CN112558582A - Helicopter avionics-based distributed in-situ troubleshooting device and method - Google Patents
Helicopter avionics-based distributed in-situ troubleshooting device and method Download PDFInfo
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- CN112558582A CN112558582A CN202011200085.XA CN202011200085A CN112558582A CN 112558582 A CN112558582 A CN 112558582A CN 202011200085 A CN202011200085 A CN 202011200085A CN 112558582 A CN112558582 A CN 112558582A
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0259—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterized by the response to fault detection
- G05B23/0262—Confirmation of fault detection, e.g. extra checks to confirm that a failure has indeed occurred
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/24—Pc safety
- G05B2219/24065—Real time diagnostics
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Abstract
The invention relates to a distributed in-situ troubleshooting device and method based on helicopter avionics. The device comprises: the system comprises a server end, a test front end and portable generator dragging equipment; the server communicates with other equipment to realize signal acquisition and simulation of each test front end and the portable generator dragging equipment; the portable generator dragging equipment is used for simulating the characteristics of a full-aircraft power supply when the helicopter flies on the ground; the test front end consists of a mainboard and a functional resource board card; the test front end mainboard is provided with a matrix addressing module, and addressing calling is carried out on each functional resource board card interface according to different test contents and requirements; the method and the system establish the distributed in-situ fault diagnosis device comprising the test front end, the server end, the remote control end and the portable generator dragging equipment to realize the distributed in-situ fault diagnosis of the helicopter avionic system, improve the fault diagnosis efficiency and accuracy, reduce the risk of troubleshooting the helicopter avionic system and improve the intelligent level of the helicopter fault diagnosis.
Description
Technical Field
The invention belongs to a fault diagnosis technology of an airborne avionics system, and relates to a distributed in-situ fault troubleshooting device and method based on helicopter avionics.
Background
The helicopter is in a relatively special technical environment when delivered to a user for use, more and more complex functional performance faults of an airborne avionic system can occur, the traditional fault troubleshooting method mainly depends on a testing instrument and a special tool to perform troubleshooting by combining a manual testing test, and the troubleshooting period is longer when the system is in cross-linking, the ground is difficult to reproduce and other complex faults occur. When the tension test flight progress and the user flight progress are carried out, the condition that the helicopter cannot fly due to faults often occurs. Moreover, the troubleshooting process can only be performed to the location of the Line Replaceable Unit (LRU) level on-board product, which often results in product ablation and other risks due to the false product replacement when the fault cause is not accurately located.
The traditional helicopter avionics troubleshooting mode mainly depends on a testing instrument and a special tool to carry out troubleshooting by combining manual experience, and when complex faults such as system cross-linking and the like are encountered, the faults are very difficult to locate, the troubleshooting efficiency is low, and the troubleshooting risk is high.
1) A fault diagnosis system and method for an intelligent switch cabinet, CN201210281754.X, discloses a fault diagnosis system and method for an intelligent switch cabinet, comprising a lower computer, a real-time database and an expert system, which improves the efficiency and accuracy of equipment fault diagnosis and the reliability of equipment operation.
2) A universal automatic test and fault diagnosis system, CN201310375453.8, discloses a universal automatic test and fault diagnosis system, which comprises a universal automatic test platform, an input/output device and an interface adapter, can automatically test and diagnose twelve types of communication devices, and has high diagnosis efficiency and accurate diagnosis result.
3) A remote monitoring and fault diagnosis system for a numerical control machine tool, CN201210014168.9, discloses a remote monitoring and fault diagnosis system for a numerical control machine tool, which comprises an information acquisition module, an information transmission module and a remote service management and expert system module, realizes the seamless butt joint of wireless and wired networks of the machine tool fault diagnosis system, and carries out all-round all-weather diagnosis service on the machine tool provided with the fault diagnosis system.
At present, the fault intelligent fault diagnosis technology is widely applied to industries such as machine tools, communication, automobiles and the like, but the fault diagnosis mode of a helicopter avionics system still remains to be tested by a traditional simple test tool, and the degree of integration, automation and intelligence is not high.
Disclosure of Invention
The purpose of the invention is: providing a distributed in-situ troubleshooting device and method based on helicopter avionics; the method solves the problem that the trial flight and the out-of-field maintenance progress of the helicopter is seriously restricted by low troubleshooting efficiency, inaccurate fault location, high troubleshooting risk and the like in the trial flight process and out-of-field operation maintenance of the current helicopter, improves the technical level of the helicopter avionics professional fault diagnosis process, establishes the high-efficiency and intelligent helicopter avionics in-situ test capability of the helicopter for quickly and accurately locating the fault and guaranteeing flight safety.
In order to solve the technical problem, the technical scheme of the invention is as follows: .
A distributed in-situ troubleshooting device based on helicopter avionics, said distributed in-situ troubleshooting device comprising: the system comprises a server end, a test front end and portable generator dragging equipment;
the server side is a core device in the troubleshooting device, is connected with other devices through a network cable, establishes local area network communication, is used as an upper computer to carry out comprehensive centralized control on the other devices, realizes signal acquisition and simulation of each test front end and the portable generator dragging device, has troubleshooting software, can carry out automatic test according to the troubleshooting logic of the helicopter airborne avionic system, carries out machine learning, establishes a fault resource library, and maps a display control picture to a handheld terminal;
portable generator drags equipment for full quick-witted power characteristic when ground simulation helicopter flies, the helicopter alternator carries out full quick-witted power supply after rotating through the rotor, for at ground simulation flight state, drags equipment through portable generator, drives the generator operation, reaches full quick-witted power characteristic when flight state.
The test front end is distributed around a helicopter parking apron or a hangar according to the installation position of the airborne equipment of the helicopter, so that in-situ fault troubleshooting can be carried out without disassembling and assembling the airborne equipment.
The test front end consists of a mainboard and a functional resource board card, and the signal types of each system are decomposed and summarized by adopting a comprehensive design; the test front end mainboard is provided with a matrix type 256-path addressing module, and addressing calling is carried out on each functional resource board card interface according to different test contents and requirements; according to the definition of the tested airborne equipment interface, signals are distinguished, and the same signal attribute interface is summarized to the functional resource board card for testing and excitation;
the method is divided into a wired connection testing front end and a wireless testing front end according to the connection mode with the airborne avionics equipment.
The functional resource board card comprises: switching value board card, acquisition board card, signal generator board card, universal meter board card, oscilloscope board card, 422 board card.
Preferably, the distributed in-situ troubleshooting device based on helicopter avionics further comprises a remote control end, a handheld display control device is used for troubleshooting personnel, a good man-machine interaction interface is provided, and ground troubleshooting personnel can call a needed troubleshooting test interface only through the remote control end to control an operation instruction of the distributed in-situ troubleshooting device;
the wired connection test front end is respectively connected with an airborne equipment end and an onboard cable end through a three-way adapter cable; a power supply system, an automatic power distribution system, an electromechanical management system, an electric fly-by-wire system and a system electrical system testing front end are respectively configured according to the airborne avionic system of the helicopter.
The wireless test front end is used for comprehensively testing an airborne radio system to realize wireless communication of helicopter communication, navigation and identification;
the server is connected with other equipment in a wired or wireless mode.
Preferably, the number of the wired connection test front ends and the wireless test front ends is configured according to working requirements.
Preferably, the server side is provided with 1 server, comprises a network switch, is provided with helicopter avionics distributed in-situ troubleshooting software and is externally connected with 220V alternating current. Fault diagnosis software exists in the server, and the fault diagnosis software is divided into manual test, in-situ verification and health monitoring modes
The manual test refers to that under an operation software interface, the configuration simulation quantity and the test acquisition are respectively carried out by an operator according to different tested systems;
the in-situ verification refers to carrying out system flow automatic verification test according to preset verification test contents and automatically outputting a conclusion;
the health monitoring is applied to a multi-system common test process, when a plurality of mutually cross-linked airborne equipment test front ends are accessed, the monitored front ends are selected to be put into a health monitoring mode, and different function variables of other test front ends are changed, so that complex faults caused by cross-linking factors among systems can be reproduced.
Preferably, the number of the remote control ends is 2. The testing front end is provided with 6, wherein 5 are wired connection testing front ends, and the wired testing front ends are respectively provided with an overvoltage and overcurrent protection module and are provided with 5 sets of three-way testing cables. The test system comprises a PSP test front end, a front-back load test front end, an electromechanical management test front end, a generator GCU test front end and an electric transmission flight control test front end, and airborne equipment is tested respectively.
Preferably, the portable generator dragging equipment is provided with 3 external 220V alternating currents.
On the other hand, the invention provides a distributed in-situ troubleshooting method based on helicopter avionics, which comprises the following steps:
step one, fault information input:
after the helicopter completes a flight task, receiving a fault phenomenon fed back by a pilot, and recording the ID and fault information of the helicopter;
step two, accessing a fault test front end and judging whether the fault test front end is newly generated fault information;
if the fault information is new fault information, automatically carrying out circuit logic detection, judging whether the fault information is a fault caused by cable aging, abrasion, open circuit and short circuit, accessing the fault caused by non-circuits to a fault front end of a related airborne system, carrying out signal acquisition and simulation on related airborne equipment through a test front end, simulating the technical state of a helicopter when a flight fault occurs, reproducing the fault moment, carrying out health monitoring on all related airborne equipment, identifying abnormal signals, positioning the fault and recording the fault information;
if the fault information is the fault information which appears before, the relevant fault information in the fault library is called out, fault trees are listed, the troubleshooting test is carried out one by one, and if the fault can not be positioned, the new fault is considered to be debugged.
The invention has the beneficial effects that:
a distributed in-situ troubleshooting method and equipment based on helicopter avionics are based on a test principle of a helicopter airborne avionics system, decompose and integrate attributes of tested signals, adopt a comprehensive and automatic design, realize signal acquisition, signal simulation excitation, health monitoring and simulation of helicopter technical state and troubleshooting, establish machine learning capacity, simplify troubleshooting steps and effectively protect the airborne avionics. The helicopter test system comprises a server end, a remote control end, a test front end and portable generator dragging equipment, can quickly and accurately position the avionic faults of the helicopter, and improves the test flight process and the outfield flight guarantee capability of the helicopter.
The invention designs that each test front section is distributed in a helicopter parking apron or a helicopter garage according to the principle of near, realizes in-situ fault troubleshooting without dismounting airborne avionic equipment, can realize signal acquisition, signal simulation excitation, technical state simulation and automatic fault diagnosis for the helicopter airborne avionic equipment, has machine learning capacity, replaces the original artificial experience troubleshooting mode, automatically retrieves the original fault information and lists fault trees, and arranges personnel reference for the fault, has power protection design, effectively prevents the airborne avionic equipment from being ablated in the troubleshooting test, can realize rapid fault positioning, and effectively improves the trial flight process of the helicopter and the capacity of guaranteeing the off-site flight of a client.
According to the invention, the distributed in-situ fault diagnosis of the helicopter avionics system is realized by establishing the test front end, the server end, the remote control end and the portable generator dragging equipment according to the signal attributes of the airborne avionics equipment, so that the fault diagnosis efficiency and accuracy are improved, the risk of the helicopter avionics system during fault troubleshooting is reduced, and the intelligent level of the helicopter fault diagnosis is improved.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings used in the embodiment of the present invention will be briefly explained. It is obvious that the drawings described below are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be obtained from these drawings without inventive effort.
FIG. 1 is a schematic diagram of a distributed in-situ troubleshooting apparatus based on helicopter avionics;
FIG. 2 is a flow chart of a distributed in-situ troubleshooting method based on helicopter avionics;
FIG. 3 is a schematic diagram of a wired test front end test mode;
FIG. 4 is a schematic diagram of a wireless test front end test mode;
wherein, 1, the portable generator drags the apparatus; 2. a server side; 3. a remote control end; 4. test front end 1; 5. a test front end 2; 6. a test front end 3; 7. a test front end 4; 8. a test front-end 5; 9. a test front end 6; 10. the helicopter to be tested.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Features of various aspects of embodiments of the invention will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without these specific details. The following description of the embodiments is merely intended to better understand the present invention by illustrating examples thereof. The present invention is not limited to any particular arrangement or method provided below, but rather covers all product structures, any modifications, alterations, etc. of the method covered without departing from the spirit of the invention.
In the drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the present invention.
Fig. 1 shows a helicopter avionics based distributed in-situ troubleshooting apparatus. A distributed in-situ troubleshooting device based on helicopter avionics mainly comprises a server end, a remote control end, a test front end and a portable generator dragging device. The server side is a core device in the troubleshooting device, is connected with other devices through a network cable, establishes local area network communication, performs comprehensive centralized control on the other devices, realizes signal acquisition and simulation of each test front end and the portable generator dragging device, has troubleshooting software, can perform automatic test according to the troubleshooting logic of the helicopter airborne avionic system, performs machine learning, establishes a fault resource library, and maps a display control picture to the handheld terminal; the remote control end is used for the troubleshooting personnel to hold the display control equipment, a good man-machine interaction interface is provided, and the ground troubleshooting personnel can call a needed troubleshooting test interface only through the remote control end to control the operation instruction of the troubleshooting equipment; the test front end is distributed around the helicopter apron or the hangar according to the principle of proximity, and in-situ fault troubleshooting is realized without dismounting airborne equipment. The method is divided into a wired connection testing front end and a wireless testing front end according to the connection mode with the airborne avionics equipment. The wired connection test front end is provided with a three-way adapter cable which is respectively connected to the test front end, the airborne equipment end and the airborne cable end, the signal types of all systems are decomposed and summarized by adopting a comprehensive design, measurement and signal excitation are uniformly carried out by various resource board cards (a switching value board card, an acquisition board card, a signal generator board card, a universal meter board card and the like), and the test front end of a power supply system, an automatic power distribution system, an electromechanical management system, an electric flight control system and a system electrical system is respectively configured according to the airborne avionics system of the helicopter. The wireless test front end is used for comprehensively testing an airborne radio system to realize wireless communication of helicopter communication, navigation and identification; the portable generator dragging equipment is characterized in that the helicopter alternating-current generator is powered by the whole helicopter after rotating through a rotor wing, and the portable generator dragging equipment drives the generator to operate to simulate a flight state on the ground so as to achieve the characteristic of a power supply of the whole helicopter in the flight state.
The server side is provided with 1 server, comprises a network switch, is provided with helicopter avionics distributed in-situ troubleshooting software and is externally connected with 220V alternating current.
Therefore, a whole equipment communication network can be established through the server side, and automatic measurement, signal acquisition, signal simulation excitation and intelligent fault analysis can be carried out according to a fault troubleshooting method.
The remote control end is provided with 2.
Therefore, the remote control of troubleshooting personnel can be realized, and a required test interface can be called.
The testing front end is provided with 6, wherein 5 are wired connection testing front ends, 1 radio comprehensive testing front end, and the wired testing front ends are provided with overvoltage and overcurrent protection modules and are provided with 5 sets of three-way testing cables.
Therefore, distributed in-situ troubleshooting of the helicopter can be realized, signal acquisition, simulation excitation and helicopter health monitoring are realized.
The portable generator dragging equipment is provided with 3 external 220V alternating current.
Therefore, the characteristic power supply of the onboard power supply under the flight state of the helicopter can be simulated, the flight state related technical state of the full-aircraft airborne avionics system can be monitored, and the flight fault which cannot occur in the ground state can be reproduced.
Fig. 2 shows a helicopter avionics based distributed in-situ troubleshooting apparatus. After the helicopter completes a flight task, receiving a fault phenomenon fed back by a pilot, and recording the ID and fault information of the helicopter; accessing a fault test front end and judging whether the fault test front end is newly generated fault information; if the fault information is new fault information, automatically carrying out circuit logic detection, judging whether the fault information is a fault caused by cable aging, abrasion, open circuit and short circuit, accessing the fault caused by non-circuits to a fault front end of a related airborne system, carrying out signal acquisition and simulation on related airborne equipment through a test front end, simulating the technical state of a helicopter when a flight fault occurs, reproducing the fault moment, carrying out health monitoring on all related airborne equipment, identifying abnormal signals, positioning the fault and recording the fault information; if the fault information is the fault information which appears before, the relevant fault information in the fault library is called out, fault trees are listed, the troubleshooting test is carried out one by one, and if the fault can not be positioned, the new fault is considered to be debugged.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the scope of the present invention.
Claims (8)
1. The utility model provides a distributed normal position troubleshooting device based on helicopter avionics which characterized in that: the helicopter avionics-based distributed in-situ troubleshooting device comprises: the system comprises a server end, a test front end and portable generator dragging equipment;
the server communicates with other equipment and is used as an upper computer to carry out comprehensive centralized control on the other equipment, so that signal acquisition and simulation of each test front end and the portable generator dragging equipment are realized;
the portable generator dragging equipment is used for simulating the characteristics of a full-aircraft power supply when the helicopter flies on the ground;
the test front end is distributed around a helicopter parking apron or a hangar according to the installation position of airborne equipment of the helicopter and consists of a main board and a functional resource board card;
the test front end mainboard is provided with a matrix addressing module, and addressing calling is carried out on each functional resource board card interface according to different test contents and requirements; according to the definition of the tested airborne equipment interface, signals are distinguished, and the same signal attribute interface is summarized to the functional resource board card for testing and excitation;
the method is divided into a wired connection testing front end and a wireless testing front end according to the connection mode with the airborne avionics equipment.
2. A helicopter avionics-based distributed in-situ troubleshooting apparatus in accordance with claim 1 wherein: the functional resource board card comprises: switching value board card, acquisition board card, signal generator board card, universal meter board card, oscilloscope board card, 422 board card.
3. A helicopter avionics-based distributed in-situ troubleshooting apparatus in accordance with claim 1 wherein: the distributed in-situ troubleshooting device based on the helicopter avionics further comprises a remote control end, a display control device is held by the remote control end for troubleshooting personnel, and ground troubleshooting personnel can call a needed troubleshooting test interface through the remote control end to control an operation instruction of the distributed in-situ troubleshooting device.
4. A helicopter avionics-based distributed in-situ troubleshooting apparatus in accordance with claim 1 wherein: the wired connection test front end is respectively connected with an airborne equipment end and an onboard cable end through a three-way adapter cable;
a power supply system, an automatic power distribution system, an electromechanical management system, an electric fly-by-wire system and a system electrical system testing front end are respectively configured according to the airborne avionic system of the helicopter.
5. A helicopter avionics-based distributed in-situ troubleshooting apparatus in accordance with claim 1 wherein: the wireless test front end is used for comprehensive test of an airborne radio system, and wireless communication of helicopter communication, navigation and identification is realized.
6. A helicopter avionics-based distributed in-situ troubleshooting apparatus in accordance with claim 1 wherein: the server is connected with other equipment in a wired or wireless mode.
7. A helicopter avionics-based distributed in-situ troubleshooting apparatus in accordance with claim 1 wherein: the number of the wired connection test front ends and the number of the wireless test front ends are configured according to working requirements.
8. A distributed in-situ troubleshooting method based on helicopter avionics, based on the distributed in-situ troubleshooting device based on helicopter avionics of claim 1, characterized in that: the helicopter avionics-based distributed in-situ troubleshooting method comprises the following steps:
step one, fault information input:
after the helicopter completes a flight task, receiving a fault phenomenon fed back by a pilot, and recording the ID and fault information of the helicopter;
step two, accessing a fault test front end and judging whether the fault test front end is newly generated fault information;
if the fault information is new fault information, automatically carrying out circuit logic detection, judging whether the fault information is a fault caused by cable aging, abrasion, open circuit and short circuit, accessing the fault caused by non-circuits to a fault front end of a related airborne system, carrying out signal acquisition and simulation on related airborne equipment through a test front end, simulating the technical state of a helicopter when a flight fault occurs, reproducing the fault moment, carrying out health monitoring on all related airborne equipment, identifying abnormal signals, positioning the fault and recording the fault information;
if the fault information is the fault information which appears before, the relevant fault information in the fault library is called out, fault trees are listed, the troubleshooting test is carried out one by one, and if the fault can not be positioned, the new fault is considered to be debugged.
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| CN202011200085.XA CN112558582A (en) | 2020-10-30 | 2020-10-30 | Helicopter avionics-based distributed in-situ troubleshooting device and method |
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| CN202011200085.XA CN112558582A (en) | 2020-10-30 | 2020-10-30 | Helicopter avionics-based distributed in-situ troubleshooting device and method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113504720A (en) * | 2021-09-07 | 2021-10-15 | 中国商用飞机有限责任公司 | Backup control system based on distributed fly-by-wire architecture and working method |
| CN113687992A (en) * | 2021-09-06 | 2021-11-23 | 天津津航计算技术研究所 | Onboard equipment power-on and power-off test method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102915029A (en) * | 2012-10-15 | 2013-02-06 | 中国运载火箭技术研究院 | Avionics system automatic test platform based on reusable spacecraft |
| 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 |
| CN207258013U (en) * | 2017-10-13 | 2018-04-20 | 北京安达维尔测控技术有限公司 | A kind of Mini Tele-Copter flight control system in situ detection equipment |
| CN207833324U (en) * | 2017-11-17 | 2018-09-07 | 北京安达维尔测控技术有限公司 | Aircraft floor flight control system in situ detection equipment |
-
2020
- 2020-10-30 CN CN202011200085.XA patent/CN112558582A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102915029A (en) * | 2012-10-15 | 2013-02-06 | 中国运载火箭技术研究院 | Avionics system automatic test platform based on reusable spacecraft |
| 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 |
| CN207258013U (en) * | 2017-10-13 | 2018-04-20 | 北京安达维尔测控技术有限公司 | A kind of Mini Tele-Copter flight control system in situ detection equipment |
| CN207833324U (en) * | 2017-11-17 | 2018-09-07 | 北京安达维尔测控技术有限公司 | Aircraft floor flight control system in situ detection equipment |
Non-Patent Citations (3)
| Title |
|---|
| 吴国宝等: "某型直升机机载电子***原位检测设计与实现", 《计算机测量与控制》 * |
| 孟文杰等: "某型直升机飞控操纵台自动点灯故障及排故原理", 《中国科技信息》 * |
| 张鹏: "MA600飞机电子飞行仪表***比较器不工作告警问题研究", 《信息与电脑(理论版)》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113687992A (en) * | 2021-09-06 | 2021-11-23 | 天津津航计算技术研究所 | Onboard equipment power-on and power-off test method |
| CN113687992B (en) * | 2021-09-06 | 2024-04-19 | 天津津航计算技术研究所 | Method for electrifying and electrifying test of airborne equipment |
| CN113504720A (en) * | 2021-09-07 | 2021-10-15 | 中国商用飞机有限责任公司 | Backup control system based on distributed fly-by-wire architecture and working method |
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Application publication date: 20210326 |