CN102221309A - Rocket and antiaircraft gun operation control and safety monitoring system and operation monitoring method - Google Patents
Rocket and antiaircraft gun operation control and safety monitoring system and operation monitoring method Download PDFInfo
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- CN102221309A CN102221309A CN201110132819XA CN201110132819A CN102221309A CN 102221309 A CN102221309 A CN 102221309A CN 201110132819X A CN201110132819X A CN 201110132819XA CN 201110132819 A CN201110132819 A CN 201110132819A CN 102221309 A CN102221309 A CN 102221309A
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Abstract
The invention discloses a rocket and antiaircraft gun operation control and safety monitoring system and an operation monitoring method. The system comprises a plurality of operation point acquisition and control units 1 and an artificially-influenced weather operation central management platform, namely an upper computer 2, wherein data is transmitted between the upper computer 2 and the operation point acquisition and control units 1 through mobile communication and the Internet. The operation monitoring method comprises the following steps of: controlling the launching of a rocket or an antiaircraft gun; automatically acquiring operation information such as a launching pitch angle, a launching azimuth angle, rocket or antiaircraft gun launching information, longitude and latitude coordinates of operation points, operation time, operation ammunition using amount, operation channel numbers, ignition circuit resistance and the like; and uploading the operation information to a management center to monitor operation safety in a unified mode. By the system and the method, the problem of inaccurate information caused by manually recording and transmitting the operation information through personnel in the prior art is solved, and an effective tool is provided for a manager to accurately and timely master the information and scientifically perform artificially-influenced weather command and management.
Description
Technical field:
The present invention relates to utilize radio communication, information gathering and electronic recognition technology control rocket, antiaircraft gun operation and process is monitored, in the time of control rocket or antiaircraft gun emission, automatically gather the emission process job information, and information is transferred to administrative center by wireless mode so that carry out the job safety management, specifically be rocket, antiaircraft gun operation control and safety monitoring system and method for monitoring operation.
Background technology:
The Weather modification operation that extensively carries out at present is by firing a rocket or shell is finished, fire a rocket or shell by ignition controller, finish by adjusting rocket pod or antiaircraft gun gun tube at emission pitching, azimuth, rocket or shell, launcher or antiaircraft gun and ignition controller, separate between three parts, fire a rocket or shell the time, can not write down the numbering of pitching, azimuth and rocket or shell automatically.Each setting of district all is hand-kept operation situation and job information, report province shadow center by report form again, form exists the people for failing to report, do not report or wrong expression condition, and information reports untimely, weather modification administrative center can't grasp the operation situation of each setting of district in real time, be difficult to the science unified management is carried out in safety work, for accomplishing the whole province's shadow job safety management, need monitor automatically the operation concrete condition of antiaircraft gun or each setting of rocket weather modification, gather job information and be transferred to administrative center and carry out security monitoring by mobile communications network.Some monitoring system is to record the field operation outdoor scene by camera system or alternate manner are installed at present, realize collecting the purpose of job information, can not get launching pitching, azimuth on the one hand, on the other hand, do not accomplish the real-time Transmission job information, and can not be synchronous with operation control; And there are resentment in many settings to monitoring, the camera phenomenon often occurs blocking, run into this type of problem, and this monitoring system is thoroughly paralysed, can't operate as normal.Other monitoring system can not be gathered All Jobs information automatically, only can gather pitching, azimuth, operation bullet amount etc. as described in patent CN200920307552.1, and can not collect the relevant information of operation rocket or shell.Therefore, the present invention proposes a kind of rocket, antiaircraft gun operation control and safety monitoring system, gathers job information automatically and upload in the emission of control rocket or shell, satisfies the job safety management expectancy.When system of the present invention is connected with other functional module, can expand the management platform function, for example be connected with the Weather Modification Operation Command System Based system, can realization science commander operation function.The present invention also can be applicable to carry out operation safe monitoring in all fields of adopting rocket or shell operation, as forest fire protection, fire extinguishing, and artificial lightning protection, the thunder that disappears, fields such as arrtificial fog dissipation operation.
Summary of the invention:
In order to overcome rocket, the antiaircraft gun Weather modification operation is not controlled, can not gather job information automatically and upload job information in real time, cause Weather modification operation can not carry out unified management, the problem of operation safe monitoring difficulty, the present invention proposes a kind of rocket, antiaircraft gun operation control and safety monitoring system and method for monitoring operation, purpose is that control is fired a rocket or antiaircraft gun the time, automatically gather and comprise the emission pitching, the azimuth, fire a rocket or shell information, the setting latitude and longitude coordinates, activity duration, operation bullet amount, operation path number, job informations such as ignition circuit resistance, and job information uploaded administrative center, carry out the job safety unified monitoring.
Consult Fig. 1, a kind of rocket, antiaircraft gun operation control and the safety monitoring system that the present invention proposes comprises a plurality of settings collection control modules 1 and a weather modification activity center management platform, and promptly host computer 2; Described host computer 2 and setting are gathered between the control module 1 and are carried out transfer of data by mobile communication and internet;
Consult Fig. 2, one of them setting is gathered control module 1 by ignition controller 101, and transcoder controller 102 in the information, collector 103, pitching, azimuth reader 104, rocket or shell identity recognizer 105, electronic identity label 106, launcher or antiaircraft gun 107, rocket or shell 108 are formed; Described rocket or shell 108 are installed on launcher or the antiaircraft gun 107; Described electronic identity label 106 contains manufacturer, and product type, numbering, date of manufacture and product performance information are fixed on rocket or the shell 108; Described pitching, azimuth reader 104 and rocket or shell identity recognizer 105 are fixed on launcher or the antiaircraft gun 107; Collector 103 reads the information of pitching, azimuth reader 104 and rocket or shell identity recognizer 105, by bi-directional transfer of data between the transcoder controller 102 in wireless communication module and the described information; 101 pairs of rockets of described ignition controller or shell 108 are controlled, and simultaneously, ignition controller 101 is also via carrying out bidirectional data exchange between collector 103 and the middle transcoder controller 102;
Consult Fig. 3, transcoder controller 102 is made up of transcoder controller wireless communication module 206, ignition control unit 207, data storage cell 208, keyboard and interface circuit 209, usb interface module 210 in transcoder controller microcontroller 205, the information in information transfer controller power circuit 201, display 202, mobile communication module 203, GPS module 204, the information in the described information; Transcoder controller wireless communication module 206, usb interface module 210, ignition control unit 207 and data storage cell 208 are connected by pin between the transcoder controller microcontroller 205 respectively with in the information in described mobile communication module 203, the information, carry out bidirectional data exchange; Described ignition control unit 207 is made up of encoder and logic circuit; Described keyboard and interface circuit 209 and display 202 provide the input and output of man-machine interaction respectively to transcoder controller microcontroller 205 in the information; Described information transfer controller power circuit 201 is given transcoder controller wireless communication module 206 and usb interface module 210 power supplies in display 202, mobile communication module 203, GPS module 204, microcontroller 205, the information respectively;
Wherein said display 202, data storage cell 208, keyboard and interface circuit 209, usb interface module 210 are not transcoder controller 102 necessary component in the information, remove transcoder controller 102 realizations function of the present invention in these not influence of module information;
Consult Fig. 4, described collector 103 is made up of collector power circuit 301, resistance detecting circuit 302, collector microcontroller 303, collector wireless communication module 304, information gathering processing unit 305, short-circuit control circuit 306 and decoder 307; Described resistance detecting circuit 302, collector wireless communication module 304 and information gathering processing unit 305 are connected by pin respectively with between the collector microcontroller 303, carry out bidirectional data exchange; Described short-circuit control circuit 306 is made of short-circuiting device and short circuit control logic circuit, is used for rocket or shell 108 ignition circuits are carried out short circuit; After the coded message that described decoder 307 generates encoder in the ignition control unit 207 is decoded, pass to collector microcontroller 303; The firing command that transcoder controller 102 sends in the described wireless communication module 304 reception information, and will instruct by collector microcontroller 303 and to transmit ignition controller 101 execution; Simultaneously, described collector wireless communication module 304 sends it back transcoder controller 102 in the information with the execution result of ignition controller 101; Described collector power circuit 301 is given collector microcontroller 303, collector wireless communication module 304 and decoder 307 power supplies respectively;
Wherein said short-circuit control circuit 306 is not collector 103 necessary component, and removing this module does not influence collector 103 realizations function of the present invention; Short-circuit control circuit is used for rocket or shell 108 ignition circuits are carried out short circuit, increases rocket, antiaircraft gun operation control and safety monitoring system security.
Based on above-mentioned rocket, antiaircraft gun operation control and safety monitoring system, the invention allows for a kind of rocket, antiaircraft gun method for monitoring operation, comprise the steps:
Step 3 is gathered job information; Gather pitching, azimuth reader 104 information α on launcher or the antiaircraft gun 107
1Information ID with electronic identity label 106
1Detect each transmission channel ignition circuit resistance R
1, gather job position latitude and longitude coordinates and operation constantly;
Step 4 is waited for and to be fired a rocket or the instruction of shell 108; If instruction is arranged, enter step 5; Otherwise, continue to wait for and to fire a rocket or the instruction of shell 108;
Step 5 judges whether current firing order satisfies ignition condition; If ignition circuit resistance R
1＜R
0, R
0For limiting resistance, 1 Ω≤R
0≤ 20 Ω, and ignition voltage U＞U
0, U
0Be rated voltage, 5V≤U
0≤ 100V, then ignition function release is fired a rocket or shell;
Otherwise, work as R
1〉=R
0The time, the network type electron function is forbidden emission, shows that resistance overflows, and enters step 4; Work as U
1≤ U
0The time, the network type electron function is forbidden emission, shows the ignition voltage deficiency, enters step 4;
Step 6 is gathered job information again; Collector 103 is gathered pitching, the azimuth reader 104 information α on launcher or the antiaircraft gun 107 again
2Information ID with electronic identity label 106
2Detect each transmission channel ignition circuit resistance R
2, gather job position latitude and longitude coordinates and operation constantly;
Step 7, comparison step 3 and step 6 job information are determined to fire a rocket or shell 108 information; If | R
1-R
2|＞2 Ω and N (ID
1)＞N (ID
2), N (ID
1) and N (ID
2) represent ID respectively
1And ID
2The information bar number, then one piece of rocket of this passage emission or shell 108, ID
1In remove ID
2Outside information for the emission rocket or shell 108 information;
Step 8, transcoder controller 102 storage operation information in the information;
Step 9 judges whether network is online, if enter step 10, otherwise this job information storage is not sent information bank;
Step 10 is uploaded host computer 101 with job information; Host computer 101 storage operation information; Host computer 101 shows job information.
The invention has the beneficial effects as follows:
Rocket, antiaircraft gun operation control and safety monitoring system and method for monitoring operation that 1 the present invention proposes, control fire a rocket or antiaircraft gun in, automatically gather comprise emission pitching, azimuth, fire a rocket or shell information, setting latitude and longitude coordinates, activity duration, operation with bullet amount, operation path number, job informations such as ignition circuit resistance, and job information uploaded administrative center, carry out the job safety unified monitoring.Solved the inaccurate problem of information that in the past caused by manual typing of personnel and transmission job information, for administrative staff accurately and timely grasp information, science is carried out the weather modification commander, management provides effective tool.
2 each part degree of modularity height of the present invention, interchangeability is good, and simple installation is easy to safeguard.
Description of drawings:
Fig. 1: rocket, antiaircraft gun operation control and safety monitoring system schematic diagram that the present invention proposes
Fig. 2: a setting is gathered the composition schematic diagram of control module
Fig. 3: transcoder controller schematic diagram in the information
Fig. 4: collector schematic diagram
Fig. 5: rocket, antiaircraft gun method for monitoring operation
Among the figure, the 1--setting is gathered control module, 2--host computer, 101--ignition controller, transcoder controller in the 102--information, the 103--collector, the 104--pitching, the azimuth reader, 105--rocket or shell identity recognizer, the 106--electronic identity label, 107--launcher or antiaircraft gun, 108--rocket or shell, 201--information transfer controller power circuit, the 202--display, the 203--mobile communication module, 204--GPS module, transcoder controller microcontroller in the 205--information, transcoder controller wireless communication module in the 206--information, the 207--ignition control unit, 208--data storage cell, 209--keyboard and interface circuit, the 210--USB interface module, 301--collector power circuit, 302--resistance detecting circuit, 303--collector microcontroller, 304--collector wireless communication module, 305--information gathering processing unit, 306--short-circuit control circuit, 307--decoder.
Specific embodiment:
Embodiment 1:
Present embodiment has provided a kind of rocket operation control and safety monitoring system and method for monitoring operation.Consult Fig. 1, rocket operation control and safety monitoring system among this embodiment comprise a plurality of settings collection control modules 1 and a weather modification activity center management platform, and promptly host computer 2; Described host computer 2 and setting are gathered between the control module 1 and are carried out transfer of data by mobile communication GPRS;
Consult Fig. 2, one of them setting is gathered control module 1 by ignition controller 101, and transcoder controller 102 in the information, collector 103, and pitching, azimuth reader 104, rocket or shell identity recognizer 105, electronic identity label 106, launcher, rocket is formed; Described rocket is installed on the launcher; Described electronic identity label 106 is installed on the rocket, described pitching, azimuth reader 104, and rocket or shell identity recognizer 105 are fixed on the launcher; Collector 103 reads the information of pitching, azimuth reader 104 and rocket or shell identity recognizer 105, bi-directional transfer of data between the transcoder controller 102 in wireless communication module by frequency 433MHz and the described information; 101 pairs of rockets of described ignition controller are controlled, and simultaneously, ignition controller 101 is also via carrying out bi-directional transfer of data between collector 103 and the middle transcoder controller 102;
Pitching in the present embodiment, azimuth reader 104 adopt three-dimensional electronic compass, are fixed on the launcher track by 3 M3 screws;
Rocket or shell identity recognizer 105 adopt UHF RFID identifier in the present embodiment, are installed in launcher finder frame central authorities;
Electronic identity label 106 adopts papery UHF RFID electronic tag to stick on the rocket; Described papery UHF RFID electronic tag contains manufacturer, and information such as product type, numbering, date of manufacture and product performance are set 10 bytes, and wherein 2 bytes are encrypted bits;
Consult Fig. 3, transcoder controller 102 is made up of transcoder controller wireless communication module 206, ignition control unit 207, data storage cell 208, keyboard and interface circuit 209, usb interface module 210 in transcoder controller microcontroller 205, the information in information transfer controller power circuit 201, display 202, mobile communication module 203, GPS module 204, the information in the described information; Mobile communication module 203 adopts the GPRS module in the present embodiment; Transcoder controller wireless communication module 206, usb interface module 210, ignition control unit 207 and data storage cell 208 are connected by pin between the transcoder controller microcontroller 205 respectively with in the information in described GPRS module, the information, carry out bidirectional data exchange; Described ignition control unit 207 is made up of encoder and logic circuit; Described keyboard and interface circuit 209 and display 202 provide the input and output of man-machine interaction respectively to transcoder controller microcontroller 205 in the information; Described information transfer controller power circuit 201 is given transcoder controller wireless communication module 206 and usb interface module 210 power supplies in display 202, GPRS module, GPS module 204, microcontroller 205, the information respectively;
Consult Fig. 4, described collector 103 is made up of collector power circuit 301, resistance detecting circuit 302, collector microcontroller 303, collector wireless communication module 304, information gathering processing unit 305, short-circuit control circuit 306 and decoder 307; Described resistance detecting circuit 302, wireless communication module 304 and information gathering processing unit 305 are connected by pin respectively with between the collector microcontroller 303, carry out bidirectional data exchange; Described short-circuit control circuit 306 is made of short-circuiting device and short circuit control logic circuit, is used for the rocket firing circuit is carried out short circuit; After the coded message that described decoder 307 generates encoder in the ignition control unit 207 is decoded, pass to collector microcontroller 303; The firing command that transcoder controller 102 sends in the described collector wireless communication module 304 reception information, and will instruct by collector microcontroller 303 and to transmit ignition controller 101 execution; Simultaneously, described collector wireless communication module 304 sends it back transcoder controller 102 in the information with the execution result of ignition controller 101; Described collector power circuit 301 is given collector microcontroller 303, collector wireless communication module 304 and decoder 307 power supplies respectively.
Consulting Fig. 5, is example with actual weather modification rocket operation once, introduces rocket operation method for supervising of the present invention:
Step 3 is gathered job information; Gather the three-dimensional compass information α on the launcher
1Information ID with papery UHF RFID electronic tag
1Detect each transmission channel ignition circuit resistance R
1, gather job position latitude and longitude coordinates and operation constantly;
Step 4 is waited for the instruction of firing a rocket; If instruction is arranged, enter step 5; Otherwise, continue to wait for the instruction of firing a rocket;
Step 5 judges whether current firing order satisfies ignition condition; If ignition circuit resistance R
1＜R
0, R
0Be qualification resistance, and ignition voltage U＞U
0, U
0Be rated voltage, then ignition function release is fired a rocket; Among this embodiment, U
1=50V, R
0=10 Ω;
Otherwise, work as R
1〉=R
0The time, the network type electron function is forbidden emission, shows that resistance overflows, and enters step 4; Work as U
1≤ U
0The time, the network type electron function is forbidden emission, shows the ignition voltage deficiency, enters step 4;
Step 6 is gathered job information again; Collector 103 is gathered the three-dimensional electronic compass information α on the launcher again
2Information ID with papery UHF RFID electronic tag
2Detect each transmission channel ignition circuit resistance R
2, gather job position latitude and longitude coordinates and operation constantly;
Step 7, comparison step 3 and step 6 job information are determined the information of firing a rocket; If | R
1-R
2|＞2 Ω and N (ID
1)＞N (ID
2), N (ID
1) and N (ID
2) represent ID respectively
1And ID
2The information bar number, one piece of rocket of this passage emission then, ID
1In remove ID
2Outside information be the information of firing a rocket;
Step 8, transcoder controller 102 storage operation information in the information;
Step 9 judges whether network is online, if enter step 10, otherwise this job information storage is not sent information bank;
Step 10 is uploaded host computer 101 with job information; Host computer 101 storage operation information; Host computer 101 shows job information.
Embodiment 2:
Present embodiment has provided a kind of antiaircraft gun operation control and safety monitoring system and method for monitoring operation.Consult Fig. 1, antiaircraft gun operation control among this embodiment and safety monitoring system comprise a plurality of settings collection control modules 1 and a host computer 2; Described host computer 2 and setting are gathered between the control module 1 and are communicated by letter by 3G;
Consult Fig. 2, one of them setting is gathered control module 1 by ignition controller 101, and transcoder controller 102 in the information, collector 103, and pitching, azimuth reader 104, the shell identity recognizer, electronic identity label 106, antiaircraft gun, shell is formed; Described shell is installed on the antiaircraft gun; Described electronic identity label 106 is fixed on the shell, and described pitching, azimuth reader 104 and shell identity recognizer are fixed on the antiaircraft gun; Collector 103 reads the information of pitching, azimuth reader 104 and shell identity recognizer, bi-directional transfer of data between the transcoder controller 102 in wireless communication module by frequency 315MHz and the described information; 101 pairs of shells of described ignition controller are controlled, and simultaneously, ignition controller 101 is also via carrying out bi-directional transfer of data between collector 103 and the middle transcoder controller 102;
Pitching in the present embodiment, azimuth reader 104 adopt angular transducer, are fixed on the antiaircraft gun gun tube;
Rocket or shell identity recognizer 105 adopt the RFID identifier in the present embodiment, are installed on the gun tube;
Electronic identity label 106 adopts anti-metal RFID electronic tag to be fixed on the shell; Described anti-metal RFID electronic tag contains manufacturer, and information such as product type, numbering, date of manufacture and product performance are set 6 bytes, and wherein 2 bytes are encrypted bits;
Consult Fig. 3, transcoder controller 102 is made up of transcoder controller wireless communication module 206, ignition control unit 207 in transcoder controller microcontroller 205, the information in information transfer controller power circuit 201, mobile communication module 203, GPS module 204, the information in the described information; Mobile communication module 203 adopts the 3G module in the present embodiment; Transcoder controller wireless communication module 206, ignition control unit 207 are connected by pin between the transcoder controller microcontroller 205 respectively with in the information in described 3G module, the information, carry out bidirectional data exchange; Described ignition control unit 207 is made up of encoder and logic circuit; Described information transfer controller power circuit 201 is given transcoder controller wireless communication module 206 power supplies in 3G module, GPS module 204, microcontroller 205 and the information respectively;
Consult Fig. 4, described collector 103 is made up of collector power circuit 301, resistance detecting circuit 302, collector microcontroller 303, collector wireless communication module 304, information gathering processing unit 305 and decoder 307; Described resistance detecting circuit 302, collector wireless communication module 304 and information gathering processing unit 305 are connected by pin respectively with between the collector microcontroller 303, carry out bidirectional data exchange; After the coded message that described decoder 307 generates encoder in the ignition control unit 207 is decoded, pass to collector microcontroller 303; The firing command that transcoder controller 102 sends in the described collector wireless communication module 304 reception information, and will instruct by collector microcontroller 303 and to transmit ignition controller 101 execution; Simultaneously, described collector wireless communication module 304 sends it back transcoder controller 102 in the information with the execution result of ignition controller 101; Described collector power circuit 301 is given collector microcontroller 303, collector wireless communication module 304 and decoder 307 power supplies respectively.
Consulting Fig. 5, is example with actual weather modification antiaircraft gun operation once, introduces antiaircraft gun method for monitoring operation of the present invention:
Step 3 is gathered job information; Gather the angular transducer information α on the antiaircraft gun
1Information ID with anti-metal RFID electronic tag
1Detect each transmission channel ignition circuit resistance R
1, gather job position latitude and longitude coordinates and operation constantly;
Step 4 is waited for the instruction that fires shells; If instruction is arranged, enter step 5; Otherwise, continue to wait for the instruction that fires shells;
Step 5 judges whether current firing order satisfies ignition condition; If ignition circuit resistance R
1＜R
0, R
0Be qualification resistance, and ignition voltage U＞U
0, U
0Be rated voltage, then ignition function release fires shells; Among this embodiment, U
1=5V, R
0=1 Ω;
Otherwise, work as R
1〉=R
0The time, the network type electron function is forbidden emission, shows that resistance overflows, and enters step 4; Work as U
1≤ U
0The time, the network type electron function is forbidden emission, shows the ignition voltage deficiency, enters step 4;
Step 6 is gathered job information again; Collector 103 is gathered the angular transducer information α on the antiaircraft gun again
2Information ID with anti-metal RFID electronic tag
2Detect each transmission channel ignition circuit resistance R
2, gather job position latitude and longitude coordinates and operation constantly;
Step 7, comparison step 3 and step 6 job information are determined the information of firing shells; If | R
1-R
2|＞2 Ω and N (ID
1)＞N (ID
2), N (ID
1) and N (ID
2) represent ID respectively
1And ID
2The information bar number, one piece of shell of this passage emission then, ID
1In remove ID
2Outside information be the information that fires shells;
Step 8, transcoder controller 102 storage operation information in the information;
Step 9 judges whether network is online, if enter step 10, otherwise this job information storage is not sent information bank;
Step 10 is uploaded host computer 101 with job information; Host computer 101 storage operation information; Host computer 101 shows job information.
Claims (5)
1. a rocket, antiaircraft gun operation control and safety monitoring system is characterized in that: comprise a plurality of settings collection control modules (1) and a weather modification activity center management platform, i.e. host computer (2); Described host computer (2) and setting are gathered between the control module (1) and are carried out transfer of data by mobile communication and internet;
One of them setting is gathered control module (1) by ignition controller (101), transcoder controller in the information (102), collector (103), pitching, azimuth reader (104), rocket or shell identity recognizer (105), electronic identity label (106), launcher or antiaircraft gun (107), rocket or shell (108) are formed; Described rocket or shell (108) are installed on launcher or the antiaircraft gun (107); Described electronic identity label (106) contains manufacturer, and product type, numbering, date of manufacture and product performance information are fixed on rocket or the shell (108); Described pitching, azimuth reader (104) and rocket or shell identity recognizer (105) are fixed on launcher or the antiaircraft gun (107); Collector (103) reads the information of pitching, azimuth reader (104) and rocket or shell identity recognizer (105), by bi-directional transfer of data between the transcoder controller (102) in wireless communication module and the described information; Described ignition controller (101) is controlled rocket or shell (108), and simultaneously, ignition controller (101) is also via carrying out bidirectional data exchange between collector (103) and the middle transcoder controller (102);
Transcoder controller in the described information (102) is by information transfer controller power circuit (201), mobile communication module 203), in the GPS module (204), information in transcoder controller microcontroller (205), the information transcoder controller wireless communication module (206), ignition control unit (207) form; Transcoder controller wireless communication module (206) and ignition control unit (207) are connected by pin between the transcoder controller microcontroller (205) respectively with in the information in described mobile communication module (203), the information, carry out bidirectional data exchange; Described ignition control unit (207) is made up of encoder and logic circuit; Described information transfer controller power circuit (201) is given transcoder controller wireless communication module (206) power supply in mobile communication module (203), GPS module (204), microcontroller (205) and the information respectively;
Described collector (103) is made up of collector power circuit (301), resistance detecting circuit (302), collector microcontroller (303), collector wireless communication module (304), information gathering processing unit (305) and decoder (307); Described resistance detecting circuit (302), collector wireless communication module (304) and information gathering processing unit (305) are connected by pin respectively with between the collector microcontroller (303), carry out bidirectional data exchange; After the coded message that described decoder (307) generates encoder in the ignition control unit (207) is decoded, pass to collector microcontroller (303); The firing command that transcoder controller (102) sends in described wireless communication module (304) the reception information, and will instruct by collector microcontroller (303) and to transmit ignition controller (101) execution; Simultaneously, described collector wireless communication module (304) sends it back transcoder controller in the information (102) with the execution result of ignition controller (101); Described collector power circuit (301) is given collector microcontroller (303), collector wireless communication module (304) and decoder (307) power supply respectively.
2. one kind is adopted the described rocket of claim 1, antiaircraft gun operation control and safety monitoring system, and it is characterized in that: described collector (103) also comprises short-circuit control circuit (306); Described short-circuit control circuit (306) is made of short-circuiting device and short circuit control logic circuit, is used for rocket or shell (108) ignition circuit are carried out short circuit.
3. a method that adopts the described rocket of claim 1, antiaircraft gun operation control and safety monitoring system to carry out rocket, antiaircraft gun monitoring operation is characterized in that, comprises the steps:
Step 1, transcoder controller (102) is shaken hands in collector (103) and the information; Unsuccessful if shake hands, collector (103) is waited for handshake; If shake hands successfully, collector (103) enters the wait command status, and transcoder controller in the information (102) enters network login;
Step 2, network login; After normally landing, transfer and do not send information bank, upload all and do not upload job information; Land failure, then continue to land, or human intervention abandons landing, directly enter step 3;
Step 3 is gathered job information; Gather pitching, azimuth reader (104) information α on launcher or the antiaircraft gun (107)
1And the Information ID of electronic identity label (106)
1Detect each transmission channel ignition circuit resistance R
1, gather job position latitude and longitude coordinates and operation constantly;
Step 4 is waited for and to be fired a rocket or the instruction of shell (108); If instruction is arranged, enter step 5; Otherwise, continue to wait for and to fire a rocket or the instruction of shell (108);
Step 5 judges whether current firing order satisfies ignition condition; If ignition circuit resistance R
1＜R
0, R
0For limiting resistance, 1 Ω≤R
0≤ 20 Ω, and ignition voltage U＞U
0, U
0Be rated voltage, 5V≤U
0≤ 100V, then ignition function release is fired a rocket or shell;
Otherwise, work as R
1〉=R
0The time, the network type electron function is forbidden emission, shows that resistance overflows, and enters step 4; Work as U
1≤ U
0The time, the network type electron function is forbidden emission, shows the ignition voltage deficiency, enters step 4;
Step 6 is gathered job information again; Collector (103) is gathered pitching, azimuth reader (104) the information α on launcher or the antiaircraft gun (107) again
2And the Information ID of electronic identity label (106)
2Detect each transmission channel ignition circuit resistance R
2, gather job position latitude and longitude coordinates and operation constantly;
Step 7, comparison step 3 and step 6 job information are determined to fire a rocket or shell (108) information; If | R
1-R
2|＞2 Ω and N (ID
1)＞N (ID
2), N (ID
1) and N (ID
2) represent ID respectively
1And ID
2The information bar number, then one piece of rocket of this passage emission or shell (108), ID
1In remove ID
2Outside information for the emission rocket or shell (108) information;
Step 8, transcoder controller in the information (102) storage operation information;
Step 9 judges whether network is online, if enter step 10, otherwise this job information storage is not sent information bank;
Step 10 is uploaded host computer (101) with job information; Host computer (101) storage operation information; Host computer (101) shows job information.
4. a method that adopts the described rocket of claim 3, antiaircraft gun monitoring operation is characterized in that, in the described step 5, limits resistance R
0Value is: R
0=10 Ω.
5. a method that adopts the described rocket of claim 3, antiaircraft gun monitoring operation is characterized in that, in the described step 5, and rated voltage U
0Value is: U
0=50V.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110132819.XA CN102221309B (en) | 2011-05-20 | 2011-05-20 | Rocket and antiaircraft gun operation control and safety monitoring system and operation monitoring method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110132819.XA CN102221309B (en) | 2011-05-20 | 2011-05-20 | Rocket and antiaircraft gun operation control and safety monitoring system and operation monitoring method |
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| Publication Number | Publication Date |
|---|---|
| CN102221309A true CN102221309A (en) | 2011-10-19 |
| CN102221309B CN102221309B (en) | 2014-01-01 |
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ID=44777934
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103123244A (en) * | 2011-11-18 | 2013-05-29 | 中国兵器科学研究院 | 57mm digitalized figure antiaircraft gun system |
| CN103353264A (en) * | 2013-07-17 | 2013-10-16 | 晋西工业集团有限责任公司 | Delayed fuse capable of igniting according to set height |
| CN104266555A (en) * | 2014-09-30 | 2015-01-07 | 程鹏 | Artificial precipitation hail prevention rocket positioning system |
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| CN108122299A (en) * | 2017-12-21 | 2018-06-05 | 北京厚力德仪器设备有限公司 | A kind of meteorological rocket charge book instrument and its charge book method |
| CN109388852A (en) * | 2018-09-07 | 2019-02-26 | 陕西中天火箭技术股份有限公司 | A kind of rocket bomb transmitting number accurate metering method |
| CN111799710A (en) * | 2020-07-14 | 2020-10-20 | 李振南 | Automatic fixing device for submarine cable laying and using method thereof |
| CN114298392A (en) * | 2021-12-23 | 2022-04-08 | 电子科技大学 | Fire wire longitude and latitude prediction algorithm for forest fire |
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| CN103123244A (en) * | 2011-11-18 | 2013-05-29 | 中国兵器科学研究院 | 57mm digitalized figure antiaircraft gun system |
| CN103353264A (en) * | 2013-07-17 | 2013-10-16 | 晋西工业集团有限责任公司 | Delayed fuse capable of igniting according to set height |
| CN104266555A (en) * | 2014-09-30 | 2015-01-07 | 程鹏 | Artificial precipitation hail prevention rocket positioning system |
| CN104266555B (en) * | 2014-09-30 | 2017-02-15 | 程鹏 | Artificial precipitation hail prevention rocket positioning system |
| CN105444618A (en) * | 2015-12-21 | 2016-03-30 | 新疆维吾尔自治区人工影响天气办公室 | Rocket launching control system |
| CN105444618B (en) * | 2015-12-21 | 2017-04-12 | 新疆维吾尔自治区人工影响天气办公室 | Rocket launching control system |
| CN106688743A (en) * | 2016-12-29 | 2017-05-24 | 雷神科技（天津）有限公司 | Antiaircraft gun launching data online monitoring device and analyzing system |
| CN108122299A (en) * | 2017-12-21 | 2018-06-05 | 北京厚力德仪器设备有限公司 | A kind of meteorological rocket charge book instrument and its charge book method |
| CN109388852A (en) * | 2018-09-07 | 2019-02-26 | 陕西中天火箭技术股份有限公司 | A kind of rocket bomb transmitting number accurate metering method |
| CN109388852B (en) * | 2018-09-07 | 2023-07-28 | 陕西中天火箭技术股份有限公司 | Rocket projectile firing number accurate counting method |
| CN111799710A (en) * | 2020-07-14 | 2020-10-20 | 李振南 | Automatic fixing device for submarine cable laying and using method thereof |
| CN111799710B (en) * | 2020-07-14 | 2021-11-19 | 中软电子(辽宁)有限公司 | Automatic fixing device for submarine cable laying and using method thereof |
| CN114298392A (en) * | 2021-12-23 | 2022-04-08 | 电子科技大学 | Fire wire longitude and latitude prediction algorithm for forest fire |
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Address after: 710075 Shaanxi city of Xi'an province high tech Zone Venture Building on the eighth floor of block C Applicant after: Shaanxi Zhongtian Rocket Technology Inc. Address before: 710025 Shaanxi Province, Xi'an city Baqiao District Tian Hong Zheng Jie te No.1 Applicant before: Shaanxi Zhongjian Rocket Technology Co., Ltd. |
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