CN204142106U - The test of New Launch, transmitting and control system - Google Patents
The test of New Launch, transmitting and control system Download PDFInfo
- Publication number
- CN204142106U CN204142106U CN201420321184.7U CN201420321184U CN204142106U CN 204142106 U CN204142106 U CN 204142106U CN 201420321184 U CN201420321184 U CN 201420321184U CN 204142106 U CN204142106 U CN 204142106U
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- 238000012360 testing method Methods 0.000 title claims abstract description 27
- 238000004891 communication Methods 0.000 claims abstract description 109
- 238000004458 analytical method Methods 0.000 claims abstract description 8
- 230000003287 optical effect Effects 0.000 claims description 112
- 238000012546 transfer Methods 0.000 claims description 7
- 230000005540 biological transmission Effects 0.000 abstract description 12
- 238000012937 correction Methods 0.000 abstract description 5
- 238000000034 method Methods 0.000 abstract description 4
- 238000012790 confirmation Methods 0.000 abstract description 3
- 101100408453 Arabidopsis thaliana PLC5 gene Proteins 0.000 description 7
- 101100408454 Arabidopsis thaliana PLC6 gene Proteins 0.000 description 7
- 102100026205 1-phosphatidylinositol 4,5-bisphosphate phosphodiesterase gamma-1 Human genes 0.000 description 4
- 101000691599 Homo sapiens 1-phosphatidylinositol 4,5-bisphosphate phosphodiesterase gamma-1 Proteins 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 230000007423 decrease Effects 0.000 description 3
- 230000008054 signal transmission Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000013307 optical fiber Substances 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
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Abstract
A kind of test of New Launch, transmitting and control system, comprise rear end equipment, headend equipment and communication apparatus, rear end equipment forward end equipment send test, launch and control signal time, adopt the discrete control of current signal, small area analysis signal is survey the executive signal sending out control logic, sends out control PLC control by front end; Big current signal is the executive signal for distribution on ground, arrow, performs PLC control by front end.The discrete process of current signal reduces the possibility of inter-signal interference, thus the reliability of elevator system work; On the other hand, communication modes adopts the TCP/UDP mode based on standard ICP/IP protocol stack; Agreement carries route, flow-control, error code correction, the automatically function such as confirmation and re-transmission, promotes the robustness of data transmission.
Description
Technical field
The utility model belongs to carrier rocket technology field, is specifically related to a kind of test of carrier rocket, transmitting and control system.
Background technology
Current carrier rocket ground test, transmitting and control system are a set of with PLC technology core, take network technology as the remote Measure and launch system of means.Because carrier rocket possesses certain risk when launching, therefore launch vehicle measurement is generally divided into front end, rear end two large divisions.Headend equipment is generally positioned on rocket launching pylon, for surveying the executing agency sending out flow process, is directly connected with rocket body by cable.Rear end equipment is generally positioned at sends out hall from the survey away from launching tower, for surveying the control and data interpretation mechanism of sending out flow process.Distance between front and back ends reaches several kilometers of even dozens of kilometres usually, passes through Fiber connection.Operating personnel send out by direct control rear end equipment in hall in survey, and Long-distance Control headend equipment performs to survey sends out flow process, and in rear end interpretation test result.
In the prior art, rear end 485 optical transmitter and receiver is connected to by 485 communication modules and 485 communication cables after carrier rocket ground test, transmitting and control system rear end PLC receive instruction, by the optical fiber of several kilometers, be connected with front end 485 optical transmitter and receiver, again by 485 communication cables and 485 communication modules by command to front end PLC, after front end PLC receives relevant instruction, control the work such as equipment or ground power supply on carrier rocket arrow power on, and partial data is carried out sampling display.
Owing to being introduced in the PLC module of front end by the small area analysis signal of unit on the big current signal of power supply and arrow simultaneously, easily cause interference, cause the saltus step of front end PLC module sampled signal, the instruction sending mistake, to unit on arrow, causes more serious consequence.
RS485 is a kind of data/address bus of difference form serial transmission, transfer rate is between 9600-115200bps, transfer rate is slower, and communication underlying protocol does not have error correction, whole network communication robustness is not strong, and use 485 communications also to need 485 special communication cables, compile special communication program etc., versatility is not strong simultaneously, inconvenient stand-alone debugging, is unfavorable for that the large data of carrier rocket, high-throughput data transmit.
Along with the mankind are to the quickening of space probation paces, transmitting closeness is higher.More safe, reliable to the launch requirements of carrier rocket.Traditional RS485 communication transfer and ground test, transmitting and control system can not meet the demand of present carrier rocket to ground test, transmitting and control system, and transfer rate is slow, and reliability is low.
Utility model content
In order to overcome the defect existed in prior art, the utility model provides a kind of test of New Launch, transmitting and control system.Concrete technical scheme is as follows:
The test of New Launch, transmitting and a control system, comprise rear end equipment, headend equipment and communication apparatus, and rear end equipment comprises rear end and sends out control PLC and host computer; Rear end is sent out control PLC and is comprised the first communication unit, second communication unit and third communication unit; Headend equipment comprises front end and sends out control PLC, front end execution PLC and a power supply; First front end is sent out control PLC and is comprised the 4th communication unit, and front end performs PLC and comprises the 5th communication unit; Communication apparatus comprises the first optical transmitter and receiver, the second optical transmitter and receiver, the 3rd optical transmitter and receiver, the 4th optical transmitter and receiver and optical cable;
Wherein, the first communication unit connects the first optical transmitter and receiver, and second communication unit connects the second optical transmitter and receiver; First optical transmitter and receiver and the second optical transmitter and receiver are used for the signal of telecommunication received being converted to optical signal and transferring to optical cable; 3rd optical transmitter and receiver connects the 4th communication unit, and the 5th communication unit connects the 4th optical transmitter and receiver; 3rd optical transmitter and receiver and the 4th optical transmitter and receiver are used for the optical signal received from optical cable to be converted to the signal of telecommunication; Third communication unit is used for and upper machine communication; Front end is sent out control PLC and is also connected with unit on an arrow, transfers to unit on arrow after the signal of telecommunication received is converted to control instruction; Front end performs PLC and is also connected with power supply, is converted to by the signal of telecommunication received and performs command to power supply;
Control PLC is sent out for receiving the small area analysis signal of telecommunication in front end, and front end performs PLC for receiving large-current electric signal;
The small area analysis signal of telecommunication corresponds to the test of carrier rocket, transmitting and control; The execution that big current signal corresponds to ground, rocket supplies distribution.
Preferably, first communication unit, second communication unit, third communication unit, the 4th communication unit and the 5th communication unit are ethernet standard communication mode, and namely the first communication unit, second communication unit, third communication unit, the 4th communication unit and the 5th communication unit are respectively the first ethernet communication unit, the second ethernet communication unit, three-ethernet communication unit, the 4th ethernet communication unit and the 5th ethernet communication unit;
First optical transmitter and receiver, the second optical transmitter and receiver, the 3rd optical transmitter and receiver and the 4th optical transmitter and receiver all adopt Ethernet optical transmitter and receiver, and namely the first optical transmitter and receiver, the second optical transmitter and receiver, the 3rd optical transmitter and receiver and the 4th optical transmitter and receiver are respectively the first Ethernet optical transmitter and receiver, the second Ethernet optical transmitter and receiver, three-ethernet optical transmitter and receiver, the 4th Ethernet optical transmitter and receiver.
Preferably, front end send out control PLC be connected by the first cable with a rocket unit; Front end is performed PLC and is connected by the second cable with power supply.
Preferably, rear end equipment and headend equipment are interconnected by the TCP/UDP protocol mode of standard ICP/IP protocol stack.
Compared with prior art, the utility model decrease front end PLC be vulnerable to interference send the problems such as instruction, transmission communication transmission rate is slow, error correcting capability is poor by mistake, make whole carrier rocket ground test, launch and reliability control system be improved; On the other hand, communication modes adopts the TCP/UDP mode based on standard ICP/IP protocol stack; Agreement carries route, flow-control, error code correction, the automatically function such as confirmation and re-transmission, promotes the robustness of data transmission.
Accompanying drawing explanation
Fig. 1 be New Launch test, launch and the structure chart of control system;
Fig. 2 is carrier rocket ground test in prior art, launches and the structure chart of control system.
Detailed description of the invention
The utility model is described in detail by way of example below in conjunction with accompanying drawing.
Embodiment 1
As shown in Figure 1, a kind of test of New Launch, transmitting and control system, comprise rear end equipment, headend equipment and communication apparatus, and rear end equipment comprises rear end and sends out control PLC1 and host computer 4; Rear end is sent out control PLC1 and is comprised the first communication unit 11, second communication unit 12 and third communication unit 13; Headend equipment comprises front end and sends out control PLC5, front end execution PLC6 and a power supply 9; First front end is sent out control PLC5 and is comprised the 4th communication unit 51, and front end performs PLC6 and comprises the 5th communication unit 61; Communication apparatus comprises the first optical transmitter and receiver 2, second optical transmitter and receiver 3, the 3rd optical transmitter and receiver 7, the 4th optical transmitter and receiver 8 and optical cable;
Wherein, the first communication unit 11 connects the first optical transmitter and receiver 2, and second communication unit 12 connects the second optical transmitter and receiver 3; First optical transmitter and receiver 2 and the second optical transmitter and receiver 3 are for being converted to optical signal by the signal of telecommunication received and transferring to optical cable; 3rd optical transmitter and receiver 7 connects the 4th communication unit the 51, five communication unit 61 and connects the 4th optical transmitter and receiver 8; 3rd optical transmitter and receiver 7 and the 4th optical transmitter and receiver 8 are for being converted to the signal of telecommunication the optical signal received from optical cable; Third communication unit 13 for host computer 4 communication; Front end is sent out control PLC5 and is also connected with a rocket unit, transfers to rocket unit after the signal of telecommunication received is converted to control instruction; Front end performs PLC6 and is also connected with power supply 9, is converted to by the signal of telecommunication received and performs command to power supply 9;
Control PLC5 is sent out for receiving the small area analysis signal of telecommunication in front end, and front end performs PLC6 for receiving large-current electric signal;
The small area analysis signal of telecommunication corresponds to the test of carrier rocket, transmitting and control; The execution that big current signal corresponds to ground, rocket supplies distribution.
Particularly, first communication unit 11, second communication unit 12, third communication unit 13, the 4th communication unit 51 and the 5th communication unit 61 are ethernet standard communication mode in the present embodiment, and namely the first communication unit 11, second communication unit 12, third communication unit 13, the 4th communication unit 51 and the 5th communication unit 61 are respectively the first ethernet communication unit 11, second ethernet communication unit 12, three-ethernet communication unit 13, the 4th ethernet communication unit 51 and the 5th ethernet communication unit 61;
First optical transmitter and receiver 2, second optical transmitter and receiver 3, the 3rd optical transmitter and receiver 7 and the 4th optical transmitter and receiver 8 all adopt Ethernet optical transmitter and receiver, and namely the first optical transmitter and receiver 2, second optical transmitter and receiver 3, the 3rd optical transmitter and receiver 7 and the 4th optical transmitter and receiver 8 are respectively the first Ethernet optical transmitter and receiver 2, second Ethernet optical transmitter and receiver 3, three-ethernet optical transmitter and receiver 7, the 4th Ethernet optical transmitter and receiver 8.
Particularly, in the present embodiment front end send out control PLC5 be connected by the first cable with a rocket unit; Front end is performed PLC6 and is connected by the second cable with power supply 9.
Particularly, rear end equipment and headend equipment are interconnected by the TCP/UDP protocol mode of standard ICP/IP protocol stack in the present embodiment.
The present embodiment is only and realizes a kind of optimal enforcement example of the present utility model; protection domain of the present utility model is not limited; any those skilled in the art passes through the non-version through creative work of the present embodiment, all in protection domain of the present utility model.
On the one hand, the utility model decrease front end PLC be vulnerable to interference send the problems such as instruction, transmission communication transmission rate is slow, error correcting capability is poor by mistake, make whole carrier rocket ground test, launch and reliability control system be improved; On the other hand, communication modes adopts the TCP/UDP mode based on standard ICP/IP protocol stack; Agreement carries route, flow-control, error code correction, the automatically function such as confirmation and re-transmission, promotes the robustness of data transmission.
Embodiment 2
Below by way of the form of a specific embodiment, introduce workflow of the present utility model further.
A. rear end is sent out control PLC1 and is received power control command signal A, converts electrical signals to optical signal and this optical signal is sent to optical cable after control command signal A enters Ethernet by the second ethernet communication unit 12 by the second Ethernet optical transmitter and receiver 3; Then, aforementioned optical signal enters the transmission that optical cable carries out growing distance, aforementioned optical signal transmission is to the 4th Ethernet optical transmitter and receiver 8, this optical signal is converted to the corresponding signal of telecommunication by the 4th Ethernet optical transmitter and receiver 8, i.e. control command signal A, this control command signal A enter front end by the 5th communication unit 61 and perform PLC6, finally, front end execution PLC6 will receive control command signal A and be converted to fill order, and by cable, instruction will be sent to ground power supply 9.
B. rear end is sent out control PLC1 and is received other control command signals B, converts electrical signals to optical signal and this optical signal is sent to optical cable after control command signal B enters Ethernet by the first communication unit 11 by the first Ethernet optical transmitter and receiver 2; Then, aforementioned optical signal entry communication optical cable carries out the transmission growing distance, aforementioned optical signal transmission is to the 4th Ethernet optical transmitter and receiver 7, optical signal is converted to the corresponding signal of telecommunication by three-ethernet optical transmitter and receiver 7, i.e. control command signal B, control command signal B enters front end by the 4th ethernet communication unit 51 and sends out control PLC5, finally, front end is sent out control PLC5 and the control command signal B received is converted to corresponding fill order, and by cable, instruction is sent to rocket unit, to reach the object to carrier rocket test or transmitting or control.
By carrier rocket ground test of the present utility model, to launch and control system decreases front end PLC and is vulnerable to disturb and sends instruction by mistake, substantially increase transmission communication transmission rate, enhance network error correction ability, further increase the problems such as network communication robustness, whole carrier rocket ground test, transmitting and reliability control system are further enhanced.
Several specific embodiments of the application being only above, but the not limited thereto the changes that any person skilled in the art can think of of the application, all should drop in the protection domain of the application.
Claims (4)
1. the test of New Launch, transmitting and a control system, comprise rear end equipment, headend equipment and communication apparatus, it is characterized in that, described rear end equipment comprises rear end and sends out control PLC (1) and host computer (4); Described rear end is sent out control PLC (1) and is comprised the first communication unit (11), second communication unit (12) and third communication unit (13); Described headend equipment comprises front end and sends out control PLC (5), front end execution PLC (6) and a power supply (9); Described front end is sent out control PLC (5) and is comprised the 4th communication unit (51), and described front end performs PLC (6) and comprises the 5th communication unit (61); Described communication apparatus comprises the first optical transmitter and receiver (2), the second optical transmitter and receiver (3), the 3rd optical transmitter and receiver (7), the 4th optical transmitter and receiver (8) and optical cable;
Wherein, described first communication unit (11) connects described first optical transmitter and receiver (2), and described second communication unit (12) connects described second optical transmitter and receiver (3); Described first optical transmitter and receiver (2) and described second optical transmitter and receiver (3) are for being converted to optical signal by the signal of telecommunication received and transferring to described optical cable; Described 3rd optical transmitter and receiver (7) connects described 4th communication unit (51), and described 5th communication unit (61) connects described 4th optical transmitter and receiver (8); Described 3rd optical transmitter and receiver (7) and described 4th optical transmitter and receiver (8) are for being converted to the signal of telecommunication the optical signal received from described optical cable; Described third communication unit (13) for described host computer (4) communication; Described front end is sent out control PLC (5) and is also connected with unit on an arrow, transfers to unit on described arrow after the signal of telecommunication received is converted to control instruction; Described front end performs PLC (6) and is also connected with described power supply (9), is converted to by the signal of telecommunication received and performs command to described power supply (9);
Control PLC (5) is sent out for receiving the small area analysis signal of telecommunication in described front end, and described front end performs PLC (6) for receiving large-current electric signal;
The described small area analysis signal of telecommunication corresponds to the test of described carrier rocket, transmitting and control; The execution that described big current signal corresponds to ground, rocket supplies distribution.
2. the test of a kind of New Launch according to claim 1, launch and control system, it is characterized in that, described first communication unit (11), described second communication unit (12), described third communication unit (13), described 4th communication unit (51) and described 5th communication unit (61) are ethernet standard communication mode, i.e. described first communication unit (11), described second communication unit (12), described third communication unit (13), described 4th communication unit (51) and described 5th communication unit (61) are respectively the first ethernet communication unit (11), second ethernet communication unit (12), three-ethernet communication unit (13), 4th ethernet communication unit (51) and the 5th ethernet communication unit (61),
Described first optical transmitter and receiver (2), described second optical transmitter and receiver (3), described 3rd optical transmitter and receiver (7) and described 4th optical transmitter and receiver (8) all adopt Ethernet optical transmitter and receiver, and namely described first optical transmitter and receiver (2), described second optical transmitter and receiver (3), described 3rd optical transmitter and receiver (7) and described 4th optical transmitter and receiver (8) are respectively the first Ethernet optical transmitter and receiver (2), the second Ethernet optical transmitter and receiver (3), three-ethernet optical transmitter and receiver (7), the 4th Ethernet optical transmitter and receiver (8).
3. the test of a kind of New Launch according to claim 1, transmitting and control system, is characterized in that, described front end is sent out control PLC (5) and is connected by the first cable with a rocket unit; Described front end is performed PLC (6) and is connected by the second cable with described power supply (9).
4. the test of a kind of New Launch according to claim 2, transmitting and control system, is characterized in that, described rear end equipment and described headend equipment are interconnected by the TCP/UDP protocol mode of standard ICP/IP protocol stack.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420321184.7U CN204142106U (en) | 2014-06-16 | 2014-06-16 | The test of New Launch, transmitting and control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420321184.7U CN204142106U (en) | 2014-06-16 | 2014-06-16 | The test of New Launch, transmitting and control system |
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| Publication Number | Publication Date |
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| CN204142106U true CN204142106U (en) | 2015-02-04 |
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| CN201420321184.7U Expired - Lifetime CN204142106U (en) | 2014-06-16 | 2014-06-16 | The test of New Launch, transmitting and control system |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109782729A (en) * | 2017-11-10 | 2019-05-21 | 北京航天万源科技有限公司 | One kind being used for the test-fired multifunctional comprehensive launch vehicle measurement of priming system |
| CN109870070A (en) * | 2019-03-01 | 2019-06-11 | 北京星际荣耀空间科技有限公司 | A kind of integrated wireless launch vehicle measurement applied to Solid Launch Vehicle |
| CN110895398A (en) * | 2019-12-05 | 2020-03-20 | 中国航天空气动力技术研究院 | Missile simulated emission testing device |
| CN111653151A (en) * | 2020-06-30 | 2020-09-11 | 四川深蓝未来航天科技有限公司 | Rocket launching experience system and rocket launching experience method |
| CN112327679A (en) * | 2020-10-12 | 2021-02-05 | 中国运载火箭技术研究院 | Ground measurement and launch control system |
-
2014
- 2014-06-16 CN CN201420321184.7U patent/CN204142106U/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109782729A (en) * | 2017-11-10 | 2019-05-21 | 北京航天万源科技有限公司 | One kind being used for the test-fired multifunctional comprehensive launch vehicle measurement of priming system |
| CN109782729B (en) * | 2017-11-10 | 2020-11-27 | 北京航天万源科技有限公司 | Multifunctional comprehensive testing and launching control system for initiating explosive device ignition test |
| CN109870070A (en) * | 2019-03-01 | 2019-06-11 | 北京星际荣耀空间科技有限公司 | A kind of integrated wireless launch vehicle measurement applied to Solid Launch Vehicle |
| CN110895398A (en) * | 2019-12-05 | 2020-03-20 | 中国航天空气动力技术研究院 | Missile simulated emission testing device |
| CN110895398B (en) * | 2019-12-05 | 2021-07-13 | 中国航天空气动力技术研究院 | Missile simulated emission testing device |
| CN111653151A (en) * | 2020-06-30 | 2020-09-11 | 四川深蓝未来航天科技有限公司 | Rocket launching experience system and rocket launching experience method |
| CN111653151B (en) * | 2020-06-30 | 2022-05-06 | 四川深蓝未来航天科技有限公司 | Rocket launching experience system and rocket launching experience method |
| CN112327679A (en) * | 2020-10-12 | 2021-02-05 | 中国运载火箭技术研究院 | Ground measurement and launch control system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20180125 Address after: 200050 Anhua Road, Shanghai, No. 492, No. Patentee after: SHANGHAI AEROSPACE COMPUTER TECHNOLOGY Research Institute Address before: 200082 Qigihar Road, Shanghai, No. 76, No. Patentee before: SHANGHAI SPACEFLIGHT ELECTRONIC AND COMMUNICATION EQUIPMENT Research Institute |
|
| TR01 | Transfer of patent right | ||
| CX01 | Expiry of patent term |
Granted publication date: 20150204 |