CN111077818B - Control box for aircraft data forwarding and transmitting control - Google Patents
Control box for aircraft data forwarding and transmitting control Download PDFInfo
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- CN111077818B CN111077818B CN201911238156.2A CN201911238156A CN111077818B CN 111077818 B CN111077818 B CN 111077818B CN 201911238156 A CN201911238156 A CN 201911238156A CN 111077818 B CN111077818 B CN 111077818B
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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
- 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
- G05B19/0421—Multiprocessor system
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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
- 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
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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
- G05B2219/21—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
- G05B2219/22—Pc multi processor system
- G05B2219/2214—Multicontrollers, multimicrocomputers, multiprocessing
-
- 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
- G05B2219/25—Pc structure of the system
- G05B2219/25008—Different buses, protocols on same line, also dsl
-
- 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
- G05B2219/2637—Vehicle, car, auto, wheelchair
Abstract
The invention provides a control box for aircraft data forwarding and transmitting control, wherein the control box comprises: the core board receives the control instruction of the upper interface connector, analyzes and recombines the control instruction, and judges the analyzed control instruction corresponding to the upper interface connector: if the command is a power supply command, the core board supplies power to an external aircraft through the lower connector; if the control command is received, the core board forwards the control command through the lower connector; the core board analyzes and recombines the data after receiving the state information of the external aircraft through the lower connector, updates the state information of the aircraft, and judges whether the fault occurs according to the state of the aircraft: the core board immediately disconnects the aircraft power supply if the external aircraft fails. The invention has the functions of multi-path control, acquisition, communication and the like, and has the functions of analyzing and recombining bus data, realizing data forwarding among different buses, emission control of the aircraft and power supply control of the aircraft.
Description
Technical Field
The invention relates to the technical field of aviation flight system emission control systems, in particular to a control box for data forwarding and emission control of an aircraft.
Background
In the field of launching of aviation aircrafts, a communication bus adopted by a conventional launching vehicle is generally an RS422 bus, and a communication bus of the aircraft is generally a 1553B bus or an RS422 bus. If the same communication bus is adopted between the launching vehicle and the aircraft, data forwarding is not needed. When the communication buses are different between the aircraft and the aircraft, namely the aircraft is suitable for hanging different bus launching platforms, the aircraft cannot complete communication and cannot complete launching.
Therefore, there is a need to provide a control box for aircraft data forwarding and launch control, so that the aircraft can complete launch on different launch platforms of buses.
Disclosure of Invention
(1) Objects of the invention
The control box for aircraft data forwarding and transmitting control is provided, and is required to have a data forwarding function to realize data forwarding between RS422 and 1553B buses; the aircraft launching control system has a launching control function, controls the aircraft launching process and completes aircraft launching.
(2) Technical scheme of the invention
A control box for aircraft data forwarding and launch control, comprising:
go up interface connector 1, lower interface connector 2, power strip 3, nuclear core plate 5, wherein:
the upper interface connector 1 is used for receiving the RS422 data issued by the external launch vehicle launch control device 9, reporting the RS422 data to the external launch vehicle launch control device 9, and providing power for the power panel 3;
the lower connector 2 is used for receiving 1553B data reported by the external aircraft 12, issuing 1553B data to the external aircraft 12 and supplying power to the external aircraft 12;
the core board 5 receives the RS422 data of the upper interface connector 1, analyzes and recombines the RS422 data into single character 1553B data, and forwards the single character 1553B data to the lower interface connector 2; receiving 1553B data of the lower interface connector 2, recombining the 1553B data into RS422 data, and forwarding the RS422 data to the upper interface connector 1;
the core board 5 receives the control instruction of the upper interface connector 1, analyzes and recombines the control instruction, recombines the single byte RS422 data into single word 1553B data, makes the single byte RS422 data meet a 1553B communication protocol between the control box and an external aircraft 12, and judges the analyzed control instruction corresponding to the upper interface connector 1:
if the command is a power supply command, the core board 5 supplies power to the external aircraft 12 through the lower connector 2;
if the control command is received, the core board 5 forwards the control command through the lower connector 2;
the core board 5 receives the state information of the external aircraft 12 through the lower connector 2, analyzes and reassembles the data, splits the data 1553B into single byte RS422 data, updates the state information of the external aircraft 12, periodically forwards the state of the external aircraft 12 to the launch vehicle launch control device 9, and judges whether the aircraft fails according to the state of the aircraft 12:
if the external aircraft 12 breaks down, the core board 5 immediately cuts off the aircraft power supply, reports the state to the launch vehicle launch control equipment 9, and the launch vehicle launch control equipment 9 cuts off the control box power supply after receiving the fault information.
(3) Advantageous effects of the invention
The invention can simultaneously have the functions of multi-channel DO control and AD acquisition, has the functions of RS422 communication and 1553B bus controller BC node, can analyze and recombine bus data, realizes data forwarding among different buses, and can simultaneously realize the launching control of an aircraft and the power supply control of the aircraft according to control logic.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below 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 creative efforts.
FIG. 1 is a schematic diagram of a control box according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a core board and a power board according to an embodiment of the invention;
fig. 3 is a schematic diagram of a connection relationship of the control box according to an embodiment of the invention.
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 and illustrative embodiments of various aspects of the invention are 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 some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is in no way limited to any specific arrangement and method set forth below, but rather covers any improvements, substitutions and modifications in structure, method, and apparatus 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.
It should be noted that, in the case of conflict, the embodiments and features of the embodiments of the present invention may be combined with each other, and the respective embodiments may be mutually referred to and cited. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
FIG. 1 is a schematic diagram of a control box according to an embodiment of the present invention; fig. 2 is a schematic diagram of a connection relationship of the control box according to an embodiment of the invention.
As shown in fig. 1 and 2, a control box for aircraft data forwarding and launch control comprises: the device comprises an upper interface connector 1, a lower interface connector 2, a power supply board 3 and a core board 5. Wherein: the upper interface connector 1 is used for receiving the RS422 data issued by the external launch vehicle launch control device 9, reporting the RS422 data to the external launch vehicle launch control device 9, and providing power for the power panel 3; the lower connector 2 is used for receiving 1553B data reported by the external aircraft 12, issuing 1553B data to the external aircraft 12 and supplying power to the external aircraft 12; the core board 5 receives the RS422 data of the upper interface connector 1, analyzes and recombines the RS422 data into single character 1553B data, and forwards the single character 1553B data to the lower interface connector 2; receiving 1553B data of the lower interface connector 2, recombining the 1553B data into RS422 data, and forwarding the RS422 data to the upper interface connector 1; the core board 5 receives the control instruction of the upper interface connector 1, analyzes and recombines the control instruction, recombines the single byte RS422 data into single word 1553B data, makes the single byte RS422 data meet a 1553B communication protocol between the control box and an external aircraft 12, and judges the analyzed control instruction corresponding to the upper interface connector 1: if the command is a power supply command, the core board 5 supplies power to the external aircraft 12 through the lower connector 2; if the control command is received, the core board 5 forwards the control command through the lower connector 2; the core board 5 receives the state information of the external aircraft 12 through the lower connector 2, analyzes and reassembles the data, splits the data 1553B into single byte RS422 data, updates the state information of the external aircraft 12, periodically forwards the state of the external aircraft 12 to the launch vehicle launch control device 9, and judges whether the aircraft fails according to the state of the aircraft 12: if the external aircraft 12 breaks down, the core board 5 immediately cuts off the aircraft power supply, reports the state to the launch vehicle launch control equipment 9, and the launch vehicle launch control equipment 9 cuts off the control box power supply after receiving the fault information.
In some embodiments, launch vehicle launch control device 9 powers the control box through upper interface connector 1 and sends control instructions to the control box through upper interface connector 1.
In some embodiments, if the aircraft 12 fails, the control box immediately disconnects the power supply of the aircraft 12, and reports the status to the launch vehicle launch control device 9, and the launch vehicle launch control device 9 disconnects the power supply of the control box after receiving the failure information.
In some embodiments, the power board 3 is used to perform secondary power conversion and power control.
In some embodiments, the control box further comprises: bottom plate 4, debugging mouth 6, apron 7 and medium plate 8, wherein: the debugging port 6 is used for providing an interface for software burning for the core board 5.
Fig. 3 is a schematic structural diagram of a core board and a power board according to an embodiment of the invention.
The core board 5 includes: RS42251, 232 circuit 52, 1553B circuit 53, DSP circuit 54 and FPGA circuit 55. Wherein: when the core board 5 receives data, the FPGA55 receives external data and stores the data in the FPGA55, and the DSP54 reads the data in the FPGA54 into the DSP55, and the application layer software acquires the data as needed. When the core board 5 sends the data, the application layer software stores the data result obtained by the calculation into the DSP54 and sends the data result to the FPGA55, and the FPGA55 sends the data to the launch vehicle launch control device 9 or the aircraft 12.
In some embodiments, the control box is mainly composed of an upper interface connector 1, a lower interface connector 2, a power board 3, a bottom board 4, a core board 5, a debugging port 6, a cover board 7, a middle board 8 and the like. The main compositional properties of the control box are as follows:
DSP, dominant frequency 200 MHz;
a memory: FLASH ROM: 1M 16 bit; SDRAM: 8M 32 bit;
power supply: DC 28V;
communication: 1 path of RS422 is adjustable in baud rate, and a 1553B bus BC node has one path of baud rate and 1 Mbps;
AD is 2 paths, and the resolution is 12 bits;
DO of 10 paths, providing output no less than 28V/10A per path;
size: less than or equal to 330mm multiplied by 50mm multiplied by 70mm (length multiplied by width multiplied by height);
weight: less than or equal to 1.5 kg.
The control box for aircraft data forwarding and transmitting control can convert 1553B and RS422 data into each other; the aircraft launching control system has a launching control function and can realize launching of the aircraft; the lower connector 2 adopts an interface the same as that of the aircraft, and can fully utilize the existing resources to complete the test.
The power panel 3 mainly comprises a DC-DC conversion module, a DO module and the like, and completes secondary power conversion and power supply control.
The core board 5 includes: RS42251, 232 circuit 52, 1553B circuit 53, DSP circuit 54, FPGA circuit 55, etc. The DSP circuit 54 completes the resolving of data, the FPGA circuit 55 realizes the data receiving and transmitting controller of each peripheral interface and controls the relevant peripheral chip, and the 232 circuit 52 completes the burning of software; RS42251 is communicated with launch vehicle launch control equipment 9 through an upper interface connector 1, and a 1553B circuit is communicated with an aircraft 12 through a lower interface connector 2.
The operating principle of the control box for aircraft data forwarding and launch control can be as follows:
1: data reception
The FPGA circuit 55 receives external data and stores the data in the FPGA, the DSP circuit 54 reads the data in the FPGA55 into the DSP54, and application layer software acquires the data as required.
2: data transmission
The application layer software stores the data result obtained by calculation into the DSP54 and sends the data result to the FPGA55, and the FPGA55 sends the data result to the launch vehicle launch control equipment 9 or the aircraft 12.
Launch vehicle launch control equipment 9 supplies power to the control box through last interface connector 1 to send control command to the control box through last interface connector 9. The control box analyzes and recombines the command after receiving the control command, and recombines the single-byte RS422 data into single-word 1553B data so as to meet a 1553B communication protocol between the control box and the aircraft 12. The control box uses DO control to power the aircraft 12 if it is a power command and forwards the control command if it is a control command. The control box receives the state information of the aircraft 12 by using the lower connector 2, analyzes and recombines the data, splits the single-word 1553B data into single-byte RS422 data, updates the state information of the aircraft, and periodically forwards the state of the aircraft 12 to the launch vehicle launch control equipment 9. If the aircraft 12 breaks down, the control box immediately cuts off the power supply of the aircraft 12, meanwhile, the state is reported to the launch vehicle launch control equipment 9, and the launch vehicle launch control equipment 9 cuts off the power supply of the control box after receiving the fault information.
It should be noted that the above-mentioned flow operations may be combined and applied in different degrees, and for simplicity, implementation manners of various combinations are not described again, and those skilled in the art may flexibly adjust the sequence of the above-mentioned operation steps according to actual needs, or flexibly combine the above-mentioned steps, and the like.
It should be further noted that the implementation manner of the functional components shown in the above embodiments may be hardware, software, firmware, or a combination thereof. When implemented in hardware, it may be, for example, an electronic circuit, an Application Specific Integrated Circuit (ASIC), suitable firmware, plug-in, function card, or the like. When implemented in software, the elements of the invention are the programs or code segments used to perform the required tasks. The program or code segments may be stored in a machine-readable medium or transmitted by a data signal carried in a carrier wave over a transmission medium or a communication link.
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. A control box for aircraft data forwarding and launch control, comprising:
go up interface connector (1), lower interface connector (2), power strip (3), nuclear core plate (5), wherein:
the upper interface connector (1) is used for receiving RS422 data issued by the external launch vehicle launch control equipment (9), reporting the RS422 data to the external launch vehicle launch control equipment (9) and providing power supply for the power panel (3);
the lower connector (2) is used for receiving 1553B data reported by an external aircraft (12), transmitting the 1553B data to the external aircraft (12), and providing power for the external aircraft (12);
the power panel (3) has 10 DO control paths, and provides output no less than 28V/10A for each path;
the core board (5) receives the RS422 data of the upper interface connector (1), analyzes and recombines the RS422 data into single-character 1553B data, and forwards the single-character 1553B data to the lower interface connector (2); receiving 1553B data of the lower interface connector (2), recombining the 1553B data into RS422 data, and forwarding the RS422 data to the upper interface connector (1);
the core board (5) receives the control instruction of the upper interface connector (1), analyzes and recombines the control instruction, recombines the single byte RS422 data into single word 1553B data, makes the single byte RS422 data meet a 1553B communication protocol between the control box and an external aircraft (12), and judges the analyzed control instruction corresponding to the upper interface connector (1):
if the command is a power supply command, the core board (5) supplies power to an external aircraft (12) through the lower connector (2);
if the control command is received, the core board (5) forwards the control command through the lower connector (2);
the core board (5) receives the state information of the external aircraft (12) through the lower connector (2), analyzes and recombines the data, splits the single-word 1553B data into single-byte RS422 data, updates the state information of the external aircraft (12), periodically forwards the state of the external aircraft (12) to the launch vehicle launch control device (9), and judges whether the aircraft breaks down according to the state of the aircraft (12):
if the external aircraft (12) breaks down, the core board (5) immediately cuts off the aircraft power supply, meanwhile, the state is reported to the launch vehicle launch control equipment (9), and the launch vehicle launch control equipment (9) cuts off the power supply of the control box after receiving the fault information.
2. The control box according to claim 1, wherein the core board (5) comprises:
RS422(51), 232 circuit (52), 1553B circuit (53), DSP circuit (54) and FPGA circuit (55).
3. The control box according to claim 2, wherein:
when the core board (5) receives data, the FPGA (55) receives external data and stores the external data in the FPGA (55), the DSP (54) reads the data in the FPGA (54) into the DSP (55), and application layer software acquires the data according to the requirement.
4. The control box according to claim 2, wherein:
when the core board (5) sends data, the application layer software stores the data result obtained by resolving into the DSP (54) and sends the data result to the FPGA (55), and the FPGA (55) sends the data to the launch vehicle launch control equipment (9) or the aircraft (12).
5. The control box according to claim 1, wherein:
the launch vehicle launch control equipment (9) supplies power to the control box through the upper interface connector (1) and sends a control instruction to the control box through the upper interface connector (1).
6. The control box according to claim 1, wherein:
if the aircraft (12) breaks down, the control box immediately cuts off the power supply of the aircraft (12), meanwhile, the state is reported to the launch vehicle launch control equipment (9), and the launch vehicle launch control equipment (9) cuts off the power supply of the control box after receiving the fault information.
7. The control box according to claim 1, wherein:
the power panel (3) is used for completing secondary power conversion and power supply control.
8. The control box according to any one of claims 1 to 7, further comprising:
bottom plate (4), debugging mouth (6), apron (7) and medium plate (8), wherein:
the debugging port (6) is used for providing a software burning interface for the core board (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201911238156.2A CN111077818B (en) | 2019-12-05 | 2019-12-05 | Control box for aircraft data forwarding and transmitting control |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911238156.2A CN111077818B (en) | 2019-12-05 | 2019-12-05 | Control box for aircraft data forwarding and transmitting control |
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| Publication Number | Publication Date |
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| CN111077818A CN111077818A (en) | 2020-04-28 |
| CN111077818B true CN111077818B (en) | 2021-04-16 |
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| CN111654506A (en) * | 2020-06-17 | 2020-09-11 | 江西洪都航空工业集团有限责任公司 | Miniaturized general type forwarding control box |
| CN111811319A (en) * | 2020-06-17 | 2020-10-23 | 江西洪都航空工业集团有限责任公司 | Small-size transmission control box |
| CN113467506B (en) * | 2021-06-28 | 2023-08-25 | 北京航天飞腾装备技术有限责任公司 | Domestic flight controller based on core board design and design method |
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| KR100645008B1 (en) * | 2005-08-01 | 2006-11-14 | 국방과학연구소 | Electrically driven turret test system |
| CN201071286Y (en) * | 2007-07-20 | 2008-06-11 | 福建省光泽县气象局 | Vehicle mounted loading and unloading frame for weather modification rocket pod |
| CN202748785U (en) * | 2012-06-20 | 2013-02-20 | 北京神州飞航科技有限责任公司 | Double-channel 1553B and RS422 converting card |
| CN104252435B (en) * | 2014-08-29 | 2017-06-13 | 北京航天自动控制研究所 | Varistructure intelligence interface and its collocation method based on dynamic reconfigurable FPGA |
| CN106789496B (en) * | 2016-11-22 | 2020-05-12 | 上海航天控制技术研究所 | 1553B communication interface circuit of optical fiber inertial measurement unit for carrier rocket |
| CN207318095U (en) * | 2017-09-30 | 2018-05-04 | 江西洪都航空工业集团有限责任公司 | A kind of engine control, the parameter measurement of HIGHER ALTITUDE TEST FACILITY rack and record system |
| CN207955443U (en) * | 2018-03-01 | 2018-10-12 | 北京爱尔达电子设备有限公司 | Sounding rocket attemperator and sounding rocket emit transport vehicle |
| CN110161880B (en) * | 2019-05-23 | 2022-03-04 | 北京电子工程总体研究所 | Simulation system and method for launching system of general aircraft |
| CN110244606A (en) * | 2019-05-30 | 2019-09-17 | 中国科学院长春光学精密机械与物理研究所 | Arm discharge control system and carry platform with the launch control system |
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