CN112722323A - Rotorcraft avionics system fault detection device - Google Patents
Rotorcraft avionics system fault detection device Download PDFInfo
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- CN112722323A CN112722323A CN202110054240.XA CN202110054240A CN112722323A CN 112722323 A CN112722323 A CN 112722323A CN 202110054240 A CN202110054240 A CN 202110054240A CN 112722323 A CN112722323 A CN 112722323A
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- 238000001514 detection method Methods 0.000 title claims abstract description 147
- 238000004088 simulation Methods 0.000 claims abstract description 34
- 239000010705 motor oil Substances 0.000 claims description 11
- 239000003921 oil Substances 0.000 claims description 8
- 238000012423 maintenance Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 4
- 238000012360 testing method Methods 0.000 description 3
- 230000008054 signal transmission Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention is suitable for the technical field of gyroplanes, and provides a gyroplane avionics system fault detection device, which comprises: the device comprises a first detection module, a second detection module, a third detection module and a fourth detection module; the first detection module is used for judging whether an engine system fails or not by sending an engine start-stop simulation signal to the engine system of the gyroplane; the second detection module judges whether the function execution part fails by sending a function control analog signal to the function execution part of the function system of the rotorcraft; the third detection module is used for judging whether the instrument system is in fault or not by sending an engine parameter simulation signal to the instrument system of the gyroplane; the fourth detection module determines whether the functional control section is malfunctioning by receiving a functional control signal sent by the functional control section of the functional system of the rotorcraft. The invention can find the faults existing in the avionic system of the rotorcraft in time, can accurately indicate the fault positions, and improves the assembly and maintenance efficiency of the rotorcraft.
Description
Technical Field
The invention belongs to the technical field of gyroplanes, and particularly relates to a fault detection device for an avionic system of a gyroplane.
Background
The avionics system, which is known as an integrated avionics system, is an important component of a rotorcraft.
The inventor of this application discovers, at the gyroplane assembly in-process, goes on in sections to the assembly of gyroplane avionics system usually, can test the avionics system after the whole equipment of gyroplane is accomplished, so if find the gyroplane avionics system to have the trouble when testing, just need disassemble the gyroplane and look for the fault point, waste time and energy, greatly reduced the packaging efficiency of gyroplane.
Disclosure of Invention
In view of this, the embodiment of the present invention provides a device for detecting a failure of an avionic system of a rotorcraft, so as to test the avionic system of the rotorcraft during an assembly process of the rotorcraft, thereby improving the assembly efficiency of the rotorcraft.
The embodiment of the invention provides a rotorcraft avionics system fault detection device, which comprises:
the device comprises a first detection module, a second detection module, a third detection module and a fourth detection module;
the first detection module is used for generating an engine start-stop analog signal and sending the engine start-stop analog signal to an engine system of the rotorcraft, and the working state of the engine system is used for indicating the fault state of the engine system;
the second detection module is used for generating a function control analog signal and sending the function control analog signal to a function execution part of a function system of the rotorcraft, and the function execution state of the function execution part is used for indicating the fault state of the function execution part;
the third detection module is used for generating an engine parameter analog signal and sending the engine parameter analog signal to an instrument system of the gyroplane, and at the moment, an instrument display state of the instrument system is used for indicating a fault state of the instrument system;
the fourth detection module is a simulation module of a function execution part of a functional system of the rotorcraft, and is used for receiving a function control signal sent by the function control part of the functional system of the rotorcraft, executing a preset action according to the function control signal, and the action execution state of the fourth detection module at this moment is used for indicating the fault state of the function control part.
Optionally, the first detection module includes:
an engine start-stop analog signal generator;
the engine start-stop analog signal generator is used for generating an engine start-stop analog signal and sending the engine start-stop analog signal to an engine system of the rotorcraft, and at the moment, the working state of the engine system is used for indicating the fault state of the engine system.
Optionally, the second detection module includes:
at least one function control analog signal generator;
at least one function control analog signal generator corresponds to each function system of the gyroplane one by one; the function control analog signal generator is used for generating a function control analog signal and sending the function control analog signal to a function execution part of a function system of the rotorcraft, and the function execution state of the function execution part at the moment is used for indicating the fault state of the function execution part.
Optionally, the third detecting module includes:
at least one third detection unit;
the at least one third detection unit corresponds to each display instrument in an instrument system of the gyroplane one by one, and comprises an engine parameter analog signal generator and a control switch;
the engine parameter analog signal generator is used for generating a preset engine parameter analog signal and sending the engine parameter analog signal to a display instrument in an instrument system of the gyroplane, and the reading of the display instrument is used for indicating the fault state of the display instrument;
the control switch is used for controlling the on-off state of the engine parameter analog signal generator.
Optionally, the fourth detecting module includes:
at least one fourth detection unit;
the at least one fourth detection unit corresponds to each functional system of the gyroplane one by one; the fourth detection unit comprises a load and an indicator light, wherein the load is used for receiving a function control signal sent by a function control part of a function system of the rotorcraft;
the indicator lamp is used for displaying the loop electrifying state of the load, and the loop electrifying state of the load is used for indicating the fault state of the function control part.
Optionally, the engine parameter simulation signal comprises:
the engine oil pressure simulation device comprises an engine rotating speed simulation signal, an oil mass simulation signal, a rotating speed simulation signal, an engine temperature simulation signal, an engine oil pressure simulation signal and an engine oil temperature simulation signal.
Optionally, the function control analog signal includes:
an oil pump control analog signal, a fan control analog signal, a strobe control analog signal, an air pump control analog signal, or a trim control analog signal.
Optionally, the rotorcraft avionics system fault detection device further comprises:
a power supply module;
the power module is used for supplying power to the first detection module, the second detection module, the third detection module and the fourth detection module.
Compared with the prior art, the embodiment of the invention has the following beneficial effects:
the device for detecting the faults of the avionic system of the gyroplane is provided with a first detection module, a second detection module, a third detection module and a fourth detection module, wherein the first detection module is used for generating an engine start-stop analog signal to detect the faults of an engine system of the gyroplane, the second detection module is used for generating a function control analog signal to detect the faults of a function execution part of a function system of the gyroplane, the third detection module is used for generating an engine parameter analog signal to detect the faults of an instrument system of the gyroplane, and the fourth detection module is used for simulating the function execution part of the function system of the gyroplane to detect the faults of the function control part of the function system of the gyroplane. According to the invention, each component of the rotorcraft avionics system is simulated through each detection module, so that each component of the rotorcraft avionics system can be tested even if the rotorcraft is not assembled, faults existing in the rotorcraft avionics system can be found in time, the fault position can be accurately indicated, and the assembly and maintenance efficiency of the rotorcraft is improved.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without inventive exercise.
Fig. 1 is a schematic structural diagram of a rotorcraft avionics system fault detection device provided by an embodiment of the present invention.
Detailed Description
In the following description, for purposes of explanation and not limitation, specific details are set forth, such as particular system structures, techniques, etc. in order to provide a thorough understanding of the embodiments of the invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced in other embodiments that depart from these specific details. In other instances, detailed descriptions of well-known systems, devices, circuits, and methods are omitted so as not to obscure the description of the present invention with unnecessary detail.
In order to explain the technical means of the present invention, the following description will be given by way of specific examples.
An embodiment of the present invention provides a rotorcraft avionics system fault detection apparatus, as shown in fig. 1, the rotorcraft avionics system fault detection apparatus 1 includes:
a first detection module 11, a second detection module 12, a third detection module 13 and a fourth detection module 14.
The first detection module 11 is configured to generate an engine start/stop analog signal, and send the engine start/stop analog signal to an engine system of the rotorcraft, where a working state of the engine system is used to indicate a fault state of the engine system.
The second detection module 12 is configured to generate a function control analog signal and send the function control analog signal to a function execution portion of a function system of the rotorcraft, where a function execution state of the function execution portion is indicative of a fault state of the function execution portion.
The third detection module 13 is configured to generate an engine parameter analog signal and send the engine parameter analog signal to an instrumentation system of the rotorcraft, where an instrumentation display state of the instrumentation system is used to indicate a fault state of the instrumentation system.
The fourth detection module 14 is a simulation module of a function execution part of a functional system of the rotorcraft, and is configured to receive a function control signal sent by a function control part of the functional system of the rotorcraft, and execute a preset action according to the function control signal, where an action execution state of the fourth detection module 14 is used to indicate a fault state of the function control part.
In the embodiment of the invention, the first detection module 11 can generate an engine start-stop analog signal and send the engine start-stop analog signal to an engine system of the rotorcraft, so that a worker can judge whether the engine system of the rotorcraft has a fault by judging whether an engine of the rotorcraft is normally started; the second detection module 12 can generate a function control analog signal and send the function control analog signal to the function execution part of the functional system of the rotorcraft, so that a worker can judge whether the function execution part has a fault according to whether the function execution part of the functional system of the rotorcraft can normally work; the third detection module 13 can generate an engine parameter analog signal and send the engine parameter analog signal to an instrument system of the rotorcraft, so that a worker can judge whether each instrument fails according to the display state of each instrument in the instrument system of the rotorcraft; fourth detection module 14 can receive the function control signal that the function control part of the functional system of gyroplane sent to according to function control signal execution default action, and then the staff can judge whether there is the trouble in the function control part of the functional system of gyroplane according to the action execution state of fourth detection module 14.
Optionally, as a specific real-time mode of the rotorcraft avionics system fault detection apparatus 1 provided in the embodiment of the present invention, the first detection module 11 includes:
an engine start-stop analog signal generator.
The engine start-stop analog signal generator is used for generating an engine start-stop analog signal and sending the engine start-stop analog signal to an engine system of the rotorcraft, and at the moment, the working state of the engine system is used for indicating the fault state of the engine system.
Optionally, as a specific real-time manner of the rotorcraft avionics system fault detection apparatus 1 provided in the embodiment of the present invention, the second detection module 12 includes:
at least one function controls the analog signal generator.
At least one function control analog signal generator corresponds to each function system of the gyroplane one by one; the function control analog signal generator is used for generating a function control analog signal and sending the function control analog signal to a function execution part of a function system of the rotorcraft, and the function execution state of the function execution part at the moment is used for indicating the fault state of the function execution part.
In the embodiment of the invention, since the front half fuselage and the rear half fuselage of the rotorcraft are assembled separately, the whole rotorcraft avionics system fault detection device 1 can be divided into two parts, the first detection module 11 and the second detection module 12 forming a first part of the rotorcraft avionics system fault detection device 1, the first part more realistically simulating the control room system of the front half fuselage of the rotorcraft.
The first detection module 11 may further include a simulation ignition switch 111 and a simulation instrument system 112 shown in fig. 1 except for an internal engine start/stop simulation signal generator, and the simulation instrument system 112 is the same as an instrument system of the rotorcraft, and specifically includes six display instruments of an engine tachometer, an oil mass simulation meter, a tachometer, an engine temperature meter, an engine oil pressure meter, and an engine oil temperature meter. The engine is started by twisting the ignition switch 111 to send an engine start-stop analog signal to an engine system of the rotorcraft, and the analog instrument system 112 can also be connected with the engine system to display the working parameters of the engine.
In the embodiment of the present invention, the signal transmission lines of the first detection module 11 and the second detection module 12 are integrated into a row of connection ports 15, and in practical applications, a worker can realize the connection between the first detection module 11 and the engine system of the rotorcraft and the connection between the second detection module 12 and the function executing part of the functional system of the rotorcraft through simple plugging and unplugging of the connection terminal row.
Optionally, as a specific real-time mode of the rotorcraft avionics system fault detection apparatus 1 provided in the embodiment of the present invention, the third detection module 13 includes:
at least one third detection unit.
At least one third detection unit is in one-to-one correspondence with each display instrument in an instrument system of the rotorcraft, and the third detection unit comprises an engine parameter analog signal generator and a control switch.
The engine parameter analog signal generator is used for generating preset engine parameter analog signals and sending the engine parameter analog signals to a display instrument in an instrument system of the rotorcraft, and the reading of the display instrument is used for indicating the fault state of the display instrument.
The control switch is used for controlling the on-off state of the engine parameter analog signal generator.
Optionally, as a specific real-time manner of the rotorcraft avionics system fault detection apparatus 1 provided in the embodiment of the present invention, the fourth detection module 14 includes:
at least one fourth detection unit.
The at least one fourth detection unit corresponds to each functional system of the gyroplane one by one; the fourth detection unit comprises a load and an indicator light, the load being intended to receive a function control signal sent by a function control portion of a functional system of the rotorcraft.
The indicator lamp is used for displaying the loop electrifying state of the load, and the loop electrifying state of the load is used for indicating the fault state of the function control part.
In an embodiment of the invention, third detection module 13 and fourth detection module 14 form a second part of rotorcraft avionics system fault detection apparatus 1.
The fourth detection module 14 is a simulation module of a function execution part of a function system of the rotorcraft, the function execution part of the function system of the original rotorcraft is replaced by a load with a certain value, an indicator lamp is arranged in a load loop, and a worker can judge whether the loop is electrified or not according to the on and off of the indicator lamp, so as to judge whether a circuit of a function control part of the function system of the rotorcraft is in fault or not.
Similarly, in the embodiment of the present invention, the signal transmission lines of the third detection module 13 and the fourth detection module 14 are integrated into a row of connection ports 16, and in practical applications, a worker can realize the connection between the third detection module 13 and the instrumentation system of the rotorcraft and the connection between the fourth detection module 14 and the function control portion of the function system of the rotorcraft through simple plugging and unplugging of the connection terminal row.
Optionally, as a specific real-time mode of the rotorcraft avionics system fault detection device 1 provided in the embodiment of the present invention, the engine parameter analog signal includes:
the engine oil pressure simulation device comprises an engine rotating speed simulation signal, an oil mass simulation signal, a rotating speed simulation signal, an engine temperature simulation signal, an engine oil pressure simulation signal and an engine oil temperature simulation signal.
Optionally, as a specific real-time mode of the rotorcraft avionics system fault detection apparatus 1 provided in the embodiment of the present invention, the function control analog signal includes:
an oil pump control analog signal, a fan control analog signal, a strobe control analog signal, an air pump control analog signal, or a trim control analog signal.
Optionally, as a specific real-time manner of the rotorcraft avionics system fault detection apparatus 1 provided in the embodiment of the present invention, the rotorcraft avionics system fault detection apparatus 1 further includes:
a power supply module;
the power module is used for supplying power to the first detection module 11, the second detection module 12, the third detection module 13 and the fourth detection module 14.
In addition, in the embodiment of the invention, the wiring port 14 and the wiring port 15 of the rotorcraft avionics system fault detection device 1 are connected to form a simulated rotorcraft avionics system which can be used for simulation teaching of new employees so that the new employees can be familiar with the structure of the rotorcraft avionics system.
As can be seen from the above, the failure detection device for an avionic system of a rotorcraft according to the present invention is provided with a first detection module, a second detection module, a third detection module, and a fourth detection module, and is configured to perform failure detection on an engine system of the rotorcraft by generating an engine start/stop analog signal by the first detection module, to generate a function control analog signal by the second detection module, to perform failure detection on a function execution part of a function system of the rotorcraft, to perform failure detection on an instrumentation system of the rotorcraft by generating an engine parameter analog signal by the third detection module, and to perform failure detection on a function control part of the function system of the rotorcraft by simulating the function execution part of the function system of the rotorcraft by the fourth detection module. According to the invention, each component of the rotorcraft avionics system is simulated through each detection module, so that each component of the rotorcraft avionics system can be tested even if the rotorcraft is not assembled, faults existing in the rotorcraft avionics system can be found in time, the fault position can be accurately indicated, and the assembly and maintenance efficiency of the rotorcraft is improved.
The above-mentioned embodiments are only used for illustrating the technical solutions of the present invention, and not for limiting the same; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not substantially depart from the spirit and scope of the embodiments of the present invention, and are intended to be included within the scope of the present invention.
Claims (8)
1. A rotorcraft avionics system fault detection device, comprising:
the device comprises a first detection module, a second detection module, a third detection module and a fourth detection module;
the first detection module is used for generating an engine start-stop analog signal and sending the engine start-stop analog signal to an engine system of the rotorcraft, and at the moment, the working state of the engine system is used for indicating the fault state of the engine system;
the second detection module is used for generating a function control analog signal and sending the function control analog signal to a function execution part of a function system of the rotorcraft, and at the moment, a function execution state of the function execution part is used for indicating a fault state of the function execution part;
the third detection module is used for generating an engine parameter analog signal and sending the engine parameter analog signal to an instrument system of the rotorcraft, and at the moment, the instrument display state of the instrument system is used for indicating the fault state of the instrument system;
the fourth detection module is a simulation module of a function execution part of a functional system of the rotorcraft, and is used for receiving a function control signal sent by a function control part of the functional system of the rotorcraft, executing a preset action according to the function control signal, and at the moment, the action execution state of the fourth detection module is used for indicating the fault state of the function control part.
2. The rotorcraft avionics system fault detection device of claim 1, wherein the first detection module comprises:
an engine start-stop analog signal generator;
the engine start-stop analog signal generator is used for generating an engine start-stop analog signal and sending the engine start-stop analog signal to an engine system of the rotorcraft, and at the moment, the working state of the engine system is used for indicating the fault state of the engine system.
3. The rotorcraft avionics system fault detection device of claim 1, wherein the second detection module comprises:
at least one function control analog signal generator;
the at least one function control analog signal generator corresponds to each function system of the gyroplane one to one; the function control analog signal generator is used for generating a function control analog signal and sending the function control analog signal to a function execution part of a function system of the rotorcraft, and at the moment, a function execution state of the function execution part is used for indicating a fault state of the function execution part.
4. The rotorcraft avionics system fault detection device of claim 1, wherein the third detection module comprises:
at least one third detection unit;
the at least one third detection unit corresponds to each display instrument in an instrument system of the gyroplane one to one, and the third detection unit comprises an engine parameter analog signal generator and a control switch;
the engine parameter analog signal generator is used for generating a preset engine parameter analog signal and sending the engine parameter analog signal to a display instrument in an instrument system of the rotorcraft, and the reading of the display instrument is used for indicating the fault state of the display instrument;
the control switch is used for controlling the on-off state of the engine parameter analog signal generator.
5. The rotorcraft avionics system fault detection device of claim 1, wherein the fourth detection module comprises:
at least one fourth detection unit;
the at least one fourth detection unit corresponds to each functional system of the gyroplane one to one; the fourth detection unit comprises a load and an indicator light, wherein the load is used for receiving a function control signal sent by a function control part of a function system of the rotorcraft;
the indicator lamp is used for displaying the loop electrifying state of the load, and the loop electrifying state of the load is used for indicating the fault state of the function control part.
6. The rotorcraft avionics system fault detection device of claim 1, wherein the engine parameter analog signals comprise:
the engine oil pressure simulation device comprises an engine rotating speed simulation signal, an oil mass simulation signal, a rotating speed simulation signal, an engine temperature simulation signal, an engine oil pressure simulation signal and an engine oil temperature simulation signal.
7. The rotorcraft avionics system fault detection device of claim 1, wherein the functional control analog signals comprise:
the control system comprises an oil pump control analog signal, a fan control analog signal, a strobe control analog signal, an air pump control analog signal and a balancing control analog signal.
8. A rotorcraft avionics system fault detection device according to any one of claims 1-7, further comprising:
a power supply module;
the power module is used for supplying power to the first detection module, the second detection module, the third detection module and the fourth detection module.
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| CN202110054240.XA CN112722323A (en) | 2021-01-15 | 2021-01-15 | Rotorcraft avionics system fault detection device |
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| CN202110054240.XA CN112722323A (en) | 2021-01-15 | 2021-01-15 | Rotorcraft avionics system fault detection device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114489139A (en) * | 2022-02-08 | 2022-05-13 | 浙江极客桥智能装备股份有限公司 | Unmanned aerial vehicle automatic rising and falling control method, system, terminal and medium |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105955065A (en) * | 2016-05-13 | 2016-09-21 | 中国航空工业集团公司西安飞机设计研究所 | Simulation testing system based on fault injection |
| 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 |
| CN207352419U (en) * | 2017-11-09 | 2018-05-11 | 北京安达维尔测控技术有限公司 | A kind of helicopter avionics system test equipment |
| CN109270918A (en) * | 2018-08-17 | 2019-01-25 | 国营芜湖机械厂 | A kind of aircraft avionics floor synthetic debugging system based on performance test |
| CN109739212A (en) * | 2019-01-04 | 2019-05-10 | 中国航发南方工业有限公司 | Auto-Test System for FADEC |
| US20190382140A1 (en) * | 2017-06-22 | 2019-12-19 | Bell Helicopter Textron Inc. | System and method for performing a test procedure |
-
2021
- 2021-01-15 CN CN202110054240.XA patent/CN112722323A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105955065A (en) * | 2016-05-13 | 2016-09-21 | 中国航空工业集团公司西安飞机设计研究所 | Simulation testing system based on fault injection |
| US20190382140A1 (en) * | 2017-06-22 | 2019-12-19 | Bell Helicopter Textron Inc. | System and method for performing a test procedure |
| 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 |
| CN207352419U (en) * | 2017-11-09 | 2018-05-11 | 北京安达维尔测控技术有限公司 | A kind of helicopter avionics system test equipment |
| CN109270918A (en) * | 2018-08-17 | 2019-01-25 | 国营芜湖机械厂 | A kind of aircraft avionics floor synthetic debugging system based on performance test |
| CN109739212A (en) * | 2019-01-04 | 2019-05-10 | 中国航发南方工业有限公司 | Auto-Test System for FADEC |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114489139A (en) * | 2022-02-08 | 2022-05-13 | 浙江极客桥智能装备股份有限公司 | Unmanned aerial vehicle automatic rising and falling control method, system, terminal and medium |
| CN114489139B (en) * | 2022-02-08 | 2024-02-02 | 浙江极客桥智能装备股份有限公司 | Unmanned aerial vehicle automatic landing control method, system, terminal and medium |
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