EP3808012A1 - Dispositif et procédé de communication de données dans un sous-ensemble d'aéronef - Google Patents
Dispositif et procédé de communication de données dans un sous-ensemble d'aéronefInfo
- Publication number
- EP3808012A1 EP3808012A1 EP19737836.7A EP19737836A EP3808012A1 EP 3808012 A1 EP3808012 A1 EP 3808012A1 EP 19737836 A EP19737836 A EP 19737836A EP 3808012 A1 EP3808012 A1 EP 3808012A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- transmitter
- aircraft
- optical channel
- light signal
- receiver
- 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.)
- Pending
Links
- 238000004891 communication Methods 0.000 title claims abstract description 18
- 238000000034 method Methods 0.000 title claims description 4
- 230000003287 optical effect Effects 0.000 claims abstract description 47
- 238000012545 processing Methods 0.000 claims description 28
- 230000005540 biological transmission Effects 0.000 claims description 26
- 238000009792 diffusion process Methods 0.000 claims description 4
- 230000001133 acceleration Effects 0.000 claims description 3
- 230000001141 propulsive effect Effects 0.000 abstract 1
- 230000010354 integration Effects 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000005192 partition Methods 0.000 description 2
- 241000252505 Characidae Species 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000003086 colorant Substances 0.000 description 1
- 230000005288 electromagnetic effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/11—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum
- H04B10/114—Indoor or close-range type systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
- B64D31/02—Initiating means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/02—Arrangements or adaptations of signal or lighting devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/76—Control or regulation of thrust reversers
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/11—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum
- H04B10/114—Indoor or close-range type systems
- H04B10/116—Visible light communication
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D2203/00—Aircraft or airfield lights using LEDs
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/301—Pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/306—Mass flow
- F05D2270/3061—Mass flow of the working fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/50—Control logic embodiments
- F05D2270/54—Control logic embodiments by electronic means, e.g. electronic tubes, transistors or IC's within an electronic circuit
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/80—Devices generating input signals, e.g. transducers, sensors, cameras or strain gauges
- F05D2270/804—Optical devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/80—Devices generating input signals, e.g. transducers, sensors, cameras or strain gauges
- F05D2270/804—Optical devices
- F05D2270/8041—Cameras
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to communication between electronic systems in an aircraft sub-assembly, in particular in an aircraft propulsion assembly.
- An aircraft propulsion unit communicates a large number of low-level data and signals either within the propulsion assemblies or between the propulsion assemblies and the aircraft.
- Optical cables are for example known from document US 5,960,626 A.
- the electrical cables are shielded, which increases their bulk and the weight of the aircraft.
- the stiffness of the shielded cables leads to integration difficulties in the propulsion units. This results in an increase in the cost of the propulsion units and, in certain cases, a modification of the shape of the aerodynamic lines.
- the communication of such data can also be carried out by carrier currents, that is to say by transmission of low level signals in electric power cables.
- An object of the present invention is to overcome the aforementioned drawbacks by proposing an aircraft subassembly facilitating the integration of communication systems, reducing manufacturing or assembly costs, and / or limiting the risks of signal pollution low levels by high frequency signals.
- the invention relates to an aircraft sub-assembly such as a propulsion unit, comprising data processing systems.
- these data processing systems can be chosen from: a full authority digital regulation calculator, called “FADEC”; a thrust reverser control system, called “ETRAS”, for controlling the opening and closing of a thrust reverser of the propulsion unit; one or more systems for measuring and / or analyzing physical parameters such as gas acceleration, pressure or flow; one or more position sensors; etc.
- This aircraft sub-assembly comprises at least one interior volume defining an optical channel.
- this optical channel is not necessarily intended to provide a clear line between a transmitter and a receiver of an optical signal. Indeed, light can be transmitted in a very congested volume by multiple reflections and diffusions on surfaces present in the volume defining the optical channel.
- communications by wireless light signals can be implemented by multiple reflections and diffusions on surfaces present in this volume.
- At least one of the data processing systems comprises at least one transmitter capable of transmitting a light signal in said at least one optical channel.
- this emitted light signal is also called “emission signal”.
- Said at least one transmitter is arranged to modulate the light signal as a function of data to be transmitted generated by this data processing system.
- at least one other of the data processing systems comprises at least one receiver capable of receiving the light signal emitted by said at least one transmitter.
- Such an aircraft subset makes it possible to communicate data by reducing the number of electrical or optical cables.
- this invention can make it possible to reduce the overall mass of a propulsion unit up to 90 kg.
- Such wireless communication also ensures the independence of low-level signals from high-power signals.
- the invention makes it possible to avoid the disconnection of cables at the level of the pylon.
- the invention also makes it possible to communicate members mounted on supports movable relative to one another, such as for example a sliding cover of thrust reverser and the fixed structure which supports it.
- the at least one transmitter can include a light emitting diode.
- said at least one other of the data processing systems can be arranged to transmit a return signal in the at least one optical channel.
- the return signal can be in a bandwidth different from that of the transmission signal.
- Such bandwidth segregation can for example be effected by a difference in modulation of the light signals by the use of signals of different colors filtered in color on reception.
- the aircraft subassembly may include a wall defining two interior volumes. These two volumes respectively form a first and a second optical channel.
- the sub-assembly comprises at least one transmission module capable of transmitting in the second optical channel a light signal emitted in the first optical channel.
- Such a transmission module makes it possible to transmit a light signal through a substantially opaque wall or partition.
- the transmission module can comprise a receiver arranged to receive the light signal emitted in the first optical channel, a transmitter arranged to emit the light signal in the second optical channel, and an electric cable passing through the wall so as to transmit the light signal from the receiver of this transmission module to the transmitter of this transmission module in the form of an electrical signal.
- the wall may include a translucent part forming the transmission module.
- a first wall can comprise a transmission module according to the first variant and a second wall can comprise a transmission module according to the second variant.
- the aircraft subassembly may comprise a pylon having an interior volume constituting an optical channel.
- the aircraft subassembly may comprise a portable digital tablet, this tablet constituting a data processing system comprising at least one of said at least one transmitter and / or comprising at least one said at least one receiver.
- Such a tablet can allow a maintenance agent to dialogue with data processing systems of the propulsion unit or of the aircraft when at least one of the pod covers is open: the volume included under the open cover constitutes an optical channel capable of transmitting maintenance data by light signals under standard lighting conditions.
- the invention also relates to a data communication method implementing a subset of aircraft as defined above.
- Figures 1 to 7 are schematic views in partial longitudinal section of an aircraft subassembly according to the invention.
- Figure 8 is a schematic cross-sectional view of an aircraft sub-assembly according to the invention in the maintenance configuration.
- FIG. 1 An aircraft sub-assembly according to the invention is shown in FIG. 1.
- This sub-assembly comprises a propulsion unit 1 and a pylon 2 connected to a wing 3 of the aircraft.
- the propulsion unit 1 taken as an example consists of a nacelle and a turbofan engine, and includes a thrust reverser.
- the present invention can be implemented in any type of aircraft and any type of corresponding propulsion unit.
- the subset of FIG. 1 comprises multiple data processing systems, in particular a full control digital control computer 10 (FADEC), a thrust reverser control system 11 (ETRAS) arranged to control the opening and closing the thrust reverser, systems for measuring and analyzing physical parameters such as the acceleration, pressure or flow of a gas, and position sensors.
- FADEC full control digital control computer
- ETRAS thrust reverser control system 11
- the invention can be implemented in a propulsion unit provided with all the data processing systems necessary for its operation.
- the sub-assembly which is illustrated therein comprises a plurality of interior volumes IA, IB, 2A ... These volumes are delimited by walls, partitions or components of this sub-assembly.
- the volume IA is delimited by an internal wall 106 and an external wall 108 of a middle section of the nacelle of the propulsion unit 1, by a wall 100 separating the middle section of an upstream section of the nacelle, and by a wall 102 separating the middle section from a rear section of the nacelle.
- the volume 2A is a volume delimited by the walls of the pylon 2.
- These interior volumes are volumes already existing in the propulsion systems of the prior art. These volumes are generally narrow and cluttered with elements or bodies constituting obstacles. These volumes are relatively protected from external light without necessarily being optically closed.
- the invention therefore takes advantage of such confined volumes to communicate data using light signals emitted in these volumes which thus define optical channels, by direct lines or multiple diffusions or reflections on the surfaces present in these volumes.
- At least one of the data processing systems comprises at least one transmitter 20 capable of transmitting a light signal in the optical channel IA.
- This transmitter 20 is arranged to modulate the light signal as a function of the data to be transmitted generated by this data processing system 10.
- at least one other of the data processing systems for example ETRAS 11, comprises at least a receiver 31 able to receive the light signal emitted by the transmitter 20.
- the ETRAS 11 - or more generally said at least one other of the data processing systems - can be arranged to send a return signal in the optical channel IA, preferably in a different bandwidth of the bandwidth of the transmission signal.
- the ETRAS 11 - or this other data processing system - may include a return transmitter 41 capable of emitting a light signal in the optical channel IA and arranged to modulate this light signal as a function of the data to be transmitted generated by this other data processing system 11.
- the FADEC 10 comprises a return receiver 50 capable of receiving the return light signal emitted by the return transmitter 41.
- FIG. 2 illustrates such a communication between FADEC 10 and ETRAS 11: the FADEC 10 transmits an order to ETRAS 11 by emission of a light signal in the optical channel IA via the transmitter 20.
- the light signal emitted by the transmitter 20 is represented by arrows in solid line: this order signal transmitted by the transmitter 20 is in this example reflected on the wall 102 before arriving at the receiver 31, due to the presence of an obstacle 91.
- ETRAS 11 transmits a return signal to FADEC 10 by sending a light signal in the optical channel IA via the return transmitter 41.
- the light signal transmitted by the return transmitter 41 is represented by an arrow in line interrupted.
- the return signal emitted by the return transmitter 41 arrives directly at the return receiver 50, possibly with multi-reflections between the engine and the covers taking into account the geometry of the volume (between cover and engine for example).
- the data processing system 11 may consist not of an ETRAS but of a system for controlling the variation in section of a secondary nozzle of the propulsion unit (not shown).
- FIG. 3 illustrates a communication between the FADEC 10 and an actuator 12 provided for modifying the geometry of a high pressure turbine (not shown) of the propulsion unit 1.
- actuator 12 is commonly designated by the acronym "VSV” ("Variable Stator Valve” in English).
- the FADEC 10 transmits an order to the actuator 12 by emission of a light signal in the optical channel IA via the transmitter 20.
- the light signal emitted by the transmitter 20 is represented by an arrow in solid line and arrives in this example directly at a receiver 36 mounted on the wall 102 so that the receiver 36 opens into the optical channel IA.
- a transmitter 26 is mounted on the wall 102 facing the receiver 36 so that this transmitter 26 opens into a volume IB defining an optical channel of the rear section of the nacelle.
- the receiver 36 and the transmitter 26 can be connected by an electric cable passing through the wall 102 so as to transmit the light signal from the receiver 36 to the transmitter 26 in the form of an electric signal.
- the light signal is then re-emitted by the transmitter 26 in the optical channel IB to arrive at a receiver 32 of the actuator 12 (arrows in solid line).
- the command signal emitted by the transmitter 26 is reflected on an obstacle 92 before arriving at the receiver 32 of the actuator 12.
- the actuator 12 transmits a return signal to the FADEC 10 by emission of a light signal in the optical channel IB via a return transmitter 42.
- the light signal emitted by this return transmitter 42 is shown by dashed arrows.
- the return signal emitted by the return transmitter 42 arrives at a return receiver 56 after reflection on the obstacle 92.
- the return receiver 56 is mounted on the wall 102 so that this return receiver 56 opens into the channel IB optics.
- a return transmitter 46 is mounted on the wall 102 facing the return receiver 56 so that this return transmitter 46 opens into the optical channel IA.
- the return receiver 56 and the return transmitter 46 can be connected by an electric cable passing through the wall 102 so as to transmit the light signal from the return receiver 56 to the return transmitter 46 in the form of an electric signal.
- the invention thus makes it possible to communicate a signal through a wall separating two interior volumes respectively forming a first and a second optical channel.
- the transmitter 26 and the receiver 36 constitute a transmission module: the receiver 36 is arranged to receive the light signal transmitted in the optical channel IA, the transmitter 26 is arranged to transmit the signal bright in the optical channel IB.
- this transmission module is able to transmit in the optical channel IB a light signal emitted in the optical channel IA.
- the return transmitter 46 and the return receiver 56 constitute another similar transmission module.
- a part of the wall delimiting two optical channels can be translucent so as to constitute a transmission module requiring no transmitter or receiver.
- FIGS. 4 to 7 Other examples of data transmission between data processing systems are represented in FIGS. 4 to 7: in the same way as in the examples of FIGS. 2 and 3, the order signals are represented by solid lines and the signals back not broken lines.
- FIG. 4 illustrates a data transmission between, on the one hand, a system 13 for measuring a physical parameter such as the flow of air entering the nacelle and, on the other hand, the FADEC 10.
- FIG. 5 illustrates a data transmission between a computer (not shown) located in the aircraft and a system 14, for example a locking system ("Tertiary Lock System”) offset towards the rear of the nacelle.
- FIG. 6 illustrates a data transmission between a sensor 15 and TETRAS 11. This sensor 15 can be powered or autonomous.
- FIG. 7 illustrates a mutual data transmission between a computer (not shown) located on the aircraft and the FADEC 10.
- a portable digital tablet 19 constitutes a data processing system.
- This tablet 19 includes a transmitter 29 and a receiver 39.
- the modulation of the light signal can comprise a frequency and / or amplitude modulation of the carrier wave, and / or a modification of the color of the light signal.
- a transmitter and a receiver of a data processing system can be coupled in a single member.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Electromagnetism (AREA)
- Computer Networks & Wireless Communication (AREA)
- Signal Processing (AREA)
- Fluid Mechanics (AREA)
- Optical Communication System (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1855322A FR3082687B1 (fr) | 2018-06-18 | 2018-06-18 | Dispositif et procede de communication de donnees dans un sous-ensemble d’aeronef |
PCT/FR2019/051320 WO2019243694A1 (fr) | 2018-06-18 | 2019-06-04 | Dispositif et procédé de communication de données dans un sous-ensemble d'aéronef |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3808012A1 true EP3808012A1 (fr) | 2021-04-21 |
Family
ID=65494173
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19737836.7A Pending EP3808012A1 (fr) | 2018-06-18 | 2019-06-04 | Dispositif et procédé de communication de données dans un sous-ensemble d'aéronef |
Country Status (4)
Country | Link |
---|---|
US (1) | US11773788B2 (fr) |
EP (1) | EP3808012A1 (fr) |
FR (1) | FR3082687B1 (fr) |
WO (1) | WO2019243694A1 (fr) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11506571B2 (en) * | 2019-09-09 | 2022-11-22 | Rohr, Inc. | System and method for gathering flight load data |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2755730B1 (fr) * | 1996-11-14 | 1999-01-08 | Hispano Suiza Sa | Systeme de commande electrique pour inverseur de poussee de turboreacteur |
US6614126B1 (en) * | 2001-10-24 | 2003-09-02 | Rockwell Collins, Inc. | Integrated lighting and data communication apparatus |
US6655125B2 (en) * | 2001-12-05 | 2003-12-02 | Honeywell International Inc. | System architecture for electromechanical thrust reverser actuation systems |
EP1858179A1 (fr) * | 2002-10-24 | 2007-11-21 | Nakagawa Laboratories, Inc. | Dispositif de diffusion pour communication |
DE102004046503B4 (de) * | 2004-09-23 | 2009-04-09 | Eads Deutschland Gmbh | Indirektes optisches Freiraum-Kommunikationssystem zur breitbandigen Übertragung von hochratigen Daten im Passagierraum eines Flugzeugs |
US8571409B1 (en) * | 2009-01-20 | 2013-10-29 | Intelligent Fiber Optic Systems, Inc. | Wavelength-multiplexed optical controller using a ring architecture |
US8666254B2 (en) * | 2011-04-26 | 2014-03-04 | The Boeing Company | System and method of wireless optical communication |
US20150090810A1 (en) * | 2013-02-11 | 2015-04-02 | Spirit Aerosystems, Inc. | Thrust reverser hydraulic actuation system with servo synchronization |
US9334807B2 (en) * | 2014-05-13 | 2016-05-10 | The Boeing Company | Methods and apparatus to determine airflow conditions at an inlet of an engine |
JP6833352B2 (ja) * | 2016-06-09 | 2021-02-24 | キヤノン株式会社 | 無線通信装置及び機器 |
-
2018
- 2018-06-18 FR FR1855322A patent/FR3082687B1/fr active Active
-
2019
- 2019-06-04 EP EP19737836.7A patent/EP3808012A1/fr active Pending
- 2019-06-04 WO PCT/FR2019/051320 patent/WO2019243694A1/fr unknown
-
2020
- 2020-12-18 US US17/126,257 patent/US11773788B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
WO2019243694A1 (fr) | 2019-12-26 |
US11773788B2 (en) | 2023-10-03 |
US20210285382A1 (en) | 2021-09-16 |
FR3082687B1 (fr) | 2021-10-01 |
FR3082687A1 (fr) | 2019-12-20 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1571080A1 (fr) | Système de montage interposé entre un moteur d'aéronef et une structure rigide d'un mât d'accrochage fixé sous une voilure de cet aéronef | |
EP3225546B1 (fr) | Drone, notamment de type aile volante, muni d'un element de superstructure multifonction | |
CA2850704A1 (fr) | Inverseur de poussee a grilles mobiles et capot mobile monobloc | |
FR2965304A1 (fr) | Dispositif de decharge d'air pour turboreacteur d'avion a double flux | |
WO2014019720A1 (fr) | Système de sonde, sonde mixte de référence primaire pour aéronef, aéronef et procédé de mesure associés | |
EP0538089A1 (fr) | Connecteur optique, notament sous-marin | |
EP0870105B1 (fr) | Tuyere divergent deployable de propulseur | |
EP2331404B1 (fr) | Dispositif de centrage d'une structure d'entree d'air sur une structure mediane d'une nacelle | |
EP3808012A1 (fr) | Dispositif et procédé de communication de données dans un sous-ensemble d'aéronef | |
FR3034601A1 (fr) | Reseau de communication, installation de communication a bord d'un aeronef et aeronef comprenant une telle installation de communication | |
EP1607328B1 (fr) | Installation motrice pour avion supersonique | |
FR2755729A1 (fr) | Turbomoteur a double flux pourvu d'une tuyere confluente et d'un inverseur de poussee | |
FR3065754B1 (fr) | Cellule d'absorption acoustique pour turboreacteur et panneau de traitement acoustique associe | |
WO2005066024A1 (fr) | Systeme optronique modulaire embarquable sur un porteur | |
EP3719293A1 (fr) | Turboréacteur comportant une nacelle équipée d'un système inverseur et une grille de cascades mobile | |
EP1315319B1 (fr) | Système de transmission de signaux numériques pour véhicule spatial | |
CA2869924A1 (fr) | Nacelle de turboreacteur a section aval | |
FR2686709A1 (fr) | Dispositif de fixation et de raccordement, notamment d'un ensemble intensificateur de lumiere sur un generateur d'images d'un viseur de casque pilote. | |
FR3078951A1 (fr) | Turboreacteur comportant une nacelle equipee d'un carter de soufflante et d'une structure fixe | |
EP4144647B1 (fr) | Système d'attache moteur avant pour un moteur d'aéronef qui comporte une structure compacte | |
EP3877799B1 (fr) | Dispositif de pointage optique bi-axe | |
FR2973342A1 (fr) | Procede de communication sur un vehicule aerien ou spatial via l'environnement exterieur | |
FR3105453A1 (fr) | Module optique pour l’éclairage et la transmission de données par la technologie Li-Fi | |
WO2015082514A1 (fr) | Systeme d'imagerie ir refroidi a filtre virtuellement froid | |
EP1334397A2 (fr) | Viseur tete haute pour aeronef a pare-brise courbe |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: UNKNOWN |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE |
|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
17P | Request for examination filed |
Effective date: 20210118 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
DAV | Request for validation of the european patent (deleted) | ||
DAX | Request for extension of the european patent (deleted) | ||
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: EXAMINATION IS IN PROGRESS |
|
17Q | First examination report despatched |
Effective date: 20230418 |