CN206115261U - Trying on clothes from dynamic testing of flight control is put - Google Patents
Trying on clothes from dynamic testing of flight control is put Download PDFInfo
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- CN206115261U CN206115261U CN201620895795.1U CN201620895795U CN206115261U CN 206115261 U CN206115261 U CN 206115261U CN 201620895795 U CN201620895795 U CN 201620895795U CN 206115261 U CN206115261 U CN 206115261U
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Abstract
The utility model belongs to the flight control measuring technology relates to the improvement to flight control testing arrangement. The work load of going on testing to aircraft control system among the prior art is big, chronic, and efficiency of software testing is low. The present invention proposes a trying on clothes from dynamic testing of flight control is put, flight control includes sensor group, flight control computer and actuator group, tries on clothes from dynamic testing and puts including signal modulator, comprehensive test computer and flight test interface data computer, synthesize test computer and connect gradually with signal modulator and flight control computer, this flight control computer and flight test interface data computer link, should try on clothes to put from dynamic testing still includes many switches digital multimeter, this many switches digital multimeter and flight control computer's input and the corresponding signal port of output connect, detect each magnitude of voltage to corresponding the signal, and workload of measurement is little, the time is short, efficiency of software testing is high.
Description
Technical field
The invention belongs to flight control system measuring technology, is related to the improvement to flight control system test device.
Background technology
The structural principle block diagram of current flight control system test device is shown in Fig. 1.Power module is mainly four remainings and flies
Row control computer is powered, and winged control control box is mainly used in flying and controls the switching of mode, alerts instruction etc., physical sensor class
Product may be connected to flight-control computer by switching switch, as the signal input of four redundance flight control systems computers, can
To provide attitude information, the overload messages of aircraft body, switching information on atmosphere data information, control stick operation information and machine.
Integration test computer, by mimic buss the analog detection mouth of four redundance flight control systems computers is connected, meanwhile, it can be produced
The pumping signal of four redundance flight control systems computers of raw test, is formed by signal modulator and meets the calculating of four redundance flight control systems
The signal that the various input signal characteristics of machine are required, then it is connected to four redundance flight control systems computers through switching switch.Control flies
The actuator of each control surface of machine, is respectively left horizontal tail actuator, right horizontal tail actuator, port aileron actuator, starboard aileron start
Device, rudder actuator and front part of a Chinese robe or jacket actuator.They are connected to four redundance flight control systems computers by mimic buss.Flight is surveyed
Try a mouthful data computer, four redundance flight control systems computers are connected by serial ports.Safeguard that built-in self test tries computer, it is same logical
Cross serial ports and connect four redundance flight control systems computers.Avionics data bus interface computer, by standard aviation bus four remainings are connected
Flight-control computer.
Its operation principle is：Testing crew is by the given four redundance flight control systems computer input institutes of integration test computer
Various simulations, the discrete test and excitation signal for needing, can observe given excitation letter on test flight interface data computer
The various status informations of four redundance flight control systems computer-internals and the actuator command information of output after number, so as to judge four
Whether redundance flight control systems computer operating state meets expected resultss.Testing crew is calculated by the examination of Operation and Maintenance built-in self test
Machine activates four redundance flight control systems computer-internal built-in self tests examination function, and obtains test result feedback.Meanwhile, can also pass through
Input instruction controls the displacement output of each actuator, by observing relevant actuator on test flight interface data computer
Whether normal status information, can test various actuator functions.Testing crew can pass through Avionics data bus interface computer mould
It is total so as to complete aviation with the communication function of the various avionic devices of four redundance flight control systems computers crosslinking on plan aircraft
The test of line interface.
It has the disadvantage：Test job amount is big, and the time is long, and testing efficiency is low.
The content of the invention
The technical problem to be solved is：Propose that a kind of test job amount is little, the time is short, testing efficiency is high flies
The automatic testing equipment of row control system.
The automatic testing equipment of the flight control system of the present invention, the flight control system includes sensor group, flight
Control computer and actuator group, automatic testing equipment includes signal modulator, integration test computer and test flight interface
Data computer, the integration test computer is sequentially connected with signal modulator and flight-control computer, the flight control
Computer is connected with test flight interface data computer, and the automatic testing equipment also includes Multi- Switch digital multimeter, and this is more
The switch numbers circuit tester signal port connection corresponding with the input and outfan of the flight-control computer, detection is every
The magnitude of voltage of a pair pairs of induction signals.
The automatic testing equipment also includes being connected with the flight-control computer and integration test computer respectively
Maintenance built-in self test examination computer and Avionics data bus interface computer.
Integration test computer can give built-in self test examination instruction, Avionics data bus interface input signal, and collection flight is surveyed
Examination interface data and Avionics data bus interface output signal.
The method for carrying out automatic test using the automatic testing equipment of above-mentioned flight control system, the integration test meter
The pumping signal for simulating the sensor group is sent to signal modulator by calculation machine, and is sent to flight-control computer, and this flies
The signal for receiving is converted to the analog control signal of actuator group and is sent to test flight number of ports by row control computer
According to computer, Multi- Switch digital multimeter detects the magnitude of voltage of the correspondence signal per a pair of, and carries out with default signal voltage value
Relatively, judge whether the flight control system is normal.
The invention has the beneficial effects as follows：Test job amount is little, and the time is short, and testing efficiency is high.One embodiment of the present of invention
Tests prove that, testing efficiency improves more than 100 times than current manual test device.
Description of the drawings
Fig. 1 is the theory diagram of current flight control system test device；
Fig. 2 is the theory diagram of the flight control system test device of the present invention.
Specific embodiment
The present invention is described in further details below.Referring to Fig. 2,
The automatic testing equipment of the flight control system of the present invention, the flight control system includes sensor group, flight
Control computer and actuator group, automatic testing equipment includes signal modulator, integration test computer and test flight interface
Data computer, the integration test computer is sequentially connected with signal modulator and flight-control computer, the flight control
Computer is connected with test flight interface data computer, and the automatic testing equipment also includes Multi- Switch digital multimeter, and this is more
The switch numbers circuit tester signal port connection corresponding with the input and outfan of the flight-control computer, detection is every
The magnitude of voltage of a pair pairs of induction signals.
The automatic testing equipment also includes being connected with the flight-control computer and integration test computer respectively
Maintenance built-in self test examination computer and Avionics data bus interface computer.Integration test computer can give built-in self test examination and refer to
Make, Avionics data bus interface input signal, collection test flight interface data and Avionics data bus interface output signal.
The method for carrying out automatic test using the automatic testing equipment of above-mentioned flight control system, the integration test is calculated
The pumping signal for simulating the sensor group is sent to signal modulator by machine, and is sent to flight-control computer, the flight
The signal for receiving is converted to the analog control signal of actuator group and is sent to test flight interface data by control computer
Computer, Multi- Switch digital multimeter detects the magnitude of voltage of the correspondence signal per a pair of, and is compared with default signal voltage value
Compared with judging whether the flight control system is normal.
One embodiment of the present of invention, the Multi- Switch digital multimeter 38 for being adopted is for finished parts.Manufacturer is：The U.S.
Agilent, model 34980A.
Claims (3)
1. a kind of automatic testing equipment of flight control system, the flight control system includes sensor group, flight control meter
Calculation machine and actuator group, automatic testing equipment includes signal modulator, integration test computer and test flight interface data meter
Calculation machine, the integration test computer is sequentially connected with signal modulator and flight-control computer, the flight-control computer
It is connected with test flight interface data computer, it is characterised in that：The automatic testing equipment also includes Multi- Switch digital multimeter,
The Multi- Switch digital multimeter signal port connection corresponding with the input and outfan of the flight-control computer, inspection
Survey the magnitude of voltage of the correspondence signal per a pair of.
2. the automatic testing equipment of flight control system according to claim 1, it is characterised in that：The automatic test dress
Put the maintenance built-in self test examination computer for also including being connected with the flight-control computer and integration test computer respectively
With Avionics data bus interface computer.
3. the automatic testing equipment of flight control system according to claim 2, it is characterised in that：Integration test computer
Built-in self test examination instruction, Avionics data bus interface input signal can be given, collection test flight interface data and Avionics data bus connect
Mouth output signal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620895795.1U CN206115261U (en) | 2016-08-17 | 2016-08-17 | Trying on clothes from dynamic testing of flight control is put |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620895795.1U CN206115261U (en) | 2016-08-17 | 2016-08-17 | Trying on clothes from dynamic testing of flight control is put |
Publications (1)
| Publication Number | Publication Date |
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| CN206115261U true CN206115261U (en) | 2017-04-19 |
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| CN201620895795.1U Active CN206115261U (en) | 2016-08-17 | 2016-08-17 | Trying on clothes from dynamic testing of flight control is put |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109319167A (en) * | 2018-09-07 | 2019-02-12 | 国营芜湖机械厂 | A kind of detection device for aircraft horizontal tail pressurized strut sensor module |
| CN109543251A (en) * | 2018-11-05 | 2019-03-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airborne equipment development guarantee grade distribution method |
| CN110716584A (en) * | 2019-10-29 | 2020-01-21 | 中国航空工业集团公司西安飞行自动控制研究所 | Automatic detection method in flight control system for actuator SOV fault |
| CN114167847A (en) * | 2022-02-14 | 2022-03-11 | 中航金城无人系统有限公司 | Test system and test method suitable for multi-rotor aircraft flight control system |
-
2016
- 2016-08-17 CN CN201620895795.1U patent/CN206115261U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109319167A (en) * | 2018-09-07 | 2019-02-12 | 国营芜湖机械厂 | A kind of detection device for aircraft horizontal tail pressurized strut sensor module |
| CN109319167B (en) * | 2018-09-07 | 2021-12-03 | 国营芜湖机械厂 | Detection device for aircraft horizontal tail actuator cylinder sensor assembly |
| CN109543251A (en) * | 2018-11-05 | 2019-03-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airborne equipment development guarantee grade distribution method |
| CN110716584A (en) * | 2019-10-29 | 2020-01-21 | 中国航空工业集团公司西安飞行自动控制研究所 | Automatic detection method in flight control system for actuator SOV fault |
| CN114167847A (en) * | 2022-02-14 | 2022-03-11 | 中航金城无人系统有限公司 | Test system and test method suitable for multi-rotor aircraft flight control system |
| CN114167847B (en) * | 2022-02-14 | 2022-04-15 | 中航金城无人系统有限公司 | Test system and test method suitable for multi-rotor aircraft flight control system |
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