CN109143931B - Integrated equipment with emission control and test functions - Google Patents
Integrated equipment with emission control and test functions Download PDFInfo
- Publication number
- CN109143931B CN109143931B CN201810977936.8A CN201810977936A CN109143931B CN 109143931 B CN109143931 B CN 109143931B CN 201810977936 A CN201810977936 A CN 201810977936A CN 109143931 B CN109143931 B CN 109143931B
- Authority
- CN
- China
- Prior art keywords
- module
- aerial vehicle
- unmanned aerial
- emission control
- test
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 33
- 230000006870 function Effects 0.000 title claims abstract description 21
- 238000004891 communication Methods 0.000 claims abstract description 19
- 230000003993 interaction Effects 0.000 claims description 3
- 239000004973 liquid crystal related substance Substances 0.000 claims description 3
- 230000008054 signal transmission Effects 0.000 claims description 3
- 238000012827 research and development Methods 0.000 abstract description 8
- 230000010354 integration Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Images
Classifications
-
- 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
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
-
- 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
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
-
- 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
-
- 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
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0423—Input/output
-
- 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
- G05B2219/21—Pc I-O input output
- G05B2219/21014—Interface, module with relays
-
- 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
- G05B2219/21—Pc I-O input output
- G05B2219/21137—Analog to digital conversion, ADC, DAC
-
- 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
- G05B2219/26—Pc applications
- G05B2219/2604—Test of external equipment
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Selective Calling Equipment (AREA)
Abstract
The invention relates to an integrated device with emission control and test functions, which comprises a main control computer (2), a display (3), a CAN communication module (4), an AD module (5), an IO module (6), a waveform generator module (7), an electrical interface (8), a control panel (9) and a mouse keyboard (10). The device simplifies the structure of the device, gives play to the performance of the device to the maximum extent, has the functions of emission control and test, is independent of each other, saves a large amount of research and development cost, and greatly shortens the research and development period.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicle launching control systems and testing systems, and particularly relates to integrated equipment with launching control and testing functions.
Background
The launching control equipment and the testing equipment in the traditional ground launching unmanned aerial vehicle system (hereinafter referred to as unmanned aerial vehicle) are essential important components for completing flight tasks, and meanwhile, the launching control and the testing are also indispensable important links in the normal use process.
Launch control and testing of conventional UAV systems are accomplished by two separate devices, one dedicated to launch control of the UAV and the other dedicated to testing of the UAV. From the use flow of the unmanned aerial vehicle, emission control and test are carried out in two different stages, and functional interference does not exist; from the perspective of hardware requirements, both the emission control equipment and the test equipment can select a ruggedized computer as a hardware platform; from the perspective of the electrical interface, the two equipment electrical interfaces can only be connected with the same electrical interface of the unmanned aerial vehicle finally due to the uniqueness of the unmanned aerial vehicle electrical interface. The biggest difference between the two devices is only: the number of channels of an AD/IO input/output module and a communication module configured by a ruggedized computer is different; secondly, the test equipment needs to be provided with a special waveform generator module; thirdly, the specific core wire definition of the electrical interface of the two is slightly different. Therefore, the three problems can be solved under the condition of hardware conditions and technical bases, and the emission control equipment and the test equipment can be integrated into an integrated equipment.
Disclosure of Invention
The purpose of the invention is as follows:
the invention aims to realize the integration of the launching control function and the testing function of the unmanned aerial vehicle on the same hardware platform, fully utilize the AD/IO input/output interface and the communication interface of the hardware platform, reduce the manpower and material resources required by the launching control system and the testing system of the unmanned aerial vehicle on the premise of ensuring the completeness of the launching control and the testing function of the unmanned aerial vehicle and mutual independence and noninterference, save a great deal of research and development cost, greatly shorten the research and development period, and have great significance for the original unmanned aerial vehicle system which pursues low cost and mass production.
The technical scheme adopted by the invention is as follows:
an integrated device with emission control and test functions comprises a main control computer (2), a display (3), a CAN communication module (4), an AD module (5), an IO module (6), a waveform generator module (7), an electrical interface (8), a control panel (9) and a mouse keyboard (10);
the main control computer (2) is respectively connected with the display (3), the CAN communication module (4), the AD module (5), the IO module (6), the waveform generator module (7) and the mouse keyboard (10); the IO module (6) is connected with the control panel (9); the electrical interface (8) is used as an external connection interface of the integrated equipment;
when the unmanned aerial vehicle is subjected to launch control, the main control computer (2) is in data communication with the unmanned aerial vehicle through the CAN communication module (4); an analog quantity signal of the unmanned aerial vehicle is collected by an A/D module (5); discrete quantity input and output control is carried out through the I/O module (6), and signal acquisition of the unmanned aerial vehicle is completed; the control panel (9) is used as a switch for generating an ignition and emission control digital quantity signal of the unmanned aerial vehicle; the display (3) and the mouse keyboard (10) finish man-machine interaction when the unmanned aerial vehicle is launched; the electrical interface (8) is used as a power supply and signal transmission channel of the equipment; when the unmanned aerial vehicle is tested, the waveform generator module (7) is required to be called to simulate the unmanned aerial vehicle signal to be tested.
The method is characterized in that the main frequency of the main control computer (2) is more than or equal to 2.0G; the internal memory is more than or equal to 4G; the display card (integration) is more than or equal to 2G; the hard disk (solid state electronic disk) is more than or equal to 256 GB.
The liquid crystal display is characterized in that the size of a liquid crystal screen of the display (3) is more than or equal to 12.1 inches; the resolution is more than or equal to 800 multiplied by 600.
The CAN communication module is characterized in that the number of channels of the CAN communication module (4) is 2; the Baud rate is more than or equal to 800 Kbps.
The AD module is characterized in that the number of channels of the AD module (5) is 8; the resolution is 12 bit; the range of the analog input direct current voltage is 0-40V.
The input channel number of the IO module (6) is 32; the number of output channels is 32; the output current is more than or equal to 500 mA.
Characterized in that the number of channels of the waveform generator module (7) is 2; the resolution is 14 bit; the maximum output frequency is 10 Khz; the output waveform is a sine wave; the output amplitude is 10 mV-10V; the output impedance is 50 omega.
The electric interface (8) comprises a power supply interface, a transmission control interface and a USB interface, and adopts a standard aviation connector.
The invention has the beneficial effects that:
1) only one device is used to realize the function which can be completed by two devices originally;
2) all modules of the equipment are fully utilized, and the performance of the equipment is exerted to the maximum extent;
3) the equipment has the functions of emission control and test, is independent from each other, and meets the use requirement of the unmanned aerial vehicle;
4) manpower and material resources required to be input by an unmanned aerial vehicle launching control system and a testing system are reduced, a large amount of research and development cost is saved, and the research and development period is greatly shortened;
5) the method meets the low-cost and batch development requirements of the unmanned aerial vehicle system.
Drawings
FIG. 1 is a schematic view of the principle of the integrated equipment
Wherein, 1 sends out accuse test integration equipment 2 main control computer 3 display 4 CAN communication module 5 AD module 6 IO module 7 wave form generator module 8 electric interface 9 mouse keyboard 10 control panel
Detailed Description
The invention is described in further detail below with reference to the drawings.
As shown in fig. 1, the integrated device with emission control and test functions of the present invention is designed to be portable, and mainly comprises a main control computer, a display, a CAN communication module, an AD module, an IO module, a waveform generator module, an electrical interface, a control panel, a mouse and a keyboard.
The main control computer is used as a control center of the sending, controlling and testing integrated equipment. When the unmanned aerial vehicle is used for launching control, the main control computer completes data communication (control information and state information returned by the unmanned aerial vehicle) with the unmanned aerial vehicle through the CAN communication module; collecting an analog quantity signal of the unmanned aerial vehicle by using an A/D module; discrete quantity input and output control is carried out through an I/O module, and signal acquisition of the unmanned aerial vehicle is completed; the control panel is used as a switch for generating an ignition and emission control digital quantity signal of the unmanned aerial vehicle; man-machine interaction is carried out when the display and the mouse keyboard finish transmitting; the electrical interface is used as a power supply and signal transmission channel of the equipment; when the unmanned aerial vehicle is tested, the waveform generator module is required to be called to simulate the unmanned aerial vehicle signal to be tested.
The invention fully utilizes the AD/IO input/output interface and the communication interface of the hardware platform, reduces manpower and material resources required to be invested by an unmanned aerial vehicle emission control system and a test system on the premise of ensuring the complete emission control and test functions of the unmanned aerial vehicle and mutual independence and noninterference, saves a large amount of research and development cost, greatly shortens the research and development period, and has great significance for originally pursuing low-cost and batched unmanned aerial vehicle systems.
Claims (8)
1. An integrated device with emission control and test functions comprises a main control computer (2), a display (3), a CAN communication module (4), an AD module (5), an IO module (6), a waveform generator module (7), an electrical interface (8), a control panel (9) and a mouse keyboard (10);
the main control computer (2) is respectively connected with the display (3), the CAN communication module (4), the AD module (5), the IO module (6), the waveform generator module (7) and the mouse keyboard (10); the IO module (6) is connected with the control panel (9); the electrical interface (8) is used as an external connection interface of the integrated equipment;
when the unmanned aerial vehicle is subjected to launch control, the main control computer (2) is in data communication with the unmanned aerial vehicle through the CAN communication module (4); an analog quantity signal of the unmanned aerial vehicle is collected by an A/D module (5); discrete quantity input and output control is carried out through the I/O module (6), and signal acquisition of the unmanned aerial vehicle is completed; the control panel (9) is used as a switch for generating an ignition and emission control digital quantity signal of the unmanned aerial vehicle; the display (3) and the mouse keyboard (10) finish man-machine interaction when the unmanned aerial vehicle is launched; the electrical interface (8) is used as a power supply and signal transmission channel of the equipment; when the unmanned aerial vehicle is tested, the waveform generator module (7) is required to be called to simulate the unmanned aerial vehicle signal to be tested.
2. The integrated equipment with the functions of emission control and test as claimed in claim 1, wherein the main frequency of the main control computer (2) is more than or equal to 2.0G; the internal memory is more than or equal to 4G; the integrated display card is more than or equal to 2G; the solid-state electronic hard disk is more than or equal to 256 GB.
3. The integrated equipment with the emission control and test functions as claimed in claim 2, wherein the size of the liquid crystal screen of the display (3) is more than or equal to 12.1 inches; the resolution is more than or equal to 800 multiplied by 600.
4. The integrated equipment with the functions of emission control and test as claimed in claim 3, wherein the number of channels of the CAN communication module (4) is 2; the Baud rate is more than or equal to 800 Kbps.
5. The integrated equipment with the functions of emission control and test as claimed in claim 4, characterized in that the number of channels of the AD module (5) is 8; the resolution is 12 bit; the range of the analog input direct current voltage is 0-40V.
6. The integrated equipment with the functions of emission control and test as claimed in claim 5, characterized in that the number of input channels of the IO module (6) is 32; the number of output channels is 32; the output current is more than or equal to 500 mA.
7. The integrated equipment with the functions of emission control and test as set forth in claim 6, wherein the number of channels of the waveform generator module (7) is 2; the resolution is 14 bit; the maximum output frequency is 10 Khz; the output waveform is a sine wave; the output amplitude is 10 mV-10V; the output impedance is 50 omega.
8. An integrated device with emission control and test functions, according to claim 7, characterized in that said electrical interface (8) comprises a power supply interface, an emission control interface and a USB interface, all using standard aeronautical connectors.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810977936.8A CN109143931B (en) | 2018-08-24 | 2018-08-24 | Integrated equipment with emission control and test functions |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810977936.8A CN109143931B (en) | 2018-08-24 | 2018-08-24 | Integrated equipment with emission control and test functions |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109143931A CN109143931A (en) | 2019-01-04 |
| CN109143931B true CN109143931B (en) | 2021-08-17 |
Family
ID=64827939
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810977936.8A Active CN109143931B (en) | 2018-08-24 | 2018-08-24 | Integrated equipment with emission control and test functions |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109143931B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110647099A (en) * | 2019-10-15 | 2020-01-03 | 江西洪都国际机电有限责任公司 | Launch vehicle control equipment based on PLVC controller and CAN communication |
| CN111572810B (en) * | 2020-04-14 | 2021-10-15 | 北京交通大学 | Launch test emission control system |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102591320A (en) * | 2011-12-22 | 2012-07-18 | 中国直升机设计研究所 | Portable integrated tester for flight control system of helicopter |
| CN102608450A (en) * | 2012-02-24 | 2012-07-25 | 江苏凌创电气自动化股份有限公司 | Testing and verifying system appropriate for intelligent transformer substation and verifying method |
| CN103019230A (en) * | 2012-12-16 | 2013-04-03 | 重庆望江工业有限公司 | Digital type alternating current servo system testing system |
| CN103092192A (en) * | 2013-01-29 | 2013-05-08 | 株洲南车时代电气股份有限公司 | Train power supply control system test device and method thereof |
| CN103558838A (en) * | 2013-11-01 | 2014-02-05 | 北京航空航天大学 | Solid-liquid power air vehicle ground test and launch control system of 422 bus |
| CN103675530A (en) * | 2013-11-28 | 2014-03-26 | 江西洪都航空工业集团有限责任公司 | Testing device for electronic onboard cabin control panel |
| CN105204494A (en) * | 2015-09-17 | 2015-12-30 | 北京航天自动控制研究所 | General external system equivalent device testing device for control system |
| CN105334760A (en) * | 2015-11-27 | 2016-02-17 | 湖北三江航天红峰控制有限公司 | Ground test launch control system for test aircraft |
| CN106292644A (en) * | 2016-09-29 | 2017-01-04 | 湖北航天技术研究院总体设计所 | The one the most unmanned platform autonomous launch vehicle measurement of aircraft |
| CN107070710A (en) * | 2017-03-31 | 2017-08-18 | 北京润科通用技术有限公司 | A kind of communication terminal Hardware In The Loop Simulation Method and analogue system |
| CN107416226A (en) * | 2017-03-28 | 2017-12-01 | 湖北航天技术研究院总体设计所 | Unpowered vehicle emission system and method under a kind of big deep-water submersible |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103592908B (en) * | 2013-10-16 | 2015-11-04 | 中国运载火箭技术研究院 | A kind of aircraft integrated measurement system based on 1553B bus |
-
2018
- 2018-08-24 CN CN201810977936.8A patent/CN109143931B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102591320A (en) * | 2011-12-22 | 2012-07-18 | 中国直升机设计研究所 | Portable integrated tester for flight control system of helicopter |
| CN102608450A (en) * | 2012-02-24 | 2012-07-25 | 江苏凌创电气自动化股份有限公司 | Testing and verifying system appropriate for intelligent transformer substation and verifying method |
| CN103019230A (en) * | 2012-12-16 | 2013-04-03 | 重庆望江工业有限公司 | Digital type alternating current servo system testing system |
| CN103092192A (en) * | 2013-01-29 | 2013-05-08 | 株洲南车时代电气股份有限公司 | Train power supply control system test device and method thereof |
| CN103558838A (en) * | 2013-11-01 | 2014-02-05 | 北京航空航天大学 | Solid-liquid power air vehicle ground test and launch control system of 422 bus |
| CN103675530A (en) * | 2013-11-28 | 2014-03-26 | 江西洪都航空工业集团有限责任公司 | Testing device for electronic onboard cabin control panel |
| CN105204494A (en) * | 2015-09-17 | 2015-12-30 | 北京航天自动控制研究所 | General external system equivalent device testing device for control system |
| CN105334760A (en) * | 2015-11-27 | 2016-02-17 | 湖北三江航天红峰控制有限公司 | Ground test launch control system for test aircraft |
| CN106292644A (en) * | 2016-09-29 | 2017-01-04 | 湖北航天技术研究院总体设计所 | The one the most unmanned platform autonomous launch vehicle measurement of aircraft |
| CN107416226A (en) * | 2017-03-28 | 2017-12-01 | 湖北航天技术研究院总体设计所 | Unpowered vehicle emission system and method under a kind of big deep-water submersible |
| CN107070710A (en) * | 2017-03-31 | 2017-08-18 | 北京润科通用技术有限公司 | A kind of communication terminal Hardware In The Loop Simulation Method and analogue system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109143931A (en) | 2019-01-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103925853B (en) | A kind of carrier rocket ground testing system device | |
| CN103678212B (en) | Based on the general-purpose interface detection device of VPX framework | |
| CN109143931B (en) | Integrated equipment with emission control and test functions | |
| CN105446318A (en) | Portable measurement and control equipment suitable for carrier rocket flight control system | |
| CN112344810A (en) | Missile weapon test equipment | |
| CN207851530U (en) | A kind of test system of vehicular amusement apparatus | |
| CN108614300B (en) | Direct-current resistivity imaging equipment and distributed measuring station thereof | |
| CN109358995A (en) | A kind of multifunctional testing backboard and test method | |
| CN105261254A (en) | A remote open-type airplane electronic line semi-physical virtual testing teaching platform | |
| CN203706212U (en) | Communication and navigation simulation system | |
| CN109388121A (en) | A kind of flight control computer test device | |
| CN114924547A (en) | Signal electrical fault injection device | |
| CN205015661U (en) | Unmanned aerial vehicle line concentrator | |
| CN103279055A (en) | Design scheme of adaptor board for connecting Arinc708 board card with field programmable gate array (FPGA) development board | |
| CN206515817U (en) | A kind of ionospheric sounding system controller based on USB3.0 | |
| CN107943634A (en) | More USB Port Auto-Test Systems | |
| CN207937858U (en) | Test system of safety and stability control device | |
| CN112484587A (en) | Miniaturized general missile test system | |
| CN202126902U (en) | Resistance device with adjustable digital quantity | |
| CN105227254A (en) | A kind of novel multi-channel meteor trail channel simulator | |
| CN213960076U (en) | Unmanned aerial vehicle data link transmission quality test equipment | |
| CN206332678U (en) | A kind of ethernet receiver of multichannel FM broadcast | |
| CN214097710U (en) | Test system for communication board card | |
| CN219496670U (en) | Data acquisition system | |
| CN204595160U (en) | The simple batch-testing device of wireless transmit chip |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |