CN105741381B - A kind of method that determining aircraft flies ginseng recording parameters set - Google Patents
A kind of method that determining aircraft flies ginseng recording parameters set Download PDFInfo
- Publication number
- CN105741381B CN105741381B CN201610059153.2A CN201610059153A CN105741381B CN 105741381 B CN105741381 B CN 105741381B CN 201610059153 A CN201610059153 A CN 201610059153A CN 105741381 B CN105741381 B CN 105741381B
- Authority
- CN
- China
- Prior art keywords
- parameter
- aircraft
- function
- equipment
- frequency
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- G—PHYSICS
- G07—CHECKING-DEVICES
- G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
- G07C5/00—Registering or indicating the working of vehicles
- G07C5/08—Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle or waiting time
- G07C5/0808—Diagnosing performance data
Abstract
The method that a kind of determining aircraft of the present invention flies ginseng recording parameters set, including aircraft system confirmation corresponding with standard Primary parameter, system operating parameters confirm, system function class parameter confirms, parameter merges and analysis five steps of calculating.This method can be according to winged ginseng functional localization, the parameter sets that procedural setting should acquire, solve previous parameter setting according to less, lack strong operability standardization flow difficulty, determine meet accident treatment, equipment monitors and flight training needed for parameter sets.Specifically can system combing and the composition and function that fly to join relevant, aircraft and its important system, provide basic fundamental support for accident investigation or other application, this work combination aircraft Top-layer Design Method synchronously completes；Parameter composition is determined in combination with the reliabilities such as FMEA and FTA, safety analysis work；Least sampling rate needed for can quantitatively being calculated according to flow.
Description
【Technical field】
Technical field belonging to the present invention is flight safety field.For determine military secret or civil aircraft in Top-layer Design Method or
During use when use demand, which change, to be carried out plus reequip, parameter sets that Flight Data Record System for Aircraft should record.It is suitable
For fixed-wing, helicopter and UAV system.
【Background technology】
Flight Data Record System for Aircraft (referred to as flying ginseng) is the equipment for automatically recording aircraft and its airborne equipment working condition.It
Can aboard electricity in the case of, it is continual that the system working condition of full machine is adopted in real time according to fixed sample rate
Collection and record, and it is stored in anti-ruin in logger.Winged ginseng is the important safety equipment of aircraft, and equipment, which flies ginseng, aboard to chase after
It traces back by 1958, is limited by technical merit, height, speed, course, time, overload, dialogue moment can only be recorded at that time
Equal key parameters, with the raising of acquisition, storage and data analysis capabilities, the data volume that can be recorded and handle rapidly increases.
Simultaneously as flight data is provided in addition to can assist in accident treatment, the scene before reduction accident generation with important references valence
It, can also be complete according to the airborne equipment information recorded in flight data to the working condition of equipment and device except the numerical value of value
Sex work is ensured at including auxiliary equipments such as troubleshooting, performance monitoring, performance detections, further, it is also possible to according to recording
Pilot to the service condition of aircraft and airborne equipment, complete pilot training's proficiency assessment, formulate specialized training plan, carry
The assisting in flying training such as high driving ability.Therefore either domestic or external, civil aviation or military secret train field,
FDR system has played increasingly important role in accident treatment, equipment performance monitoring and assisting in flying training etc..
Although the working service field in flight safety field, training field and aircraft has realized that the importance for flying ginseng
The immense value contained with these data, but still there is following three factor to restrict FDR system exploitation, upgrade job.First
It is that aged aircraft design is of the remote past, does not account for flying ginseng record demand at the beginning of design, therefore to the winged ginseng of this part of aircraft
The problem of being related to upgrading, how upgrade job, which determines, flies the problem that ginseng reference record set is most crucial.Second is that new machine is opened
When hair is taken a flight test, very more data are had recorded using winged ginseng record system, although these data are to assessing and verifying work
It is particularly significant, but so numerous parameters is not needed in routine use, and bring airborne equipment aspect parametric calibration, unload
The difficulty and data screening carry, safeguarded, the added burden checked, analyzed are unfavorable for flying ginseng using work, need again really
It is fixed to fly ginseng reference record set.Third how is determined to parameter acquisition frequency in parameter sets, because frequency is higher, on the one hand
The cost of harvester is high, design is complicated, reliability reduces, and on the other hand excessively high frequency requirement logger capacity is big, unloading
It is long to handle data time.But frequency is low to be difficult to dynamic process necessary to reflecting parameter, influences the actual use of data.
Although there is the winged ginseng recording parameters standard for fixed-wing, two class aircraft of helicopter at present, really for set of records ends
Set pattern has drawn basic data content, but during specific implement, due to the airborne equipment thousand poor ten thousand of each type aircraft
Not, technologically advanced degree is had nothing in common with each other, simple to determine that specific type is impossible by abstract standard.
For solve the problems, such as it is above restrict FDR system exploitation, three of upgrade job, it is winged The present invention gives how to determine
The method for joining recording parameters set and frequency acquisition, can be used for the determination work of the winged ginseng recording parameters set of institute's organic type aircraft
Make.
【Technical solution】
Goal of the invention：
The purpose of the present invention is fly ginseng recording parameters standard general requirements under, comprehensive utilization fault tree, failure mode with
The methods of effect analysis, safety analysis determine the winged ginseng reference record set of specific model, to meet flight data in accident
The needs that processing, Training valuation and equipment monitor.
Technical solution：
The present invention the course of work include aircraft system it is corresponding with standard Primary parameter confirmation, system operating parameters it is true
Recognize, system function class parameter confirms, parameter merges and analysis calculates five steps.
Step 1：Aircraft system is corresponding with standard Primary parameter to be confirmed
It is to fixed-wing and the unified formulation of helicopter two major classes aircraft to fly ginseng recording parameters standard, is specific at each
Type decline real parameter set needs to match the system required by standard with the system of the machine, should clearly give and analyze
System classification.
Fly specific parameter in ginseng recording parameters standard and be divided into 4 ranks, the first order must record, this is just meaned
Even if the equipment for not acquiring this parameter even if the type aircraft, it is also necessary to which the mode by installing sensor special additional is implemented.
These parameters include most basic height, speed, posture, overload, engine control and state, the manipulation of aircraft and rudder face, electricity
Pressure, fire alarm and Beijing time.The second level is the parameter that must be recorded if the aircraft has this equipment or sensor special.The
If three-level is to have sensor or equipment, it is proposed that record.The fourth stage is to suggest recording.
According to the requirement of parameter and standard, except the first outer grade, whether what other parameters record with larger flexibility,
It needs to provide a kind of method determination analyzed with operable, systematization and answers recording parameters set.
Therefore it is required according to standard, step 1 of the present invention is to determine first order record ginseng according to the working condition of airborne equipment
Whether number has covered, if not covering, the sensor special of addition is clearly required, to meet the requirement of standard.
It according to first order parameter attribute, is matched in the existing system of aircraft, according to the state measurement of each system
Ability is matched with parameter, is found the parameter that can not be implemented, is solved the problems, such as to propose demand as priority.
Step 2：System operating parameters confirm
The purpose for flying ginseng recording parameters standard is three important needs when meeting accident investigation：
There is the type of grade accident in 2.1 such clear aircraft.These types include：Into complex state, substantial deviation
Course line controllably contacts to earth, encounters the terrible weathers such as thunderstorm or wind shear, the part or all of loss of consciousness of pilot, important airborne sets
Standby failure, aircaft configuration damage.This work is used to determine that the classification that accident occurs to judge required foundation class parameter.
The working condition types of the 2.2 clear important airborne equipments of such aircraft, feature, work opportunity, system input and defeated
Go out relationship.This work be used to determine important equipment normally with the foundation class parameter needed for abnormal judgement.
The pattern classification for using and manipulating of 2.3 such clear aircraft, important airborne equipment process for using.This work is used
In determine pilot to aircraft and equipment process for using, opportunity, input quantity etc. judge needed for foundation class parameter.
Therefore, to meet these demands, it is necessary to the operation sequence flow conditions of major system of clear aircraft.
The purpose of this work is to understand the operate with method and pattern of big system, and realization operates with pilot
Situation is assessed.
According to the covered systematic order of standard, the flow that operates with of major system described successively, and determination can describe be
The parameter name of system operating quantity and operation order.
Step 3：System function class parameter confirms
It is flexibly the third level and fourth stage parameter with the parameter for being most difficult to hold that parameter, which determines work most, that is, suggests record
Parameter.The practicable of this work is the manipulation for embodying the present invention and systematic important step.
The method for solving the problems, such as this is the function situation and its failure mode and effect by major system of clear aircraft
Analysis, and the method for Bindery security analysis carries out the confirmation of final argument set.
The purpose of this work is to understand the functional composition situation of institute of big system, specifies the sub- work(of device level in system
Energy.
For each specific type, need to according to System Working Principle, form system all parts it is mutual
Dependence carries out complete consideration, and parameter acquisition set is determined according to component-level.
Aircraft system state parameter confirms that the purpose of work is to understand the composition situation of aircraft and its big system, between system
The input and output situation of crosslinking relationship and system.
According to systematic name cited in the parameter and standard of the affiliated type of aircraft, specific aircraft type is compareed to being contained
Convering system is judged item by item, selects the control that can describe each system to input, the parameter name of the state output of system.It is right
The crosslinking relationship between big system should give explicitly stated, including the type of Inter-System Information, flow direction and remaining backup feelings
Condition.
3.1 clear functions
According to the covered systematic order of standard, each function of major system is described successively, for each function, to be
Device related with the function is least unit in system, and the function of the device is described, and determination can representation function operation
The parameter name of situation.For the big system of software content in device, in addition to parameter needed for the function of determining device, it is also necessary to really
The intermediate state parameter of software reusage branch judgement can be described surely.
The disabler Harm of major system of 3.2 clear aircrafts
The purpose of this work is clearly to answer the weight of recording parameters according to the hazard rating after big system function failure,
Determine parameter sets.
According to the covered systematic order of standard, harm when each disabler of major system is described successively, and to danger
Evil be classified, according to the severity of harm with：It is disaster, dangerous or serious, heavier, lighter, without influence
It is divided into A-E totally 5 classes.
" disaster " refers to the failure state that cannot continue safe flight and landing；
" dangerous/serious " refers to the performance for reducing aircraft and crew overcomes the ability of unfavorable operation state, unfavorable
Degree include substantially reducing margin of safety or ability that function can be performed or physical fatigue (or other painful situations)
Or high load capacity prevents flight unit from accurately or completely completing their task, or to the adverse effect of passenger to include to few
Number passengers are serious or potential mortal injury；
" heavier " refer to the performance that may be decreased aircraft and crew overcome unfavorable operation state ability failure
State.Unfavorable degree includes：Larger reduction safe clearance or Functional Capability, the workload for significantly increasing crew or
Weaken the state of crew's working efficiency, or cause that passenger's is uncomfortable, including possible certain injury；
" lighter ", which refers to, will not seriously reduce aircraft safety and crew's ability interior energy completes the mistake of task very well
Effect state.Including：Safe clearance or Functional Capability are slightly reduced, slightly increases the workload of unit, more such as airline operation plan
Change or certain inconveniences of passenger；
" no influence " refers to the working performance for not influencing aircraft or does not increase the failure state of unit workload.
Above-mentioned crew refers in the common horizontal personnel that can be competent at aircraft handling and equipment uses.
The hazard rating of each disabler of major system is described in the function of A, B, C three-level, according to the function with
Device related with the function is least unit in system, is retouched to the failure of system corresponding function to the disabler of the device
It states, and determination can describe the parameter name of the disabler situation.
Step 4：Determine parameter sets
4.1 merge parameter
Step 1 is formed parameter to be known as to remember class parameter, step 2, which is formed parameter, to be known as operating class parameter, by step 3
Parameter is known as critical function class parameter.Merge parameter to refer to that must remember that class, operation class and critical function class parameter seek union, be formed
Aircraft safety parameter sets.
4.2 screening parameters
The parameter of C grades is endangered for being related to disabler, if not direct output information or output information in system design
Difficulty, reliability is high and can not be acquired by other parameters side light.
It summarizes known to above-mentioned work：
Standard formulation works to obtain：The system scope being considered as per type aircraft undetermined parameter set.
System composition, operating process and function describe to obtain：It system composition situation and aircraft per type aircraft and airborne sets
Standby manipulation service condition, these information describe the key of system mode for determining aircraft and the input/output relation of equipment
Parameter name specifies the workflow and use pattern and various alarms and instruction situation of aircraft and equipment, and can be correct
Distinguish and distinguish the parameter name of above- mentioned information.
Disabler and disabler influence description and obtain：It is influenced according to the disabler of every type aircraft statistics and after failing
Analysis determines and generates parameter name needed for heavier, serious and calamity source aircraft function description, the shadow after disabler
Ring parameter name needed for description.
Step 5：Analysis calculates
When analysis calculating is referred to for parameter acquisition is carried out by investigation fixed wing aircraft, helicopter and UAV system, determine
The process of sample rate.To dynamic when this work is for determining that accident investigation, equipment performance detection are assessed with monitoring and flight training
The minimum requirements of state.
Determine that the constraint of sample rate includes three, first is able to meet minimum reduction aircraft dynamic and equipment work change
The transient requirements of change；Second is that can capture pilot between the of short duration input of equipment and the minimum time of the of short duration output of equipment
Every requiring；Third is met needed for the record byte-aligned for flying ginseng collector.
It is constrained according to above three, the sample rate setting up procedure of design parameter is divided into three steps：
The dimensionality reduction model of 5.1 dynamic models used using aircraft system when the design phase carrying out theoretical calculation, or
Wind tunnel test, iron bird platform, the inputoutput data collection that installed high-frequency parameter harvester is acquired when the stage of taking a flight test
Carry out System Discrimination.
Since FDR system is not involved in the control of system, approximation obtains its current intelligence changing rule and can meet to adopt
Collection requires, and weighs the frequency that 3db is down on the right side of the upper frequency limit selection Amplitude Frequency Characteristic curve of dynamic change.System is according to 2
The mode of level system carries out System Discrimination, and it is that 2 levels are united with the input and output situation of simulation system that high order system, which needs depression of order,.
2 levels system the differential equation be：
Wherein x is output, and u is input, and a, b and c are coefficient undetermined.Its transmission function is：
The natural frequency ω of required system can be obtained using System Discrimination tooln, dampingratioζ；Obtain the two numerical value
Afterwards, using its amplitude versus frequency characte calculation formula, the frequency when amplitude versus frequency characte declines the position of 3dB is adopted highest frequency for system
ω s theoretically can correctly restore measured signal according to Shannon's sampling theorem when sample frequency is more than 2 ω s.
After the completion of 5.1st step, the sampling rate score needed for system state change can be obtained.
5.2 are directed to the input of system, i.e., pilot is to the input quantity of aircraft or airborne equipment, because the input of system is driven
The inherent damping limitation of bar, throttle lever, minimum sampling interval can meet acquisition between 0.1-0.2 seconds and require.
5.3 record the restraint condition of byte-aligned according to collector, and the general numerical value that sets is 1,4,8,12,16 etc., if examining
The difference of worry AD conversion precision, also there is the case where being set as 1,5,10 equal numerical value.
After being worked by above-mentioned 5.1 to 5.3 step, you can determine the setting to the sample rate of institute's acquisition parameter, i.e., it is logical first
It crosses discrimination method acquisition frequency values and is scaled the sampling interval, and required according to the sampling interval of input signal, remembered in conjunction with collector
The specific discrete situation for recording byte-aligned, selects most suitable sample rate.
Beneficial effects of the present invention：
Advantage of the invention is that can be according to winged ginseng functional localization, the parameter sets that procedural setting should acquire,
Solve previous parameter setting according to less, lack strong operability standardization flow difficulty, according to aircraft practical operation situation, work(
The materialization process between contents, with standard parameter set such as energy and representation function failure, determines and meets accident treatment, dress
Parameter sets needed for standby monitoring and flight training.Specifically there are following three advantages：
Advantage 1：Can system combing and the composition and function that fly to join relevant, aircraft and its important system, be accident tune
It looks into or other application provides basic fundamental and supports, this work combination aircraft Top-layer Design Method synchronously completes.
Advantage 2：Parameter composition is determined in combination with the reliabilities such as FMEA and FTA, safety analysis work.
Advantage 3：Least sampling rate needed for can quantitatively being calculated according to flow.
【Specific implementation mode】
Specific embodiment one：Illustrate by taking the atmosphere data information of certain type fixed wing aircraft as an example.
Step 1 is required according to parameter and standard, specifies the parameter that the atmosphere data information of aircraft must be remembered；These parameters include
Pressure altitude, indicator air speed, total Air Temperature.
Step 2 understands the operation of air data system.The atmosphere data said system of aircraft is atmospheric engine system, control
System input is that air data system binds field press operation.The parameter of description includes bookbinding field pressure.Understand the behaviour of air data system
Make, operation order is：Opening system electric switch, self-test after system electrification carry out scene pressure bookbinding after self-test, make its height
Degree is shown as relative altitude, starts to work normally, and after hours, closes power supply, system stalls.Operation order is described
Parameter includes：Relative altitude, bookbinding field pressure；
Step 3 understands the state variable of air data system.The atmosphere data said system of aircraft is atmospheric engine system.
Its state variable includes the true air speed, indicator air speed, horse being calculated according to information such as total head, static pressure, total temperature and local angle of attack
Conspicuous number, pressure altitude, the true angle of attack.The parameter of description includes true air speed, indicator air speed, Mach number, pressure altitude, the true angle of attack, dress
Order field pressure.
The crosslinking relationship of air data system and other systems is：There is provided static pressure and dynamic pressure two simulation letters to flight control system
Number conduct is spare；Two switching signals are provided to inlet control system.When Mach number is more than 1.2, intake valve deposit is controlled
Rule withdraws inclined plate when height is less than 6.3km；Four switching signals are provided to engine, when height is more than 2km, Mach number
When more than 0.65, notice engine should be noted that anti-asthma, and anti-icing system relay is disconnected when Mach number is more than 1.15, when instruction is empty
When speed is more than 220km/h, engine receives spout when controlling aircraft landing；Switching signal is provided to probe heating control box, works as height
When degree is more than 8km, the heating of total temperature probe is connected；The reference signal that 10V is provided is ordered to field press fitting, is ordered for field press fitting；To
Avionics system provides continuous number amount and air data computer working state signal is：Pressure altitude, relative altitude, Mach
Number, Static Air Temperature, total Air Temperature, calibrated airspeed, true air speed, lifting speed, pressure ratio, the true angle of attack, static pressure, atmospheric density ratio,
It shows, control, calculate, pass for aobvious control, inertial navigation, task engine, winged control, communication and navigation identifying system, number biography, Health Monitor Computer
It is defeated.
Understand the function of air data system and each device subfunction.The function of air data system is to provide full machine and uses
Atmospheric parameter, wherein height, speed, lifting speed, angle of attack information be navigation and automatic Pilot required argument, pressure altitude,
Mach number and indicator air speed are that engine system adjusts necessary parameter.Its composition includes four parts, first, pitot-static pressure pick-up, packet
It includes 4 to back up again, function is to provide the information such as required air static pressure, total head and the angle of attack for air data computer, second is that air
Data calculate, and function is by atmospheric informations such as atmospheric information reduced height, speed, third, to the heating portion of pitot-static pressure pick-up
Part prevents pitot-static pressure pick-up icing failure, fourth, attachment means is pressed in field, provides airdrome scene air pressure for atmospheric engine, makes air pressure height
Degree instruction is correct.According to system and device function, parameter includes necessary to representation function：Pitot-static pressure pick-up part is：It is defeated
Enter dynamic pressure, total head, total temperature and local angle of attack's numerical value；Atmosphere data calculating section is：Pressure altitude, indicator air speed, true air speed, horse
Conspicuous number, lifting speed, the true angle of attack, the atmospheric density when required on-off model of miscellaneous equipment.In addition, description warming member
Working properly or not also need warming member fault-signal.
Understand air data system disabler and its hazard rating.The information such as the height velocity that air data system provides
It is one of most important aircraft status information, disabler is A grades, i.e. disaster grade；Wherein, single pitot-static pressure pick-up loses
Effect, has no effect on system worked well, is E grades, and whole pick-up failures are A grades, and air data computer failure is B grades, is added
Reviewing knowledge already acquired barrier is C grades, and bookbinding field depressor failure is C grades.Therefore according to above-mentioned disabler and its hazard rating analysis it is found that the type
The atmosphere data that fixed wing aircraft should acquire includes whole pick-up failures；The pressure altitude of air data computer output refers to
Show air speed, true air speed, the true angle of attack, Mach number, lifting speed, pick-up whole failure, warming member failure, bookbinding field pressure.
Step 4 merges parameter.After state class parameter, operation class and function class are merged, atmosphere data system is obtained
System answers acquisition parameter title.State class includes：Pressure altitude, indicator air speed, true air speed, Mach number, lifting speed, the true angle of attack,
Total Air Temperature, bookbinding field pressure；Operating class includes：Pressure altitude, bookbinding field pressure；Function class includes：Pressure altitude, indicator air speed,
True air speed, the true angle of attack, Mach number, lifting speed, whole pick-up failure, air data computer failure, warming member failure,
Bind field pressure.The recording parameters are answered to be after merging parameter：Pressure altitude, bookbinding field pressure；Function class includes：Pressure altitude, instruction are empty
Speed, true air speed, the true angle of attack, Mach number, lifting speed, total Air Temperature, whole pick-up failure, air data computer failure,
Warming member failure, bookbinding field pressure.
Screening parameter.All C grades or more parameter can acquire, therefore after screening parameter, do not change the parameter merged after arranging
Set.
Step 5 calculates sample rate.When being three-level flight quality under most harsh conditions, Short-period oscillation and long week
The bandwidth upper limit of phase oscillation is respectively 5Hz and 2Hz, since the true angle of attack reflects that the Short-period oscillation of aircraft, sample frequency are
10Hz, the aircraft long periodic oscillation of the reflections such as pressure altitude, indicator air speed, true air speed, Mach number, lifting speed, it is contemplated that deposit
The requirement of reservoir byte-aligned, sample frequency are set as 5Hz.It is not frequent adjustment equipment to bind field pressure, and sample frequency is set as most
Low value, that is, 1Hz.Whole pick-up failures, air data computer failure, warming member failure are not frequent variable quantities, sampling frequency
Rate is set as minimum 1Hz.
Specific embodiment two：Illustrate by taking the atmosphere data information of another type fixed wing aircraft as an example.
Step 1 is required according to parameter and standard, the parameter that the atmosphere data information of aircraft must record；These parameters include
Pressure altitude, indicator air speed, total Air Temperature.Inspection system system related with air, without the sensing for directly exporting total Air Temperature
Device, it is therefore desirable to be equipped with sensor special, be acquired to export total Air Temperature for flying ginseng.
Step 2 understands the control input of air data system.The atmosphere data said system of aircraft is pitot-static pressure system,
It is that pitot-static pressure system binds field press operation that it, which controls input,.The parameter of description includes bookbinding field pressure.Understand the behaviour of pitot-static pressure system
Make, operation order is：Opening system electric switch, self-test after system electrification carry out scene pressure bookbinding after self-test, make its height
Degree is shown as relative altitude, and flight front opening pitot heating switch starts to work normally, after hours, closes power supply, be
System is stopped.Description operation order parameter include：Relative altitude, bookbinding field pressure, pitot heating switch；
Step 3 understands the state variable of air data system.The atmosphere data said system of aircraft is pitot-static pressure system,
Its state variable includes the indicator air speed that total head, static pressure information are calculated, pressure altitude according to bookbinding field pressure.The ginseng of description
Number includes indicator air speed, pressure altitude, bookbinding field pressure.
Pitot-static pressure system is not crosslinked relationship with the other systems of aircraft.
Understand the function of pitot-static pressure system and each device subfunction.The function of pitot-static pressure system is to provide flight for pilot
The accurate pressure altitude parameter of middle needs.Its composition includes two parts, first, pitot-static pressure pick-up, function is for pitot-static pressure system
Computer provides required air static pressure, total head information, second is that atmosphere data calculates, function is high by atmospheric information conversion
Degree, velocity information prevent pitot-static pressure pick-up icing failure third, to the warming member of pitot-static pressure pick-up.According to system and
Device function, parameter necessary to representation function include：Pitot-static pressure pick-up part is：Input dynamic pressure, total head numerical value, pick-up
Icing failure；Atmosphere data calculating section is：Pressure altitude, indicator air speed signal.In addition, description warming member it is working properly with
It is no also to need warming member fault-signal.
Understand pitot-static pressure system function failure and its hazard rating.The pressure altitude and indicator air speed that pitot-static pressure system provides
Information is one of important aircraft status information, provides height and velocity information for pilot, is not involved in the control of the other systems of aircraft
Work processed, disabler are B grades, i.e., serious grade；Wherein, pitot-static pressure pick-up failure effect pitot-static pressure system and backup machinery
Formula instrument works normally, and is B grades, and because there is the mechanical instrument of backup, it is C grades that atmosphere data, which calculates failure, and heating failure is C grades,
It is C grades that field press fitting, which is ordered,.Therefore according to above-mentioned disabler and its hazard rating analysis it is found that the type fixed wing aircraft should acquire
Atmosphere data includes pick-up failure；Atmosphere data calculate output pressure altitude, indicator air speed, pitot-static pressure pick-up failure,
Warming member failure, bookbinding field pressure.
Step 4 merges parameter.After state class parameter, operation class and function class are merged, pitot-static pressure system is obtained
Answer acquisition parameter title.State class includes：Pressure altitude, indicator air speed, bookbinding field pressure；Operating class includes：Pressure altitude, bookbinding
Field pressure, pitot heating switch are opened；Function class includes：Pressure altitude, indicator air speed, bookbinding field pressure, pick-up failure, heating
Unit failure.The recording parameters are answered to be after merging parameter：Pressure altitude, indicator air speed, pick-up failure, warming member failure, dress
Order field pressure, pitot heating switch is opened；
Screening parameter.Pick-up failure, warming member failure and bookbinding field press three parameters not flying in C grades of parameters
The signal individually exported on machine, since pick-up and warming member are simple and mechanical structure and simple electric heating warming mechanism, reliably
Property it is high, fault mode only has ice blockage, can be by pilot's visual finding after blocking, and can be heated and be opened by pitot
Pass judges whether anti-icing system devotes oneself to work, bookbinding field pressure can according to aircraft in ground roll-out when height it is neighbouring and indirect for 0
Judge whether correctly to bind pressure altitude, therefore after screening parameter, answer recording parameters collection to be combined into pressure altitude, indicator air speed, air speed
Pipe heating switch is opened.
Step 5 calculates sample rate.When according to being three-level flight quality under most harsh conditions, long periodic oscillation
The bandwidth upper limit is 2Hz, the aircraft long periodic oscillation of the reflections such as height, speed, it is contemplated that memory byte alignment requirements, sampling frequency
Rate is set as 4Hz.Pitot heating switch is not the equipment frequently switched on, therefore its sample frequency is determined as low-limit frequency, i.e.,
1Hz。
Claims (7)
1. a kind of method that determining aircraft flies ginseng recording parameters set, it is characterised in that：Join including aircraft system and standard level-one
Several corresponding to confirms, system operating parameters confirm, system function class parameter confirms, determines parameter sets and five steps of analysis calculating
Suddenly；
Step 1：Aircraft system is corresponding with standard Primary parameter to be confirmed
It is to fixed-wing and the unified formulation of helicopter two major classes aircraft, in each specific model to fly ginseng recording parameters standard
Decline real parameter set, needs to match the system required by standard with the system of the machine, and should clearly give analysis is
System classification；
Fly specific parameter in ginseng recording parameters standard and be divided into 4 ranks, the first order must record, even if aircraft does not have
The equipment for acquiring this parameter, it is also necessary to which the mode by installing sensor special additional is implemented；These parameters include height, speed,
Posture, overload, engine control and state, the manipulation of aircraft and rudder face, voltage, fire alarm and Beijing time；The second level be if
The aircraft has the parameter that this equipment or sensor special must then record；If the third level is to have sensor or equipment, it is proposed that note
Record；The fourth stage is to suggest recording；
Step 2：System operating parameters confirm
The purpose for flying ginseng recording parameters standard is three important needs when meeting accident investigation：
There is the type of grade accident in 2.1 such clear aircraft, this work is used to determine needed for the classification judgement that accident occurs
Foundation class parameter；
Working condition type, feature, work opportunity, the system of the 2.2 clear important airborne equipments of such aircraft output and input pass
System；This work be used to determine important equipment normally with the foundation class parameter needed for abnormal judgement；
The pattern classification for using and manipulating of 2.3 such clear aircraft, important airborne equipment process for using；This work is used for
Determine pilot to aircraft and equipment process for using, work opportunity, input quantity judgement needed for foundation class parameter；
Step 3：System function class parameter confirms
By the function situation and its failure related of major system of clear aircraft, and Bindery security analysis
Method carries out the confirmation of final argument set,
According to systematic name cited in the parameter and standard of the affiliated type of aircraft, compare specific aircraft type is to covering
System is judged item by item, selects the control that can describe each system to input, the parameter name of the state output of system；For big
Crosslinking relationship between system, it should be understood that the type of Inter-System Information, flow direction and remaining backup instances；
Step 4：Determine parameter sets
4.1 merge parameter
Step 1 is formed parameter to be known as to remember class parameter, step 2, which is formed parameter, to be known as operating class parameter, by the parameter of step 3
Referred to as critical function class parameter；Merge parameter to refer to that must remember that class, operation class and critical function class parameter seek union, forms aircraft
Security parameters set；
4.2 screening parameters
The parameter of C grades is endangered for being related to disabler, if not direct output information or output information are difficult in system design,
Its reliability is high and can not acquire；
Step 5：Analysis calculates
When analysis calculating is referred to for parameter acquisition is carried out by investigation fixed wing aircraft, helicopter and UAV system, sampling is determined
The process of rate；To dynamic when this work is for determining that accident investigation, equipment performance detection are assessed with monitoring and flight training
Minimum requirements.
2. the method that a kind of determining aircraft according to claim 1 flies ginseng recording parameters set, it is characterised in that：The step
Rapid 1 is to determine whether first order recording parameters have covered according to the working condition of airborne equipment, if not covering, clearly requires and adds
The sensor special added, to meet the requirement of standard.
3. the method that a kind of determining aircraft according to claim 1 or 2 flies ginseng recording parameters set, it is characterised in that：Root
It according to first order parameter attribute, is matched in the existing system of aircraft, according to the state measurement ability and parameter of each system
It is matched, finds the parameter that can not be implemented, solve the problems, such as to propose demand as priority.
4. the method that a kind of determining aircraft according to claim 1 flies ginseng recording parameters set, it is characterised in that：Step
The type of 2.1 middle grade accidents includes：Into complex state, substantial deviation course line, controllably contacts to earth, encounters thunderstorm or wind shear
Terrible weather, the part or all of loss of consciousness of pilot, important AEF airborne equipment failure, aircaft configuration damage.
5. the method that a kind of determining aircraft according to claim 1 flies ginseng recording parameters set, it is characterised in that：The step
Further include following steps in rapid 3：
3.1 clear functions
According to the covered systematic order of standard, each function of major system is described successively, for each function, in system
Device related with the function is least unit, the function of the device is described, and determination can representation function operating condition
Parameter name；For the big system of software content in device, in addition to parameter needed for the function of determining device, it is also necessary to which determination can
The intermediate state parameter that software reusage branch judges is described；
The disabler Harm of major system of 3.2 clear aircrafts
According to the covered systematic order of standard, harm when each disabler of major system described successively, and to endanger into
Row classification, according to the severity of harm with：Disaster, dangerous or serious, heavier, lighter, being divided into without influence
A-E totally 5 classes；
" disaster " refers to the failure state that cannot continue safe flight and landing；
" dangerous/serious " refers to the performance for reducing aircraft and crew overcomes the ability of unfavorable operation state, unfavorable journey
Degree includes substantially reducing margin of safety or ability that function can be performed or physical fatigue or high load capacity make flight unit not
It can accurately or completely complete their task, or to a few passengers are serious or potential mortal injury；
" heavier " refer to reduce aircraft performance and crew overcome unfavorable operation state ability failure state；It is unfavorable
Degree includes：Larger reduction safe clearance or Functional Capability significantly increase the workload of crew or weaken unit
The state of person works' efficiency, or cause that passenger's is uncomfortable；
" lighter ", which refers to, will not seriously reduce aircraft safety and crew's ability interior energy completes the failure shape of task very well
State；Including：Safe clearance or Functional Capability are slightly reduced, the workload of unit is slightly increased,
" no influence " refers to the working performance for not influencing aircraft or does not increase the failure state of unit workload；
Above-mentioned crew refers in the common horizontal personnel that can be competent at aircraft handling and equipment uses；
The hazard rating of each disabler of major system is described in the function of A, B, C three-level, according to the function with system
In device related with the function be least unit, the failure of system corresponding function is described in the disabler of the device,
And determination can describe the parameter name of the disabler situation.
6. the method that a kind of determining aircraft according to claim 1 flies ginseng recording parameters set, it is characterised in that：Step 5
The constraint of middle determining sample rate includes three, and first is able to meet the wink of minimum reduction aircraft dynamic and equipment work variation
State requirement；Second is that can capture pilot to want the minimum interval of the of short duration input of equipment and the of short duration output of equipment
It asks；Third is met needed for the record byte-aligned for flying ginseng collector.
7. the method that a kind of determining aircraft according to claim 6 flies ginseng recording parameters set, it is characterised in that：According to step
Determine that the constraint of sample rate, the sample rate setting up procedure of design parameter are divided into three steps in rapid 5：
The dimensionality reduction model of 5.1 dynamic models used using aircraft system when the design phase carrying out theoretical calculation, or in wind-tunnel
The inputoutput data collection system that experiment, iron bird platform, lower the installed high-frequency parameter harvester of phase scenario of taking a flight test are acquired
System identification；
Since FDR system is not involved in the control of system, approximation obtains its current intelligence changing rule and meets acquisition wanting
It asks, weighs the frequency for being down to 3db on the right side of the upper frequency limit selection Amplitude Frequency Characteristic curve of dynamic change；System is according to 2 levels
The mode of system carries out System Discrimination, and it is that 2 levels are united with the input and output situation of simulation system that high order system, which needs depression of order,；
2 levels system the differential equation be：
Wherein x is output, and u is input, and a, b and c are coefficient undetermined；Its transmission function is：
The natural frequency ω of required system is obtained using System Discrimination tooln, dampingratioζ；After obtaining the two numerical value, it is utilized
Amplitude versus frequency characte calculation formula, the frequency when amplitude versus frequency characte declines the position of 3dB are adopted highest frequency ω s for system, according to
Shannon's sampling theorem can correctly restore measured signal when sample frequency is more than 2 ω s；
After the completion of 5.1st step, the sampling rate score needed for system state change is obtained；
5.2 are directed to the input of system, i.e. pilot to the input quantity of aircraft or airborne equipment, because system input by control stick,
The inherent damping of throttle lever limits, and minimum sampling interval meets acquisition between 0.1-0.2 seconds and requires；
5.3 record the restraint condition of byte-aligned according to collector, and it is 1,4,8,12,16 set numerical value, if consideration AD conversion is smart
The difference of degree also has the case where numerical value for being set as 1,5,10；
After being worked by above-mentioned 5.1 to 5.3 step, that is, determines to the setting of the sample rate of institute's acquisition parameter, i.e., pass through identification first
Method obtains frequency values and is scaled the sampling interval, and is required according to the sampling interval of input signal, and byte is recorded in conjunction with collector
The specific discrete situation of alignment, selects suitable sample rate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610059153.2A CN105741381B (en) | 2016-01-28 | 2016-01-28 | A kind of method that determining aircraft flies ginseng recording parameters set |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610059153.2A CN105741381B (en) | 2016-01-28 | 2016-01-28 | A kind of method that determining aircraft flies ginseng recording parameters set |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105741381A CN105741381A (en) | 2016-07-06 |
| CN105741381B true CN105741381B (en) | 2018-08-17 |
Family
ID=56246817
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610059153.2A Active CN105741381B (en) | 2016-01-28 | 2016-01-28 | A kind of method that determining aircraft flies ginseng recording parameters set |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105741381B (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106114876B (en) * | 2016-08-25 | 2019-04-02 | 中国商用飞机有限责任公司 | The parameter identification method of Aircraft Flight Test data |
| CN107782558A (en) * | 2016-08-30 | 2018-03-09 | 中国飞行试验研究院 | One kind flies the quick interpretation method of ginseng |
| CN106789499A (en) * | 2016-12-12 | 2017-05-31 | 石家庄飞机工业有限责任公司 | A kind of integrated avionic system for light-small aircraft |
| CN108100301B (en) * | 2017-12-03 | 2021-02-26 | 中国直升机设计研究所 | Test flight data processing method for objective test of helicopter simulator |
| US10815009B2 (en) * | 2017-12-15 | 2020-10-27 | The Boeing Company | Method for manufacturing aircraft components optimized for flight and system and method for their design |
| CN108629866B (en) * | 2018-05-07 | 2023-03-10 | 上海海鹰机械厂 | Trial repair method for certain type of flight parameter recording system |
| CN113377033B (en) | 2019-01-15 | 2024-03-22 | 北京百度网讯科技有限公司 | Data acquisition method, device, equipment and computer readable storage medium |
| CN110490445A (en) * | 2019-08-13 | 2019-11-22 | 成都飞机工业（集团）有限责任公司 | A kind of military secret is taken a flight test complete period integrated supportability dynamic evaluation model |
| CN112131182A (en) * | 2020-08-14 | 2020-12-25 | 陕西千山航空电子有限责任公司 | Rapid alignment processing method for packet mining type flight parameter data |
| CN112215982A (en) * | 2020-09-28 | 2021-01-12 | 广州航新航空科技股份有限公司 | Helicopter data acquisition method, system, device and storage medium |
| CN112734346B (en) * | 2021-04-02 | 2021-09-28 | 北京三快在线科技有限公司 | Method, device and equipment for determining lane coverage and readable storage medium |
| CN115099693B (en) * | 2022-07-21 | 2023-10-13 | 宁波迈泰克磁材科技有限公司 | Production control method and system for sintered NdFeB magnetic steel material |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6735505B2 (en) * | 2002-01-17 | 2004-05-11 | Cubic Defense Systems, Inc. | Aircraft flight and voice data recorder system and method |
| CN101634612B (en) * | 2009-08-21 | 2011-01-05 | 北京航空航天大学 | Method for determining long-endurance flight parameter of unmanned plane |
| FR2956735B1 (en) * | 2010-02-24 | 2012-03-30 | Airbus Operations Sas | ON-BOARD FLIGHT STRATEGY EVALUATION SYSTEM ABOVE AN AIRCRAFT |
| CN101944142A (en) * | 2010-08-24 | 2011-01-12 | 中国人民解放军63796部队 | Method for determining optimal fusion of multi-source information of spacecraft flight parameters |
| CN102915036B (en) * | 2012-07-26 | 2014-12-03 | 北京航空航天大学 | Method for suppressing limit cycle of inclination angle control system of aircraft with parameter uncertainty |
-
2016
- 2016-01-28 CN CN201610059153.2A patent/CN105741381B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN105741381A (en) | 2016-07-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105741381B (en) | A kind of method that determining aircraft flies ginseng recording parameters set | |
| CN107168205B (en) | A kind of online health monitoring data collection and analysis method of civil aircraft air-conditioning system | |
| US7031812B1 (en) | System and method for monitoring aircraft engine health and determining engine power available, and applications thereof | |
| US9663243B2 (en) | Power safety instrument system | |
| CN108045596A (en) | The flying quality inspection and detection system and method for a kind of fixed-wing unmanned plane | |
| CN106164793B (en) | The method of the failure in air-conditioning package for diagnosing aircraft | |
| US10325504B2 (en) | System and method for optimization of aircraft fuel economy in real-time | |
| CN104471502A (en) | Safe takeoff monitoring system | |
| US5608627A (en) | Device for supervising the propulsion system of an aircraft | |
| CN104515683A (en) | Engine power margin and heat margin examining method for two-engine helicopter | |
| CN109470712A (en) | A kind of wind electricity blade detection system | |
| CN111680391A (en) | Accident model generation method, device and equipment for man-machine loop coupling system | |
| BR102019026202A2 (en) | METHOD AND SYSTEM FOR AN AUTOMATED AIRCRAFT LANDING ANALYSIS | |
| Brotherton et al. | A testbed for data fusion for helicopter diagnostics and prognostics | |
| Germanetti | The 43rd Alexander A. Nikolsky Honorary Lecture:“Fifty Years of Innovation, Reducing Pilot Workload, and Enhancing Safety by Helping Pilots Manage Helicopter Performance” | |
| Grabill et al. | Helicopter structural life modeling: flight regime and gross weight estimation | |
| Kaye | Dynamics health and usage monitoring system-programme update | |
| Berry et al. | Automatic regime recognition using neural networks | |
| Larin et al. | Decision-making Algorithm in Case of Failure of the Electric Motor of a Multi-rotor Unmanned Aerial Vehicle. | |
| Ray et al. | Real-time in-flight engine performance and health monitoring techniques for flight research application | |
| Quan et al. | Health Evaluation and Failsafe | |
| Yan et al. | The investigation and demand analysis of HUMS on the civil helicopter | |
| CN115783278A (en) | Pilot operation monitoring method based on threshold-feature-result matching | |
| Allison | Applicability of NASA (ARC) two-segment approach procedures to Boeing Aircraft | |
| Hillman et al. | Future flight deck design |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |