CN204750596U - Aircraft in situ test equipment - Google Patents
Aircraft in situ test equipment Download PDFInfo
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- CN204750596U CN204750596U CN201520328741.2U CN201520328741U CN204750596U CN 204750596 U CN204750596 U CN 204750596U CN 201520328741 U CN201520328741 U CN 201520328741U CN 204750596 U CN204750596 U CN 204750596U
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- test equipment
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Abstract
The utility model relates to an aircraft in situ test equipment, this test equipment respectively with the peaceful system that shows of atmospheric engine, course gesture system, test equipment include test circuit, remote terminal and signal simulation detection circuitry, test circuit pass through wireless network and be connected with remote terminal, test circuit respectively with the peaceful headtotail that shows of signal simulation detection circuitry, atmospheric engine, course gesture system. Compared with the prior art, the utility model has the advantages of convenient to carry, easy operation, low cost, interchangeable, application range are extensively.
Description
Technical field
The utility model relates to a kind of airplane test equipment, especially relates to a kind of aircraft in situ test equipment.
Background technology
At present when carrying out aircraft in situ test, because volume reason check implement can not be placed in passenger cabin.Need two people or many people to coordinate when carrying out in situ detection.One man operation check implement, a people operates or parameter on reading instrument in passenger cabin.Sometimes the work that also needs a people to complete to pass on a message (have noise after aircraft start, the people in the people of operation detection equipment and passenger cabin can not actual conversation).A small amount of equipment can be equipped with " palm terminal ", and its palm terminal is all adopt wire communication.It carries inconvenience, is also subject to the restriction of communication distance, communication speed simultaneously.
Utility model content
The purpose of this utility model be exactly in order to overcome above-mentioned prior art exist defect and a kind of aircraft in situ test equipment is provided.
The purpose of this utility model can be achieved through the following technical solutions:
A kind of aircraft in situ test equipment, this test equipment is connected with atmospheric engine, the aobvious system of heading and attitude system peace respectively, it is characterized in that, described test equipment comprises test circuit, remote terminal and signal imitation testing circuit, described test circuit is connected with remote terminal by wireless network, and described test circuit is connected with signal imitation testing circuit, atmospheric engine, the aobvious system of heading and attitude system peace respectively.
Described test circuit is connected with atmospheric engine, the aobvious system of heading and attitude system peace respectively by adapter.
Described adapter comprises the atmospheric engine adapter, the aobvious system adapter of heading and attitude system adapter peace that are connected with test circuit respectively, described atmospheric engine adapter is connected with atmospheric engine, described heading and attitude system adapter is connected with heading and attitude system, and described flat aobvious system adapter is connected with flat aobvious system.
Described test circuit comprises electric parameters transducer, CPU and the radio communication plate be connected with CPU respectively, AD/DA collection plate, digital I/O board, ARINC429 plate and power management module, described radio communication plate is connected with remote terminal, and described electric parameters transducer is connected with AD/DA collection plate.
Described test circuit is connected with remote terminal by WIFI.
Described remote terminal is panel computer with WIFI function or notebook.
Compared with prior art, the utility model has the following advantages:
1, easy to carry, simple to operate.
2, low cost, interchangeable, range of use is wide.
3, communication distance is far away, and speed is fast, high reliability.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the utility model is described in detail.
Embodiment
As shown in Figure 1, a kind of aircraft in situ test equipment, this test equipment is connected with atmospheric engine 2, the aobvious system 4 of heading and attitude system 3 peace respectively, described test equipment comprises test circuit 1, remote terminal 5 and signal imitation testing circuit 6, described test circuit 1 is connected with remote terminal 5 by wireless network, and described test circuit 1 is connected with signal imitation testing circuit 6, atmospheric engine 2, the aobvious system 4 of heading and attitude system 3 peace respectively.
Described test circuit 1 is connected with atmospheric engine 2, the aobvious system 4 of heading and attitude system 3 peace respectively by adapter 7.Described adapter 7 comprises the atmospheric engine adapter 71, the aobvious system adapter 73 of heading and attitude system adapter 72 peace that are connected with test circuit 1 respectively, described atmospheric engine adapter 71 is connected with atmospheric engine 2, described heading and attitude system adapter 72 is connected with heading and attitude system 3, and described flat aobvious system adapter 73 is connected with flat aobvious system 4.
Described test circuit 1 comprises electric parameters transducer, CPU and the radio communication plate be connected with CPU respectively, AD/DA collection plate, digital I/O board, ARINC429 plate and power management module, described radio communication plate is connected with remote terminal, and described electric parameters transducer is connected with AD/DA collection plate.Described test circuit is connected with remote terminal by WIFI.Described remote terminal is panel computer with WIFI function or notebook.
Board in cabinet receives the instruction of CPU, and AD/DA collection plate sends DA signal, and part DA signal outputs to airborne equipment after circuit card amplifies; The d. c. voltage signal that airborne equipment exports is given AD/DA collection plate after treatment and is read; The AC signal that airborne equipment exports is given AD/DA collection plate and is read after electric parameters transducer process; Numeral I/O plate controls the relay of self-control circuit card; ARINC429 plate can send 429 data to airborne equipment, also can read 429 signals that airborne equipment sends simultaneously.
Test circuit 1 is furnished with WiFi communication plate, is set to access point mode.What remote terminal adopted is common industrial grade panel computer, decreases the cost of hardware design.Any computer with WiFi function, as long as install test software as remote terminal, can have interchangeability.Multiple stage test equipment can share a remote terminal, as long as it is just passable to run corresponding test software simultaneously.
During test equipment work, signal imitation detecting unit provides three-phase synchronous signal and excitatory for flat aobvious system, measures the three-phase synchronous signal that aviation attitude system exports simultaneously.The signal of signal imitation detecting unit is connected to airborne equipment after equipment switching after tested.Test equipment provides ARINC429 signal, DA signal, DC28V power supply signal, on-off model etc. for airborne equipment.Remote terminal is communicated with test equipment by WIFI, and operating personal can select remote terminal to take in passenger cabin.Control test equipment by touch-screen to test, export the signal needed, then read the numerical value that in passenger cabin, instrument is corresponding.
When atmospheric engine detects, necessary application testing equipment, can be directly connected to test equipment by check cable during test, also can select SPQ-3B adapter, be connected to test equipment test by adapter after being transferred.
The aobvious systems axiol-ogy of aviation attitude system peace must application testing equipment and signal imitation detecting unit.Check cable can be directly connected to test equipment during test, also can select SPQ-4A, SPQ-5A adapter, be connected to test equipment after being transferred by adapter and test.
When atmospheric engine, boat appearance, flat aobvious test, can the directly touch-screen read test data of application testing apparatus front panel, control signal output.Also can choice for use remote terminal, take and locally easily read data, control test.Two device synchronization display test pictures.
Adapter panel leaves test interface, can data in Real-Time Monitoring test, convenient monitoring and fault localization.Adapter, remote terminal are apolegamy equipment, and alerting ability is larger.
Claims (6)
1. an aircraft in situ test equipment, this test equipment is connected with atmospheric engine, the aobvious system of heading and attitude system peace respectively, it is characterized in that, described test equipment comprises test circuit, remote terminal and signal imitation testing circuit, described test circuit is connected with remote terminal by wireless network, and described test circuit is connected with signal imitation testing circuit, atmospheric engine, the aobvious system of heading and attitude system peace respectively.
2. a kind of aircraft in situ test equipment according to claim 1, is characterized in that, described test circuit is connected with atmospheric engine, the aobvious system of heading and attitude system peace respectively by adapter.
3. a kind of aircraft in situ test equipment according to claim 1, it is characterized in that, described adapter comprises the atmospheric engine adapter, the aobvious system adapter of heading and attitude system adapter peace that are connected with test circuit respectively, described atmospheric engine adapter is connected with atmospheric engine, described heading and attitude system adapter is connected with heading and attitude system, and described flat aobvious system adapter is connected with flat aobvious system.
4. a kind of aircraft in situ test equipment according to claim 1, it is characterized in that, described test circuit comprises electric parameters transducer, CPU and the radio communication plate be connected with CPU respectively, AD/DA collection plate, digital I/O board, ARINC429 plate and power management module, described radio communication plate is connected with remote terminal, and described electric parameters transducer is connected with AD/DA collection plate.
5. a kind of aircraft in situ test equipment according to claim 1, it is characterized in that, described test circuit is connected with remote terminal by WIFI.
6. a kind of aircraft in situ test equipment according to claim 1 or 5, is characterized in that, described remote terminal is panel computer with WIFI function or notebook.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520328741.2U CN204750596U (en) | 2015-05-20 | 2015-05-20 | Aircraft in situ test equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520328741.2U CN204750596U (en) | 2015-05-20 | 2015-05-20 | Aircraft in situ test equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204750596U true CN204750596U (en) | 2015-11-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520328741.2U Active CN204750596U (en) | 2015-05-20 | 2015-05-20 | Aircraft in situ test equipment |
Country Status (1)
| Country | Link |
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| CN (1) | CN204750596U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105366076A (en) * | 2015-12-04 | 2016-03-02 | 重庆德新机器人检测中心有限公司 | Multi-rotor unmanned aircraft performance detection system and device |
| CN106516158A (en) * | 2016-11-25 | 2017-03-22 | 中国人民解放军海军航空工程学院 | Automatic signal-oriented airplane in-situ test system and fault diagnosis method |
| CN112874811A (en) * | 2021-01-21 | 2021-06-01 | 北京安达维尔航空设备有限公司 | Distributed airplane in-situ test system and method |
| CN115876243A (en) * | 2023-03-08 | 2023-03-31 | 航宇伟创科技(北京)有限公司 | Aircraft atmospheric data system check out test set |
-
2015
- 2015-05-20 CN CN201520328741.2U patent/CN204750596U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105366076A (en) * | 2015-12-04 | 2016-03-02 | 重庆德新机器人检测中心有限公司 | Multi-rotor unmanned aircraft performance detection system and device |
| CN106516158A (en) * | 2016-11-25 | 2017-03-22 | 中国人民解放军海军航空工程学院 | Automatic signal-oriented airplane in-situ test system and fault diagnosis method |
| CN106516158B (en) * | 2016-11-25 | 2020-03-31 | 中国人民解放军海军航空工程学院 | Signal-oriented airplane in-situ automatic test system and fault diagnosis method |
| CN112874811A (en) * | 2021-01-21 | 2021-06-01 | 北京安达维尔航空设备有限公司 | Distributed airplane in-situ test system and method |
| CN115876243A (en) * | 2023-03-08 | 2023-03-31 | 航宇伟创科技(北京)有限公司 | Aircraft atmospheric data system check out test set |
| CN115876243B (en) * | 2023-03-08 | 2023-06-06 | 航宇伟创科技(北京)有限公司 | Aircraft atmospheric data system check out test set |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20161221 Address after: 200436 Shanghai Road, Jingan District, No. 3127 Patentee after: SHANGHAI HAIYING MACHINERY PLANT Address before: 200443 Shanghai city Baoshan District Dakang Road No. 100 Patentee before: Shanghai Kaidike Aviation Engineering Technology Co., Ltd. |
|
| CU03 | Correction of utility model patent gazette |
Correction item: Inventor Correct: Zhou Baodi|Shen Xiaoyang|Dong Dan|Zhang Ben False: Zhou Baodi|Shen Xiaoyang|Zhang Ben Number: 02 Volume: 33 |
|
| ERR | Gazette correction |