CN204228003U - To increase rain artificially hail-suppression rocket navigation system - Google Patents
To increase rain artificially hail-suppression rocket navigation system Download PDFInfo
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- CN204228003U CN204228003U CN201420570019.5U CN201420570019U CN204228003U CN 204228003 U CN204228003 U CN 204228003U CN 201420570019 U CN201420570019 U CN 201420570019U CN 204228003 U CN204228003 U CN 204228003U
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Abstract
The utility model discloses one to increase rain artificially hail-suppression rocket navigation system, it comprises rocket projectile, gps satellite, mobile communication base station, mobile terminal and data server, characterized by further comprising the rocket setting unit be located on described rocket projectile.Described rocket setting unit comprises GPS module, triaxial accelerometer and three-axis gyroscope, adopts gsm communication mode.Rocket setting unit also comprises button cell power supply and third gear stirs dynamic switch.The combination of described rocket setting unit and rocket has: assembled, plug-in type, implanted and external labeling type.This system employing rocket projectile carries electronic positioning unit and together launches use, and real time record flight attitude and rocket are upspring, drop point site, and by data returned data storehouse.Can reflect that rocket projectile and kick down a situation immediately awing, thus heading when effectively controlling to launch, kick down an area, avoid the signs of human habitation to greatest extent, have at heart when making commanding formulate operation scheme when the end, operating personnel's operation and know what's what.
Description
Technical field
The utility model relates to one and to increase rain artificially hail suppression system, hail-suppression rocket navigation system of especially increasing rain artificially.
Background technology
Weather modification is prevented and reduced natural disasters, and air water resource develops, Scientific And Technical means of improving the ecological environment, and obtained the extensive approval of society.From phase late 1990s, a kind of new assignment instrument-Artificial Hail Suppression increases rain rocket-firing system and is born, due to it, to have cloud seeding area large, features such as sowing path length, catalyst nucleation rate is high, operation is motor-driven, be safe, become ground people very soon to increase rain artificially for pre-anti-hail, enforcement, Exploiting And Utilizing Climatic Resources, the powerful reducing natural calamity, ensure agricultural development.The Artificial Hail Suppression operation carried out based on rocket is the important means of weather modification, is also the important measures of the work of preventing and reducing natural disasters.
At present at the rocket projectile that hail-suppression rocket navigation system of increasing rain artificially uses, though there are the safety precautions such as parachute, but point of impact after launching, parachute-opening situation are failed to understand, all the time operating personnel is made to have certain scruples when considering drinking water project, in addition existing detection means can't accomplish real-time monitored operating direction, height wind direction and wind velocity, cause the bad control in rocket projectile drift direction, repeatedly hear that basic unit operating personnel reflection does not know What gives because launch, dare not beat, beat less as far as possible, fearness goes wrong, even when really needing operation in order to safety is also just performed a task perfunctorily; Especially along with socio-economic development, the environment around many settings there occurs great variety, and the place of firing direction rare signs of human habitation has in the early time been that situation bustling with vehicles occurs repeatedly now, and job safety is ensured, and difficulty strengthens further.
Utility model content
The purpose of this utility model is to provide the visible of a kind of rocket flight track, can reflect the impact of upper-level winds on rocket flight intuitively, operation command personnel is adjusted in time, revises the hail-suppression rocket navigation system of increasing rain artificially of operation.
For reaching above-mentioned purpose, the technical solution of the utility model is:
One is increased rain artificially hail-suppression rocket navigation system, and it comprises rocket projectile, gps satellite, mobile communication base station, mobile terminal and data server, characterized by further comprising the rocket setting unit be located on described rocket projectile.
Described rocket setting unit comprises GPS module, triaxial accelerometer and three-axis gyroscope, adopts GSM and GPRS communication mode.
Described rocket setting unit also comprises button cell power supply and third gear stirs dynamic switch.
The combination of described rocket setting unit and rocket has: assembled, plug-in type, implanted and external labeling type.
The third gear of described rocket setting unit is stirred dynamic switching function and is:
〇 shelves: the power supply controlling all components and parts;
I grade: after all components and parts energisings, start GSM, GPRS network registration immediately, start GPS module location, triaxial accelerometer, three-axis gyroscope record data is started after obtaining the time from mobile communication base station or GPS module, locate successfully with mobile communication base station, send a note by rocket setting unit to appointment background server number; Triaxial accelerometer, three-axis gyroscope intra-record slack byte 10 milliseconds.Within every 10 minutes, be saved as a text, be sent to rocket setting unit by GPRS network and specify FTP address;
II grade: postpone within 5 minutes, to start GSM/GPRS network registry, GPS module location, II shelves are identical with the action of I shelves, just II shelves postpone to start for 5 minutes in order that after rocket launching interconnection network again, be adapted at thundery sky work, because thundery sky uses microwave communication instrument to have the risk of drawing thunder, but do not postpone triaxial accelerometer, gyroscope startup; Switch is allocated to II grade, and toggle switch is double-shift type in upright arrangement, 0 grade at Far Left, centre is I shelves, and rightmost is II shelves, and gear is all manually switch when ground.Triaxial accelerometer, three-axis gyroscope normal boot-strap work record data, now locator is not outwards launched, is received any electromagnetic wave signal; After 5 minutes, Auto Power On carries out base station, GPS location after completing GSM, GPRS network registration, the same with gear I after obtaining positional information success, locate per minutely to send one to assigned number and comprise locating information note successfully afterwards.
The hail-suppression rocket navigation system of increasing rain artificially of above structure, adopt rocket projectile to carry electronic positioning unit and together launch use, real time record flight attitude and rocket are upspring, drop point site, and by data returned data storehouse.Advantage is: accurate positioning, and precision is high; Flight attitude, rocket situation record are reliable; Record feedback response speed is fast; Less input, realizes effective; Easy and simple to handle, can reduce background maintenance, a background server can use in the whole nation simultaneously, convenient popularization.Can reflect the adding of rocket setting unit that rocket projectile and situation about kicking down a little immediately awing, thus rocket bomb transmitting direction and the elevation angle can be adjusted in time, heading when indirect control is launched, kick down an area, avoid the signs of human habitation to greatest extent, have at heart when making commanding formulate operation scheme when the end, operating personnel's operation and know what's what.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
Fig. 2 is the structural representation of one of rocket setting unit and rocket projectile combination;
Fig. 3 is the structural representation of rocket setting unit and rocket projectile combination two;
Fig. 4 is the structural representation of rocket setting unit and rocket projectile combination three;
Fig. 5 is the structural representation of rocket setting unit and rocket projectile combination four;
In the drawings, rocket warhead 1, rocket setting unit circuit board 2, indicator lamp 3, gauge tap 4, buckle 5, radome fairing 6, locator chuck 7, rocket projectile body 8, locator bracket 9, paster 10.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is described in further detail.
Shown in Fig. 1, structural representation of the present utility model, as we know from the figure, the utility model comprises gps satellite, rocket setting unit, mobile communication base station, GPRS modem, data server, mobile terminal and desktop terminal.Wherein, rocket setting unit is arranged on rocket projectile, and rocket projectile carries electronic positioning unit and together launches use, and real time record flight attitude and rocket are upspring, drop point site, and related data are passed to the database of data server.Rocket setting unit obtains the GPS locating information such as longitude, latitude, height above sea level from gps satellite, and GPS locating information is sent to neighbouring mobile communication base station, also obtains system time, base station position information etc. from mobile communication base station.After locator obtains the positional information success of mobile communication base station, comprise the note of the locating information of rocket to GPRS modem by mobile communication base station and GSM network transmission.Data server obtains the short message content comprising rocket locating information from GPRS modem, stored in database after resolving.Rocket is located by mobile communication base station by the locator flown with rocket, the related data of attitude utilizes wireless network transmissions to data server, desktop terminal utilizes internet and data server to carry out data communication, obtains the data such as rocket location, attitude information; In like manner, mobile terminal utilizes wireless network and SMS and data server to carry out data communication, obtains the relevant information of rocket location, attitude.
Rocket setting unit is primarily of central processing element, GPS locating module, GSM/GPRS communication module, servo antenna, and triaxial accelerometer chip, three-axis gyroscope chip, storage chip, toggle switch, LED light and the formation such as pcb board material and auxiliary circuit.Central processing element is responsible for processing all programmed instruction, GPS module is responsible for UNICOM's gps satellite acquisition satellite-signal and is obtained geographical longitude and latitude, height above sea level, the functions such as GPS time service, GSM/GPRS communication module has been responsible for communication base station acquisition of information, base station time service, radio communication, the functions such as data transmission and reception, triaxial accelerometer chip is responsible for acceleration of gravity and is measured also value on request, three-axis gyroscope chip is responsible for locator position (orientation) change records and value on request, storage chip is responsible for all measurement data to store according to specified format and supply to call to be sent to background server, toggle switch is responsible for the switching of rocket setting unit function, LED light is responsible for display rocket setting unit current operating state.
After rocket bomb transmitting, rocket setting unit arranges function according to gear and starts working, triaxial accelerometer and three-axis gyroscope record rocket attitudes vibration data, rocket setting unit storage sensor the data obtained, and by data back to background server.Operating personnel is by calling return data and showing in client; data can be finally inversed by the skyborne ballistic curve of rocket projectile; by contrasting actual air ballistic curve and theoretical trajectory curve situation; high-altitude, operating area differing heights layer wind direction, wind speed can be calculated; the satellite cloud picture superposed by client and Radar Products can adjust rocket launching azimuth and the elevation angle accordingly in time; to avoid dense population areas; guarantee rocket remains safe landing point; enable the catalyst sowed better arrive cloud middle ideal catalytic site, reach better operation effectiveness.
Shown in Fig. 2, being one of rocket setting unit and rocket projectile combination, is assembled: rocket projectile separates with rocket setting unit to be deposited, and refills and join use during transmitting.From in the drawings, rocket setting unit comprises rocket setting unit circuit board 2, indicator lamp 3 and gauge tap 4, the profile of rocket setting unit makes the shape with rocket radome fairing 6 front end rocket warhead 1 tip taper partial response, and insert in rocket warhead 1, rocket warhead 1 is combined with rocket by the mode of screw socket buckle 5.After rocket setting unit being installed to rocket warhead 1 during use, open the gauge tap 4 of rocket setting unit, indicator lamp 3 is bright, illustrates that location is in running order.
Shown in Fig. 3, rocket setting unit and rocket projectile combination two, i.e. plug-in type: rocket setting unit profile makes card-like, is fixedly installed on one piece of locator chuck 7 by rocket setting unit circuit board 2, then assigned in the slot that rocket warhead 1 inside is provided with by locator chuck 7.
Shown in Fig. 4, be rocket setting unit and rocket projectile combination three, i.e. implanted: in rocket projectile body 8, be provided with the bracket 9 for installing rocket setting unit; Just rocket setting unit is installed on bracket 9 when rocket general assembly, when rocket projectile dispatches from the factory, locator has just been combined with rocket projectile and has installed.Arrow of starting to exchange fire during use leads to locator power supply.The optional many places, position of implanting, as rocket projectile head safety landing system is inner, the main parachute place of body etc.
Shown in Fig. 5, rocket setting unit and rocket projectile combination four, i.e. external labeling type: rocket setting unit profile makes the structure of paster 10, the appearance of rocket projectile body 8 is fixed on by modes such as viscose glue, buckle, bolt or draw-in grooves, the locator comprising rocket setting unit circuit board 2, indicator lamp 3 and gauge tap 4 is fixed on paster 10, launches with rocket projectile.
The gauge tap 4 of described rocket setting unit stirs dynamic switch for third gear, and its function is:
〇 shelves: the power supply controlling all components and parts of locator;
I grade: after all components and parts energisings of rocket setting unit, start GSM, GPRS network registration immediately, start GPS module location, triaxial accelerometer, three-axis gyroscope record data is started after obtaining the time from mobile communication base station or GPS module, locate successfully with mobile communication base station, send a note by rocket setting unit to appointment background server number;
II grade: rocket setting unit postpones within 5 minutes, to start GSM/GPRS network registry, GPS module location, but does not postpone triaxial accelerometer, gyroscope startup; When switch is allocated to II grade, triaxial accelerometer, three-axis gyroscope normal boot-strap work record data, now locator is not outwards launched, is received any electromagnetic wave signal; After 5 minutes, Auto Power On carries out mobile communication base station, gps satellite location after completing GSM, GPRS network registration, the same with gear I after obtaining positional information success, after the location success of mobile communication base station and gps satellite, rocket setting unit per minute comprises locating information note to specifying background server number to send one.
The form of described locating information note is: gear information, M1: latitude, longitude G1: latitude, longitude, highly, movement direction angle, speed (in the sea/hour be converted into meter per second), triaxial accelerometer (instantaneous value) X-axis, Y-axis, Z axis, three-axis gyroscope angle X-axis, Y-axis, Z axis, three-axis gyroscope temperature.It is per minute again to specifying background server number to send a note that rocket setting unit successfully located by rocket setting unit, and content, form are the same.Triaxial accelerometer, three-axis gyroscope intra-record slack byte 10 milliseconds, within every 10 minutes, be saved as a text and be sent to appointment FTP address by GPRS network, file is called: gear code+this locator sim card hand plane No. or sim card imei code+_+this segment record time started+_+this segment record end time+file suffixes name, concrete is as shown in the table:
The parameter request of each device of locator:
1. power supply: locator adopts gel lithium ion battery.Service time > 3 hours;
2. triaxial accelerometer measurement category is not less than 100G;
3. three-axis gyroscope acceleration tolerance is not less than 100G, and temperature drift, drift, error are little.Adding gyrostatic main purpose is because locator is in use in high-speed motion all the time and has tumbling action, simple use accelerometer cannot determine attitude completely, need the change of pitch angle knowing locator, thus calculate the component of acceleration of gravity on each axle of accelerometer, remove gravity effect, determine locator attitude, accurately redraw out movement locus by data.Initial data gap compared with actual that three-axis gyroscope gathers out because of himself reason such as principle and production technology is comparatively large, whether can add the poor program that disappears (such as using the methods such as Kalman filtering) in a program, improve the accuracy exporting data;
In 4.GPS module precision 10 meters, hot and cold startup is rapid, positioning stablity, and drift is few;
5. the data file time mainly calculates according to the end time, and therefore the end of file time (after filename a time) will try one's best accurately;
6. this locator requires on the basis of reliable operation, and components and parts are as far as possible few, and accelerometer and gyroscope can divide two elements also can use six axle gyroscopes.
System data acquisition: because data contain geography information and time, so the transmission of all data adopts encipher transmit mode.Data Collection is divided into two kinds of modes to carry out.
GPRS terminal:
Collect the data SMS that locator is beamed back, and peek warehouse-in, data form field comprises: sim card hand plane No. or sim card imei code, note time, M1 latitude, M1 longitude, G1 latitude, G1 longitude, G1 height, G1 movement direction angle (degree), G1 speed (meter per second), each note is saved as a line item.Such as S1:M1La:22.5532424_M1Lo:114.055345_G1La:22.5632424_G1Lo: 113.985345_H:324.9_An:270.65_S:13.4_Ax:-0.309_Ay:8.279_A z:5.145_Gx:0.0153_Gy:-0.5721_Gz:0.0102_Ga:21.2168_Gb:31. 2314_Gc:21.4432_T:36.21.
Network service:
Adopt 8M to fix IP fiber broadband network, transfer rate, transmission bandwidth, stability are secure.
FTP database:
The sensing data compressed package that locator 2G wireless network is passed back is compiled, stored, calculates for software transfer, initial data distribution etc.Store path design is tree structures node with time, namely year/moon.
System data display application:
Because data relate to geography information and time, therefore anonymous download service is not provided, need the user of data query must exist in demographic data storehouse, demographic data storehouse is provided by applying unit, comprises the personal information such as personnel's name, cell-phone number, operation qualification job qualification certificate number.
Client application:
Client application is divided into desktop client end and mobile client, and desktop end temporarily only develops MS version of window, Android and iOS operating system version is temporarily only developed in mobile terminal.The application of desktop version comprises Rocket location, the display of rocket projectile flight curve (penetrating height) two dimension, rocket bomb transmitting to landing overall process three-dimensional demonstration, the omnidistance content such as playback, data download of weather system processing operations.Extender comprises the contents such as catalyst distribution, recruitment evaluation.Mobile edition application comprises rocket projectile bullet record, Rocket location, the display of rocket projectile flight curve (penetrating height) two dimension, rocket bomb transmitting to landing outside the content such as overall process three-dimensional demonstration, data download, uses also develop flashlight, electronic compass, level meter, plummet, protractor, seek and play radar, attitude playback, function such as customization note, telephone communication, transmitting record, one-dimension code, Quick Response Code scanning, radio frequency chip reading etc. for convenience of operating personnel.
System data is distributed:
All types application terminal all provides data download service, provide data be all without processing, calibration initial data, facilitate researcher to recalculate and use with scientific research.Data comprise locator GSM message part and sensing data.There is provided diversified download service, downloading mode can single download also can be downloaded in batches and also can download according to the time period by number; Also can according to appointed area download service.
System realizes effect:
The utility model implement after the shadow rocket projectile realization is launched, fly, land overall process record.This navigation system adopts GPS, base station Dual positioning, drop point precise control; Locating information high arrival rate is guaranteed in double-channel data transmission; The dual logging of triaxial accelerometer and electronic gyroscope guarantees record rocket projectile flight curve precision; Broadband background server is guaranteed data acquisition, stores, is called and be protected.Drop point can be located and drinking water project is ensured safely conscientiously, solves the problem of operating personnel " dare not operation " " not sure ".Shadow rocketry is made to be in international similar equipment top standard.
Claims (8)
1. increase rain artificially a hail-suppression rocket navigation system, it comprises rocket projectile, gps satellite, mobile communication base station, mobile terminal and data server, characterized by further comprising the rocket setting unit be located on described rocket projectile.
2. hail-suppression rocket navigation system of increasing rain artificially according to claim 1, is characterized in that:
Described rocket setting unit comprises GPS module, triaxial accelerometer and three-axis gyroscope, adopts GSM and GPRS communication mode.
3. hail-suppression rocket navigation system of increasing rain artificially according to claim 1, is characterized in that:
Described rocket setting unit also comprise gel lithium ion battery power supply and III grade stir dynamic switch.
4. hail-suppression rocket navigation system of increasing rain artificially according to claim 1, is characterized in that:
The combination of described rocket setting unit and rocket has: assembled, plug-in type, implanted and external labeling type.
5. the hail-suppression rocket navigation system of increasing rain artificially according to claim 1 or 3, is characterized in that:
Stirring dynamic switching function for III grade of described rocket setting unit is:
〇 shelves: the power supply controlling all components and parts;
I grade: after all components and parts energisings, start GSM, GPRS network registration immediately, start GPS module location, triaxial accelerometer, three-axis gyroscope record data is started after obtaining the time from mobile communication base station or GPS module, locate successfully with mobile communication base station, send a note by rocket setting unit to appointment background server number; Triaxial accelerometer, three-axis gyroscope intra-record slack byte 10 milliseconds; Within every 10 minutes, be saved as a text, be sent to rocket setting unit by GPRS network and specify FTP address;
II grade: postpone within 5 minutes, to start GSM/GPRS network registry, GPS module location, II shelves are identical with the action of I shelves, just II shelves postpone to start for 5 minutes in order that after rocket launching interconnection network again, but do not postpone triaxial accelerometer, gyroscope starts; III grade of toggle switch is double-shift type in upright arrangement, 0 grade at Far Left, centre is I shelves, and rightmost is II shelves, all manually switches; Triaxial accelerometer, three-axis gyroscope normal boot-strap work record data, now locator is not outwards launched, is received any electromagnetic wave signal; After 5 minutes, Auto Power On carries out base station, GPS location after completing GSM, GPRS network registration, the same with gear I after obtaining positional information success, locate successfully and per minutely send to assigned number the note that comprises locating information, and be saved as a text by every for data file 10 minutes and be compressed into zip compressing file bag, be sent to rocket setting unit by GPRS network and specify FTP address, file format is identical with gear I.
6. hail-suppression rocket navigation system of increasing rain artificially according to claim 5, is characterized in that:
The form of described locating information note is: gear information, M1: latitude, longitude G1: latitude, longitude, highly, movement direction angle, speed (in the sea/hour be converted into meter per second), triaxial accelerometer (instantaneous value) X-axis, Y-axis, Z axis, three-axis gyroscope angle X-axis, Y-axis, Z axis, three-axis gyroscope temperature.
7. hail-suppression rocket navigation system of increasing rain artificially according to claim 6, is characterized in that:
Described locating information Data Filename naming rule is: gear code+this locator sim card hand plane No. or this sim card imei code+_+this segment record time started+_+this segment record end time+file suffixes name.
8. hail-suppression rocket navigation system of increasing rain artificially according to claim 7, is characterized in that:
Described locating information data text form is: adopt line item pattern, each data occupies a line, and every data line type is triaxial accelerometer X-axis from left to right successively, Y-axis, Z axis accekeration (unit: meter per second
2), three-axis gyroscope X-axis, Y-axis, Z axis magnitude of angular velocity, three-axis gyroscope X-axis, Y-axis, Z axis angle, temperature (degree Celsius), the time interval (unit: millisecond); Empty lattice between data and data.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420570019.5U CN204228003U (en) | 2014-09-30 | 2014-09-30 | To increase rain artificially hail-suppression rocket navigation system |
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| CN201420570019.5U CN204228003U (en) | 2014-09-30 | 2014-09-30 | To increase rain artificially hail-suppression rocket navigation system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104266555A (en) * | 2014-09-30 | 2015-01-07 | 程鹏 | Artificial precipitation hail prevention rocket positioning system |
| CN110006296A (en) * | 2019-03-29 | 2019-07-12 | 河北省人工影响天气办公室 | Hail-suppression rocket bullet of increasing rain artificially sows job trace monitoring and trajectory deviation-rectifying system |
-
2014
- 2014-09-30 CN CN201420570019.5U patent/CN204228003U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN110006296A (en) * | 2019-03-29 | 2019-07-12 | 河北省人工影响天气办公室 | Hail-suppression rocket bullet of increasing rain artificially sows job trace monitoring and trajectory deviation-rectifying system |
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Effective date of registration: 20161014 Address after: Dragon Spirit B unit B-1-1205 No. 33 Park Avenue XiXiangTang District, Nanning City 530000 the Guangxi Zhuang Autonomous Region Patentee after: Guangxi Jin Lin Technology Co., Ltd. Address before: 530022 Guangxi Meteorological Observatory, No. 81 national Avenue, Nanning, the Guangxi Zhuang Autonomous Region Patentee before: Cheng Peng |