CN103984337B - Method for rapid testing of correctness of onboard control law - Google Patents
Method for rapid testing of correctness of onboard control law Download PDFInfo
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- CN103984337B CN103984337B CN201410154221.4A CN201410154221A CN103984337B CN 103984337 B CN103984337 B CN 103984337B CN 201410154221 A CN201410154221 A CN 201410154221A CN 103984337 B CN103984337 B CN 103984337B
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Abstract
The invention belongs to the technical field of aviation flight control and particularly relates to a method for rapid testing of the correctness of an onboard control law. The method is characterized by comprising the following steps that firstly, data of a flight parameter recorder, data of a flight control recording device and data, capable of being used for verifying the correctness of the control law of a flight control system, of telemeasuring data are selected; secondly, time scale unification and data point unification are conducted on the obtained data, and the accuracy of the recorded data are verified through comparison; thirdly, simulating calculation is conducted on the recorded data according to a control law rule, a simulating result is compared with actual recorded data, and the operation accuracy of the control law is verified. According to the method for rapid testing of the correctness of the onboard control law, data stored by different aircraft recording devices are used reasonably, the operation condition of the control law in a flight control computer can be calculated and analyzed rapidly, a traditional method that a flight control device needs to be dismantled for laboratory testing is replaced, and the working efficiency of troubleshooting tasks in an external field is improved.
Description
Technical field
The invention belongs to aviation flight control technology field, and in particular to quickly test to a kind of airborne control law correctness
Method.
Background technology
Flight control system is the important component part of aircraft, and flight control system control law need to ensure in whole flight envelope
Ensure that aircraft has good flight quality, therefore the correct operation of control law is the key for ensureing flight safety.
If going wrong in the stage of taking a flight test of aircraft, the working order for checking each system, wherein flight control system control are needed
The accuracy testing of system rule is firstly the need of carrying out.Traditional method of testing be flight control computer is dismantled from aircraft under
Come, control law correctness test is carried out on iron bird test-bed, testing procedure includes：Control law open-loop branch is tested and system
Closed loop test.And the purpose of iron bird test is the function and performance of abundant checking system in more real integrated environment,
The reliability of soft and hardware.The method test period is long, and and underuses the existing test flight data of aircraft.
The content of the invention
The purpose of the present invention is：Present invention is generally directed to fly-by-wire flight control system aircraft, there is provided a kind of airborne control law
The method for rapidly testing of correctness.
The technical scheme is that：
1. a kind of method for rapidly testing of airborne control law correctness, it is characterised in that as follows including step：
First, record airplane data：The each system of aircraft can be according to its demand history correlation test or test flight data, including winged
Ginseng recorder data, winged control recording equipment data, telemetry.Due to each recording equipment it is relatively independent, therefore, its record lattice
Formula, recording frequency（Record number per second）, precision have difference.This step is to choose the data of each recording equipment memory storage, bright
Data sense representated by true difference filenames.Needing the data of record includes：The angle of attack, in length and breadth yaw angle, course angular speed, method
To and lateral overload, the angle of pitch, roll angle, yaw angle, dynamic and static pressure, pilot's vertical pole, cross bar and pedal input, throttle lever position
Put, oil mass, engine speed, undercarriage control switch, the command information of sensor failure signals and each rudder face of aircraft.
Second, process airplane data：To ensure flight control system control law checking accuracy, need to ensure record data first
The normal operation of accuracy, i.e. recording equipment.Therefore each recording equipment the data obtained need to be processed, including data name
Unified, data markers unification and missing data is claimed to supplement.Data name unification is the number for renaming distinct device record data
According to variable name in order to inquiring about and manage.
Because distinct device can produce cumulative errors in recording process, particularly with the flight test subject that the time is longer,
Therefore markers unification need to be carried out to interpretation of records data.Using method is with undercarriage folding and unfolding switch as mark, to fly
The control recording equipment time is foundation, and the time of record data is unified, and afterwards data is united using the method for linear interpolation
One is 30 measuring points per second.After processing more than, the same data message of different recording equipments is taken, with the time as transverse axis, number
Curve is drawn according to for the longitudinal axis, compares to confirm the correctness of record data.
3rd, simulation analysis control law data：The input of this step obtains record data for upper two step, by data with fly
Machine control law is combined and carries out time-domain calculation, obtains the rudder face command information of each data point, will be calculated gained information and is remembered with aircraft
The command information of record is depicted as the curve with the time as axle and compares, if curve is consistent, illustrate the inspection section control law with
Design is consistent.
It is an advantage of the invention that：
The inventive method, using aircraft difference recording equipment data storage, can quickly be resolved and analyze winged by reasonably
The operation conditions of control law, instead of and need to dismantle in the past flying control equipment to carry out the tradition side of laboratory's test in control computer
Method, improves the operating efficiency of outfield troubleshooting task.
Specific embodiment
Below by actual test process, the present invention is described in further detail：
First, record airplane data：Record data source includes：Aerial seeding vegetation, winged control recording equipment and tele rcording
Equipment.After data sense clearly representated by difference filename, the data of each recording equipment memory storage are chosen.Need the number of record
According to including：The angle of attack, yaw angle, in length and breadth course angular speed, normal direction and lateral overload, the angle of pitch, roll angle, yaw angle, dynamic and static pressure,
The input of pilot's vertical pole, cross bar and pedal, throttle lever position, oil mass, engine speed, undercarriage control switch, sensor event
Barrier signal, command information of each rudder face of aircraft etc..
Such as certain flying quality, angle of attack data record is as follows：
| Flight data | 1.396 | - | 1.375 | - | 1.393 | - | 1.366 | - | 1.402 |
| Flight control data | 1.384 | 1.369 | 1.402 | 1.399 | 1.375 | 1.378 | 1.390 | 1.399 | 1.375 |
| Telemetry | 1.369 | - | 1.387 | - | 1.396 | - | 1.402 | - | 1.39 |
Second, process airplane data：First verify that the normal operation of the accuracy of record data, i.e. recording equipment.First
Each recording equipment the data obtained is processed, is supplemented including data name unification, the unification of data markers and missing data.
Data name unification be the data variable name for renaming distinct device record data in order to inquiring about and managing, it is like flying ginseng record
Instrument records data to Data Filename prefixing fc, flies control recording equipment and records data to Data Filename prefixing fk, remote measurement
Recording equipment records data to Data Filename prefixing yc.
Markers unification is carried out to interpretation of records data.Using method is to be switched as mark with undercarriage folding and unfolding, with
It is foundation to fly the control recording equipment time, the time of record data is unified, afterwards using the method for linear interpolation by data
Unified is 30 measuring points per second.After processing more than, the same data message of different recording equipments is taken, with the time as transverse axis,
Data are that the longitudinal axis draws curve, compare to confirm the correctness of record data.
Such as record data of illustrating in first step, using linear interpolation is by Supplementing Data and compares：
| Flight data | 1.396 | 1.386 | 1.375 | 1.384 | 1.393 | 1.38 | 1.366 | 1.384 | 1.402 |
| Flight control data | 1.384 | 1.369 | 1.402 | 1.399 | 1.375 | 1.378 | 1.390 | 1.399 | 1.375 |
| Telemetry | 1.369 | 1.378 | 1.387 | 1.392 | 1.396 | 1.399 | 1.402 | 1.396 | 1.39 |
3rd, simulation analysis control law data：It is input into and obtains record data for upper two step, by data and aircraft control law
With reference to, according to control law require calculation criterion input data is calculated, such as：
Horizontal tail instruction=longitudinal drive rod volume * 0.2+ pitch rate * 0.1+ the angles of attack
The horizontal tail command information of each data point is then calculated by the rule, the horizontal tail of gained information and aircraft record will be calculated
Command information is depicted as the curve with the time as axle and compares, if curve is consistent, illustrates the inspection section control law with design
Unanimously.
Claims (1)
1. a kind of airborne control law correctness method for rapidly testing, it is characterised in that comprise the steps：First, choose and fly ginseng
Can be used to verify the data of flight control system control law correctness in recorder data, winged control recording equipment data and telemetry；
Second, markers unification and data point unification are carried out to the data obtained, compare the accuracy of checking record data, its using method
For：With undercarriage folding and unfolding switch as mark, to fly the control recording equipment time as foundation, the time of record data is united
One, the use of the method for linear interpolation is afterwards 30 measuring points per second by data unification；The same number of different recording equipments is taken again
It is believed that breath, with the time as transverse axis, data are that the longitudinal axis draws curve, compare to confirm the correctness of record data；3rd, according to control
System rule rule simulation calculates record data, and simulation result is mutually compared with physical record data, access control rule operation accuracy.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105159141B (en) * | 2015-08-11 | 2019-03-22 | 中国航空工业集团公司西安飞机设计研究所 | The verification method and device of Flying by wire rule transmission ratio |
| CN109992623B (en) * | 2019-02-25 | 2023-06-16 | 平安科技（深圳）有限公司 | Block chain-based aviation service data sharing method and related equipment |
| CN112015109B (en) * | 2020-09-02 | 2024-01-23 | 四川腾盾科技有限公司 | Large unmanned aerial vehicle takeoff front wheel lifting test flight control law and design method thereof |
| CN113961015B (en) * | 2021-09-24 | 2024-02-02 | 中国航空工业集团公司西安飞机设计研究所 | One-dimensional interpolation table design method for flight control law |
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| CN101739845A (en) * | 2009-12-18 | 2010-06-16 | 中国航空无线电电子研究所 | Aeronautical data chain information-based civil aircraft aviation electronic verification system and method thereof |
| CN101907890A (en) * | 2010-08-19 | 2010-12-08 | 中国航空工业第六一八研究所 | Method for automatically testing control law of flying control system |
| CN102915038A (en) * | 2012-11-16 | 2013-02-06 | 北京航空航天大学 | Dual-redundancy autonomous flight control system for micro-miniature unmanned helicopters |
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| CN101739845A (en) * | 2009-12-18 | 2010-06-16 | 中国航空无线电电子研究所 | Aeronautical data chain information-based civil aircraft aviation electronic verification system and method thereof |
| CN101907890A (en) * | 2010-08-19 | 2010-12-08 | 中国航空工业第六一八研究所 | Method for automatically testing control law of flying control system |
| CN102915038A (en) * | 2012-11-16 | 2013-02-06 | 北京航空航天大学 | Dual-redundancy autonomous flight control system for micro-miniature unmanned helicopters |
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