CN203773350U - Automatic test adapter of flight control computer - Google Patents
Automatic test adapter of flight control computer Download PDFInfo
- Publication number
- CN203773350U CN203773350U CN201420139202.XU CN201420139202U CN203773350U CN 203773350 U CN203773350 U CN 203773350U CN 201420139202 U CN201420139202 U CN 201420139202U CN 203773350 U CN203773350 U CN 203773350U
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- Prior art keywords
- control computer
- test
- mainboard
- cable
- flight
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- Expired - Lifetime
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 58
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title claims abstract description 38
- 230000003750 conditioning effect Effects 0.000 claims abstract description 7
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
Abstract
The utility model discloses an automatic test adapter of a flight control computer. The automatic test adapter of the flight control computer comprises a chassis. A mainboard is arranged in the chassis. The mainboard is connected to a load plate and a cable. A front panel and a rear panel of the chassis are provided with a plurality of interfaces used for connecting the mainboard, a relay plate, the load plate, the cable and automatic test software respectively. The mainboard, the relay plate and the load plate are used for testing resource conditioning and distribution. The cable is used for connecting the flight control computer and the chassis. The adapter is mainly served as hardware portion of the automatic test and is cooperated with the automatic test software so as to complete the test of the flight control computer. During the test, the test software is used to start the adapter to work. Various kinds of signals needed by the test are switched to an appropriate input pin of the flight control computer through a board card and output of the light control computer is transmitted to an appropriate test device so as to carry out result collection so that the test of the flight control computer is completed.
Description
Technical field
The utility model relates to a kind of aircraft components proving installation, particularly relates to the automatic test adapter of a kind of flight-control computer.
Background technology
Flight-control computer is the ingredient of aircraft automated driving system, for management and the control of aircraft automatic Pilot.By statistics, flight-control computer belongs to troublesome key device, if can not keep in repair timely and accurately, will affect the normal flight of aircraft.Adapter is for the required key equipment of test flight control computing machine, and stability, reliability and the convenience of this device is the prerequisite of accurately carrying out fault test.At present conventional adapter only relies on line to carry out the switching of settling signal, due to the complicated fallibility of wiring, and not easy-to-search of wiring error.In addition, this device bulky, therefore carries and uses equal inconvenience.So be necessary the automatic test adapter structure of existing flight-control computer to improve.
Utility model content
The purpose of this utility model is to solve the problems of the technologies described above, and provides a kind of and needn't carry out complicated line, the volume automatic test adapter of flight-control computer little, easy to carry and use.
For achieving the above object, the technological means that the utility model adopts is to provide the automatic test adapter of a kind of flight-control computer, it is characterized in that: the automatic test adapter of described flight-control computer comprises cabinet, is provided with mainboard in cabinet, is connected with load board and cable on mainboard; Wherein the front panel of cabinet with on rear panel, be respectively equipped with multiple for being connected the interface of mainboard, relay board, load board, cable and automatic testing software; Mainboard, relay board and load board are for conditioning and the distribution of test resource; Cable is used for connecting flight-control computer and cabinet.
Wherein preferred technical scheme is that the interface on described front panel comprises multiple IO interface, power interface, equipment interface and connector; Wherein IO interface is connected with the test point on mainboard in cabinet by wire; Power interface is used for connecting ac/Dc power equipment; Equipment interface is used for connecting signal output apparatus synchronizing signal, function generator and testing apparatus oscillograph, multimeter; Connector is used for connecting automatic testing software.
Preferred technical scheme also has, and described rear panel is provided with cable connector, standby power supply connector and ARINC429 signal connector; Wherein cable connector is for stube cable; Standby power supply connector is for connecting test standby power supply; ARINC429 signal connector is used for connecting ARINC429 signal.
Preferred technical scheme also has, and described mainboard, relay board and load board formed flight-control computer signal condition and distribution maincenter; Wherein mainboard is used for connecting rear panel and relay board, load board; Relay board is subject to the control of automatic testing software, for conditioning and allocation for test input/output signal, signal output apparatus synchronizing signal, function generator output signal are switched on pin suitable on cable connector, and being outputted in testing apparatus oscillograph, multimeter input flight-control computer; Load board is used to test that electrical load is provided.
Advantage of the present utility model and beneficial effect are, the automatic test adapter of this flight-control computer is the bridge for connecting signal output apparatus and testing apparatus and flight-control computer, when test, start by automatic testing software and control adapter work, the needed various signals of test that signal output apparatus is produced are nursed one's health and distribute, and be transferred to flight-control computer, the output of flight-control computer is transferred to testing apparatus through conditioning simultaneously and carries out analyzing and processing, thereby complete the test of flight-control computer.Due to reasonable in design, the compact conformation of this test adapter, therefore easy to carry and use, thus exempt the numerous and diverse of complicated proving installation signal converting adaptation.
Brief description of the drawings
Be elaborated below in conjunction with accompanying drawing and the concrete automatic test adapter of flight-control computer of implementing the utility model to provide.
Fig. 1 is the formation schematic diagram of the automatic test adapter of the utility model flight-control computer;
Fig. 2 is the front panel schematic diagram of cabinet in the automatic test adapter of the utility model flight-control computer;
Fig. 3 is the rear panel schematic diagram of cabinet in the automatic test adapter of the utility model flight-control computer.
In figure: 1-computing machine, 2-cable, 3-cabinet, 4-mainboard, 5-relay board, 6-load board, 7-automatic testing software, 31-rear panel, 32-front panel, 50-IO interface, 51-power interface, 52-equipment interface, 53-connector, 54～59-cable connector, 60-standby power supply connector, 61-ARINC429 signal connector.
Embodiment
As shown in Figure 1 to Figure 3, the automatic test adapter of flight-control computer that the utility model provides comprises cabinet 3, mainboard 4, relay board 5, load board 6 and cable 2; On the front panel 32 of cabinet 3 and rear panel 31, be respectively equipped with multiple interfaces, multiple interfaces are used for connecting mainboard 4, relay board 5, load board 6 and cable 2 and automatic testing software 7; Mainboard 4, relay board 5 and load board 6 are arranged on to the inside of cabinet 3, for conditioning and the distribution of test resource; Cable 2 is for connecting flight-control computer 1 and cabinet 3.
In the utility model, on described front panel 32, be provided with multiple IO interface 50, power interface 51, equipment interface 52 and connector 53; Wherein IO interface 50 will be connected with the test point on mainboard 4 at cabinet 3 by wire; Power interface 51 is for connecting ac/Dc power equipment, for test provides power supply; Equipment interface 52 is for connecting signal output apparatus synchronizing signal, function generator and testing apparatus oscillograph, multimeter; Connector 53 is for connecting automatic testing software.
In the utility model, on described rear panel 31, be provided with cable connector 54～59, standby power supply connector 60 and ARINC429 signal connector 61; Wherein cable connector 54～59 is for stube cable 2; Standby power supply connector 60 is for connecting test standby power supply; ARINC429 signal connector 61 is for connecting ARINC429 signal.
In the utility model, flight-control computer signal condition and distribution maincenter are formed in described mainboard 4, relay board 5 and load board 6; Wherein mainboard 4 is for connecting rear panel 31 and relay board 5, load board 6; Relay board 5 is subject to the control of automatic testing software 7, for conditioning and allocation for test input/output signal, signal output apparatus synchronizing signal, function generator output signal are switched on pin suitable on cable connector 54～59, and being outputted in testing apparatus oscillograph, multimeter input flight-control computer 1; Load board 6 is used to test that electrical load is provided.
Wherein, mainboard model is: AWTC-0293-1;
Relay board model is: AWTC-0293-2;
Load board model is: AWTC-0293-3;
Automatic testing software title: AWTP-0293, flies to control automatic testing software, for test flight control computing machine, for test provides single step, multistep test, can show test event detail, printing test result etc.;
Cable connector model is: DPX2MB-67S67S-33B-0001(54～57, DB67(58～59;
Standby power supply connector model is: YP24;
ARINC429 signal connector model is: DB37;
ARINC429 signal is a kind of bipolarity return-to-zero code signal of being formulated by the US Airways electronic engineering council.
Below be only specific embodiment of the utility model, on the basis without prejudice to said structure principle, the improvement of then carrying out all belongs to the scope of the utility model protection.
Claims (3)
1. the automatic test adapter of flight-control computer, it is characterized in that: the automatic test adapter of described flight-control computer comprises cabinet (3), in cabinet (3), be provided with mainboard (4), on mainboard (4), be connected with relay board (5), load board (6) and cable (2); Wherein the front panel (32) of cabinet (3) with on rear panel (31), be respectively equipped with multiple for being connected the interface of mainboard (4), relay board (5), load board (6), cable (2) and automatic testing software (7); Mainboard (4), relay board (5) and load board (6) are for conditioning and the distribution of test resource; Cable (2) is for connecting flight-control computer (1) and cabinet (3).
2. the automatic test adapter of flight-control computer according to claim 1, is characterized in that: the interface on described front panel (32) comprises multiple IO interface (50), power interface (51), equipment interface (52) and connector (53); Wherein IO interface (50) is connected by the test point on the mainboard (4) in wire and cabinet (3); Power interface (51) is for connecting ac/Dc power equipment; Equipment interface (52) is for connecting signal output apparatus synchronizing signal, function generator and testing apparatus oscillograph, multimeter; Connector (53) is for connecting automatic testing software.
3. the automatic test adapter of flight-control computer according to claim 1, is characterized in that: described rear panel (31) is provided with cable connector (54～59), standby power supply connector (60) and ARINC429 signal connector (61); Wherein cable connector (54～59) is for stube cable (2); Standby power supply connector (60) is for connecting test standby power supply; ARINC429 signal connector (61) is for connecting ARINC429 signal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420139202.XU CN203773350U (en) | 2014-03-25 | 2014-03-25 | Automatic test adapter of flight control computer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420139202.XU CN203773350U (en) | 2014-03-25 | 2014-03-25 | Automatic test adapter of flight control computer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203773350U true CN203773350U (en) | 2014-08-13 |
Family
ID=51290518
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420139202.XU Expired - Lifetime CN203773350U (en) | 2014-03-25 | 2014-03-25 | Automatic test adapter of flight control computer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203773350U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110031751A (en) * | 2019-05-23 | 2019-07-19 | 北京安达维尔测控技术有限公司 | A kind of airliner audio-frequency control panel automatic testing equipment |
-
2014
- 2014-03-25 CN CN201420139202.XU patent/CN203773350U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110031751A (en) * | 2019-05-23 | 2019-07-19 | 北京安达维尔测控技术有限公司 | A kind of airliner audio-frequency control panel automatic testing equipment |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140813 |