CN103984337A - 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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- CN103984337A CN103984337A CN201410154221.4A CN201410154221A CN103984337A CN 103984337 A CN103984337 A CN 103984337A CN 201410154221 A CN201410154221 A CN 201410154221A CN 103984337 A CN103984337 A CN 103984337A
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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, be specifically related to a kind of airborne control law correctness method for rapidly testing.
Background technology
Flight control system is the important component part of aircraft, and flight control system control law need ensure to ensure within the scope of whole flight envelope that aircraft has good flight quality, and therefore the true(-)running of control law is the key that ensures flight safety.
If the stage of taking a flight test at aircraft goes wrong, need to check the working order of each system, wherein first the accuracy testing of flight control system control law needs to carry out.Traditional method of testing is that flight control computer is disassembled from aircraft, carries out the test of control law correctness on iron bird test-bed, and testing procedure comprises: the test of control law open-loop branch and system closed loop test.And the object of iron bird test is in more real integrated environment, fully function and the performance of verification system, the reliability of soft and hardware.The method test period is long, and and underuses the existing test flight data of aircraft.
Summary of the invention
The object of the invention is: the present invention, mainly for fly-by-wire flight control system aircraft, provides a kind of method for rapidly testing of airborne control law correctness.
Technical scheme of the present invention is:
1. a method for rapidly testing for airborne control law correctness, is characterized in that, comprises that step is as follows:
The first, record airplane data: the each system of aircraft can be according to its demand history correlation test or test flight data, comprise flying to join registering instrument data, flying to control recording unit data, telemetry.Because each recording unit is relatively independent, therefore, its record format, recording frequency (number that records per second), precision all have difference.This step is to choose the data of storage in each recording unit, specifies the data sense of different filename representatives.Need the data of record to comprise: the angle of attack, yaw angle, the command information of course angle speed, normal direction and lateral overload, the angle of pitch, roll angle, crab angle, dynamic and static pressure, pilot's vertical pole, cross bar and pedal input, throttle lever position, oil mass, engine speed, undercarriage control switch, sensor fault signal and the each rudder face of aircraft in length and breadth.
The second, process airplane data: for ensureing flight control system control law checking accuracy, first need to ensure the accuracy of record data, i.e. the normal operation of recording unit.Therefore need each recording unit the data obtained to process, supplement comprising data name unification, the unification of data markers and missing data.Data name unification is to rename the data variable name of distinct device record data so that inquiry and management.
Because distinct device all can produce cumulative errors in recording process, especially for the long subject of taking a flight test of time, therefore need interpretation of records data to carry out markers unification.Using method, for taking undercarriage folding and unfolding switch as mark, to fly controlling the recording unit time as foundation, is unified the time of record data, and using afterwards the method for linear interpolation is 30 measuring point per second by data unification.After above processing, get the same data message of different recording units, taking the time as transverse axis, data are longitudinal axis curve plotting, comparison is to confirm the correctness of record data.
The 3rd, simulation analysis control law data: two steps that are input as of this step obtain record data, data are combined and are carried out time domain calculating with aircraft control law, obtain the rudder face command information of each data point, the curve that the command information that calculates gained information and aircraft record was depicted as taking the time as axle is compared, if curve is consistent, illustrate that this inspection section control law is consistent with design.
Advantage of the present invention is:
The inventive method is by reasonably being used the different recording unit storage of aircraft data, can resolve fast and analyze the operation conditions of control law in flight control computer, replace and needed to dismantle flying control equipment to carry out the classic method of testing laboratory's test in the past, improved the work efficiency of outfield troubleshooting task.
Embodiment
Below by actual test process, the present invention is described in further detail:
The first, record airplane data: record data source comprises: fly to join registering instrument, fly to control recording unit and tele rcording equipment.Specify after the data sense of different filename representatives, choose the data of storage in each recording unit.Need the data of record to comprise: the angle of attack, yaw angle, the command information etc. of course angle speed, normal direction and lateral overload, the angle of pitch, roll angle, crab angle, dynamic and static pressure, pilot's vertical pole, cross bar and pedal input, throttle lever position, oil mass, engine speed, undercarriage control switch, sensor fault signal, the each rudder face of aircraft in length and breadth.
As certain flying quality, angle of attack data recording is as follows:
| Flight data | 1.396 | - | 1.375 | - | 1.393 | - | 1.366 | - | 1.402 |
| Fly to 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 |
The second, process airplane data: first verify the accuracy of record data, i.e. the normal operation of recording unit.First each recording unit the data obtained is processed, supplemented comprising data name unification, the unification of data markers and missing data.Data name unification is to rename the data variable name of distinct device record data so that inquiry and management, ginseng registering instrument like flying is recorded data to Data Filename prefixing fc, fly to control recording unit and record data to Data Filename prefixing fk, tele rcording equipment is recorded data to Data Filename prefixing yc.
Interpretation of records data are carried out to markers unification.Using method, for taking undercarriage folding and unfolding switch as mark, to fly controlling the recording unit time as foundation, is unified the time of record data, and using afterwards the method for linear interpolation is 30 measuring point per second by data unification.After above processing, get the same data message of different recording units, taking the time as transverse axis, data are longitudinal axis curve plotting, comparison is to confirm the correctness of record data.
As the record data of giving an example in first step, use linear interpolation by data completion and compare:
| Flight data | 1.396 | 1.386 | 1.375 | 1.384 | 1.393 | 1.38 | 1.366 | 1.384 | 1.402 |
| Fly to 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 |
The 3rd, simulation analysis control law data: be input as two steps and obtain record data, data are combined with aircraft control law, the calculation criterion requiring according to control law is calculated input data, as:
Horizontal tail instruction=longitudinal drive bar amount * 0.2+ pitch rate * 0.1+ angle of attack
Calculate the horizontal tail command information of each data point by this rule, the curve that the horizontal tail command information that calculates gained information and aircraft record was depicted as taking the time as axle is compared, if curve is consistent, illustrates that this inspection section control law is consistent with design.
Claims (1)
1. an airborne control law correctness method for rapidly testing, is characterized in that, comprises the steps: the first, chooses and fly to join registering instrument data, flies to control the data that can be used for verifying flight control system control law correctness in recording unit data and telemetry; The second, the data obtained is carried out to markers unification and data point unification, the accuracy of comparatively validate record data; The 3rd, calculate record data according to control law rule simulation, simulation result and physical record data are compared to access control rule operation accuracy.
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| CN201410154221.4A CN103984337B (en) | 2014-04-17 | 2014-04-17 | Method for rapid testing of correctness of onboard control law |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105159141A (en) * | 2015-08-11 | 2015-12-16 | 中国航空工业集团公司西安飞机设计研究所 | Fax control law transmission ratio verification method and apparatus |
| CN109992623A (en) * | 2019-02-25 | 2019-07-09 | 平安科技（深圳）有限公司 | Aviation engineering data sharing method and relevant device based on block chain |
| CN112015109A (en) * | 2020-09-02 | 2020-12-01 | 四川腾盾科技有限公司 | Large unmanned aerial vehicle takeoff and front wheel lift test flight control law and design method thereof |
| CN113961015A (en) * | 2021-09-24 | 2022-01-21 | 中国航空工业集团公司西安飞机设计研究所 | Flight control law one-dimensional interpolation table design method |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105159141A (en) * | 2015-08-11 | 2015-12-16 | 中国航空工业集团公司西安飞机设计研究所 | Fax control law transmission ratio verification method and apparatus |
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| 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 |
| CN112015109A (en) * | 2020-09-02 | 2020-12-01 | 四川腾盾科技有限公司 | Large unmanned aerial vehicle takeoff and front wheel lift test flight control law and design method thereof |
| 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 |
| CN113961015A (en) * | 2021-09-24 | 2022-01-21 | 中国航空工业集团公司西安飞机设计研究所 | Flight control law one-dimensional interpolation table design method |
| 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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