GB2603944A - Aircraft comprising fuel storage tank monitoring system - Google Patents
Aircraft comprising fuel storage tank monitoring system Download PDFInfo
- Publication number
- GB2603944A GB2603944A GB2102447.6A GB202102447A GB2603944A GB 2603944 A GB2603944 A GB 2603944A GB 202102447 A GB202102447 A GB 202102447A GB 2603944 A GB2603944 A GB 2603944A
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- United Kingdom
- Prior art keywords
- sensors
- fuel storage
- aircraft
- storage tank
- data
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- Pending
Links
- 238000003860 storage Methods 0.000 title claims abstract description 59
- 239000000446 fuel Substances 0.000 title claims abstract description 56
- 238000012544 monitoring process Methods 0.000 title claims abstract description 15
- 230000015654 memory Effects 0.000 claims abstract description 33
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 20
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 20
- 239000001257 hydrogen Substances 0.000 claims abstract description 20
- 239000002131 composite material Substances 0.000 claims abstract description 15
- 239000000835 fiber Substances 0.000 claims abstract description 13
- 238000013473 artificial intelligence Methods 0.000 claims abstract description 5
- 238000001931 thermography Methods 0.000 claims abstract description 4
- 238000004458 analytical method Methods 0.000 claims abstract description 3
- 238000002604 ultrasonography Methods 0.000 claims abstract description 3
- 238000012545 processing Methods 0.000 claims description 12
- 238000000034 method Methods 0.000 claims description 9
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims 1
- 229910052799 carbon Inorganic materials 0.000 claims 1
- 238000004590 computer program Methods 0.000 description 6
- 238000007689 inspection Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 6
- 230000032798 delamination Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 3
- 238000001514 detection method Methods 0.000 description 3
- 239000002245 particle Substances 0.000 description 3
- 238000011179 visual inspection Methods 0.000 description 3
- 230000000875 corresponding effect Effects 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 230000002950 deficient Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000011156 evaluation Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 241000282412 Homo Species 0.000 description 1
- 239000012790 adhesive layer Substances 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000012512 characterization method Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 238000013500 data storage Methods 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005305 interferometry Methods 0.000 description 1
- 230000002427 irreversible effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000011089 mechanical engineering Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- 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
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
-
- 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
- B64D37/00—Arrangements in connection with fuel supply for power plant
-
- 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
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/30—Fuel systems for specific fuels
-
- 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
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
-
- 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
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/0085—Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
-
- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/30—Hydrogen technology
- Y02E60/32—Hydrogen storage
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
An aircraft has a fuel storage tank monitoring system 100 with one or more sets of sensors 104A,104B,104C, a memory unit 110, and a transmitter 112 arranged to receive sensor data. Each set of sensors has one or more individual sensors arranged to detect the condition of a respective aircraft fuel storage tank 10A,10B,10C and to generate corresponding data. Data may be downloaded from the memory unit of the monitoring system, or receiving data from the transmitter, and processed to determine the condition of the fuel storage tank; this may be processed in part by an artificial intelligence. Fuel storage tanks may be replaced following determining their condition. The fuel storage tanks may be for gaseous hydrogen fuel and the sensor sets may be embedded within a carbon-fibre composite laminate wall structure of the tanks. The monitoring system may include one or more sensors of the following type: fibre-optic, ultrasound, thermography, shearography, acoustic emission, acousto-ultrasonic, vibro-acoustic, modal analysis, electrical resistivity, eddy current, or particle-tagging sensors.
Description
AIRCRAFT COMPRISING FUEL STORAGE TANK MONITORING SYSTEM
TECHNICAL FIELD
The invention relates to aircraft and to monitoring and inspection of fuel storage tanks of aircraft.
BACKGROUND
Currently, the fuel storage tanks of an aircraft are inspected, and their conditions assessed, by an inspection team of humans when the aircraft is on the ground. Typically, an inspection team comprises an entry supervisor, a standby attendant and entry personnel. The entry personnel climb inside a fuel storage tank and perform a visual inspection of the tank, while the standby attendant waits outside the tank and monitors the safety of the entry personnel. Human inspection is slow, labour-intensive, prone to error and limited efficacy and may present a safety risk for the entry personnel. The requirement for human inspection places design constraints on a tank and on the airframe in which it is comprised. For some designs and types of tank, satisfactory human visual inspection of a tank may be physically impossible or ineffective. For example, the condition of a fuel storage tank comprising carbon-fibre composite material is not fully ascertainable by human visual inspection alone. Robotic assistance of a human inspection team has been proposed (e.g. G. Niu et al, Advances in Mechanical Engineering 10 (2018), pp1-10), however this approach requires a robot to be introduced into the interior of a fuel storage tank. Safety concerns and labour cost may be reduced by such robotic assistance, however other problems remain.
BRIEF SUMMARY
A first aspect of the present invention provides an aircraft comprising a fuel storage tank monitoring system which comprises one or more sets of sensors, each set comprising one or more individual sensors associated with and arranged to detect the condition of a respective fuel storage tank of the aircraft and to generate corresponding data, and at least one of a memory unit and a transmitter arranged to receive the data. Data generated by a sensor or sensors of the system may be stored in a memory unit of the system during flight and downloaded for processing when the aircraft lands in order to determine the condition of one or more fuel storage tanks of the aircraft. Alternatively or additionally such data may be passed to a transmitter of the system for onward transmission to a location remote from the aircraft for processing to determine the condition of one or more fuel storage tanks of the aircraft, whilst the aircraft is airborne or on the ground.
The aircraft may comprise one or more hydrogen fuel storage tanks, each of one or more sets of sensors being associated with a respective hydrogen fuel storage tank of the aircraft. The one or more hydrogen fuel storage tanks may be tanks for storing gaseous hydrogen fuel. One or more of the hydrogen fuel storage tanks may comprise a carbon-fibre composite wall structure or a carbon-fibre composite laminate wall structure. At least one of the sets of sensors associated with the one or more hydrogen fuel storage tanks may be embedded within the carbon-fibre wall structure, or as the case may be the carbon-fibre composite laminate wall structure, of the associated hydrogen fuel storage tank.
At least one set of sensors may comprise one or more fibre-optic sensors, ultrasound sensors, thermography sensors, shearography sensors, acoustic emission sensors, acousto-ultrasonsic sensors, vibro-acoustic sensors, modal analysis sensors, electrical resistivity sensors, eddy current sensors or particle-tagging sensors.
A second aspect of the invention provides a method of determining the condition of a fuel storage tank comprised in an aircraft according to the first aspect of the invention, the method comprising the steps of downloading data from the memory unit of the fuel storage tank monitoring system of the aircraft, or receiving data from the transmitter unit of the system, and processing the data to determine the condition of the fuel storage tank. The step of processing the data may be carried out at least in part by an artificial intelligence. Following determination of the condition of the fuel storage tank, it may be replaced.
BRIEF DESCRIPTION OF THE DRAWINGS
Embodiments of the invention are described below by way of example only and with reference to the accompanying drawings in which: Figure 1 3 Figure 2 shows a part of the apparatus of an aircraft of the invention; shows how data corresponding to the condition of the fuel storage tanks of the aircraft may be transmitted to a ground station for processing; and Figure 3 is a flow chart showing steps in an example method of the invention.
DETAILED DESCRIPTION
Referring to Figures 1 and 2, an aircraft 150 of the invention comprises three carbon-fibre composite laminate liquid hydrogen fuel storage tanks 10A, 103, 103 and a fuel storage tank monitoring system 100. The fuel storage tank monitoring system 100 comprises three sets 104A, 104B, 1040 of five individual fibre-optic sensors, data buses 106A, 106B, 1060, a controller 108, a memory unit 110 and a transmitter 112.
Each of the sets 104A, 1043, 1040 of fibre-optic sensors is embedded within the wall structure of a respective composite laminate liquid hydrogen fuel storage tank 10A, 10B, 100. In operation of the aircraft 150, gaseous hydrogen fuel stored within the tanks 10A, 103, 100 is conveyed to a hydrogen-fuelled propulsion system (not shown) of the aircraft 150, the propulsion system comprising one or more fuel cells and/or one or more gas turbine engines.
During flight of the aircraft, data from each set 104A, 104B, 1040 of sensors is provided to a respective data bus 106A, 1063, 1060 and stored in the memory unit 110 under control of the controller 108. Data stored in the memory unit 110 is passed to the transmitter 112 under control of the controller 108 and transmitted to a satellite and thence to a ground station 170 where it is processed to establish the conditions of the tanks 10A, 10B, 10B before the aircraft 150 lands at its next destination. In the event that one or more of the tanks 10A, 10B, 100 is in a structurally-unsatisfactory condition, for example due to micro-cracking or delamination of a wall structure of a tank 10A, 10B, 100, one or more replacement tanks may be prepared at the destination for installation in the aircraft 150 as soon as the aircraft 150 lands, thereby not adversely affecting the turn-around time of the aircraft 150 in service. In the event that the transmitter 112 fails, data stored in the memory unit 110 may be downloaded and processed when the aircraft 150 lands at its destination.
Data received at the ground station 170, either by transmission from the aircraft 150 in flight or on the ground, or by download from the memory unit 110 when the aircraft 150 is on the ground, is processed by a computer to determine the condition of the tanks 10A, 10B, 100. Some or all of the processing may be carried out by an artificial intelligence trained to recognise data features associated with various types of degradation of the wall structure of a composite laminate tank, for example micro-cracking and delaminafion, caused by repeated filling and emptying of the tanks 10A, 10B, 100 or by impacts to the tank.
A second aircraft of the invention is similar to the aircraft 150 but does not include a memory unit, data from sensors being passed directly to a transmitter for onward transmission to a ground station without being stored in a memory unit. A third aircraft of the invention is similar to the aircraft 150 but does not include a transmitter, data from sensors being stored in memory unit and downloaded from the memory unit when the aircraft is on the ground.
In other embodiments of the invention, sensors other than embedded fibre-optic sensors may be associated with one or more fuel storage tanks of an aircraft in order to monitor the condition of the tanks. Depending on the material of construction of the fuel storage tanks of an aircraft, and the particular sensing technology used, sensors associated with a tank for monitoring and evaluation purposes may be applied to the outer surface of a tank or may be spaced apart from it.
Sensing technologies which may be used in other embodiments of the invention include thermography, based on detection of IR radiation, and shearography, based on speckle pattern shearing interferometry. Acoustic emission sensing may be utilised, based on the production of elastic waves in a solid when a material undergoes irreversible changes in its internal structure such as crack formation or delamination. Other applicable sensing technologies include vibro-acoustic sensing (which is especially sensitive to leak detection), and acousto-ultrasonic (AU) sensing. Unlike conventional ultrasonics, AU s not concerned with the detection and characterisation of individual flaws but rather with evaluation of integrated effects of diffuse subcritical flaw populations and microstructural aberrations in composites. Porosity, fibre breaks, resin richness, poor curing and fibre/matrix bonding are some examples of these, which in turn govern mechanical properties and durability of composite structures. These factors also influence AU signals that consequently reveal variations in mechanical properties such as tensile strength, stiffness and toughness.
Eddy current sensors can detect broken fibres caused by damage in conductive composite materials. Such sensors can aiso detect inclusions, tense faiiure and imr..'act damage, but not delamination.
Some embodiments of the invention may employ particle-tagging sensors. Particle tagging involves embedding micron-sized particles into materials, such as composites, or adhesive layers to make them an integral part of a host material. When interrogated by suitable instrumentation, embedded particle sensors interact with the host material and generate measurable signatures. The signatures can be correlated with a material type and structural conditions, such as internal stress states, voids, inclusions, state-of-cure and delamination.
In some embodiments, a set of sensors associated with a given fuel storage tank may include two or more sensors utilising different sensing technologies.
Figure 3 is a flow chart showing steps in an example method 200 of the invention. In a first step 202, data is downloaded from the memory unit 110 or received from the transmitter unit 112. In a second step 204 the data is processed, for example in whole or part by an artificial intelligence, in order to determine the condition of the tanks 104A-C. Any tank 104-C having an unacceptably poor condition may be replaced.
The controller 108 may comprise any suitable circuitry to cause storage of data generated by the sets of sensors 104A, 1043, 104C in the memory unit 110. The controller 108 may comprise: control circuitry; and/or processor circuitry; and/or at least one application specific integrated circuit (ASIC); and/or at least one field programmable gate array (FPGA); and/or single or multi-processor architectures; and/or sequential/parallel architectures; and/or at least one programmable logic controller (PLC); and/or at least one microprocessor; and/or at least one microcontroller; and/or a central processing unit (CPU); and/or a graphics processing unit (GPU), to perform the method.
In various examples, the controller 108 may comprise at least one processor and at least one memory. The memory stores a computer program comprising computer readable instructions that, when read by the processor, causes data from the sets of sensors 104A, 104B, 104C to be stored in the memory unit 110 and/or passed to the transmitter 112. The computer program may be software or firmware or may be a combination of software and firmware.
The processor may include at least one microprocessor and may comprise a single core processor, may comprise multiple processor cores (such as a dual core processor or a quad core processor), or may comprise a plurality of processors (at least one of which may comprise multiple processor cores) The memory of the controller 108 may be any suitable non-transitory computer readable storage medium, data storage device or devices, and may comprise a hard disk and/or solid-state memory (such as flash memory). The memory may be permanent non-removable memory or may be removable memory (such as a universal serial bus (USB) flash drive or a secure digital card). The memory of the controller 108 may include: local memory employed during actual execution of the computer program; bulk storage; and cache memories which provide temporary storage of at least some computer readable or computer usable program code to reduce the number of times code may be retrieved from bulk storage during execution of the code.
The computer program may be stored on a non-transitory computer readable storage medium. The computer program may be transferred from the non-transitory computer readable storage medium to the memory. The non-transitory computer readable storage medium may be, for example, a USB flash drive, a secure digital (SD) card, an optical disc (such as a compact disc (CD), a digital versatile disc (DVD) or a Blu-ray disc). In some examples, the computer program may be transferred to the memory via a wireless signal or via a wired signal.
In other example aircraft of the invention, a controller may carry out processing of data from sensors which monitor storage tanks of the aircraft, in order to determine the physical condition and structural integrity of the tanks. Data identifying any defective tank is passed to a transmitter and transmitted to a ground station or stored in a memory unit and downloaded when the aircraft is on the ground. Thus, processing to identify defective tanks is carried out on board the aircraft, and only data identifying which tanks are to be replaced is transmitted or downloaded from the aircraft. This reduces the amount of data which has to be transmitted or downloaded from the aircraft.
In other embodiments, an aircraft may comprise fuel storage tanks for storing gaseous hydrogen.
Claims (10)
- CLAIMS1. An aircraft (150) comprising a fuel storage tank monitoring system (100) which comprises one or more sets of sensors (104A, 104B, 1040), each set comprising one or more individual sensors associated with and arranged to detect the condition of a respective fuel storage tank (10A, 10B, 100) of the aircraft and to generate corresponding data, and at least one of a memory unit (110) and a transmitter arranged to receive the data (112).
- An aircraft according to claim 1 wherein the aircraft comprises one or more hydrogen fuel storage tanks and each of one or more sets of sensors of the system is associated with a respective hydrogen fuel storage tank of the aircraft.
- 3. An aircraft according to claim 2 wherein the one or more hydrogen fuel storage tanks are tanks for storing gaseous hydrogen fuel.
- An aircraft according to claim 2 or claim 3 wherein the one or more hydrogen fuel storage tanks each comprise a carbon fibre composite wall structure.
- An aircraft according to claim 2 or claim 3 wherein the one or more hydrogen fuel storage tanks each comprise a carbon-fibre composite laminate wall structure.
- 6. An aircraft according to claim 4 or claim 5 wherein at least one of the sets of sensors associated with the one or more hydrogen fuel storage tanks is embedded within the carbon-fibre wall structure, or as the case may be the carbon-fibre composite laminate wall structure, of the associated hydrogen fuel storage tank.
- 7. An aircraft according to any preceding claim wherein the individual sensors of the fuel storage tank monitoring system comprise one or more fibre-optic sensors, ultrasound sensors, thermography sensors, shearography sensors, acoustic emission sensors, acousto-ultrasonsic sensors, vibro-acoustic sensors, modal analysis sensors, electrical resistivity sensors, eddy current sensors or particle-tagging sensors.
- 8. A method of determining the condition of a fuel storage tank comprised in an aircraft according to claim 1, the method comprising the steps of: (i) downloading data from the memory unit of the fuel storage tank monitoring system of the aircraft, or receiving data from the transmitter unit of the fuel storage tank monitoring system of the aircraft; and (ii) processing the data to determine the condition of the fuel storage tank.
- A method according to claim 8 wherein the step of processing the data is carried out at least in part by an artificial intelligence.
- 10. A method according to claim 9 or claim 10 further comprising the step of replacing a fuel storage tank of the aircraft following determination of the condition of the fuel storage tank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2102447.6A GB2603944A (en) | 2021-02-22 | 2021-02-22 | Aircraft comprising fuel storage tank monitoring system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2102447.6A GB2603944A (en) | 2021-02-22 | 2021-02-22 | Aircraft comprising fuel storage tank monitoring system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB202102447D0 GB202102447D0 (en) | 2021-04-07 |
| GB2603944A true GB2603944A (en) | 2022-08-24 |
Family
ID=75339206
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2102447.6A Pending GB2603944A (en) | 2021-02-22 | 2021-02-22 | Aircraft comprising fuel storage tank monitoring system |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2603944A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3140911A1 (en) * | 2022-10-18 | 2024-04-19 | Airbus | INSTALLATION INCLUDING A DEVICE FOR REGULATING A DIHYDROGEN CONCENTRATION |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160282308A1 (en) * | 2013-11-08 | 2016-09-29 | Bombardier Inc. | Health monitoring of composite structures |
-
2021
- 2021-02-22 GB GB2102447.6A patent/GB2603944A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160282308A1 (en) * | 2013-11-08 | 2016-09-29 | Bombardier Inc. | Health monitoring of composite structures |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3140911A1 (en) * | 2022-10-18 | 2024-04-19 | Airbus | INSTALLATION INCLUDING A DEVICE FOR REGULATING A DIHYDROGEN CONCENTRATION |
| EP4357250A1 (en) * | 2022-10-18 | 2024-04-24 | Airbus SAS | Plant comprising a device for regulating a dihydrogen concentration |
Also Published As
| Publication number | Publication date |
|---|---|
| GB202102447D0 (en) | 2021-04-07 |
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