CN103979115B - The monitoring method of hydraulic fluid liquid level in aircraft - Google Patents
The monitoring method of hydraulic fluid liquid level in aircraft Download PDFInfo
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- CN103979115B CN103979115B CN201410176999.5A CN201410176999A CN103979115B CN 103979115 B CN103979115 B CN 103979115B CN 201410176999 A CN201410176999 A CN 201410176999A CN 103979115 B CN103979115 B CN 103979115B
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Abstract
A kind of method (100) of hydraulic fluid liquid level in monitoring aircraft, the lever piece (102) of predetermined stability criterion is met including identification aircraft, receive the output (104) from fluid sensor, calculate the hydraulic fluid liquid level (106) at least one hydraulic reservoir, the hydraulic fluid value (108) for indicating amount of hydraulic fluid in aircraft is at least calculated based on the hydraulic fluid liquid level calculated, and the instruction (110) of hydraulic fluid value is provided.
Description
Technical field
The present invention relates to the method for hydraulic fluid liquid level in monitoring aircraft.
Background technology
Present aircraft can include hydraulic system, for running or starting the mobile component in aircraft, for example, rise and fall
Frame, brake etc..It can happen that being that aircraft hydraulic system loses fluid over time, or turn between storage point
Advection body is excessive so as to fill storage tank.In addition, including that can be caused due to outside the plan due to excessive leakage caused by filling excessively
Maintenance delay.This may cause further influence on system operation, and cause the loss of course line income.Currently acquired energy is true
The reading for representing hydraulic pressure fluid level between the aircraft runtime in fact is extremely difficult, particularly sliding including aircraft, take off,
During the aircraft movement of landing and flight, because flow of pressurized in the mobile storage tank that can change stored by fluid of aircraft
The liquid level of body.The brief description of the present invention
In one embodiment, the present invention relates to a kind of method of monitoring hydraulic fluid liquid level, and including identification when flight
Device operationally meets the target phase of predetermined stability criterion, receive the output of fluid sensor during recognized target phase from
And stable output is defined, and hydraulic fluid liquid level is calculated based on the stable output, it is at least true based on the hydraulic fluid liquid level calculated
Surely indicating in aircraft the hydraulic fluid value of amount of hydraulic fluid, there is provided the instruction of hydraulic fluid value.
A kind of method for monitoring hydraulic fluid liquid level in aircraft hydraulic system, the hydraulic system has at least one liquid
Storage tank is pressed, the storage tank supplies hydraulic fluid at least one aircraft assembly, and the hydraulic system has fluid sensor
The output for indicating amount of hydraulic fluid in the storage tank is provided, methods described includes：
The target phase of predetermined stability condition is met during identification aircraft operation；
The output from the fluid sensor is received during the target phase recognized to define stable output；
The hydraulic fluid liquid level at least one described hydraulic reservoir is calculated based on the stable output；
At least determine to indicate the hydraulic fluid of amount of hydraulic fluid in the aircraft based on the hydraulic fluid liquid level calculated
Value；And
The instruction of the hydraulic fluid value is provided.
In one embodiment, the target phase recognized includes multiple stages of the aircraft flight.
In one embodiment, multiple stages of the flight include sliding and cruising.
In one embodiment, calculating the hydraulic fluid liquid level is included when the aircraft is run at least some institutes
State hydraulic fluid and adjust calculated hydraulic fluid liquid level.
In one embodiment, adjusting calculated hydraulic fluid liquid level includes adding to the hydraulic fluid liquid level calculated
Hydraulic fluid at least some uses.
In one embodiment, the addition includes adding known hydraulic pressure used in the component of predictable use hydraulic pressure
Fluid.
In one embodiment, the component of the predictable use hydraulic pressure includes trailing edge flap.
In one embodiment, this method also includes identified hydraulic pressure value and predetermined threshold being compared.
Indicate to include described comparing hydraulic pressure value determined by instruction more than described pre- there is provided described in one embodiment
When determining threshold value, instruction should empty hydraulic fluid.
Indicate to include described comparing hydraulic pressure value determined by instruction less than described pre- there is provided described in one embodiment
When determining threshold value, instruction should adding hydraulic fluid.
In one embodiment, this method also includes identified hydraulic fluid value being compared with history value.
In one embodiment, this method also includes relatively determining liquid based on identified hydraulic fluid value and history value
Leakage in pressure system.
There is provided indicate to include indicating leakage in one embodiment.
In one embodiment, stability criterion include it is following at least one：Lateral within model of flight value 0.01g plus
The direct of travel of longitudinal acceleration, change less than every 3 degree of half second row within speed, model of flight value 0.02g, and flight mould
Rolling within 1 degree of state value.
In one embodiment, stability criterion includes parameter, the parameter include it is following at least one：Appropriate flow-disturbing
Device state, appropriate wing flap handling position, appropriate trhrust-reversal device position and appropriate landing gear position.
A kind of method for monitoring hydraulic fluid liquid level in aircraft hydraulic system, the hydraulic system has two hydraulic pressure storages
Tank, the hydraulic reservoir supplies hydraulic fluid at least one mobile component of aircraft, and the hydraulic system has operable
Ground is coupled to each hydraulic reservoir and provides the fluid sensor for indicating the output of amount of hydraulic fluid in its associated reservoir, described
Method includes：
Determine the position of aircraft and the movement of aircraft；
Determine the position of at least one mobile component on aircraft；
The target phase of predetermined stability criterion is met during identification aircraft operation；
The output from fluid sensor is received during the target phase recognized to define stable output；
The hydraulic fluid liquid level in hydraulic reservoir is calculated based on the stable output；
At least determine to indicate the hydraulic pressure of amount of hydraulic fluid in each hydraulic reservoir based on the hydraulic fluid liquid level calculated
Fluid value.
The excessive condition of filling is determined by identified hydraulic fluid value, one of condition and leak condition is required supplementation with；With
And
The instruction related to identified condition is provided.
In one embodiment, calculating hydraulic fluid liquid level is included based at least one received on aircraft
The output of mobile component position, calculated hydraulic fluid liquid level is adjusted to the hydraulic fluid at least some uses.
In one embodiment, determine that hydraulic fluid value includes determining at least as next：Counted in two hydraulic reservoirs
Average value, intermediate value, mode and the standard deviation of the hydraulic fluid liquid level of calculation.
In one embodiment, determine condition include by the average value of identified hydraulic fluid liquid level, intermediate value, mode with
And at least one in standard deviation is compared with historic fluid liquid level.
Brief description of the drawings
In accompanying drawing：
Fig. 1 is the schematic diagram of a part for the aircraft with demonstration hydraulic system；
Fig. 2 is the perspective view of aircraft in Fig. 1, and can wherein realize the earth station of the embodiment of the present invention；And
Fig. 3 is flow chart, the method for showing the hydraulic fluid liquid level in monitoring aircraft according to embodiments of the present invention.
Embodiment
Commonly using hydraulic-driven system during due to changing pitching, rolling, driftage on runway and in the air and accelerating
System, it is highly difficult that the value of the fluid level of true representations hydraulic reservoir 22, which is separated,.During all flight points periodically
Reading is gathered, but most of in these readings is insecure for these reasons.Embodiments of the invention are explained such
Insecure data, and allow the liquid level of more accurately monitoring hydraulic fluid.
Accompanying drawing 1 exemplarily represents a part for aircraft 10, and it can implement embodiments of the invention and may include
The one or more engine modules 12 coupled with fuselage, the cockpit 16 in fuselage 14 and the wing stretched out from fuselage 14
Component 18.With hydraulic reservoir 22 and hydraulic circuit 24, and hydraulic system 20 comprising the desired amount of hydraulic fluid is included
In aircraft 10.In illustrated example, two hydraulic reservoirs 22 are illustrated, and the two hydraulic reservoirs
22 are circulated each other by hydraulic circuit 24.Fluid sensor 26 is operationally coupled with each hydraulic reservoir 22, and often
It is individual that the output for indicating the amount of hydraulic fluid in hydraulic reservoir 22 can be provided.
Hydraulic circuit 24 can provide hydraulic fluid to the hydraulic package 28 of aircraft 10.The example of hydraulic package 28 in aircraft
Attached bag includes brake 30, the wing flap 32 comprising multiple trailing edge flaps and multiple droope snoots, in the installation of the front end of trailing edge flap 32
Flow spoiler, undercarriage 34, lift 36, rudder 38, trhrust-reversal device etc..Various control mechanism can be included in cockpit 16
40, for starting and operating such hydraulic package 28.Controlling organization 40 can be any appropriate mechanism.Shown by unrestricted
A kind of mode of example, controlling organization 40 may include wing flap handle 42, and pilot can operate to set multiple trailing edge flaps 32 to it
Position.Term " wing flap handle " used in this description is not restricted to physics handle, but it is related to for setting the flap
The control device of wing position.In the whole early stage of aviation history, the control device is handle, and term " wing flap handle " is at present
The general name of the control device for setting flap configuration is had been changed to, whether is that handle or touch-screen are used but regardless of control device
Button on the interface of family.One or more pumps 44 can be provided in hydraulic circuit 24, so that hydraulic fluid is sent to comprising liquid
The different piece of the aircraft 10 of component 28 is pressed, and is transmitted between two hydraulic reservoirs 22 itself.
Big quantity sensor 46 can be also included in aircraft 10, and such sensor 46 is exportable any number of on flying
The operation of row device 10 and its available signal of various systems and component.For example, sensor 46 can include various sensors, for true
Determine the state of hydraulic package, including whether hydraulic package is using.In addition, sensor 46 may include various sensors, this is various
Sensor determines the various actions of aircraft 10, includes pitching, rolling, driftage and the acceleration of aircraft 10.
With reference now to accompanying drawing 2, it can see that aircraft 10 is normally run multiple extra flies with easier
Row device system 48, and controller 50 and the communication system with wireless communication link 52 can also reside in aircraft 10.Control
Device 50 processed is operatively coupled to multiple aerocraft systems 48, including hydraulic system 20.For example, hydraulic package 28, sensing fluid flow
Device 26, controlling organization 40, pump 44, aerocraft system 48 and sensor 46 can be operatively coupled to controller 50.
Controller 50 can also be connected with other controllers of aircraft 10.Controller 50 may include memory 54, storage
Device 54 may include random access memory (RAM), read-only storage (ROM), flash memory, one or more different types of portable electricity
Quantum memory, such as disk, DVD, CD-ROM, or these type of memory is any appropriately combined.Controller 50 can be included
One or more processors 56, it can run any appropriate program.Controller 50 can be a FMS part, Huo Zheke
It is operatively coupled to FMS.
Computer retrievable information database purchase can be accessed in memory 54 by processor 56.Processor 56
Operation accesses the set of the executable instruction of database.Alternatively, controller 50 can be operatively coupled to information database.
For example, such database is storable on alternate computer or memory.It can be any appropriate to be appreciated that the database
Database, including the centralized database with multi-group data, multiple discrete data storehouses or even simple for interlinking
Tables of data.It is contemplated that database can merge mass data storehouse or the database can essentially be substantial amounts of independent data
Storehouse.Database can be with data storage, and the data include the historical data related to the hydraulic system 20 of aircraft 10, the history number
According to the hydraulic fluid liquid level of the hydraulic system 20 including before.Known to the hydraulic package 28 that database can also be including the use of in
The value that hydraulic pressure is used, and the stability criterion for aircraft 10.
It is alternatively possible to which contemplating database can separate with controller 50, but it can be communicated with controller 50, so as to can be by
Controller 50 conducts interviews to it.For example, it is envisioned that contain the database on portable memory devices, and in such case
Under, aircraft 10 may include accommodate portable memory devices port, and such port will with the electronic communication of controller 50, with
Just controller 50 can read the content of portable storage device.It is also contemplated that can be entered by wireless communication link 52 to database
Row updates.Additionally, it is contemplated that such database can be located remotely from the position of aircraft 10, such as course line Operation Centre,
Flight commands control unit or another position.Controller 50 can be operatively coupled with wireless network, can by the wireless network
Database information is supplied to controller 50.
Although being illustrated that commercial aircraft, it is contemplated that the part of the embodiment of the present invention can be real anywhere
Apply, be included in the computer 60 of ground system 62.In addition, database as described above can also be located at destination server or meter
In calculation machine 60, the destination server or computer 60 are positioned at the ground system 62 specified and comprising specified ground system 62.It is standby
Selection of land, database can be located at alternative ground location.Ground system 60 can communicate with miscellaneous equipment, and miscellaneous equipment includes control
Device 50 and the database that computer 60 is located remotely from by wireless communication link 64.Ground system 62 can be any type of
Communicate ground system 62, such as flight course control or flight commander department.
One of controller 50 and computer 60 may include all or part of of computer program, the computer
Program has the executable instruction set for being used for monitoring the hydraulic fluid liquid level in hydraulic system 20.Not tube controller 50 or computer
60 whether the program of operational monitoring hydraulic fluid liquid level, the program may include computer program product, the computer program product
It may include machine readable media, the machine readable media carries or can operating instruction or data with the machine stored thereon
Structure.Such machine readable media can be any usable medium, and it by universal or special computer or other can be carried
The machine of processor is accessed.As a rule, such computer program includes routine, program, object, component, data structure, calculation
Method etc., it has the technique effect for performing particular task or implementing particular abstract data type.Machine can operating instruction, association
Data structure and program representation be used for the example that performs the program code that information disclosed herein is exchanged.Machine can be run
Instruction includes such as instruction and data, and it causes all-purpose computer, special-purpose computer or dedicated processes machine to perform necessarily
Function or one group of function.
It is appreciated that aircraft 10 and computer 60 only represent two example embodiments, it is arranged for carrying out the present invention
Embodiment or embodiment part.During running, aircraft 10 and/or computer 60 can be monitored in hydraulic system 20
Fluid level.Among other things, controller 50 and/or computer 60 can analyze the data output of fluid sensor 26, so that
Monitor the fluid level in hydraulic system 20.For example, in the exportable hydraulic reservoir 22 of fluid sensor 26 fluid level signal.
Because fluid flows in aircraft 10, it is to be appreciated that the mobile signal that can influence fluid sensor 26 of aircraft 10 is defeated
Go out, even if the fluid level in hydraulic reservoir 22 keeps constant.
When aircraft 10 is currently running, it is possible to use various controlling organizations 40 set the position of hydraulic package 28.With
The startup of some systems, hydraulic package 28 is pumped into by fluid from hydraulic storage system 22.The usage changes hydraulic reservoir 22
Interior fluid level.For example, wing flap handle 42 can be used to control the position of trailing edge flap 32, this can cause after fluid is pumped into
Edge wing flap 32.Controller 50 and/or computer 60 can monitor the liquid level result in hydraulic reservoir 22 by different system.Alternatively
Ground, some hydraulic packages 28 use the amount of hydraulic fluid of very predictable, such as trailing edge flap 32.Controller 50 and/or calculating
Machine 60 is using the input from controlling organization 40, the input from fluid sensor 26, the input from multiple sensors 46
And the input from database and/or the information from flight course control or flight headquarter monitor the hydraulic pressure in aircraft 10
Fluid level.
More accurate fluid level can be calculated by being had determined by the output during receiving part of having a smooth flight.Due to
Some fluids are used for the flight of aircraft 10, and such liquid level may not be completely accurate.However, the hydraulic pressure in use
The given value of fluid level can pay attention to when making more accurate determination.Determined based on such, can detect and/or predict
When these liquid levels are too low, too high or with unacceptable rate reduction.Once it is determined that amount of hydraulic fluid, so that it may
Instruction is provided on aircraft 10 and/or at ground system 62.It is contemplated that such determination can be completed during flying, can be with
Completed after flight or completed after any sortie flight at the end of one day or any day after it is complete after any sortie flight
Into.Wireless communication link 52 and wireless communication link 64 may serve to transmit data, so as to controller 50 and/or computer 60
Monitoring can be completed.
Embodiments in accordance with the present invention, the illustration method 100 of accompanying drawing 3, it can be used for monitoring hydraulic pressure system when aircraft 10 is run
Hydraulic fluid liquid level in system 20.Method 100 starts at 102, and identification wherein aircraft 10 meets predetermined stable during running
The target phase of property standard.Stability criterion is typically at nearly zero pitching, rolling and the acceleration of aircraft 10.Stability criterion is also
It may include the deployment of various hydraulic packages 28 or do not dispose, and thus may include at least as next：Appropriate flow spoiler bar
Part, appropriate wing flap handling position, appropriate trhrust-reversal device position and appropriate landing gear position.For example, show can for table 1
Various parameters and predetermined stability criterion for recognizing the target phase at 102.
Table 1：Demonstration stability criterion
In upper table, side acceleration and longitudinal acceleration have the stability criterion related to the acceleration due to gravity.
The reading from sensor 46 and the information from aerocraft system 48 can be analyzed to determine it is such whether inflight phase meets
Stability criterion, wherein the information from aerocraft system 48 is, for example, the binary value output of aerocraft system 48.Therefore, really
Determine whether inflight phase meets position and the movement of aircraft that stability criterion may include to determine aircraft, and determine flight
Such information is simultaneously compared by the position of at least one movable member of device to related stability criterion.Once it is determined that flight
What stage meet the stability criterion, it is possible to by fluid level should stablize reading group separate.It is contemplated that knowing
Other target phase may include multiple mission phases of aircraft 10.For example, multiple stages of flight are included before taking off and after landing
Slide and cruise.
At 104, during the target phase recognized at 102, it is steady to define to receive the output from fluid sensor 26
Fixed output.At 106, the hydraulic fluid liquid level in hydraulic reservoir can be calculated based on the stable output received at 104.Can be with various
Mode calculates the hydraulic fluid liquid level in hydraulic reservoir 22.Controller 50 and/or computer 60 can be for example based on from fluids
Hydraulic fluid liquid level is calculated as Fluid Volume by the signal of sensor 26.Alternatively, controller 50 and/or computer 60 can be accessed
It is stored in the hydraulic fluid liquid level inquiry table in one of database, and being received from fluid sensor 26 can be used
Export to inquire about the hydraulic fluid liquid level in each hydraulic reservoir 22.
In addition, calculating hydraulic fluid liquid level includes working as aircraft 10 operationally, to the flow of pressurized at least some uses
Body adjusts calculated hydraulic fluid liquid level.For example, any area can be corrected when hydraulic packages 28 only are can be predicted using these
Domain wherein has the quantity of the stable reading exported to increase.For example, the calculated hydraulic fluid liquid level of adjustment may include to institute
The hydraulic fluid liquid level of calculating increases the hydraulic fluid at least some uses.The increase, which can be limited to increase can be predicted, uses hydraulic pressure
Component used in known hydraulic fluid.
At 108, it at least can determine to indicate amount of hydraulic fluid in aircraft 10 based on the hydraulic fluid liquid level calculated at 106
Hydraulic fluid value.For example, controller 50 and/or computer 60 can be determined as the capacity of hydraulic reservoir 22 or size percentage
Function hydraulic fluid value.By this way, the hydraulic fluid value of a hydraulic reservoir 22 may be 90%.Alternatively, liquid
Pressure fluid value may include to determine at least following a kind of：Hydraulic fluid liquid level average value determined by two hydraulic reservoirs 22, in
Value, mode and standard deviation.It is also conceivable that determining that hydraulic fluid value may include to determine that hydraulic fluid value is lower value or added
Noted angle value wherein which.
At 110, it is possible to provide the instruction of hydraulic fluid value.Or, controller 50 and/or computer 60 can provide hydraulic pressure
The instruction of fluid value.It is contemplated that it can be the independent instruction for hydraulic system 20 to indicate, or it can be each hydraulic reservoir
22 are provided separately instruction.The instruction can be provided in any appropriate location in any suitable manner, including in cockpit 16 and ground
At face station 62.If for example, the operation program of controller 50, then appropriate instruction can be provided on aircraft 10 and/or on
Pass to ground system 62.Alternatively, if the operation program of computer 60, it indicates that can upload or otherwise transfer be sent to it is winged
Row device 10.Alternatively, transfer transmission can will be indicated, so as in another place of such as flight course control or flight headquarter
The instruction is provided.According to it is identified be that what hydraulic fluid numerical value can provide any number of instruction.For example, can indicate compared with
Low value filled angle value and the Fluid Volume that should be added or remove.Compare for example, providing instruction at 110 and may include to work as
Hydraulic pressure value determined by indicating indicates that hydraulic fluid should be emptied when being more than predetermined threshold.On the contrary, can wrapped indicated at 110
Include when compare indicate determined by hydraulic pressure value be less than predetermined threshold when indicate should adding hydraulic fluid.If any one is canned full
Degree can provide low severity between 105% and 112%, then and fill excessive alarm.If any one tank filling level is higher than
112%, then high severity can be provided and fill excessive alarm.If any one tank filling level, can between 80% and 75%
Low severity is provided and requires supplementation with alarm.If tank filling level is less than 75%, high severity can be provided and require supplementation with alarm.
Implement when, it is determined that, value and it is any compare may be converted into monitor fluid level and export its indicate
Algorithm.Such algorithm can be converted to computer program, and it includes can be run by controller 50 and/or computer 60 one group
Can operating instruction.
It is appreciated that the monitoring method of hydraulic fluid liquid level is more flexible, and shown method is used for the purpose of saying
Bright purpose.For example, each sequence of steps of description is for illustrative purposes only, it is not intended to limit method in any way
100, because it is appreciated that these steps can be carried out according to different logical orders, or increased or insertion step
Suddenly it can also be included without departing from embodiments of the invention.By way of non-limiting example, method may include from
The hydraulic fluid value of determination determines to fill excessive condition, requires supplementation with one of condition and leak condition, and institute
The instruction of offer can be related to identified condition.
In addition, this method may include the hydraulic fluid value of determination being compared with history value.This is included hydraulic fluid
Average value, intermediate value, mode and the standard deviation and historic fluid value of value are compared.It can therefrom determine in hydraulic system 20
Leakage, and the instruction of leakage can be provided.More specifically, the embodiment of this method may include to be based on hydraulic fluid liquid level information
Analysis prediction include leak different conditions.Embodiments of the invention can also be detected by trend analysis and leaked.For example, control
Device 50 and/or computer 60 processed can find five flight oil mass changes (that is, pasta before current fuel head and five flight
The difference of height).If the difference is above centesimal reduction, such information can be further adjusted.
First, irregular change is foreclosed according to one group of rule.For example, the group rule may include if another liquid
The hydraulic fluid liquid level of pressure storage tank 22 has increased, then the value added should be subtracted from decreasing value.This explains the oil between tank
Exchange because the situation for appearing to the leakage in a hydraulic reservoir 22 may be any amount hydraulic reservoir
Exchange between 22.The group rule may include if in 5 trend any time difference flown twice be more than 12 hours, and
And do not know whether all flying qualities are all recorded in database, then larger decreasing value can be neglected.The group rule can
If exceeding such as 110% some high values including another hydraulic reservoir 22, ignore higher negative change, this is due to
Hydraulic reservoir 22 can not exactly be recorded in such amount and decreasing value be probably be transferred to another hydraulic reservoir 22 and not
Record value added.If the group rule may include that hydraulic reservoir 22, more than 105%, can be neglected higher before flying for five times
Negative change, this is due to that may detect filling excessively and oil is removed manually from hydraulic reservoir 22, rather than represent it is any its
Its situation.The group rule may include if the standard deviation of the point for being used in the pasta average value of any log is more than
5%, then five times larger flight decreasing value are ignored to these flights, because the confidence level of such reading is relatively low.The group
Rule may include if for the flight or three flight altogether in five flight pasta changes twice or repeatedly in rapid succession
Reading can not be obtained due to lacking available point, then ignores change.The group rule may include if any in five flight ranges
Flight increase compared with its preceding flight is more than 3%, then ignores the change.
Five flight pastas change before other adjustment may include to start from 30 flights of current flight can phase Calais
Obtain accumulated change.This can also be completed according to one group of rule.The group rule may include if for calculating when first five flight
In five flights of pasta change the change of single flight pasta liquid levels be more than once it is positive, then summation reset to zero and after
It is continuous.The group rule may include that its five times flight changes of experience are ignored one of due to mentioning before to fly if summed
OK, then summation is reset to zero and continues summation.(this is typically in the case of any obtained average value is not recorded
Because according to when can be with the no available point of limitation above point of use), just enter row interpolation to allow by them
Continue to sum towards current flight.
For the change of addition, intermediate value and mode propagation summation can be used in combination.Mode value in any one tank or
The accumulation reduction amount of intermediate value be higher than 20%, the accumulation reduction amount of remaining mode value or intermediate value at least on 14%, and
Nearest 20 times in-flight each intermediate value of the effective accumulating point of at least six and mode loss imply that letting out for high severity higher than 5%
Leak failure.The accumulation reduction amount of both mode value and intermediate value in any one tank is higher than 35%, but does not fly at nearest 20 times
The each intermediate value of at least six point and mode loss imply that the leakage failure of middle severity higher than 5% in row.In any one tank
Mode value or intermediate value accumulation reduction amount be higher than 20%, remaining mode value or intermediate value do not exist at least on 14%
Nearest 20 times in-flight each intermediate value of the effective accumulating point of at least six and mode loss imply that letting out for low severity higher than 5%
Leak failure.For example, table 2 shows workable various similar instruction standards during prediction leakage.
Table 2：Leak instruction standard
Therefore, by being compared with flight reading before, it can detect and whether use more streams than usual
Body, and leakage can be recognized.
The data that aircraft is collected during the beneficial effect of above-described embodiment includes flight can be used for monitoring aircraft fortune
Hydraulic fluid liquid level during row in its hydraulic system, and the instruction on hydraulic fluid liquid level or hydraulic fluid value is provided.On
The advantage for stating embodiment is can to obtain and analyze stable reading.In addition, by before the critical liquid level of operation is reached on
Low or high liquid level carries out alarm, can be set apart to the plan for changing liquid level without causing delay.Embodiments of the invention can
To detect leakage, it similarly allows for obtaining more preferable operational plan, reduces the worry to economic loss.In addition, by manual
Human error easily occurs for the current system of input information, and automation, which records these process, will provide more accurate given
The history of aircraft, this would be useful in future maintenance.In addition, embodiments of the invention have predictive ability so that at this
The situation of sample can carry out maintenance plan before occurring.This allows by reducing maintenance cost, replanning cost and minimum
Influence on system operation (including minimizing aircraft time on the ground) carries out cost savings.
This printed instructions uses examples to disclose the present invention, including optimal mode, and also makes those skilled in the art
The present invention can be implemented, including manufacture and use any equipment or system and perform any method being incorporated to.The present invention can quilt
Patentable scope is defined by the claims, and may include the other examples that those skilled in the art expect.
If the expression of the structural element that such other examples have and claim surface language is as good as, or if it is such its
Its example includes not having the equivalent structural elements of essence difference with claim surface language, then it is intended to fall into claim
In the range of book.
List of parts：
10 aircraft
12 engine modules
14 fuselages
16 cockpits
18 wing components
20 hydraulic systems
22 hydraulic reservoirs
24 hydraulic circuits
26 fluid sensors
28 hydraulic packages
30 brakes
32 wing flaps
34 undercarriages
36 lifts
38 rudders
40 controlling organizations
42 wing flap handles
44 pumps
46 sensors
48 aerocraft systems
50 controllers
52 wireless communication links
54 memories
56 processors
60 computers
62 ground systems
64 wireless communication links
100 methods
102 identification target phases
104 receive output
106 calculate hydraulic fluid liquid level
108 determine hydraulic fluid value
110 provide instruction
Accompanying drawing 3
102 identification target phases
104 receive output
106 calculate hydraulic fluid liquid level
108 determine hydraulic fluid value
110 provide instruction
Claims (19)
1. a kind of method for monitoring hydraulic fluid liquid level in aircraft hydraulic system, the aircraft hydraulic system has at least one
Individual hydraulic reservoir, it supplies hydraulic fluid at least one component of aircraft, and wherein fluid sensor, which is provided, indicates the storage
The output of amount of hydraulic fluid in tank, methods described includes：
Recognize that the aircraft during aircraft operation meets the lever piece of predetermined stability criterion；
The output from the fluid sensor is received during the lever piece recognized to limit stable output；
The hydraulic fluid liquid level at least one described hydraulic reservoir is calculated based on the stable output；
Determine to indicate the hydraulic fluid value of amount of hydraulic fluid in the aircraft based on the hydraulic fluid liquid level at least calculated；With
And
The instruction of the hydraulic fluid value is provided.
2. according to the method described in claim 1, wherein the lever piece of the identification includes multiple ranks of the aircraft flight
Section.
3. method according to claim 2, wherein multiple stages of the flight are including sliding and cruising.
4. the method according to foregoing any one claim, wherein calculating the hydraulic fluid liquid level includes flying when described
The hydraulic fluid liquid level that row device is calculated at least some adjustment in the hydraulic fluid in use when operating.
5. method according to claim 4, wherein adjusting the hydraulic fluid liquid level of the calculating is included to the calculating
Hydraulic fluid liquid level adds the hydraulic fluid at least some uses.
6. method according to claim 5, wherein the component that the addition includes adding predictable use hydraulic pressure is made
Known hydraulic fluid.
7. method according to claim 6, wherein the component of the predictable use hydraulic pressure includes trailing edge flap.
8. according to the method described in claim 1, in addition to by identified hydraulic fluid value it is compared with predetermined threshold.
9. method according to claim 8, wherein providing described indicate including hydraulic pressure determined by instruction described ought be compared
When fluid value is more than the predetermined threshold, instruction should empty hydraulic fluid.
10. the method according to any one of claim 8 or 9, wherein providing described indicate including instruction described ought be compared
When identified hydraulic fluid value is less than the predetermined threshold, instruction should adding hydraulic fluid.
11. according to the method described in claim 1, in addition to by identified hydraulic fluid value it is compared with history value.
12. method according to claim 11, in addition to it is true based on the comparison of identified hydraulic fluid value and history value
Determine the leakage in hydraulic system.
13. method according to claim 12, indicates to include indicating leakage wherein providing.
14. according to the method described in claim 1, wherein, stability criterion include it is following at least one：Model of flight value
The row of the longitudinal acceleration within side acceleration, model of flight value 0.02g, change less than every 3 degree of half second row within 0.01g
The rolling entered within direction, and 1 degree of model of flight value.
15. according to the method described in claim 1, wherein, stability criterion includes parameter, and the parameter includes following at least one
It is individual：Appropriate flow spoiler state, appropriate wing flap handling position, appropriate trhrust-reversal device position and appropriate undercarriage position
Put.
16. a kind of method for monitoring hydraulic fluid liquid level in aircraft hydraulic system, the hydraulic system has two hydraulic pressure storages
Tank, the hydraulic reservoir supplies hydraulic fluid at least one mobile component of aircraft, and the hydraulic system has operable
Ground is coupled to each hydraulic reservoir and provides the fluid sensor for indicating the output of amount of hydraulic fluid in its associated reservoir, described
Method includes：
Determine the position of aircraft and the movement of aircraft；
Determine the position of at least one mobile component on aircraft；
The lever piece of predetermined stability criterion is met during identification aircraft operation；
The output from fluid sensor is received during the lever piece recognized to limit stable output；
The hydraulic fluid liquid level in hydraulic reservoir is calculated based on the stable output；
At least determine to indicate the hydraulic fluid of amount of hydraulic fluid in each hydraulic reservoir based on the hydraulic fluid liquid level calculated
Value；
The excessive condition of filling is determined by identified hydraulic fluid value, one of condition and leak condition is required supplementation with；And
The instruction related to identified condition is provided.
17. method according to claim 16, wherein calculating hydraulic fluid liquid level is included based on received on flying
The output of at least one mobile component position of row device, calculated flow of pressurized is adjusted to the hydraulic fluid at least some uses
Body fluid position.
18. the method according to any one of claim 16 or 17, wherein determining that hydraulic fluid value includes determining at least such as
It is next：Average value, intermediate value, mode and the standard deviation of the hydraulic fluid liquid level calculated in two hydraulic reservoirs.
19. method according to claim 18, wherein the condition of determination includes being averaged identified hydraulic fluid liquid level
At least one in value, intermediate value, mode and standard deviation is compared with historic fluid liquid level.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1302426.0A GB2510634B (en) | 2013-02-12 | 2013-02-12 | Methods of monitoring hydraulic fluid levels in an aircraft |
| GB1302426.0 | 2013-02-12 | ||
| US14/152,258 US9316520B2 (en) | 2013-02-12 | 2014-01-10 | Methods of monitoring hydraulic fluid levels in an aircraft |
| US14/152258 | 2014-01-10 | ||
| US14/152,258 | 2014-01-10 |
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| CN103979115A CN103979115A (en) | 2014-08-13 |
| CN103979115B true CN103979115B (en) | 2017-10-03 |
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| CN112208781A (en) * | 2020-10-10 | 2021-01-12 | 江西洪都航空工业集团有限责任公司 | Low oil level warning system of dual-redundancy aircraft fuel tank |
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| US4273303A (en) * | 1979-03-16 | 1981-06-16 | The Boeing Company | Adaptive airplane landing gear |
| US4286464A (en) * | 1980-01-14 | 1981-09-01 | Technical Development Company | Optical fluid level monitor |
| US4704865A (en) * | 1984-07-16 | 1987-11-10 | The Boeing Company | Hydraulic reserve system for aircraft |
| US5331850A (en) * | 1993-03-05 | 1994-07-26 | Arkwin Industries Incorporated | Apparatus for indicating the level of a material in a container |
| CN102472657A (en) * | 2009-04-03 | 2012-05-23 | 伊顿公司 | Fuel gauging system utilizing a digital fuel gauging probe |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| FR2922521A1 (en) * | 2007-10-23 | 2009-04-24 | Airbus France Sas | HYDRAULIC SYSTEM FOR AIRCRAFT. |
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|---|---|---|---|---|
| US4273303A (en) * | 1979-03-16 | 1981-06-16 | The Boeing Company | Adaptive airplane landing gear |
| US4286464A (en) * | 1980-01-14 | 1981-09-01 | Technical Development Company | Optical fluid level monitor |
| US4704865A (en) * | 1984-07-16 | 1987-11-10 | The Boeing Company | Hydraulic reserve system for aircraft |
| US5331850A (en) * | 1993-03-05 | 1994-07-26 | Arkwin Industries Incorporated | Apparatus for indicating the level of a material in a container |
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