CN202676892U - Airborne power supply integrated test system - Google Patents
Airborne power supply integrated test system Download PDFInfo
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- CN202676892U CN202676892U CN 201220077369 CN201220077369U CN202676892U CN 202676892 U CN202676892 U CN 202676892U CN 201220077369 CN201220077369 CN 201220077369 CN 201220077369 U CN201220077369 U CN 201220077369U CN 202676892 U CN202676892 U CN 202676892U
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Abstract
The utility model belongs to the technology of airborne testing, and relates to an airborne power supply integrated test system. The airborne power supply integrated test system comprises four test units and universal test equipment, wherein the four test units are a DC power supply system test unit, an AC power supply system test unit, a power distribution logic function test unit and an external power supply monitoring test unit; each test unit comprises an industrial personal computer, a signal conditioning box, a signal converter, and a manual/automatic control test module which are connected successively; the universal test equipment is connected with the manual/automatic control test modules of the test units through output channels; and the manual/automatic control test modules are connected to load interfaces through feedback channels. The airborne power supply integrated test system provided by the utility model can check power supply systems of different models, improves the expansibility, practicability and compatibility of the systems, and has great practical value. Furthermore, the airborne power supply integrated test system can realize automatic test on airborne power supply systems, and the test time is shortened.
Description
Technical field
The utility model belongs to the airborne testing technology, relates to a kind of airborne power supply integrated test system.
Background technology
In the helicopter test, traditional test does not have the concept of system testing, can only test for single finished product, method of testing also can only be carried out line according to circuit on the machine, and finally carrying out patch by common apparatus such as shunt, digital avometers measures, cause finished product test operating difficulties efficient low, and can't carry out Combined Trials to whole system, cause easily that state and test mode are not inconsistent on the machine.
The utility model content
The purpose of this utility model is: propose fast, the compatible strong airborne power supply system integration testing system of a kind of detection speed.
The technical solution of the utility model is: a kind of airborne power supply integrated test system, it comprises four test cells and general purpose test equipment, wherein be respectively the DC power system test cell, the AC power supply system test cell, distribution logic function test cell, external power control and measuring unit, each test cell comprises the industrial computer that links to each other in turn, signal process box, signal converter and manual/auto control test module, wherein, general purpose test equipment links to each other with the manual/auto control test module of each test cell by output channel, and manual/auto control test module is connected to loading interfaces by feedback channel.
General purpose test equipment comprises signal output source and feedback execution module, wherein the signal output source comprises drag source and display device, gearbox and the ground ac-dc power supply that all links to each other with manual/auto control test module, and the feedback execution module comprises generator, dc controller, alternating-current controller, DC load and the AC load that also all links to each other with manual/auto control test module.
The signal condition module of each test cell links to each other with loading interfaces.
Drag source and display device are comprised of the power distribution cabinet, frequency converter, the adjustable frequency motor that link to each other in turn.
The utility model has the advantages that: the utility model airborne power supply integrated test system is by changing interface type, change control test cell interface and upgrading industrial computer software, thereby the power-supply system to different model checks, finally play the effect of system extension, the extendability of raising system and practicality, improved the compatibility of measuring technology, have larger practical value, larger appreciation space is arranged.And can realize helicopter-mounted power-supply system is tested automatically, shorten the test duration to whole system, have larger actual application value.
Description of drawings
Fig. 1 is the utility model airborne power supply integrated test system theory diagram;
Wherein, 1-DC power system test cell, 2-AC power supply system test cell, 3-distribution logic function test cell, 4-external power control and measuring unit, 5-industrial computer, 6-signal process box, 7-signal converter, the manual/auto control test module of 8-, 9-drag source and display device, 10-power distribution cabinet, 11-frequency converter, 12-adjustable frequency motor, 13-gearbox, 14-generator, 15-dc controller, 16-alternating-current controller, 17-DC load, 18-AC load, 19-ground ac-dc power supply.
Embodiment
The below is described in further details the utility model.
See also Fig. 1, wherein, Fig. 1 is the theory diagram of the utility model airborne power supply integrated test system.The utility model airborne power supply integrated test system comprises four test cells and general purpose test equipment, wherein be respectively DC power system test cell, AC power supply system test cell, distribution logic function test cell, external power control and measuring unit, each test cell comprises industrial computer, signal process box, signal converter and the manual/auto control test module that links to each other in turn.Wherein, general purpose test equipment links to each other with the manual/auto control test module of each test cell by output channel, and manual/auto control test module is connected to loading interfaces by feedback channel.
Described general purpose test equipment comprises signal output source and feedback execution module, wherein the signal output source comprises drag source and display device, gearbox and the ground ac-dc power supply that all links to each other with manual/auto control test module, and the feedback execution module comprises generator, dc controller, alternating-current controller, DC load and the AC load that also all links to each other with manual/auto control test module.
The signal condition module of each test cell links to each other with loading interfaces, because load signal is different from most of general-purpose simulation signal, therefore need to nurses one's health the equipment such as rear and industrial computer by the signal condition module and carry out communication.
Drag source and display device are comprised of the power distribution cabinet, frequency converter, the adjustable frequency motor that link to each other in turn.Power distribution cabinet offers frequency converter with industrial three-phase alternating current, and frequency converter sends instruction by the RS485 interface to adjustable frequency motor, thereby regulates the adjustable frequency motor correlation parameter.
Described helicopter-mounted power supply integrated test system at first provides initiating signal by the industrial computer of each test module to frequency converter, initiating signal after frequency converter will be processed offers adjustable frequency motor, gearbox and generator, behind the generator starting information is fed back to manual/auto control test module and alternating current-direct current controller.Manual/auto control test module and alternating current-direct current controller feed back to alternating current-direct current load and generator according to experimenter's operation steps with associated control signal.Finally whole testing procedure is finished in circulation according to above-mentioned steps.
The utility model airborne power supply system integration testing system can be by choosing the industrial computer test parameter, can realize the automatic test to the different electrical power system, reach unattended purpose, with respect to traditional means of testing, testing efficiency is significantly improved.
The utility model airborne power supply system integration testing system can realize the AC and DC generator of multiple different model is checked by changing dragging on the platform output flange and axle sleeve, greatly improve the compatible practicality of system.
In addition, the utility model airborne power supply system integration testing system can submit dissimilar machines by the software of change industrial computer, DC power distribution unit (PDU) is tested, so that the AC and DC load can be mated according to the AC and DC block terminal of different model, reach test purpose.
Claims (4)
1. airborne power supply integrated test system, it is characterized in that: comprise four test cells and general purpose test equipment, wherein be respectively DC power system test cell [1], AC power supply system test cell [2], distribution logic function test cell [3], external power control and measuring unit [4], each test cell comprises the industrial computer [5] that links to each other in turn, signal process box [6], signal converter [7] and manual/auto control test module [8], wherein, general purpose test equipment links to each other with the manual/auto control test module [8] of each test cell by output channel, and manual/auto control test module [8] is connected to loading interfaces by feedback channel.
2. airborne power supply integrated test system according to claim 1, it is characterized in that: general purpose test equipment comprises signal output source and feedback execution module, wherein the signal output source comprises drag source and display device [9], gearbox [13] and the ground ac-dc power supply [19] that all links to each other with manual/auto control test module [8], and the feedback execution module comprises generator [14], dc controller [15], alternating-current controller [16], DC load [17] and the AC load [18] that also all links to each other with manual/auto control test module [8].
3. airborne power supply integrated test system according to claim 1, it is characterized in that: the signal condition module of each test cell links to each other with loading interfaces.
4. airborne power supply integrated test system according to claim 1 is characterized in that: drag source and display device [9] are comprised of the power distribution cabinet [10], frequency converter [11], the adjustable frequency motor [12] that link to each other in turn.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220077369 CN202676892U (en) | 2012-03-02 | 2012-03-02 | Airborne power supply integrated test system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220077369 CN202676892U (en) | 2012-03-02 | 2012-03-02 | Airborne power supply integrated test system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202676892U true CN202676892U (en) | 2013-01-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 201220077369 Expired - Lifetime CN202676892U (en) | 2012-03-02 | 2012-03-02 | Airborne power supply integrated test system |
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| CN (1) | CN202676892U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104635093A (en) * | 2015-02-27 | 2015-05-20 | 北京精密机电控制设备研究所 | Test device for power consumption feature of electromechanical servo system |
| CN105425767A (en) * | 2015-11-04 | 2016-03-23 | 中国直升机设计研究所 | Method of maintenance equipment for automatically identifying different helicopter types to be tested |
| CN106053976A (en) * | 2016-04-19 | 2016-10-26 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Civil aircraft variable-frequency power supply system power quality detection and analysis system and method |
| CN106569146A (en) * | 2016-11-01 | 2017-04-19 | 四川九洲电器集团有限责任公司 | Power supply module test system and method |
| CN107505529A (en) * | 2017-09-30 | 2017-12-22 | 江西洪都航空工业集团有限责任公司 | A kind of DC power distribution unit (PDU) testing stand |
-
2012
- 2012-03-02 CN CN 201220077369 patent/CN202676892U/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104635093A (en) * | 2015-02-27 | 2015-05-20 | 北京精密机电控制设备研究所 | Test device for power consumption feature of electromechanical servo system |
| CN104635093B (en) * | 2015-02-27 | 2017-07-28 | 北京精密机电控制设备研究所 | A kind of test device of electromechanical servo system electrical characteristics |
| CN105425767A (en) * | 2015-11-04 | 2016-03-23 | 中国直升机设计研究所 | Method of maintenance equipment for automatically identifying different helicopter types to be tested |
| CN105425767B (en) * | 2015-11-04 | 2018-05-18 | 中国直升机设计研究所 | A kind of method of the different types to be measured of maintained equipment automatic identification |
| CN106053976A (en) * | 2016-04-19 | 2016-10-26 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Civil aircraft variable-frequency power supply system power quality detection and analysis system and method |
| CN106569146A (en) * | 2016-11-01 | 2017-04-19 | 四川九洲电器集团有限责任公司 | Power supply module test system and method |
| CN107505529A (en) * | 2017-09-30 | 2017-12-22 | 江西洪都航空工业集团有限责任公司 | A kind of DC power distribution unit (PDU) testing stand |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: JINGDEZHEN CHANGHANG AVIATION HIGH-TECH CO., LTD. Free format text: FORMER OWNER: CHANGHE AIRCRAFT INDUSTRIAL(GROUP) CO., LTD. Effective date: 20130715 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20130715 Address after: 109 box 49, box 333002 (Lv Meng factory area), Jingdezhen, Jiangxi Patentee after: Jingdezhen Changhang Aviation High-Tech Co., Ltd. Address before: 109 mailbox 333002, Jiangxi City, Jingdezhen Province Patentee before: Changhe Aircraft Industries (Group) Co., Ltd. |
|
| CX01 | Expiry of patent term |
Granted publication date: 20130116 |
|
| CX01 | Expiry of patent term |