CN203054590U - Flight control system regular detection device - Google Patents
Flight control system regular detection device Download PDFInfo
- Publication number
- CN203054590U CN203054590U CN 201220669225 CN201220669225U CN203054590U CN 203054590 U CN203054590 U CN 203054590U CN 201220669225 CN201220669225 CN 201220669225 CN 201220669225 U CN201220669225 U CN 201220669225U CN 203054590 U CN203054590 U CN 203054590U
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- flight control
- control system
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Abstract
The utility model provides a flight control system regular detection device, which can improve the working efficiency and shorten the maintenance time. The technical scheme is that, the device comprises a cable, a product connection socket and a measuring terminal, wherein a plug at one end of the cable is connected with an interface of a device to be detected of the flight control system, a plug at the other end of the cable is connected with the product connection socket, the interface of the device to be detected of the flight control system has pins corresponding to pins of the product connection socket through the cable, the product connection socket is connected with the measuring terminal, and the measuring terminal has a jack corresponding to the pins of the product connection socket.
Description
Technical field
The utility model belongs to the flight control system detection range, relates to the regular pick-up unit of a kind of flight control system.
Background technology
The helicopter flight control system is mainly used in improving the maneuverability of helicopter, stable quality.In the 200h regular working of every interval, need the connect maintenance overhaul work of electric steering engine and bar displacement transducer of flight control system, it is limited by the installation site, and service clearance is narrow and small, can't realize in situ detection, the measurement of need offing normal.Off normal and measure not only dismounting complexity, need multiple ground handling equipment simultaneously, after finishing detection, need the control linkage of full machine is readjusted, need great amount of manpower and material resources, and the work period is longer, greatly reduced work efficiency.
The utility model content
Utility model purpose: provide a kind of flight control system regular pick-up unit, can increase work efficiency, shorten and safeguard the guarantee time.
Technical scheme: the regular pick-up unit of a kind of flight control system comprises:
Cable, product gang socket, measurement terminal, cable one end plug connects flight control system equipment under test interface, cable other end plug connects product gang socket, the contact pin of flight control system equipment under test interface is corresponding with the contact pin of product gang socket by cable, product gang socket is connected with measurement terminal, and the jack of measurement terminal is corresponding with the contact pin of product gang socket.
Beneficial effect: flight control system by transit cable, links to each other the measurement terminal of the disconnection piece on tested contact pin and the test box panel when using the utility model to carry out ground maintenance to detect, and only needs two ad hoc professionals can finish this system testing and operates.Adopt the method when guaranteeing the test result accuracy, largely reduced the required personnel of this work and safeguarded support equipment, greatly improved work efficiency, shorten and safeguard the guarantee time, ensured the progress that scientific research is taken a flight test simultaneously.
Description of drawings
Fig. 1 is the utility model disconnection piece test section synoptic diagram.
Fig. 2 connects piece annexation synoptic diagram for flight control system series connection steering wheel and bar displacement transducer test box section in the utility model.
Fig. 3 is flight control system series connection steering wheel and bar displacement transducer test box annexation synoptic diagram in the utility model.
Embodiment
The utility model provides a kind of flight control system regular pick-up unit, comprising:
Cable, product gang socket, measurement terminal, cable one end plug connects flight control system equipment under test interface, cable other end plug connects product gang socket, the contact pin of flight control system equipment under test interface is corresponding with the contact pin of product gang socket by cable, product gang socket is connected with measurement terminal, and the jack of measurement terminal is corresponding with the contact pin of product gang socket.
Embodiment
The test box panel of the utility model embodiment is made up of 2 parts: disconnection piece test section (being provided with measurement terminal) and attachment plug district (being provided with product gang socket).
As shown in Figure 1, the left side is series connection steering wheel test section in the disconnection piece test section, can test one by one four series connection steering wheels, the A district links to each other with cable on the machine, the B district links to each other with steering wheel, and contact pin is corresponding one by one, can measure the output impedance of servoamplifier and the resistance of steering wheel respectively by A district and B district; The right side of disconnection piece test section is bar displacement transducer test section, and same, its A district and B district can measure the output impedance of flight control computer and the resistance of bar displacement transducer respectively.In addition, adopt the short circuit sheet A, B can be linked to each other at 2, soon cable is communicated with product on the machine.
This test box is considered the requirement that use in the outfield in design, have simple in structure, characteristics such as panel is clear, sign is clear and definite, be easy to carry.
As Fig. 2, shown in Figure 3, when measuring series connection steering wheel and bar displacement transducer resistance, respective cable is ready to, one end links to each other with the butt joint of product (namely connect steering wheel and bar displacement transducer) socket, one end links to each other with the butt joint of test box socket, confirm to connect firm after, directly number measure in hole, correspondence B district, the corresponding test section of test box disconnection piece with the test pencil of avometer and to get final product.
Measure the output impedance of servoamplifier or flight control computer as needs, also be according to flight control system series connection steering wheel and bar displacement transducer test box annexation among Fig. 3, respective cable is ready to, one end links to each other with the butt joint of product (namely connect steering wheel and bar displacement transducer) plug, one end links to each other with the butt joint of test box socket, confirm to connect firm after, directly number measure in hole, corresponding A district, the corresponding test section of test box disconnection piece with the test pencil of avometer and to get final product.
Flight control system series connection steering wheel and bar displacement transducer test box are that flight control system periodic maintenance inspection is from now on had laid a good foundation, for maintainability, the maintainability that improves helicopter provides important leverage, saved a large amount of maintenance, repair time, avoided greatly damaging because deciding repeated disassembled and assembled equipment causes in the overhaul period maintenance mistake and parts, reduce maintenance cost, improved the attendance rate.
The utility model is simple in structure, and panel is clear, sign is clear and definite, (specification: 30cm*25cm*30cm) is easy to carry;
The utility model transit cable transfer impedance to the test box disconnection piece line is no more than 1 Ω;
The utility model disconnection piece, disconnection is convenient, and contact is reliable, and measurement data is accurate;
The utility model has improved the maintainability of helicopter, makes flight control system examine work surely, and 88 groups of measurement data can not be accomplished to this equipment of use from situ detection and finish in 1 hour;
The utility model has improved the maintainability of helicopter, but uses this equipment fast detecting flight control system core component: the output impedance of servoamplifier, flight control computer, and the resistance of series connection steering wheel, bar displacement transducer is for quick repair system provides important leverage;
The utility model is saved manpower 4 people, saves time 3-5 days, saves support equipment (supply vehicle, dedicated ground hydraulic pressure car) each one time, saves common tool, specific purpose tool is some;
The utility model testing amount big (3-5 days) of avoiding offing normal, measurement data is inaccurate, incurs loss through delay the attendance rate;
The utility model is avoided offing normal and is detected maintenance mistake, the parts that repeated disassembled and assembled equipment causes and damage;
The utility model has been saved the maintenance, repair time, has reduced the maintenance, repair cost; Improve the attendance rate of type, strengthened the quick reaction operations ability of type.
Claims (1)
1. the regular pick-up unit of flight control system is characterized in that, comprising:
Cable, product gang socket, measurement terminal, cable one end plug connects flight control system equipment under test interface, cable other end plug connects product gang socket, the contact pin of flight control system equipment under test interface is corresponding with the contact pin of product gang socket by cable, product gang socket is connected with measurement terminal, and the jack of measurement terminal is corresponding with the contact pin of product gang socket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220669225 CN203054590U (en) | 2012-12-07 | 2012-12-07 | Flight control system regular detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220669225 CN203054590U (en) | 2012-12-07 | 2012-12-07 | Flight control system regular detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203054590U true CN203054590U (en) | 2013-07-10 |
Family
ID=48737523
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220669225 Expired - Fee Related CN203054590U (en) | 2012-12-07 | 2012-12-07 | Flight control system regular detection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203054590U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106681309A (en) * | 2017-02-15 | 2017-05-17 | 合肥市融宇电子有限公司 | Comprehensive test platform for unmanned aerial vehicle |
| CN108121329A (en) * | 2018-02-14 | 2018-06-05 | 中国人民解放军第四三二八工厂 | Supply vehicle measurement and control system, method, supply vehicle, computer system and medium |
-
2012
- 2012-12-07 CN CN 201220669225 patent/CN203054590U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106681309A (en) * | 2017-02-15 | 2017-05-17 | 合肥市融宇电子有限公司 | Comprehensive test platform for unmanned aerial vehicle |
| CN106681309B (en) * | 2017-02-15 | 2019-08-23 | 合肥市融宇电子有限公司 | A kind of unmanned plane comprehensive test platform |
| CN108121329A (en) * | 2018-02-14 | 2018-06-05 | 中国人民解放军第四三二八工厂 | Supply vehicle measurement and control system, method, supply vehicle, computer system and medium |
| CN108121329B (en) * | 2018-02-14 | 2024-04-12 | 中国人民解放军第四三二八工厂 | Power supply vehicle data measurement and control system and method, power supply vehicle, computer system and medium |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130710 Termination date: 20191207 |