CN110727625A - Data loading equipment and data interaction method after loading of missile-borne integrated guide machine - Google Patents
Data loading equipment and data interaction method after loading of missile-borne integrated guide machine Download PDFInfo
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- CN110727625A CN110727625A CN201910899474.7A CN201910899474A CN110727625A CN 110727625 A CN110727625 A CN 110727625A CN 201910899474 A CN201910899474 A CN 201910899474A CN 110727625 A CN110727625 A CN 110727625A
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- 238000011068 loading method Methods 0.000 title claims abstract description 94
- 238000000034 method Methods 0.000 title claims abstract description 24
- 230000003993 interaction Effects 0.000 title claims abstract description 10
- 238000004891 communication Methods 0.000 claims abstract description 17
- 238000000926 separation method Methods 0.000 claims abstract description 16
- 238000013524 data verification Methods 0.000 claims description 11
- 238000001514 detection method Methods 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 claims description 2
- 238000012360 testing method Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000003631 expected effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F13/00—Interconnection of, or transfer of information or other signals between, memories, input/output devices or central processing units
- G06F13/38—Information transfer, e.g. on bus
- G06F13/40—Bus structure
- G06F13/4063—Device-to-bus coupling
- G06F13/4068—Electrical coupling
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F13/00—Interconnection of, or transfer of information or other signals between, memories, input/output devices or central processing units
- G06F13/38—Information transfer, e.g. on bus
- G06F13/42—Bus transfer protocol, e.g. handshake; Synchronisation
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Abstract
The invention relates to data loading equipment after the bullet loading of a bullet-loaded integrated guide machine, which comprises a GJB289A bus data communication board card, data loading software, a separation socket, a GJB289A bus cable and an electric control box. And the method also relates to a data interaction method after the bullet loading of the bullet-loaded integrated guide machine, and loads the data of the integrated guide machine by adopting a GJB289A bus. On the premise of not detaching the missile upper cover, the invention realizes software loading by connecting the data loading equipment with the missile separation plug and using GJB289A bus. Compared with an RS232 serial port loading method, the GJB289A bus loading method is simple and easy to operate, high in speed and high in reliability.
Description
Technical Field
The invention belongs to the field of missile data interaction, and relates to data loading equipment and a data interaction method after a missile-borne integrated leader is loaded, wherein the method is a method for loading data of the missile-borne integrated leader through a GJB289A bus.
Background
The integrated guidance machine is a core component of a missile flight control system, and target codes generated by compiling flight control software, navigation software and the like need to be loaded into the integrated guidance machine. In the process of model development, flight control software needs to be continuously changed and upgraded due to changes of various requirements. In the past model development, software loading is carried out through an RS232 serial port of an integrated guide making machine test port, after loading, software loading and upgrading are carried out, an upper opening cover needs to be disassembled, then a plug cover of the integrated guide making machine test port is disassembled and an RS232 serial port loading cable is connected, then software loading and upgrading are carried out, after software upgrading, a loading cable of the test port needs to be disassembled and the plug cover needs to be connected again, and the guided missile is restored to the state before software upgrading. The whole process needs to consume larger manpower and time, and meanwhile, the dismounting process can have the risks of accidentally damaging products and the problem of repeated dismounting of the cabin section caused by the fact that redundant materials fall into the cabin section.
Disclosure of Invention
The invention aims to provide equipment and a method for carrying out integrated guide making data interaction directly through a GJB289A bus in a separation plug on a missile without detaching the missile, and the equipment and the method are suitable for carrying out integrated guide making data loading and upgrading after the missile is loaded.
The technical scheme of the invention is as follows:
the data loading equipment after the bullet loading of the bullet-loaded integrated guide machine comprises a GJB289A bus data communication board card, data loading software, a separation socket, a GJB289A bus cable and an electrical control box;
wherein, the separation socket is connected with the missile; the electrical control box realizes the electrical control of the data loading equipment; the GJB289A bus data communication board card is connected to the separated socket through a GJB289A bus cable; and the data loading equipment performs data interaction according to the data loading software.
The electric control box is characterized in that a 28V direct-current power supply is arranged in the electric control box and supplies power for the integrated guide making machine.
The electric control box is characterized in that the electric control box is also provided with an address line for hardware data verification between the data loading equipment and the missile.
The method for data interaction after the bullet loading of the bullet-loaded integrated guide machine loads data of the integrated guide machine by adopting a GJB289A bus, and comprises the following steps of:
1) formulating a GJB289A bus communication protocol between the missile-borne integrated guide machine and the data loading equipment;
2) the separation socket of the data loading equipment is connected with the missile separation plug;
3) powering on the data loading equipment, and starting data loading software;
4) electrifying the integrated guide making machine and completing self-detection;
5) hardware data verification is carried out between the data loading equipment and the missile, and if the hardware data verification is passed, the step 6) is carried out;
6) the data loading equipment sends handshake information to the integrated guide machine, and if the integrated guide machine receives the handshake information within the specified time, the data loading equipment sends feedback information to the data loading equipment;
7) if the data loading equipment receives the feedback information sent by the integrated guiding machine, sending a target file and loading address information to the integrated guiding machine;
8) after receiving the target file and the loading address information, the integrated guiding machine writes target file data into the corresponding loading address, and sends feedback information to the data loading equipment after the writing is finished;
9) and if the data loading equipment receives feedback information sent after the integrated guide making machine finishes writing, the data loading equipment prompts the end of loading, requests to cut off a power supply of the integrated guide making machine, and the integrated guide making machine is powered off.
The missile-borne integrated leader system is characterized in that a GJB289A bus communication protocol between the missile-borne integrated leader system and the data loading equipment comprises communication address information, handshake information and data transmission format information.
The method is characterized in that a 28V direct current power supply in the data loading equipment supplies power for the integrated guide making machine.
The method is characterized in that hardware data verification is carried out between the data loading device and the missile through an address line.
Wherein, in the step 5), if the verification fails, the communication is interrupted.
The method is characterized in that in the step 6), if the handshake information is not received, the receiving integrated guide machine is always waited for sending the handshake information.
The invention has the beneficial effects that:
on the premise of not detaching the missile upper cover, the invention realizes software loading by connecting the data loading equipment with the missile separation plug and using GJB289A bus. Compared with an RS232 serial port loading method, the GJB289A bus loading method is simple and easy to operate, high in speed and high in reliability.
Drawings
Fig. 1 is a schematic flow chart of a data loading method for a GJB289A bus according to the present invention.
FIG. 2 is a schematic diagram of a data loading device connected to a missile.
Detailed Description
The connection structure of the present invention will be described in detail with reference to the accompanying drawings and examples.
As shown in fig. 2, the data loading device after the missile-borne integrated guide machine is loaded comprises a GJB289A bus data communication board card, data loading software, a separation socket, a GJB289A bus cable and an electrical control box; the separation socket is connected with the missile; the electric control box is provided with a 28V direct-current power supply which supplies power for the integrated guide making machine, and is also provided with an address line which is used for hardware data verification between the data loading equipment and the missile; the GJB289A bus data communication board is connected to the separated socket through a GJB289A bus cable.
As shown in fig. 1, the data interaction method after the loading of the missile-borne integrated guide machine loads the data of the integrated guide machine by using a GJB289A bus, and includes the following steps:
1) formulating a GJB289A bus communication protocol between the missile-borne integrated guide machine and the data loading equipment;
2) the separation socket of the data loading equipment is connected with the missile separation plug;
3) powering on the data loading equipment, and starting data loading software;
4) a 28V direct-current power supply in the data loading equipment supplies power to the integrated guide making machine, the integrated guide making machine is electrified, and self-detection is completed;
5) hardware data verification is carried out between the data loading equipment and the missile through an address line, if the hardware data verification is passed, the step 6) is carried out, and if the hardware data verification is not passed, the communication is interrupted;
6) the data loading equipment sends handshake information to the integrated guide machine, if the integrated guide machine receives the handshake information within the specified time, the data loading equipment sends feedback information to the data loading equipment, and if the handshake information is not received, the data loading equipment waits for receiving the handshake information sent by the integrated guide machine all the time;
7) if the data loading equipment receives the feedback information sent by the integrated guiding machine, sending a target file and loading address information to the integrated guiding machine;
8) after receiving the target file and the loading address information, the integrated guiding machine writes target file data into the corresponding loading address, and sends feedback information to the data loading equipment after the writing is finished;
9) and if the data loading equipment receives feedback information sent after the integrated guide making machine finishes writing, the data loading equipment prompts the end of loading, requests to cut off a power supply of the integrated guide making machine, and the integrated guide making machine is powered off.
The invention has been successfully applied to multi-model air-ground missiles, obtains expected effect, can be used in other model projects and has wide application prospect.
Claims (9)
1. The data loading equipment after the bullet loading of the bullet-loaded integrated guide machine comprises a GJB289A bus data communication board card, data loading software, a separation socket, a GJB289A bus cable and an electrical control box;
wherein, the separation socket is connected with the missile; the electrical control box realizes the electrical control of the data loading equipment; the GJB289A bus data communication board card is connected to the separated socket through a GJB289A bus cable; and the data loading equipment performs data interaction according to the data loading software.
2. The post-loading data loading apparatus of a missile-borne integrated leader according to claim 1 wherein the electrical control box has a 28V dc power supply therein for powering the integrated leader.
3. The data loading device of claim 1, wherein the electrical control box further comprises an address line for hardware data verification between the data loading device and the missile.
4. The method for interacting the data after the loading of the integrated missile-borne guide by using the data loading equipment after the loading of the integrated missile-borne guide according to any one of claims 1 to 3, wherein the data of the integrated missile-borne guide is loaded by using a GJB289A bus, and the method comprises the following steps:
1) formulating a GJB289A bus communication protocol between the missile-borne integrated guide machine and the data loading equipment;
2) the separation socket of the data loading equipment is connected with the missile separation plug;
3) powering on the data loading equipment, and starting data loading software;
4) electrifying the integrated guide making machine and completing self-detection;
5) hardware data verification is carried out between the data loading equipment and the missile, and if the hardware data verification is passed, the step 6) is carried out;
6) the data loading equipment sends handshake information to the integrated guide machine, and if the integrated guide machine receives the handshake information within the specified time, the data loading equipment sends feedback information to the data loading equipment;
7) if the data loading equipment receives the feedback information sent by the integrated guiding machine, sending a target file and loading address information to the integrated guiding machine;
8) after receiving the target file and the loading address information, the integrated guiding machine writes target file data into the corresponding loading address, and sends feedback information to the data loading equipment after the writing is finished;
9) and if the data loading equipment receives feedback information sent after the integrated guide making machine finishes writing, the data loading equipment prompts the end of loading, requests to cut off a power supply of the integrated guide making machine, and the integrated guide making machine is powered off.
5. The method as claimed in claim 4, wherein the GJB289A bus communication protocol between the missile-borne integrated leader and the data loading device comprises communication address information, handshake information and data transmission format information.
6. The method of claim 5, wherein the 28 volt dc power supply in the data loading device powers the integrated leader.
7. The method of claim 6, wherein the hardware data check is performed between the data loading device and the missile via the address lines.
8. The method of claim 7, wherein in step 5), if the check fails, the communication is interrupted.
9. The method as claimed in claim 8, wherein in step 6), if no handshake information is received, the receiving integrated leader is always waiting to send the handshake information.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910899474.7A CN110727625A (en) | 2019-09-23 | 2019-09-23 | Data loading equipment and data interaction method after loading of missile-borne integrated guide machine |
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| CN201910899474.7A CN110727625A (en) | 2019-09-23 | 2019-09-23 | Data loading equipment and data interaction method after loading of missile-borne integrated guide machine |
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| CN110727625A true CN110727625A (en) | 2020-01-24 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104461626A (en) * | 2014-12-08 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Software loading method using 1553B bus |
| CN204992021U (en) * | 2015-09-29 | 2016-01-20 | 北京明航技术研究所 | An accuse cable connector protection device of function is detected to tape channel |
| CN105866578A (en) * | 2016-04-01 | 2016-08-17 | 中航飞机股份有限公司西安飞机分公司 | Airplane standard hanger management system detection method |
| CN109582573A (en) * | 2018-11-23 | 2019-04-05 | 江西洪都航空工业集团有限责任公司 | Test missile-borne integration control plane software version method |
-
2019
- 2019-09-23 CN CN201910899474.7A patent/CN110727625A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104461626A (en) * | 2014-12-08 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Software loading method using 1553B bus |
| CN204992021U (en) * | 2015-09-29 | 2016-01-20 | 北京明航技术研究所 | An accuse cable connector protection device of function is detected to tape channel |
| CN105866578A (en) * | 2016-04-01 | 2016-08-17 | 中航飞机股份有限公司西安飞机分公司 | Airplane standard hanger management system detection method |
| CN109582573A (en) * | 2018-11-23 | 2019-04-05 | 江西洪都航空工业集团有限责任公司 | Test missile-borne integration control plane software version method |
Non-Patent Citations (1)
| Title |
|---|
| 张晓曦等: "弹载一体化制导与控制系统设计", 《航空计算技术》 * |
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Application publication date: 20200124 |