCH DEVICE AND CORRESPONDING METHOD 1. TECHNICAL FIELD OF THE INVENTION The invention relates to a device and a method for assisting a propulsion system of a single engine helicopter. Such a device is particularly intended to assist a single-engine helicopter during an autorotational flight following the engine failure of the helicopter, said engine can be a turbine engine, a combustion engine or an electric motor. 2. Background Technology A single-engine helicopter is a helicopter that is equipped with only one turbine engine or internal combustion engine. When the single engine of such a helicopter fails during a mission, the pilot must very quickly follow a degraded flight procedure known as autorotation flight. This procedure is in practice complicated to implement, in particular the step to lower the collective pitch at the beginning of the maneuver and the step to synchronize the action on the collective pitch and the approach of the ground at the end of maneuver. Statistics show that in practice more than 50% of the autorotations practiced by the pilots lead to damages on the helicopters. There is therefore a need for a helper device for a single-engined helicopter that can be used during an autorotational flight or for securing autorotation flight in the event of failure of the single engine of a helicopter. single engine helicopter. 3. OBJECTIVES OF THE INVENTION The invention aims at providing a device for assisting a propulsion system of a single-engine helicopter making it possible to assist a single-engine helicopter during an autorotation flight, in the event of a non-stop. controlled engine. The invention also aims to provide, in at least one embodiment, such a device that has no significant impact on the total weight of the helicopter.
    [0002] The invention also aims to provide a method of assisting a propulsion system of a single-engine helicopter. 4. DISCLOSURE OF THE INVENTION To this end, the invention relates to a device for assisting a propulsion system of a single-engine helicopter comprising a motor connected to a power transmission gearbox adapted to drive in rotation a rotor of the engine. 'helicopter. A device according to the invention is characterized in that it comprises: a turbine driving in rotation of an output shaft mechanically connected to said power transmission box, controlled means for supplying said drive turbine pressurized fluid to enable said turbine to transform the energy of said pressurized fluid into rotational mechanical energy of said output shaft. A device according to the invention therefore makes it possible to supply mechanical power to the power transmission box (hereinafter BTP) when necessary. Such a device is therefore particularly suitable for assisting the helicopter mechanically during an autorotation flight, particularly during the last phases of the flight. In addition, such a device comprises a drive turbine and fluid supply means of this turbine. These are small equipment and have a negligible weight compared to the total weight of a helicopter. They can therefore be installed on a single-engine helicopter without degrading the performance of the helicopter. These devices also have high reliability, which gives a device according to the invention robustness and reliability. The use of a device according to the invention thus makes it possible to make autorotal flights of a helicopter more reliable and to thus substantially improve the landing rates without damage necessitating a long immobilization of the helicopter. Advantageously and according to the invention, said controlled fluid supply means of said turbine comprise, as the case may be, pneumatic, hydraulic, pyrotechnic and / or electric means. A driving turbine of a device according to the invention can be of all types. In particular, it is fed with a gaseous fluid under pressure. The means for controlling the actuation of said turbine may be pneumatic, hydraulic, electric or pyrotechnic. Advantageously and according to the invention, said controlled power supply means of the driving turbine comprise: at least one solid propellant gas generator comprising a gas outlet connected to an inlet of the driving turbine, at least one An Electrically Controlled Gas Generator Ignition Device Such controlled power supply means of the pressurized fluid drive turbine utilize novel technology which includes a solid propellant gas generator. Such a generator is relatively compact and can easily integrate for example either in a turbine engine, or at other points in the power transmission chain to the main gearbox. A solid propellant makes it possible, by combustion (oxidation-reduction reaction), the generation of highly energetic gas combustion products. Such controlled power supply means of the drive turbine have a high density of power and energy compared to an electric accumulator for example. In addition, such power supply means have full autonomy vis-à-vis the electrical network of the helicopter. When an engine failure occurs, the ignition device of the gas generator is activated at the opportune moment by the pilot (at the very beginning of the failure to restore a sudden fall of rotor turns or near the ground). This activation causes the start of the solid propellant gas generator. The gases produced by the generator rotate the drive turbine of the output shaft, and therefore the power transmission box mechanically connected to the output shaft.
    [0003] An assistance device according to this variant of the invention thus makes it possible to quickly assist a single-engine helicopter having lost the use of its engine, by providing the power to maintain a drive of the power transmission gearbox and thus the speed rotor of the helicopter. Such a device can be operated either at the beginning of autorotation to assist the pilot in the critical phase which aims to lower the collective pitch, or at the end of autorotation during the phase which aims to synchronize the action on the collective pitch and the approach of the ground. Advantageously and according to the invention, the device comprises several solid propellant gas generators so as to have several different sources of power supply and thus allow successive activations of said device. Advantageously and according to this variant, the power supply means of the driving turbine further comprise a distribution valve controlled by an electronic box connecting the gas outlet of a gas generator to the inlet of the drive turbine. . Advantageously, an assistance device according to the invention is mainly intended to equip a propulsion system of a turbine engine comprising a gas generator, a free turbine powered by the gas generator, a gearbox and a so-called free wheel of power connected to said power transmission gearbox. Such a device advantageously comprises a gearbox and a freewheel arranged between the output shaft of the drive turbine and the power transmission box (BTP). Advantageously and according to a variant of the invention, the freewheel is connected directly to said power transmission box. Such a configuration has the advantage of being able to supply surplus power as close as possible to the BTP and to be suitable in this configuration for other types of engines, such as for example an internal combustion engine. The assistance device thus makes it possible to overcome the failures of all the engine components located upstream of the BTP. An assistance device according to this first configuration can also be used to assist another type of engine such as an internal combustion engine. Advantageously and according to another variant of the invention, the free wheel is connected directly to a shaft arranged between said power free wheel of said motor and said power transmission box. Such a configuration also has the advantage of being able to supply the surplus power as close as possible to the input of the BTP. Compared to the previous configuration, this variant also has the advantage of providing a connection with a shaft arranged in the motor perimeter. Advantageously and according to another variant, the freewheel is connected directly to a shaft arranged between said gearbox of said motor and said power freewheel of said motor. Such a configuration has the advantage of remaining in the motor perimeter. On the other hand, it does not make it possible to mitigate a possible failure of the free wheel of power. According to another variant, the device does not include a gearbox. Such a device comprises only a freewheel connected directly to a shaft upstream of the gearbox of the engine. Such a configuration has the advantage of not requiring a speed reducer specific to the assistance device since it uses that of the engine. This saves space and mass.
    [0004] The invention also relates to an architecture of a propulsion system of a single-engine helicopter, characterized in that it comprises at least one assistance device according to the invention. Advantageously and according to a variant of the invention, the architecture of the propulsion system comprises: a turbine engine comprising a gas generator, a free turbine supplied by said gas generator, a gearbox arranged at the outlet of the free turbine and a free wheel, said power wheel, arranged between the gear reducer and a power transmission box, an assistance device according to the invention comprising a freewheel arranged between the output shaft of the drive turbine and the input of the turbine engine speed reducer. Advantageously and according to another variant of the invention, the architecture of the propulsion system comprises: a turbine engine comprising a gas generator, a free turbine powered by said gas generator, a gearbox arranged at the outlet of the free turbine and a free wheel, said power wheel, arranged between the gearbox and a power transmission box, an assistance device according to the invention comprising a gearbox and a freewheel arranged between the output shaft of the turbine drive and the power transmission box. The invention also relates to a helicopter comprising a propulsion system characterized in that said propulsion system has an architecture according to the invention.
    [0005] The invention also relates to a method of assisting a propulsion system of a single-engine helicopter comprising a motor connected to a power transmission gearbox adapted to rotate a rotor of the helicopter, characterized in that it comprises a step of controlling the supply of fluid under pressure of a drive turbine mechanically connected to said power transmission box, a step of transformation by said drive turbine of the power of the fluid under pressure in mechanical power for rotating said power transmission gearbox.
    [0006] The invention also relates to an assistance method, an architecture of a propulsion system and a helicopter characterized in combination by all or some of the characteristics mentioned above or below. 5. List of Figures Other objects, features and advantages of the invention will become apparent on reading the following description given solely by way of non-limiting example and which refers to the appended figures in which: FIG. 1 is a diagrammatic view of a device for assisting a propulsion system of a single-engine helicopter according to one embodiment of the invention, FIG. 2 is a schematic view of an architecture of a propulsion system according to one embodiment of the invention comprising an assistance device according to one embodiment of the invention, FIG. 3 is a schematic view of an architecture of a propulsion system according to another embodiment of the invention comprising an assistance device according to a embodiment of the invention, FIG. 4 is a schematic view of an architecture of a propulsion system according to another embodiment of the invention comprising a salt-assisted device FIG. 5 is a schematic view of an architecture of a propulsion system according to another embodiment of the invention comprising an assistance device according to another embodiment of the invention. FIG. 6 is a schematic view of an architecture of a propulsion system according to another embodiment of the invention comprising an assistance device according to another embodiment of the invention. DETAILED DESCRIPTION OF AN EMBODIMENT OF THE INVENTION An assistance device according to the invention comprises, as represented in FIG. 1, a turbine 18 for driving in rotation a mechanical output shaft 34 to the power transmission box 15 of a helicopter, itself connected to a rotor 88 of the helicopter. It also includes controlled means 16 for supplying the turbine 18 for driving fluid under pressure to enable the turbine 18 to transform the energy of the pressurized fluid into the mechanical energy of rotation of the output shaft 34. According to the embodiment of FIG. 1, the controlled power supply means 16 of the turbine 18 are pyrotechnic means. They comprise a solid propellant gas generator 22, an electrically controlled solid propellant ignition device 24 and a computer 28 connected to the ignition device 24. The gas outlet of the generator 22 is connected via a line to an inlet 44 of the turbine 18 for driving. The gas generator 22 here comprises a cylindrical body containing one or more solid propellant charges of shapes adapted to the desired gas flow law of the generator, this body serving as a combustion chamber. It should be noted that the desired flow rate can be obtained by means of an appropriate choice of the shape of the load and / or by the total or partial inhibition of certain loading parts. After ignition of the surface of the propellant charge, the surface of the charge burns and progresses producing combustion gases under high pressure, according to the law of flow resulting from the shape and the inhibition of the loading. The gases are evacuated at the output of the generator and are conveyed to the inlet 44 of the turbine 18. The path of the gases is represented by the arrows 30 and 32.
    [0007] The ignition device 24 is electrically controlled by the computer 28 and is intended to activate the combustion of the propellant as soon as a corresponding signal is emitted by the computer 28. The computer 28 is an electronic control unit such as those commonly used in the aeronautical field. When the pilot detects a loss of power on the single turbine engine of the single engine helicopter, the pilot sends an order to the computer 28 which activates the ignition device 24 so that the turbine 18 is powered by the gas combustion generated by burning solid propellant. The turbine 18 for driving is for example a turbine of the supersonic type. It essentially comprises a shaft 34 carrying a rotor wheel 36, the shaft 34 being guided in rotation by bearings 40 mounted in a casing 42 of the turbine. The housing 42 comprises a radial orifice forming the inlet 44 of the turbine 18 and opening into an annular cavity 46 for feeding the turbine. This cavity 46 may have a constant section from upstream to downstream or, conversely, have a scalable section from upstream to downstream, the optimization of this cavity being carried out by those skilled in the art. The combustion gases that enter the cavity 46 expand and flow through the vanes 48 of the wheel 36 (arrows 50), which causes the wheel 36 and thus the shaft 34 to rotate about its axis (arrow 52). The gases then escape from the turbine 18 through a nozzle thereof and are discharged to the outside (arrows 50). A filter 53 may be mounted upstream of the turbine so as to limit the introduction of solid particles into the vein of the turbine. The shaft 34 makes it possible to transmit a torque to the power transmission box 15 by means of a gearbox 19 and a freewheel 20.
    [0008] According to other embodiments, the drive turbine may be a centripetal turbine and generally all types of rotating machines for converting the power of a fluid into a mechanical power. It may for example be a spur gear motor as described in the patent application FR2990004 in the name of the applicant.
    [0009] Figures 2 to 6 show various embodiments of the architecture of a propulsion system of a helicopter comprising an assistance device according to the invention. These different architectures highlight different coupling configurations between the shaft 34 and the gearbox 15. In FIGS. 2 to 6, the turbine 18 and the means 16 for controlling and generating energy fluids are not detailed for the sake of clarity.
    [0010] According to the embodiment of FIGS. 2 to 6, the propulsion system comprises either an internal combustion engine or a turbine engine formed of a gas generator 7 supplying a free turbine 12, a speed reducer 13 and a freewheel 14, known as power, connected to the power transmission box 15. The gas generator 7 comprises, in known manner, at least one air compressor 8 supplying a combustion chamber 9 with a fuel in the compressed air which delivers hot gases to at least one partial gas expansion turbine 10 in rotation the compressor 8 via a drive shaft 11. The gases then drive the free power transmission turbine 12. This free turbine 12 comprises a power transmission shaft 6 connected to the power transmission box 15 by means of the speed reducer 13 and the freewheel 14 of power. This freewheel 14 of power makes it possible to prevent a mechanical blockage of the turbine engine resulting in a mechanical blocking of the power transmission box 15 and by extension 15 of the rotor of the helicopter on which this turbine engine is mounted. FIG. 2 is an embodiment in which the free wheel 20 is connected directly to the power transmission box 15. This embodiment is also suitable for an internal combustion engine. Figure 3 is an embodiment in which the freewheel 20 is connected to a shaft 21 arranged between the freewheel 14 of the turbine engine and the power transmission box 15. This embodiment is also suitable for an internal combustion engine. Figure 4 is an embodiment in which the freewheel 20 is connected to the output or an intermediate stage of the speed reducer 13 of the turbine engine. This mechanical connection between the free wheel 20 and the output of the gearbox 13 is represented by the shaft 66 in FIG. 4. FIG. 5 is an embodiment in which the free wheel 20 is connected to the input of the gearbox 13. turbine engine speeds. According to this embodiment, the assistance device does not include a specific gearbox 30. This mechanical connection between the free wheel 20 and the inlet of the gearbox 13 is represented by the shaft 6 in FIG.
    [0011] Finally, Figure 6 is an embodiment in which the assistance device comprises at least two generators 16a, 16b of solid propellant gas. Such an assistance device forms a multi-shot system which therefore has more power than a single-shot system. In the case of this multi-stroke system, the controlled supply means of the driving turbine 18 may comprise, besides the generators 16a, 16b of solid propellant gas, a distribution valve 26 connecting the gas outlet of the generators. at the inlet 44 of the turbine 18 drive, so as to select which gas generator feeds the turbine 18 drive. The computer that controls the ignition device of gas generators is connected to this valve 26 for control. According to another variant, an isolation valve 23 is arranged between the generator 16a and the turbine 18 to protect the generator 16a during the operation of the generator 16b. Such a variant is particularly suitable in the case where it is always the generator 16b that operates first. According to another variant, not shown in the figures, and for the case where it is not determined which generator will operate first, two isolation valves 23 are arranged respectively between the generator 16a and the turbine 18 and between the generator 16b and the turbine 18. Such a variant protects each generator during operation of the other generator. Figure 6 simultaneously shows an isolation valve 23 and a distribution valve 26 for clarity. However, it is not necessary to keep both valves simultaneously. In other words, three architectures are possible: an architecture in which two isolation valves are provided; an architecture in which a single isolation valve is provided in the case where it is always the same generator that is activated first; and an architecture in which a single distribution valve is provided. The invention also relates to a method of assisting a propulsion system of a single-engine helicopter comprising a turbine engine connected to a power transmission gearbox adapted to rotate a rotor of the helicopter. Such a method comprises a step of controlling the pressurized fluid supply of a drive turbine mechanically connected to said power transmission box and a step of transformation by said drive turbine of the power of the fluid under pressure. mechanical power to rotate said power transmission. The control order of the pressurized fluid supply of the turbine 18 is performed by the pilot of the helicopter through a contactor housed in the cockpit piloting. This contactor makes it possible, for example, to supply, via a dedicated electrical network, the computer 28, which serves as a pyrotechnic initiator, in the case of a supply of the turbine by gases from a solid propellant gas generator such as described in connection with Figure 1. To avoid inadvertent activation of the assistance device, the control means can be configured so that the control command is not executed if at least one predetermined condition is not met . Each predetermined condition is characteristic of a situation which makes the training of the BTP by the system dangerous or useless taking into account the conditions of flight. For example, logical combinations of the following conditions may be provided to inhibit the execution of the control command: - the helicopter is flying at a height greater than a minimum height Hsol min (for example, 100 feet) - the speed rotation NR of the rotor is greater than a minimum predetermined rotation speed NRmin (eg NRmin flight manual), Of course, other conditions may be provided according to the needs and depending on the safety that you want to put in. square. The invention is not limited to the embodiments described. In particular, according to other embodiments, the assistance device can comprise several solid propellant gas generators so that the driving turbine can be powered by one or other of the generators. This makes it possible to have a complement of power by at least two different lanes possibly at two different instants of the flight (at the beginning and the end of the autorotation procedure for example). In addition, this makes it possible to have storers of different size, which also makes it possible to modulate the desired profile.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. Device for assisting a propulsion system of a single-engine helicopter comprising a motor connected to a gearbox (15) adapted to drive a rotor (88) of the helicopter in rotation, characterized in that it comprises a turbine (18) for driving in rotation an output shaft (34) mechanically connected to said power transmission box (15); - controlled power supply means (16) for said turbine (18) fluid pressurizing drive to enable said turbine (18) to transform the energy of said pressurized fluid into rotational mechanical energy of said output shaft (34).
    [0002]
    2. Device according to claim 1 characterized in that said means (16) for supplying said drive turbine (18) comprise pneumatic, hydraulic, pyrotechnic and / or electric means.
    [0003]
    3. Device according to claim 1, characterized in that said means (16) for supplying power to said turbine (18) comprises: - at least one solid propellant gas generator (22) comprising a connected gas outlet at an inlet (44) of the drive turbine, - at least one device (24) for igniting an electrically controlled gas generator (22)
    [0004]
    4. Device according to one of claims 1 to 3, characterized in that it comprises several solid propellant gas generators so as to have several separate sources of power supply.
    [0005]
    5. Device according to claims 3 and 4 taken together, characterized in that said means (16) for supplying said turbine (18) for driving further comprises a valve (26) for distribution controlled by a housing (28) electronic connecting the gas outlet of the gas generators (22) to the inlet (44) of the drive turbine.
    [0006]
    6. Device according to one of claims 1 to 5 for a propulsion system of a turbine engine comprising a generator (7) of gas, a turbine (12) free connected to the gas generator (7), a reducer (13) of and a free wheel (14), said power, connected to said transmission box (15), characterized in that it comprises a housing (19) gear and a free wheel (20) arranged between said shaft ( 34) output of said turbine (18) drive and said box (15) power transmission.
    [0007]
    7. Device according to claim 6, characterized in that said free wheel (20) has one or other of the following configurations: a configuration in which it is connected directly to said transmission box (15), a configuration in which it is directly connected to a shaft arranged between said power free wheel (14) of said turbine engine and said power transmission box (15), a configuration in which it is directly connected to a shaft (66) arranged between said speed reducer (13) of said turbine engine and said free wheel (14) of power of said turbine engine.
    [0008]
    8. Device according to one of claims 1 to 5 for a propulsion system of a turbine engine comprising a generator (7) of gas, a turbine (12) free connected to the gas generator (7), a reducer (13) of and a free wheel (14) said power, connected to said transmission box (15), characterized in that it comprises a free wheel (20) connected directly to a shaft (6) arranged between said turbine ( 12) and said speed reducer (13) of said turbine engine.
    [0009]
    9. Architecture of a propulsion system of a single-engine helicopter, characterized in that it comprises at least one assistance device according to one of claims 1 to 8.
    [0010]
    10. Helicopter comprising a propulsion system, characterized in thatthe propulsion system has an architecture according to claim 9.
    [0011]
    11. A method of assisting a propulsion system of a single-engine helicopter comprising a motor connected to a power transmission box (15) adapted to rotate a rotor (88) of the helicopter, characterized in that it comprises: a step of controlling the pressurized fluid supply of a drive turbine (18) mechanically connected to said power transmission box (15), a step of transformation by said turbine (18) driving the power of the pressure fluid under mechanical power to rotate said power transmission box (15).
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3129619B1|2019-02-27|Solid propellant device for assisting a propulsion system of a single-engine helicopter, single-engine helicopter comprising such a device
    CA2389780C|2010-10-12|Emergency device for restarting a turbojet in autorotation
    EP2635782B1|2017-07-05|Method of optimizing the specific fuel consumption of a twin engine helicopter and twin engine architecture for implementing it
    EP2148066B1|2011-08-17|Hybrid power plant and method of controlling such a power plant
    EP3175090B1|2019-05-22|Pneumatic device for rapidly reactivating a turbine engine, architecture for a propulsion system of a multi-engine helicopter provided with such a device, corresponding helicopter and method
    EP3047117B1|2017-11-01|System and method for the emergency starting of aircraft turbomachines
    WO2014118458A1|2014-08-07|Structure for providing an aircraft with emergency electric power
    EP3055531B1|2018-07-25|Method for optimising the specific consumption of a twin helicopter
    FR3019221A1|2015-10-02|HYDRAULIC DEVICE FOR THE EMERGENCY STARTING OF A TURBOMOTEUR, ARCHITECTURE OF A PROPULSIVE SYSTEM OF A MULTI-ENGINE HELICOPTER EQUIPPED WITH SUCH A DEVICE AND CORRESPONDING HELICOPTER
    EP2547583B1|2014-02-26|Method and device for driving at least one landing gear wheel of an aircraft by means of a wheel motor
    WO2020008147A1|2020-01-09|Aircraft propulsion system and aircraft powered by such a propulsion system built into the rear of an aircraft fuselage
    EP3448751B1|2020-10-14|Auxiliary system for driving a shaft of a helicopter propulsion system
    FR3078681A1|2019-09-13|METHOD FOR PUTTING A POWER DEFICIT IN THE EVENT OF AN ENGINE FAILING ON A MULTI-ENGINE ROTARY WING AIRCRAFT
    FR3033882A1|2016-09-23|GAS GENERATOR
    同族专利:
    公开号 | 公开日
    CA2944839A1|2015-10-15|
    EP3129619A1|2017-02-15|
    US20170114723A1|2017-04-27|
    JP6740137B2|2020-08-12|
    RU2684693C2|2019-04-11|
    WO2015155450A1|2015-10-15|
    RU2016142637A3|2018-10-29|
    KR102258405B1|2021-05-31|
    CN106536350A|2017-03-22|
    CN106536350B|2021-10-19|
    ES2719437T3|2019-07-10|
    FR3019588B1|2019-06-14|
    JP2017521589A|2017-08-03|
    KR20170002400A|2017-01-06|
    RU2016142637A|2018-05-08|
    EP3129619B1|2019-02-27|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2986879A|1957-06-12|1961-06-06|Bendix Corp|Solid propellant starter|
    GB2460246A|2008-05-21|2009-11-25|Matthew P Wood|A helicopter emergency power system|
    FR2992024A1|2012-06-15|2013-12-20|Turbomeca|METHOD AND ARCHITECTURE OF OPTIMIZED ENERGY TRANSFER BETWEEN AN AUXILIARY POWER MOTOR AND THE MAIN MOTORS OF A HELICOPTER|WO2017187078A1|2016-04-28|2017-11-02|Safran Helicopter Engines|Auxiliary system for driving a shaft of a helicopter propulsion system|
    WO2017187079A1|2016-04-28|2017-11-02|Safran Helicopter Engines|Mechanical drive device comprising an ignition system|
    WO2018150121A1|2017-02-15|2018-08-23|Safran Helicopter Engines|Propulsion system for a single-engine helicopter|
    WO2018150138A1|2017-02-15|2018-08-23|Safran Helicopter Engines|Method and system for controlling an emergency device|
    EP3461742A1|2017-10-02|2019-04-03|Bell Helicopter Textron Inc.|Hybrid power systems for aircraft|
    EP3362357A4|2015-10-13|2019-06-12|Newrocket Ltd.|Thrusting rockets for enhancing emergency autorotation|
    FR3104136A1|2019-12-10|2021-06-11|Airbus Operations |Aircraft propulsion system|GB605971A|1944-12-30|1948-08-04|British Thomson Houston Co Ltd|Improvements relating to speed governors for rotary wing aircraft|
    US2460246A|1945-04-07|1949-01-25|Redmond Company Inc|Speed-responsive rheostat|
    GB1389403A|1971-06-01|1975-04-03|Westland Aircraft Ltd|Helicopter power transmission systems|
    US5020316A|1989-05-19|1991-06-04|Coltec Industries Inc.|Helicopter control with multiple schedule rotor speed decay anticipator|
    JPH05193579A|1992-01-20|1993-08-03|Mitsubishi Heavy Ind Ltd|Turboshaft engine|
    RU2065381C1|1993-01-19|1996-08-20|Вертолетный научно-технический комплекс им.Н.И.Камова|Helicopter primary gearbox|
    US7032860B1|2004-11-05|2006-04-25|Eatts, Llc|Emergency anti-torque thruster system|
    FR2922860B1|2007-10-26|2010-01-22|Eurocopter France|IMPROVEMENT TO GIRAVIONS EQUIPPED WITH TURBOMOTORS|
    FR2967132B1|2010-11-04|2012-11-09|Turbomeca|METHOD OF OPTIMIZING THE SPECIFIC CONSUMPTION OF A BIMOTING HELICOPTER AND DISSYMMETRIC BIMOTOR ARCHITECTURE WITH A CONTROL SYSTEM FOR ITS IMPLEMENTATION|
    FR2990004B1|2012-04-27|2014-04-18|Turbomeca|METHOD AND SYSTEM FOR EMERGENCY STARTING ENERGY GENERATING ARCHITECTURE|FR3019524B1|2014-04-03|2017-12-08|Turbomeca|HELICOPTER ENGINE CHAIN INCORPORATING A PYROTECHNIC ENGINE ASSISTANCE MODULE AND HELICOPTER COMPRISING THE SAME|
    FR3104333A1|2019-12-10|2021-06-11|Airbus Operations |Aircraft comprising an emergency source of electrical power.|
    法律状态:
    2015-04-14| PLFP| Fee payment|Year of fee payment: 2 |
    2016-04-21| PLFP| Fee payment|Year of fee payment: 3 |
    2016-05-06| RM| Correction of a material error|Effective date: 20160404 |
    2017-04-07| PLFP| Fee payment|Year of fee payment: 4 |
    2017-08-25| CD| Change of name or company name|Owner name: SAFRAN HELICOPTER ENGINES, FR Effective date: 20170725 Owner name: HERAKLES, FR Effective date: 20170725 Owner name: SNECMA, FR Effective date: 20170725 |
    2017-09-01| CD| Change of name or company name|Owner name: HERAKLES, FR Effective date: 20170727 Owner name: SAFRAN HELICOPTER ENGINES, FR Effective date: 20170727 Owner name: SNECMA, FR Effective date: 20170727 |
    2017-10-27| TQ| Partial transmission of property|Owner name: SAFRAN HELICOPTER ENGINES, FR Effective date: 20170922 Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170922 Owner name: SNECMA, FR Effective date: 20170922 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 5 |
    2018-03-23| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180221 Owner name: SAFRAN HELICOPTER ENGINES, FR Effective date: 20180221 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 Owner name: SAFRAN HELICOPTER ENGINES, FR Effective date: 20170719 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1453123A|FR3019588B1|2014-04-08|2014-04-08|DEVICE FOR ASSISTING A SOLID PROPERGOL PROPULSIVE SYSTEM OF A MONOMOTING HELICOPTER, MONOMOTOR HELICOPTER COMPRISING SUCH DEVICE AND CORRESPONDING METHOD|
    FR1453123|2014-04-08|FR1453123A| FR3019588B1|2014-04-08|2014-04-08|DEVICE FOR ASSISTING A SOLID PROPERGOL PROPULSIVE SYSTEM OF A MONOMOTING HELICOPTER, MONOMOTOR HELICOPTER COMPRISING SUCH DEVICE AND CORRESPONDING METHOD|
    US15/301,939| US20170114723A1|2014-04-08|2015-04-03|Device for assisting a solid propellant propulsion system of a single-engine helicopter, single-engine helicopter comprising such a device|
    EP15719802.9A| EP3129619B1|2014-04-08|2015-04-03|Solid propellant device for assisting a propulsion system of a single-engine helicopter, single-engine helicopter comprising such a device|
    CN201580021826.9A| CN106536350B|2014-04-08|2015-04-03|Auxiliary device for assisting the propulsion system of a single-engine helicopter|
    JP2016561761A| JP6740137B2|2014-04-08|2015-04-03|Device to assist solid propellant propulsion system of single-shot helicopter, single-shot helicopter equipped with such device|
    PCT/FR2015/050878| WO2015155450A1|2014-04-08|2015-04-03|Device for assisting a solid propellant propulsion system of a single-engine helicopter, single-engine helicopter comprising such a device|
    RU2016142637A| RU2684693C2|2014-04-08|2015-04-03|Device for facilitating a power plant on solid propergol of a single-engine helicopter, a single-engine helicopter containing such a device and a corresponding method|
    ES15719802T| ES2719437T3|2014-04-08|2015-04-03|Assistance device for a solid propergol propellant system of a single-engine helicopter, single-engine helicopter comprising said device|
    CA2944839A| CA2944839A1|2014-04-08|2015-04-03|Device for assisting a solid propellant propulsion system of a single-engine helicopter, single-engine helicopter comprising such a device|
    KR1020167030416A| KR102258405B1|2014-04-08|2015-04-03|Device for assisting a solid propellant propulsion system of a single-engine helicopter, single-engine helicopter comprising such a device|
    [返回顶部]