CN102632995B - The method of aircraft, passenger accommodation emergency oxygen equipment and operation and this equipment of activation - Google Patents
The method of aircraft, passenger accommodation emergency oxygen equipment and operation and this equipment of activation Download PDFInfo
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- CN102632995B CN102632995B CN201110057818.3A CN201110057818A CN102632995B CN 102632995 B CN102632995 B CN 102632995B CN 201110057818 A CN201110057818 A CN 201110057818A CN 102632995 B CN102632995 B CN 102632995B
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- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 title claims abstract description 165
- 239000001301 oxygen Substances 0.000 title claims abstract description 165
- 229910052760 oxygen Inorganic materials 0.000 title claims abstract description 165
- 230000004308 accommodation Effects 0.000 title claims abstract description 29
- 238000000034 method Methods 0.000 title claims abstract description 20
- 230000004913 activation Effects 0.000 title claims abstract description 12
- 238000004146 energy storage Methods 0.000 claims abstract description 110
- 230000003213 activating effect Effects 0.000 claims abstract description 23
- 238000003860 storage Methods 0.000 claims abstract description 5
- 230000008054 signal transmission Effects 0.000 claims abstract description 3
- 238000012360 testing method Methods 0.000 claims description 48
- 230000008859 change Effects 0.000 claims description 16
- 230000008569 process Effects 0.000 claims description 9
- 238000013461 design Methods 0.000 claims description 6
- 238000007599 discharging Methods 0.000 claims description 3
- 238000012545 processing Methods 0.000 claims description 3
- 239000012190 activator Substances 0.000 claims description 2
- 238000012546 transfer Methods 0.000 description 14
- 238000003306 harvesting Methods 0.000 description 11
- 230000005540 biological transmission Effects 0.000 description 9
- 238000010586 diagram Methods 0.000 description 7
- 230000008901 benefit Effects 0.000 description 5
- 230000007274 generation of a signal involved in cell-cell signaling Effects 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 230000006698 induction Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 230000001737 promoting effect Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 239000003990 capacitor Substances 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011990 functional testing Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
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- 230000007246 mechanism Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 230000029058 respiratory gaseous exchange Effects 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 230000001131 transforming effect Effects 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Classifications
-
- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62B—DEVICES, APPARATUS OR METHODS FOR LIFE-SAVING
- A62B7/00—Respiratory apparatus
- A62B7/14—Respiratory apparatus for high-altitude aircraft
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- Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- General Health & Medical Sciences (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Accommodation For Nursing Or Treatment Tables (AREA)
- Respiratory Apparatuses And Protective Means (AREA)
- Hybrid Cells (AREA)
Abstract
The present invention relates to the method for aircraft, passenger accommodation emergency oxygen equipment and operation and this equipment of activation, this equipment comprises: at least one electric drive activated equipment, for activating this emergency oxygen equipment; At least one energy storage device, is supplied to this at least one activated equipment for storage of electrical energy and by electric energy; At least one controller, for Received signal strength to activate emergency oxygen equipment; And energy source.Energy source and energy storage device are coupled, thus transmit the energy of somewhat constant from this energy source to this energy storage device with the first energy level, activated equipment and controller are coupled, with from this controller to the Signal transmissions of this activated equipment, activated equipment and energy storage device are coupled, thus with the second energy level higher than this first energy level from this energy storage device to this activated equipment transmitting energy, and an individual unit being suitable for being inserted in the top lid member of aircraft cabin inside set up by activated equipment, energy storage device and controller.
Description
Technical field
The present invention relates to a kind of passenger accommodation emergency oxygen equipment for aircraft, be particularly useful for as the passenger on aircraft or crew provide oxygen.The invention further relates to a kind of method in case of emergency activating passenger accommodation emergency oxygen equipment for aircraft.Another aspect of the present invention is the method for a kind of operation for the passenger accommodation emergency oxygen equipment of aircraft.Further, the present invention relates to a kind of aircraft comprising multiple emergency oxygen equipment.
Background technology
Arrange that this emergency oxygen equipment of aforementioned type is used for multiple object, wherein for people provides oxygen to be necessary temporarily or forever.A special application of this emergency oxygen equipment is aircraft circles, and the pressure drop wherein in the aircraft of High aititude flight may make to be necessary for passenger and crew provides oxygen.Usually, for every crew and every passenger or its combination provide emergency oxygen equipment, and usually by emergency oxygen facility location above passenger.In case of emergency, this emergency oxygen equipment such as presses monitored control system automatic activation or by crew's manual actuation, the oxygen mask being connected to source of oxygen subsequently by flexible pipe is dropped above passenger, and can for passenger downwards by cabin.The flowing of oxygen can be started automatically by crew's activation system, or the specific action can made by passenger activates, such as by oneself, face shield being pulled down, activating this equipment with the pulling force transmitted by the flexible pipe or the subsidiary lashing that is coupled in oxygen mask through guiding oxygen flowing thus.
The emergency oxygen equipment of aforementioned type is known in the state of the art and is connected to aircraft energy system, and receives the energy activated needed for emergency oxygen equipment from this aircraft energy system.In emergency circumstances many, cabin internal drop and other defect exist aboard simultaneously, the damage of such as turbine or other damage.In emergency circumstances this, be necessary to save energy as much as possible.The multiple emergency oxygen equipment activated in the passenger accommodation of aircraft may cause energy ezpenditure to reach less desirable peak, and this may cause entirely collapsing of aircraft energy system.
Summary of the invention
The present invention aims to provide a kind of passenger accommodation emergency oxygen equipment for aircraft, and it overcomes at least some aforementioned drawback, and provides higher safety for the people being provided with emergency oxygen equipment, especially when the unusual emergency state.
According to a first aspect of the invention, as previously described, realize this object by the passenger accommodation emergency oxygen equipment being provided for aircraft, this equipment comprises: at least one electric drive activated equipment, for activating emergency oxygen equipment, at least one urgent storage equipment, for storage of electrical energy and by described electric power supply at least one activated equipment, and at least one controller, be applicable to receive and processing signals, to activate emergency oxygen equipment and energy source, wherein said energy source and described energy storage device are coupled, so that the energy of somewhat constant is transferred to this energy storage device from this energy source with the first energy level, wherein said activated equipment and described controller are coupled so that from this controller to the Signal transmissions of this activated equipment, wherein said activated equipment and described energy storage device are coupled so that energy is transferred to this activated equipment from this energy storage device at the second energy level higher than this first energy level, wherein said activated equipment, an individual unit being suitable for being inserted in the top lid member of aircraft cabin inside set up by described energy storage device and described controller.
According to this aspect of the invention, the emergency oxygen equipment provided eliminates and in emergency circumstances transmits from aircraft energy system to the high peak energies of emergency oxygen equipment.This allows when not having the energy system of aircraft to cause this risk of collapse by overload, activates the multiple emergency oxygen equipment in aircraft simultaneously.During emergency situation, energy storage device does not receive a high second stage high peak energy value, and receives the low first order Energy Transfer of somewhat constant from energy source, to store this energy.In case of emergency, emergency signal is sent to controller, and when receiving this signal, controller connects electric drive activated equipment and energy storage device, makes activated equipment can receive the energy of requirement from energy storage device.Energy source is the interface being suitable for connecting the energy networks of emergency oxygen equipment and aircraft and/or energy harvesting elements or being integrated in the analogue in emergency oxygen equipment herein.Be appreciated that first order Energy Transfer herein has the energy level lower than second stage Energy Transfer.Preferably, first order Energy Transfer is lower than the Energy Transfer for activating emergency oxygen equipment required for activated equipment.Especially, according to the present invention, the ratio of the first and second inter-stages is in the scope of 1 to 60, in case of emergency, do not need from aircraft energy system to emergency oxygen device transmission peak value second stage energy, this causes the better safety of aircraft, especially in both cases: will provide urgent enough energy from energy storage device to electric drive activated equipment, when to activate all emergency oxygen equipment.When not needing from aircraft energy system transmission peak value second stage energy, the energy saved can be provided to miscellaneous equipment, such as driving compartment safety apparatus or analogue.
Unexpected further advantage is, the present invention contributes to the expectation of the integral light structure realizing providing aircraft, and to reduce the fuel oil consumption of aircraft, and the fuel oil consumption reducing aircraft is a common problem relevant to present generation aircraft.Especially the weight of element in cabin is alleviated.By transmitting the low first order energy of somewhat constant from aircraft energy system to energy storage device, do not need the wiring being widely suitable for transmitting peak value second stage energy from aircraft energy system to electric drive activated equipment, thus cause the safety of aircraft to improve.
Advantage unexpected is further the reduction manufacturing and overhaul cost.In present generation aircraft, expect the variation of indoor design.This causes needing to be suitable at the cabin inner member that diverse location is implemented with different quantity in aircraft, such as emergency oxygen equipment or passenger's unit.Surprisingly, according to the present invention, when indoor design changes, aircraft, the inside, cabin especially comprising PSU can carry out overhauling and transforming and do not have a large amount of building-up work in the later stage.On the contrary, overhaul with in transformation process in the initial manufacture of aircraft and later stage, the emergency oxygen equipment of prior art needs to prepare widely or design effort, isolation and installation.
According to the first preferred implementation, described emergency oxygen equipment is suitable for receiving and process emergency signal, especially aircraft cabin pressure drop signal, is electrically connected with energy storage device to make activated equipment.According to this embodiment, this controller is suitable for receiving and process emergency signal, and energy storage device is suitable for receiving and store the low first order energy from energy source transmission somewhat constant.When receiving emergency signal, controller makes activated equipment communicate with energy storage device, to make electric energy can flow to activated equipment from energy storage device, thus can activate emergency oxygen equipment.This activated equipment in this embodiment can comprise electrical motor, motor switch, electromagnetic switch or lock bolt or electrically controllable latch, or analogue.Controller in this embodiment can comprise transistor or electromagnet, or is suitable for analogue that energy storage device is electrically connected with electric drive activated equipment.Cabin pressure drop herein refers to the ambient pressure of aircraft cabin inside.Aircraft can comprise the sensor being suitable for measurement environment air pressure, and this ambient pressure is the air pressure of the inside, cabin of aircraft.When cabin air pressure declines, the pressure reduction between cabin ambient pressure and the ambient pressure of aircraft exterior declines.But, preferably, send cabin pressure drop signal when cabin ambient pressure drops to below preset level.
According to the further preferred implementation of emergency oxygen equipment, described controller is suitable for by signal wire (SW) from transmitter Received signal strength.When controller being connected to signal wire (SW) and by controller, activated equipment being coupled to energy storage device, signal wire (SW) can be designed as has small diameter.This causes the weight of aircraft to reduce.This signal wire (SW) is connected to sensor, and this sensor can comprise the sensor by signal wire (SW), cabin pressure drop signal being supplied to controller of interior of aircraft.Aircraft can comprise more than one sensor, such as, be dispersed throughout four sensors on aircraft.This causes connecting up and reduces further, because there is no need to make line pass whole aircraft.
According to the further preferred implementation of emergency oxygen equipment, described energy source and described energy storage device are coupled by described signal wire (SW), so that at described first energy level transmitting energy.According to this embodiment, the low-yield of somewhat constant is transferred to energy storage device by signal wire (SW) from energy source, and is preferably also transferred to controller.This Energy Transfer can be low-down energy level, keeps less to make the section of signal wire (SW).This energy storage device can gather transmitted energy and in case of emergency this energy is supplied to activated equipment, to activate emergency oxygen equipment.
According to the further preferred implementation of emergency oxygen equipment, described controller is suitable for receiving the signal different with process at least two kinds, comprise the emergency signal in case of emergency activating described activated equipment, and for activating the test signal of described activated equipment in a test case.Emergency oxygen equipment is necessity and the lifesaving parts of present generation aircraft.Therefore test emergency oxygen equipment whether defectiveness is necessary.According to this embodiment, this controller can receive the emergency signal in case of emergency activating described activated equipment.In the case, activated equipment is set to be electrically connected with energy storage device, to activate emergency oxygen equipment.This controller is also suitable for receiving the test signal for activating described activated equipment in a test case.This test case can be the test case performed when aircraft keeps on the ground.In this case, this controller can make activated equipment and energy storage device telecommunication, to activate emergency oxygen equipment.In one embodiment, controller is suitable for activated equipment is communicated in a short time with energy storage device.In alternate embodiments, this controller comprises signal generation apparatus, such as lamp or loud speaker, and when controller receives test signal, this controller is suitable for energy storage device is communicated with signal generation apparatus.
According to the further preferred implementation of emergency oxygen equipment, described signal characteristic is the change of voltage of described signal wire (SW) and/or the change of frequency of electric current, and preferably, the change of voltage sent out an emergency signal and/or change of frequency are different from the change of voltage and/or change of frequency that send test signal.According to this embodiment, this signal wire (SW) can be connected to energy storage device, to transmit the energy of somewhat constant from energy source to energy storage device with the first energy level.This transmission can have low first order voltage or specific power frequency.In case of emergency, the situation that such as cabin air pressure declines, transmitter can change voltage in a short time and send the second stage voltage signal slightly higher than the first order.This controller is suitable for the voltage peak identifying that this is short, and this short voltage peak is used for energy storage device is electrically connected with activated equipment as desired signal, to activate emergency oxygen equipment.This second stage voltage peak sending emergency signals can be different from the second stage voltage peak sending test case signal, especially higher than this test voltage.In an alternative embodiment, transmitter is energy source and is suitable for using the specific first frequency of this grade that the energy of somewhat constant is transferred to energy storage device from energy source with the first energy level.In order to send test case or emergency signals, described first frequency can change, and the second frequency level wherein sending test case signal can be different from the 3rd frequency level sending emergency signals, and controller is suitable for identifying that these are distinguished.In further alternate embodiments, can be sent the signal of test case by second stage voltage peak, and send the signal of emergency situation by the change of provided frequency 1 grade, vice versa.In further alternate embodiments, the voltage transferring to the energy of controller and/or energy storage device from transmitter by raising sends test case signal, and sends emergency signals by reducing this voltage.In further alternate embodiments, formed the first order Energy Transfer of somewhat constant by AC electric current, and sent out an emergency signal and/or test signal by the change of DC electric current, vice versa.
According to the further preferred implementation of emergency oxygen equipment, described controller comprises the receptor being suitable for wirelessly receiving described signal from transmitter, and wherein said controller is coupled in energy source or is integrated in the energy storage device in emergency oxygen equipment.According to this embodiment, eliminate and use signal wire (SW) in aircraft cabin inside.This causes the total weight of aircraft to reduce further.This wireless receiver can be integrated in controller or can be independent equipment.In order to operate this receptor, receptor can be connected to energy source, such as aircraft energy system.In case of emergency, this receptor can receive emergency signal, and this signal is delivered to controller, and wherein this controller is suitable for making energy storage device and activated equipment electrical contact, to activate emergency oxygen equipment.In an alternative embodiment, this receptor can be connected to the identical energy source connected with energy storage device.In further alternate embodiments, receptor comprises and is connected to energy storage device.In further alternate embodiments, receptor comprises the additional energy storage device being connected to energy source.In another further alternate embodiments, receptor comprises energy storage device, and this energy storage device is connected to the identical energy source or the identical energy that connect with the first energy storage device.In further alternate embodiments, receptor is suitable for receiving at least two different wireless signals, comprises the emergency signal for activated equipment described in emergency activation, and for activating the test signal of described activated equipment in test case.By being wireless receiver by receiver design, improve the overall flexibility of design aircraft.In aircraft cabin inside in order to the wiring using emergency oxygen equipment to carry out is eliminated the most widely.Further, can expect to close specific emergency oxygen equipment, such as, in the situation only having the aircraft seat of half to be taken by passenger.Further, in some cases, can expect to have additional emergency oxygen equipment, such as portable emergency oxygen equipment, this additional emergency oxygen equipment also can comprise the receptor in case of emergency receiving and/or process wireless emergency signal.
According to the further preferred embodiment of emergency oxygen equipment, described controller comprises and is suitable for detecting cabin pressure drop and providing the sensor of cabin pressure drop signal to described controller, and wherein this controller preferred coupled in energy source or the energy storage device that is integrated in emergency oxygen equipment.Sensor is herein suitable for measurement environment air pressure, and this ambient pressure is the air pressure of the inside, cabin of aircraft.When cabin air pressure declines, the pressure reduction between cabin ambient pressure and the ambient pressure of aircraft exterior reduces.But preferably, this sensor is suitable for sending cabin pressure drop signal when measuring specific cabin ambient pressure.According to this embodiment, eliminate the signal transmitting apparatus of the interior of aircraft of the distance join component of being separated by far away as far as possible each other.Further, do not need wireless receiver, above-mentioned two aspects all cause the total weight of aircraft to reduce further.Sensor can be integrated in controller, and is suitable for identifying aircraft altitude switch, and is suitable for producing the signal being supplied to controller.Sensor and/or controller can be connected to energy source, such as aircraft energy system.In an alternative embodiment, controller and/or sensor are connected to the identical energy source that energy storage device connects.In further alternate embodiments, controller and/or sensor are connected to energy storage device, and this energy storage device can be suitable for the identical energy storage device that activated equipment provides energy.
According to the further preferred implementation of emergency oxygen equipment, described energy source is interface for Energy Transfer or energy harvesting elements.According to this embodiment, the interface for Energy Transfer can be the interface being connected to aircraft energy system, with by the first order Energy Transfer of somewhat constant to energy storage device.In an alternative embodiment, it can also be the interface being connected to other energy system, such as the system of the loud speaker in cabin light or cabin or analogue.Further, according to this embodiment, be connected to energy storage device energy harvesting elements can for Peltier (Peltier) element of thermal source thermal contact, produce electric energy with the thermal drop of from then on peltier-element.This thermal drop can be the gradient of the inner temperature in portion extremely out of my cabin in cabin, or other arbitrary temp gradient from thermal source to another target.In an alternative embodiment, energy harvesting elements can be the element being suitable for vibratory movement to convert to electric energy.This vibratory movement can be performed by the passenger or crew being provided with oxygen by emergency oxygen equipment.Further, this gathering element can comprise crank, button, handle or the analogue for applying shaking force.Further, known during flight or ground transfer, especially during the startup and landing maneuver of aircraft, in whole aircraft, cause obvious vibration, and cause the obvious oscillating movement of the arbitrary equipment be arranged in aircraft.According to this embodiment, this oscillating movement can be preferred for as energy storage device provides energy.According to another alternate embodiments, wherein, controller comprises the receptor being suitable for receiving wireless signal, and the emittance that this energy harvesting elements is suitable for radio transmitters to send is converted to electric energy, to be supplied to energy storage device.
According to further embodiment of the present invention, described energy storage device comprises at least one cond and/or at least one rechargeable battery.This cond can be preferably have the ultracapacitor of high-energy-density and high power density or super capacitor or analogue.It also additionally or alternatively can comprise rechargeable battery, such as hull cell.In an alternative embodiment, energy storage device comprises multiple cond and/or battery.Due to high-energy-density and power density, preferably these elements are used for light structures.In addition, do not having in defective situation, they can repeatedly recharge, and in case of emergency provide energy from energy storage device to activated equipment to ensure.
According to a further aspect in the invention, realize the object of the invention by the passenger accommodation emergency oxygen equipment being provided for aircraft, this equipment comprises: an electric drive activated equipment, for activating emergency oxygen equipment; At least one controller, be applicable to receive and processing signals to activate emergency oxygen equipment.Wherein, described activated equipment comprises multi-mode lock bolt, this multi-mode lock bolt is suitable for by discharging bottom under at least two kinds of different modes and activates emergency oxygen equipment, described at least two kinds of patterns comprise test case pattern and emergency situation pattern, wherein under test case pattern, this bottom is discharged into constrained position from off position, and this bottom is discharged into fully open position from described closedown or described constrained position in emergency mode.According to this aspect of the invention, described multi-mode lock bolt is associated with activated equipment, is suitable for activating emergency oxygen equipment under at least two kinds of different modes.This multi-mode lock bolt can be driven by electrical motor, electromagnet, solenoid component, piezoelectric element or analogue.Under test case pattern, bottom is only released to limited extent.
According to this embodiment, emergency oxygen equipment may further include the oxygen mask being bearing in appropriate location by bottom or hatch or analogue, wherein this bottom supported by activated equipment, and when emergency oxygen equipment is activated, this bottom is opened, and oxygen mask can drop downwards through bottom opening.In this embodiment, test case pattern refers to the pattern that bottom remains on constrained position, to make oxygen mask can not drop from the cover comprising breathing equipment, thus is not supplied to the passenger accommodation of aircraft.By contrast, in emergency situation pattern, bottom can be opened completely, thinks that passenger accommodation provides oxygen mask.In an alternative embodiment, test case pattern refers to emergency oxygen equipment and is activated and does not have the pattern that oxygen can provide, and emergency situation pattern refers to emergency oxygen equipment and is activated to make aerobic air lift to supply the passenger of aircraft and/or the pattern of crew.Be appreciated that and comprise different types of activation herein.By simply performing test to emergency oxygen equipment is implemented, the safety that emergency oxygen equipment comprises the aircraft of such as emergency oxygen equipment is in addition improved.
As another unexpected advantage, make a multi-mode lock bolt be suitable for comprising two kinds of different modes (especially test case pattern and emergency mode) and reduce maintenance cost, especially when aircraft is positioned at the situation on ground.Whether this installs correct for testing bottom and does not have excessive restriction or tension/pressure to enter aircraft.This test will be carried out continually, to guarantee emergency oxygen system function integrally.But, undesirably in this test process, discharge bottom completely, because oxygen mask is released and drops in this case, thus have to carry out packaging after a test and be again stored in after bottom.Further, after discharging completely, reinstall bottom can cause assembling by mistake the mal function caused.These defects can be overcome by multi-mode lock bolt according to the present invention.This multi-mode lock bolt is limited in the release of test mode lower bottom cover, and allows easily lid group to be pushed into complete off position after this test.In this way, after this test, the risk of mistake assembling significantly reduces.After testing results situation pattern, aircraft easily can enter the state of normal flight conditions.
According to the embodiment improved further, provide the driving arrangement being suitable for bottom being moved to complete off position from the position after testing results situation pattern.This actuator can be integrated in multi-mode lock bolt, or can be independent equipment.Actuator makes all bottoms can easily, safely reconfigure after functional test, thus it is minimum that the risk of failure after this test is dropped to.
According to the preferred implementation of this equipment, described multi-mode lock bolt comprises the first and second uncinuses, and wherein this first uncinus is suitable for bottom to remain on described closed condition, and described second uncinus is suitable for bottom to remain on described constrained position.According to this embodiment, the first uncinus is coupled in activated equipment, and the second uncinus to be coupled in can be dish or the releasing member of plate.
This activated equipment can be suitable for activating this equipment, such as test case pattern and emergency situation pattern in a kind of pattern or two kinds of different modes.According to the first optional manner, activated equipment is suitable for activating this equipment in one mode, and the first uncinus equipment that is activated discharges.Then the second uncinus comprises two kinds of diverse locations, makes bottom remain on the test position of constrained position and bottom is discharged into the emergency location of fully open position.The second uncinus can be made two positions are entered by promoting or pull releasing member.Alternatively, it also can enter two positions automatically.
According to another embodiment of this equipment, multi-mode lock bolt comprises uncinus, this uncinus comprises the first and second grooves, and wherein this first groove is suitable for bottom to remain on described off position, and described second groove is suitable for bottom to remain on described constrained position.According to this embodiment, activated equipment is suitable for activating emergency oxygen equipment under two kinds of different modes, such as test case pattern and emergency situation pattern.According to test case pattern, uncinus discharges by this way: the bottom being bearing in off position by the first groove is opened to the constrained position supported by the second groove.According to this embodiment, only need a uncinus, and activate emergency oxygen equipment and do not need passenger to take action.
According to further preferred embodiment, indicating device is integrated in equipment, and whether the bottom that described indicating device is suitable under instruction test case pattern discharges.This indicating device can be d/d mechanical element under bottom is released situation, and can from other protrusion of surface any of bottom or equipment, to indicate this release.If bottom returns complete off position, then this indicating device can automatic drawing back, or after closedown bottom, can need each manual clawback.
In another preferred implementation of the present invention, comprise the feature of the characteristic of claim 10 to 12 according to the passenger accommodation emergency oxygen equipment for aircraft of claim 1 to 9.In this case, not only by comprise according to claim 1 at least one for activating the emergency oxygen equipment of the electric drive activated equipment of emergency oxygen equipment, and there is the advantage of safety raising and weight reduction, and due to emergency oxygen equipment according to claim 10, achieve the advantage of safety raising and maintenance time minimizing.By this combination, achieve object of the present invention in a preferred manner.According to a further aspect in the invention, this object is achieved by providing the aircraft comprising multiple emergency oxygen equipment, wherein, this aircraft comprises and arranging according at least one of at least one the emergency oxygen equipment in described multiple emergency oxygen equipment of arbitrary feature of claim 1 to 13.This aircraft will be lightweight and it is safeguarded and cost of installation totally reduces.
According to a further aspect in the invention, this object is realized by a kind of method in case of emergency activating the passenger accommodation emergency oxygen equipment being used for aircraft, the method comprises Received signal strength to activate emergency oxygen equipment by controller, make electric drive activated equipment for be electrically connected with energy storage device, and use the energy activated emergency oxygen equipment from energy storage device.According to the method, eliminate in case of emergency from aircraft energy system to emergency oxygen device transmission second stage high peak energies.During emergency situation, energy storage device does not receive a second stage high energy peak, and receives the Energy Transfer of the somewhat constant of the first energy level from energy source, to store this energy.In case of emergency, emergency signal is sent to controller, and then electric drive activated equipment is connected with energy storage device by this controller.Activated equipment receives the energy of the amount activated required for emergency oxygen equipment from energy storage device.Energy source can be the interface and/or the energy harvesting elements that are connected to aircraft energy system.By transmitting the low first order energy of somewhat constant from aircraft energy system to energy storage device, do not need the wiring being widely suitable for transmitting high peak energies from aircraft energy system to electric drive activated equipment, thus cause the total weight of aircraft to reduce.In case of emergency, the energy saved from aircraft energy system may be used for other the security-related equipment aircraft, thus cause the overall security of aircraft to improve, and significantly reduce the danger of aircraft energy system fault in the process that is simultaneously activated at emergency oxygen equipment.
According to another aspect of the invention, the method being used for the passenger accommodation emergency oxygen equipment of aircraft by operation realizes this object, the method comprises the energy transmitting somewhat constant by this way with the first energy level from energy source at least one energy storage device, namely, store in energy storage device enough with the energy of the interim energy supply of the second energy level so that electric drive activated equipment, this second energy level is higher than described first energy level.According to this aspect of the invention, the energy transmitting this somewhat constant with the first energy level is for for energy storage device supply energy.Energy storage device preferably has such volume, that is, make to store the energy being enough to activate emergency oxygen equipment in case of emergency this energy storage device.When reaching this volume, mean when storing enough energy, the constant Energy Transfer substantially transmitted with the first energy level is used as to safeguard transmission, lacks energy to prevent energy storage device.According to this aspect of the invention, the safety of aircraft is improved, even because emergency oxygen equipment also can be activated when aircraft energy system collapses.
Accompanying drawing explanation
The preferred embodiment of the present invention is described with reference to the drawings, wherein
Fig. 1 is the schematic diagram of emergency oxygen equipment according to first embodiment of the invention,
Fig. 2 is the schematic diagram of emergency oxygen equipment second embodiment of the invention,
Fig. 3 is the schematic diagram of the emergency oxygen equipment according to the 3rd embodiment of the present invention,
Fig. 4 is the schematic diagram of the emergency oxygen equipment according to the 4th embodiment of the present invention,
Fig. 5 for emergency oxygen equipment, the partial schematic diagram of framework at off position with lock bolt,
Fig. 6 for emergency oxygen equipment, the partial schematic diagram of framework in constrained position with lock bolt,
Fig. 7 for emergency oxygen equipment, the partial schematic diagram of framework in fully open position with lock bolt,
Fig. 8 for emergency oxygen equipment, the section-drawing of framework at off position with lock bolt,
Fig. 9 for emergency oxygen equipment, the section-drawing of framework in constrained position with lock bolt,
Figure 10 is for emergency oxygen equipment, the section-drawing of framework in fully open position with lock bolt.
Detailed description of the invention
With reference to figure 1, emergency oxygen equipment 1 according to first embodiment of the invention comprises activated equipment 11, controller 5 and energy storage device 9 for activating emergency oxygen equipment.These equipment are contained in shell 2, and this shell 2 is closed by the bottom 4 being positioned at its bottom surface.Bottom 4 is attached to shell 2 by hinge 21 in side at the right-hand side of Fig. 1.At opposite side, bottom 4 is fixed on shell by the lock bolt 12 being attached to activated equipment 11.Controller 5 is coupled in activated equipment 11 and energy storage device 9 is coupled in controller 9 by cable 17.Further, energy storage device 9 is coupled in energy source 7 by cable 15, and in this embodiment, energy source 7 is positioned at the outside of shell.Energy source 7 is suitable for the first order to energy storage device 9 somewhat constant ground transmitting energy.Therefore, cable 15 can be designed as has small diameter, because there is no need to carry out high energy transmission by cable 15.Controller 5 is coupled in the transmitter 3 being suitable for sending emergency signal or test signal.Usually do not send signal with high-energy, also can be designed as to make signal cable 13 and there is small diameter.
This and below embodiment in, energy storage device 9,109,209,309 can be formed as rechargeable battery or cond.The preferably rechargeable battery of such as hull cell because its can the time ratio capacitance device of stored energy longer.On the other hand, can the cond of preferred such as ultracapacitor, because its power density had.This causes the weight of aircraft to reduce.Both battery and cond all can comprise the shell with particular port, and this particular port is used for the connection between cable 15,17,115,117,215,217,314,317.
If transmitter 3 sends emergency signal by cable 13 to controller 5, controller makes energy storage device 9 be communicated with activated equipment 11 by cable 17,19, to activate emergency oxygen equipment 1.Lock bolt 12 discharges by activated equipment, and bottom 4 is opened under gravity.In order to discharge and/or activate lock bolt 12, activated equipment 11 can comprise electrical motor or piezoelectricity activator appliance.Electromagnetic switch or analogue can also be implemented.Oxygen mask (not shown) can directly be stored in above bottom 4, to make, when bottom 4 is opened, to provide oxygen mask to the passenger in aircraft.In this embodiment, transmitter 3 can for being suitable for the cabin baroceptor of survey room air pressure, or can be the manual transmitter activated by crew in cabin.Energy source 7 in this embodiment can be the interface to aircraft energy system or other energy source arbitrarily.
In the second embodiment of the emergency oxygen equipment 101 shown in Fig. 2, energy storage device 109 is coupled in transmitter 103 by cable 114.Further, in this embodiment, controller 105 is coupled in transmitter 103 and activated equipment 111 is coupled in controller.By being connected with transmitter 103 by energy storage device 109, energy storage device 109 receives electric energy to be stored from transmitter 103.Transmitter 103 is applicable to voltage and the transmission of low current amplitude of the somewhat constant of the first energy level.Energy storage device 109 stores this electric energy until store the energy of specified quantitative.Then use constant Energy Transfer as the ME for maintenance of energy storage device 109.In case of emergency, transmitter 103 will send short peak voltage signal.Controller 105 identifies this differential voltage and result makes energy storage device 109 and activated equipment 111 telecommunication.
In fig. 2, the shell of emergency oxygen equipment 101 is not shown.But, preferably, this emergency oxygen equipment 101 or it wrap in shell at least partially.In an alternative embodiment, activated equipment 111 also can be arranged in housing exterior and be coupled in lock bolt, activates emergency oxygen equipment with the bottom by the shell shown in release graphics 1.
With reference to figure 3, the 3rd embodiment comprises wireless receiver 203, first energy storage device 209 and the second energy storage device 225.This first energy storage device 209 is coupled in controller 205 by cable 217.Second energy storage device 225 is coupled in wireless receiver 203 by cable 227.In an alternative embodiment, the second energy storage device 225 also can integrate with wireless receiver 203.Energy storage device 229,225 is all coupled in energy source 207.This energy source 207 can be aircraft energy system or other energy source arbitrarily.Preferably, energy source 207 is energy harvesting elements.This energy harvesting elements 207 can be attached to the shell of emergency oxygen equipment 211 and be suitable for converting the mechanical energy coming self-excited oscillation, acceleration etc. acted on this shell to electric energy.This energy harvesting elements 207 can comprise the induction coil with removable magnetic core, this magnetic core is arranged in coil, and produce bias voltage by mechanical spring thus be exposed to magnetic core at shell and energy harvesting elements 207 when moving relative to the vibratory movement effect of coil, allow the induction electric energy in coil.
The electric energy produced in energy harvesting elements 207 is supplied to the first and second energy storage devices 209,255 by cable 215.Therefore, in case of emergency, the energy from the second energy storage device 227 is supplied to wireless receiver and the energy from the first energy storage device 209 is supplied to activated equipment.
Due in case of emergency, it is crucial for being enough to the energy that activated equipment 211 activates in the first energy storage device 209 storage inside, the energy storage device 209,225 that therefore preferably enforcement two is independent.But in an alternative embodiment, wireless receiver 203 and controller 205 are coupled in identical energy storage device.In this embodiment, be necessary to ensure at any time, the amount of the energy stored all is enough to run activated equipment 211.
Wireless signal 223 is sent to wireless receiver 203 from the transmitter of interior of aircraft.This transmitter can be coupled in sensor and/or be suitable for being manually activated, such as, activated by crew in cabin.In an alternative embodiment, wireless receiver 203 and controller integrate.Therefore, the housing size of emergency oxygen equipment can keep less.
With reference to figure 4, the emergency oxygen equipment 301 of the 4th embodiment comprises the controller 305 with integrated sensor.In this embodiment, energy storage device 309 to be coupled with controller 305 by cable 317 and to be coupled with energy source 307, and energy source 307 can be aircraft energy system or gathering element as described.If sensor integrated in controller 305 records low cabin height above sea level air pressure, this makes to be necessary for passenger's supply oxygen, and controller 305 makes energy storage device 309 for be electrically connected with activated equipment 311, to activate emergency oxygen equipment 301.Preferably, all these elements can be contained in a shell.This causes productive costs to reduce, because reduce the complexity be assembled to by emergency oxygen equipment 1,101,201,301 in aircraft.
When aircraft cabin internal gas pressure declines suddenly, emergency oxygen equipment 1,101,201,301 according to the present invention will work as follows.By signal cable 13,113, wireless signal path 223 or after receiving emergency signal by the sensor be integrated in controller 305, controller 5,105,205,305 make energy storage device 9,109,209,309 for and activated equipment 11,111,211,311 electrical contact.Therefore, electric energy flows to activated equipment by cable 17,19,117,119,217,219,317,319 from energy storage device.Parallel therewith, controller sends a signal to activated equipment, to activate emergency oxygen equipment 1,101,201,301 completely.The activation activated completely when the bottom 4 referring to shell 2 is opened herein, so that oxygen mask is supplied to passenger, and makes oxygen flow to face shield.Therefore not exclusively activating to refer to makes this bottom 4 remain on the activation of constrained position.
If should test emergency oxygen equipment 1,101,201,301, workflow follows step identical as explained before, but have following difference, that is, transmitter 3,103 sends test massage controller 5,105,205,305 or wireless receiver 203.Then controller 5,105,205,305 makes energy storage device 9,109,209,309 and activated equipment 11,111,211,311 electrical contact, and also sends signal not exclusively to activate emergency oxygen equipment 1,101,201,301.Therefore, emergency oxygen equipment 1,101,201,301 equipment 11,111,211,311 that is activated not exclusively activates.Incomplete activation herein refers to the activation making bottom 4 remain on constrained position, does not provide to make oxygen mask remain on device interior to passenger.Under this test case, oxygen is not had to flow to face shield.In an alternative embodiment, emergency oxygen equipment 1,101,201,301 comprises lamp or other signal generation apparatus, and this signal generation apparatus is activated the signal sending emergency oxygen equipment 1,101,201,301 correct work.
With reference to figure 5 to 10, its illustrate in detail for emergency oxygen equipment 1,101,201,301, can as the framework 400 of an emergency oxygen equipment part.Framework 400 comprises the base plate 404 with opening 402, this opening 402 by edge 406 institute around.In the side of base plate 404, bearing set 408 is installed.At opposite side, bottom 4 is fixed on one end of base plate by hinge 21 axle pivot.At off position (Fig. 5,8), bottom covers opening 402.Oxygen mask (not shown) can be stored in above bottom, once release bottom 4, oxygen mask just can drop (Fig. 7,10) through opening 402.
Further, framework 400 comprises lock bolt 12.Lock bolt 12 in this embodiment comprises the first uncinus 418 and the second uncinus 422.First uncinus 418 operates together with hole 420.The two is all roughly the direction perpendicular to base plate 404.Bottom 4 is fixed on and opening 414 when bottom 4 is positioned at off position on extend through base plate 404 in hole 420.First uncinus 418 is connected to bar 426, and wherein the two all passes through rod 410 relative to the installation of bearing set (holdingmeans) 408 axle pivot ground.Be installed to activated equipment 411, in this embodiment, this activated equipment 411 is embodied as electromagnetic component bar 426 axle pivot.Activated equipment 411 is fixed on bearing set 408 and is connected to energy source or controller (the two is all not shown), for high energy transmission by cable 419.
Lock bolt 12 or latch mechanism 12 comprise the second uncinus 422.As preferably in Fig. 8 to 10 see, the second uncinus 422 is installed on bottom 4 by pivot 428 axle pivot.Release board 430 is furnished with in one end of the second uncinus 422.At the off position of bottom 4, release board 422 flushes installation (flush-mount) substantially on the surface of bottom 4.Second uncinus 422 remains on this position by the guide springs 424 being fixed on bottom 4.At the off position of bottom 4, guide springs 424 leans on rod 410 and works.Both second uncinus 422 and guide springs 424 opening 416 all on extend through base plate 404.
If release the first uncinus 418, then by guide springs 424 positive opening bottom 4.Once release spring 424, second uncinus 422 can tilt around its pivot 428.The curved end 432 of the second uncinus 422 is suitable for engaging with rod 410, thus makes bottom 4 remain on constrained position (Fig. 6,9).Because the second uncinus 422 is rotated by axle pivot, then release board 430 no longer flush be arranged on bottom 4 surface on.Depart from rod 410 by the curved end 432 promoting release board 430, second uncinus 422, thus bottom 4 can be opened (Fig. 7,10) completely.
Claims (13)
1., for a passenger accommodation emergency oxygen equipment for aircraft, comprising:
At least one electric drive activated equipment, for activating this emergency oxygen equipment;
At least one energy storage device, for storage of electrical energy and by described electric power supply to this at least one activated equipment;
At least one controller, is applicable to Received signal strength to activate this emergency oxygen equipment;
Energy source,
Wherein, described energy source and described energy storage device are coupled, so that the energy of somewhat constant is transferred to this energy storage device from this energy source with the first energy level,
Wherein, described activated equipment and described controller are coupled, so that from this controller to the Signal transmissions of this activated equipment,
Wherein, described activated equipment and described energy storage device are coupled, so that energy is transferred to this activated equipment from this energy storage device at the second energy level higher than this first energy level,
Wherein, an individual unit being suitable for being inserted in the top lid member of aircraft cabin inside set up by described activated equipment, described energy storage device and described controller,
Wherein, described controller is suitable for by the described signal of signal wire (SW) reception from transmitter,
Wherein, described energy source and described energy storage device are coupled by described signal wire (SW), so that at described first energy level transmitting energy.
2. the passenger accommodation emergency oxygen equipment for aircraft according to claim 1, wherein, described controller is suitable for
Receive and process emergency signal, especially cabin pressure drop signal;
Preferably by activator switch, this activated equipment is electrically connected with this energy storage device.
3. according to the passenger accommodation emergency oxygen equipment for aircraft in any one of the preceding claims wherein, wherein, described controller is suitable for receiving the signal different with process at least two kinds, comprising:
For in case of emergency activating the emergency signal of described activated equipment;
For activating the test signal of described activated equipment in a test case.
4. the passenger accommodation emergency oxygen equipment for aircraft according to claim 1, is characterized in that, the feature of described signal is the change of voltage of described signal wire (SW) and/or the change of frequency of electric current.
5. the passenger accommodation emergency oxygen equipment for aircraft according to claim 4, is characterized in that, this change of voltage and/or the change of frequency that send this emergency signal are different from this change of voltage and/or change of frequency of sending this test signal.
6. the passenger accommodation emergency oxygen equipment for aircraft according to claim 1, wherein, described controller comprises and is suitable for receiving the receptor of described signal from sender wireless, and wherein said controller is coupled in energy source or is coupled in the energy storage device be integrated in this emergency oxygen equipment.
7. the passenger accommodation emergency oxygen equipment for aircraft according to claim 1, wherein, described controller comprises sensor, this sensor is suitable for detecting cabin pressure drop and providing cabin pressure drop signal to described controller, and wherein, this controller is coupled in energy source or is coupled in the energy storage device be integrated in this emergency oxygen equipment.
8. the passenger accommodation emergency oxygen equipment for aircraft according to claim 1, wherein, described energy storage device comprises at least one cond or at least one rechargeable battery.
9. the passenger accommodation emergency oxygen equipment for aircraft according to claim 1, also comprises:
An electric drive activated equipment, for activating this emergency oxygen equipment;
At least one controller, is applicable to receive and processing signals, to activate this emergency oxygen equipment;
It is characterized in that, described activated equipment comprises multi-mode lock bolt, and this multi-mode lock bolt is suitable for by discharging bottom under at least two kinds of different modes and activates this emergency oxygen equipment, and these at least two kinds of patterns comprise:
Test case pattern, wherein this bottom is discharged into constrained position from off position;
Emergency situation pattern, wherein this bottom is discharged into fully open position from described closedown or described constrained position.
10. the passenger accommodation emergency oxygen equipment for aircraft according to claim 9, it is characterized in that, described multi-mode lock bolt comprises the first and second uncinuses, wherein this first uncinus is suitable for this bottom to remain on described closed condition, and described second uncinus is suitable for this bottom to remain on described constrained position.
The 11. passenger accommodation emergency oxygen equipment for aircraft according to claim 9,
It is characterized in that, described multi-mode lock bolt comprises uncinus, and this uncinus comprises the first and second grooves, and wherein this first groove is suitable for this bottom to remain on described off position, and described second groove is suitable for this bottom to remain on described constrained position.
12. 1 kinds of aircrafts, comprise multiple passenger accommodation emergency oxygen equipment for aircraft,
It is characterized in that, any one of claim 1 to 11, design at least one passenger accommodation emergency oxygen equipment for aircraft.
13. 1 kinds of in case of emergency activation are used for the method for the passenger accommodation emergency oxygen equipment of aircraft,
Comprise:
By signal wire (SW) Received signal strength to be activated this emergency oxygen equipment by controller;
Electric drive activated equipment is electrically connected with energy storage device;
Use this emergency oxygen equipment energy activated from this energy storage device;
Comprise and transmit the energy of somewhat constant namely by described signal wire (SW) from energy source at least one energy storage device with the first energy level in the following manner: store energy storage device enough with the energy of the interim energy supply of the second energy level so that electric drive activated equipment.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP11153950.8A EP2486958B1 (en) | 2011-02-10 | 2011-02-10 | Passenger cabin emergency oxygen device |
| EP11153950.8 | 2011-02-10 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102632995A CN102632995A (en) | 2012-08-15 |
| CN102632995B true CN102632995B (en) | 2016-04-20 |
Family
ID=44236750
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110057818.3A Expired - Fee Related CN102632995B (en) | 2011-02-10 | 2011-03-10 | The method of aircraft, passenger accommodation emergency oxygen equipment and operation and this equipment of activation |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP2486958B1 (en) |
| CN (1) | CN102632995B (en) |
| BR (1) | BR102012002936A2 (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9683395B2 (en) * | 2013-06-14 | 2017-06-20 | B/E Aerospace, Inc. | Advanced latch for emergency oxygen container deployment |
| US20150175104A1 (en) * | 2013-12-20 | 2015-06-25 | B/E Aerospace, Inc. | Energy harvesting for the electronic regulation of oxygen flow |
| US11247448B2 (en) | 2014-02-27 | 2022-02-15 | B/E Aerospace, Inc. | Panel with paint ready surface |
| US20160138301A1 (en) * | 2014-11-14 | 2016-05-19 | The Boeing Company | Self-contained electronic stowage bin system |
| KR102363632B1 (en) * | 2014-12-29 | 2022-02-16 | 삼성전자주식회사 | Method and apparatus for generating distress signal |
| CN113562181B (en) * | 2021-07-29 | 2023-04-18 | 北京安达维尔航空设备有限公司 | Novel long-endurance passenger oxygen supply device |
| EP4306432B1 (en) | 2022-07-15 | 2025-09-03 | Airbus Operations GmbH | Device for latching a door of an oxygen mask container in an aircraft cabin |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4718572A (en) * | 1985-08-08 | 1988-01-12 | Societe De Fabrication D'instruments De Mesure (S.F.I.M.) | Device for half-opening the door of a box containing safety equipment, such as oxygen masks |
| EP2090335A1 (en) * | 2008-02-12 | 2009-08-19 | Intertechnique SA | Oxygen breathing device |
| EP2168635A1 (en) * | 2008-09-26 | 2010-03-31 | Intertechnique SA | Oxygen breathing device with redundant signal transmission |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4518179A (en) * | 1982-12-09 | 1985-05-21 | The Boeing Company | Test stop assembly for oxygen box door |
-
2011
- 2011-02-10 EP EP11153950.8A patent/EP2486958B1/en not_active Not-in-force
- 2011-03-10 CN CN201110057818.3A patent/CN102632995B/en not_active Expired - Fee Related
-
2012
- 2012-02-09 BR BR102012002936-7A patent/BR102012002936A2/en not_active Application Discontinuation
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4718572A (en) * | 1985-08-08 | 1988-01-12 | Societe De Fabrication D'instruments De Mesure (S.F.I.M.) | Device for half-opening the door of a box containing safety equipment, such as oxygen masks |
| EP2090335A1 (en) * | 2008-02-12 | 2009-08-19 | Intertechnique SA | Oxygen breathing device |
| EP2168635A1 (en) * | 2008-09-26 | 2010-03-31 | Intertechnique SA | Oxygen breathing device with redundant signal transmission |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102632995A (en) | 2012-08-15 |
| EP2486958B1 (en) | 2016-07-13 |
| EP2486958A1 (en) | 2012-08-15 |
| BR102012002936A2 (en) | 2014-01-07 |
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