CN109780929A - A universal launch platform for missiles - Google Patents
A universal launch platform for missiles Download PDFInfo
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- CN109780929A CN109780929A CN201910137358.1A CN201910137358A CN109780929A CN 109780929 A CN109780929 A CN 109780929A CN 201910137358 A CN201910137358 A CN 201910137358A CN 109780929 A CN109780929 A CN 109780929A
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- 238000004891 communication Methods 0.000 claims abstract description 33
- 238000012544 monitoring process Methods 0.000 claims abstract description 26
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- 238000000034 method Methods 0.000 claims abstract description 8
- 230000005855 radiation Effects 0.000 claims description 4
- 238000009434 installation Methods 0.000 claims description 2
- 238000012545 processing Methods 0.000 claims description 2
- 238000012549 training Methods 0.000 claims description 2
- 239000000446 fuel Substances 0.000 claims 2
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- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
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Abstract
本发明公开了一种导弹通用发射平台，包括综合控制终端、指挥终端、驾驶终端。综合控制终端包括导弹发射模式、导弹发射方式、定位状态信息、平台状态信息、导弹状态信息、供电系统信息。指挥终端包括发射流程监控、平台状态、导弹状态、定位定向信息、电源状态。驾驶终端包括底盘监测、环境参数、方位信息、平台温控、胎压监测。采用Can总线和UDP通信协议和交换机实现各个终端之间的信息传输。此系统能够实时监控导弹、发射装置以及其他装置的信息，以及实现对发射装置的控制和操作。
The invention discloses a universal launching platform for missiles, which includes a comprehensive control terminal, a command terminal and a driving terminal. The integrated control terminal includes missile launch mode, missile launch mode, positioning status information, platform status information, missile status information, and power supply system information. The command terminal includes monitoring of the launch process, platform status, missile status, positioning and orientation information, and power status. The driving terminal includes chassis monitoring, environmental parameters, orientation information, platform temperature control, and tire pressure monitoring. The Can bus and UDP communication protocols and switches are used to realize the information transmission between each terminal. This system can monitor the information of missiles, launch devices and other devices in real time, and realize the control and operation of launch devices.
Description
Technical field
The present invention relates to a kind of general flat pads of guided missile, belong to automatic control, field of communication technology.
Background technique
As the great-leap-forward development of the weaponrys such as space flight, aviation, weapons needs, newer versions of these missiles emerges one after another.Compel to be essential
A kind of general missile launching platform is wanted, real-time monitoring and control are carried out to the state of guided missile.Utilize UDP communication protocol and exchange
Machine realizes that the information between each terminal is transmitted.This system can monitor the letter of guided missile, emitter and other devices in real time
Breath, and realize and emitter is controled and operated.
Summary of the invention
The purpose of the present invention is to provide one kind, to can be realized intellectual monitoring, adjusting in real time, intelligence computation analysis, function complete
Face, the general flat pad of guided missile practical, that construction cost is low.
To reach above-mentioned purpose, the technical solution adopted in the present invention is as follows: a kind of general flat pad of guided missile, including comprehensive
It closes controlling terminal, command terminal, drive terminal, computer and interchanger；The comprehensively control terminal is one and is used to be counted
According to the controlling terminal of processing, data transmission, it is installed in the computer of linux system, this terminal includes MISSILE LAUNCHING mode, leads
Play radiation pattern, positioning states information module, platform status information module, guided missile status information module, power supply system information mould
Block and the communication protocol and communication format transmitted for data；Each module is installed on comprehensively control terminal, utilizes UDP communication protocols
View carries out data communication, is stored in computer with visualization interface；
The command terminal includes that command terminal includes transmitting process monitoring module, platform status display module, guided missile shape
State display module, positioning and directing information module, power supply status module and communication protocol and communication format for data transmission,
Command terminal is to be installed on the insertion of the linux system based on ARM for receiving and conveying the terminal from comprehensively control terminal
In formula computer, carried out data transmission with UDP communication protocol, it includes other terminals also all counted with UDP communication protocol
According to transmission, various information both is from comprehensively control terminal；
The driving terminal include chassis monitoring modular, environmental parameter module, azimuth information module, platform temperature control module,
Tire pressure monitoring module and the communication protocol and communication format transmitted for data；Terminal is driven to be used to monitor all kinds of of car launcher
State, for receiving and convey the terminal from comprehensively control terminal, be installed on the linux system by ARM it is embedded based on
In calculation machine, carried out data transmission with UDP communication protocol, it includes other terminals also all with UDP communication protocol carry out data biography
Defeated, various information both is from comprehensively control terminal.
Further, the MISSILE LAUNCHING mode selection module is divided into manual emission mode, automatic hair according to mission need
Emission mode and steps mode, operator's installation requirements select MISSILE LAUNCHING mode, and selection mode is utilized udp protocol
Send information to guided missile；
Missile launching includes combat mode, training mode；
Positioning states information module includes autonomous positioning directed information, navigation satellite information, launch point information；
Platform status information module includes emitter information, environmental parameter, chassis state；
Guided missile status information include track transmission result, guided missile original state, guided missile power supply state, missile gear self-test,
Missile takeoff state etc., these information are sent to comprehensively control terminal by information collecting device；
Power supply system information includes power-supply system information, load equipment information.
Further, the transmitting process monitoring module includes emission mode, radiation pattern, launch point longitude and latitude and hair
Exit point height above sea level, comprehensively control terminal will send information to command terminal using UDP communication protocol；
Platform status display module includes state of transmitting apparatus, environmental parameter, chassis state；
Guided missile state display module includes that track transmits result, guided missile original state, guided missile power supply state, missile gear certainly
Inspection, inertial navigation alignment, battery activated, boost motor state, missile takeoff state, current channel, inertial navigation are directed at time, inertial navigation mistake
Word；
Positioning and directing information module includes autonomous positioning orientation, navigation satellite location information；
Power supply status module includes power-supply system information, load equipment information.
Further, chassis monitoring modular is used to detect the information of transmitting chassis, including motor speed information, motor temperature
Spend information；
Environmental parameter module includes the temperature, humidity, pressure of launching tube, temperature, humidity, the pressure of driver's cabin, equipment compartment
Temperature, humidity, pressure；
Azimuth information module include at least longitude, latitude, height, north orientation speed, east orientation speed, independent assortment longitude, from
By the information of combination latitude, combinations of satellites longitude, combinations of satellites latitude；
Platform temperature control module includes site safety monitoring, nuclear radiation monitoring, toxic agent monitoring, hair control cabin smog；
Tire pressure monitoring module includes the left pressure of each bridge and the right pressure of each bridge.
Further, data information of the autonomous positioning information module to collect guided missile, including at least the work shape of guided missile
The data information of course angle, pitch angle, the roll angle of state, the height of satellite and longitude and latitude and guided missile, collection is communicated using UDP
Agreement is sent to comprehensively control terminal；
Information of the navigation satellite information module to collect missile truck, including at least navigation satellite working method,
The data information of positioning method, the north orientation speed of car launcher, east orientation speed, collection is sent to comprehensive control using UDP communication protocol
End processed；
Launch point information includes the longitude and latitude and height above sea level and launch point distance of launch point.
Further, state of transmitting apparatus included perpendicular, Hui Ping, leveling state, Angle of Heel, Angle of Trim, fixator state,
Firing box state, air deflector state；
Environmental parameter includes launching tube temperature, humidity, pressure, cabin temperature, humidity, pressure, equipment compartment temperature, wet
Degree, pressure, send comprehensively control terminal from each equipment for data using data acquisition device.
Further, chassis state includes speed, mileage, oil mass, drives terminal for collected speed, mileage, oil mass
Data are sent to comprehensively control terminal；
Power-supply system information includes chassis DC bus-bar voltage, battery remaining capacity, control main road voltage, control branch
Voltage, control main road electric current, control branch current, driving voltage, driving current；
Load equipment information, which includes at least, drives terminal, command terminal, universal control unit.
Beneficial effect
The invention discloses a kind of general flat pad of guided missile, including comprehensively control terminal, command terminal, drive terminal,
Computer and interchanger.Comprehensively control terminal includes MISSILE LAUNCHING mode, Missile launching, positioning states information, platform-like
State information, guided missile status information, power supply system information.Command terminal include transmitting flow monitoring, platform status, guided missile state,
Positioning and directing information, power supply status.Driving terminal includes chassis monitoring, environmental parameter, azimuth information, platform temperature control, tire pressure prison
It surveys.Realize that the information between each terminal is transmitted using Can bus and UDP communication protocol and interchanger.This system can be real-time
The information of guided missile, emitter and other devices is monitored, and realizes and emitter is controled and operated.
Detailed description of the invention
Fig. 1 is a kind of system block diagram of the general flat pad of guided missile of the present invention.
Fig. 2 is a kind of comprehensively control software block diagram of the general flat pad of guided missile of the present invention.
Fig. 3 is a kind of command terminal block diagram of the general flat pad of guided missile of the present invention.
Fig. 4 is a kind of driving terminal block diagram of the general flat pad of guided missile of the present invention.
Specific embodiment
In order to better understand the technical content of the present invention, special to lift specific embodiment and institute's accompanying drawings is cooperated to be described as follows.
As shown in Figure 1, preferred embodiment according to the present invention, a kind of general flat pad of guided missile, including comprehensively control are whole
End 101.Wherein, comprehensively control terminal 101 includes computer, MISSILE LAUNCHING mode 202, Missile launching 203, positioning states
Information 204, platform status information 205, guided missile status information 206, power supply system information 207, comprehensively control software pass through exchange
Machine sends various information by protocol format to command terminal 103, driving terminal 104.Other relevant information pass through Can bus
It is sent in first piece of CPU, and comprehensively control terminal is sent to by first piece of CPU.
Comprehensively control terminal 201 is by sending all kinds of agreements and order to interchanger, to collect the information and reality of power supply
Now to the control of power supply and adjusting.
The general flat pad of a kind of guided missile that the present embodiment proposes, the purpose of the present invention is to provide one kind can be realized intelligence
It can monitoring, in real time adjusting, intelligence computation analysis, the general flat pad of guided missile full-featured, practical, that construction cost is low.
Although the present invention has been disclosed as a preferred embodiment, however, it is not to limit the invention.Skill belonging to the present invention
Has usually intellectual in art field, without departing from the spirit and scope of the present invention, when can be used for a variety of modifications and variations.Cause
This, the scope of protection of the present invention is defined by those of the claims.
Claims (7)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910137358.1A CN109780929B (en) | 2019-02-25 | 2019-02-25 | Universal missile launching platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910137358.1A CN109780929B (en) | 2019-02-25 | 2019-02-25 | Universal missile launching platform |
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| Publication Number | Publication Date |
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| CN109780929A true CN109780929A (en) | 2019-05-21 |
| CN109780929B CN109780929B (en) | 2022-03-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910137358.1A Active CN109780929B (en) | 2019-02-25 | 2019-02-25 | Universal missile launching platform |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112268489A (en) * | 2020-09-30 | 2021-01-26 | 南京邮电大学 | A Missile Command and Control System Based on Localized Platform |
| CN114485264A (en) * | 2022-04-19 | 2022-05-13 | 四川赛狄信息技术股份公司 | Ignition control method and system for barrel-mounted missile launching |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101968653A (en) * | 2010-08-19 | 2011-02-09 | 西安理工大学 | Console device detector and console device detection method |
| CN202294988U (en) * | 2011-10-10 | 2012-07-04 | 湖北航天技术研究院总体设计所 | Missile launching vehicle mounted cabin |
| CN104296605A (en) * | 2014-09-30 | 2015-01-21 | 北京航空航天大学 | FPGA (Field Programmable Gate Array) based ground launching control device of small and medium-sized rocket |
| CN107037750A (en) * | 2016-12-13 | 2017-08-11 | 上海机电工程研究所 | Missile launching control method and system based on TMS320F28335 |
| CN108490297A (en) * | 2018-05-25 | 2018-09-04 | 芜湖天航装备技术有限公司 | Automatically embedded device and its control method are detected in a kind of aviation emitter outfield |
-
2019
- 2019-02-25 CN CN201910137358.1A patent/CN109780929B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101968653A (en) * | 2010-08-19 | 2011-02-09 | 西安理工大学 | Console device detector and console device detection method |
| CN202294988U (en) * | 2011-10-10 | 2012-07-04 | 湖北航天技术研究院总体设计所 | Missile launching vehicle mounted cabin |
| CN104296605A (en) * | 2014-09-30 | 2015-01-21 | 北京航空航天大学 | FPGA (Field Programmable Gate Array) based ground launching control device of small and medium-sized rocket |
| CN107037750A (en) * | 2016-12-13 | 2017-08-11 | 上海机电工程研究所 | Missile launching control method and system based on TMS320F28335 |
| CN108490297A (en) * | 2018-05-25 | 2018-09-04 | 芜湖天航装备技术有限公司 | Automatically embedded device and its control method are detected in a kind of aviation emitter outfield |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112268489A (en) * | 2020-09-30 | 2021-01-26 | 南京邮电大学 | A Missile Command and Control System Based on Localized Platform |
| CN114485264A (en) * | 2022-04-19 | 2022-05-13 | 四川赛狄信息技术股份公司 | Ignition control method and system for barrel-mounted missile launching |
| CN114485264B (en) * | 2022-04-19 | 2022-06-24 | 四川赛狄信息技术股份公司 | Ignition control method and system for barrel-packed missile launching |
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| CN109780929B (en) | 2022-03-15 |
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