CN110727218A - Launching control equipment and method suitable for launching double-launched missiles - Google Patents
Launching control equipment and method suitable for launching double-launched missiles Download PDFInfo
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- CN110727218A CN110727218A CN201910917270.1A CN201910917270A CN110727218A CN 110727218 A CN110727218 A CN 110727218A CN 201910917270 A CN201910917270 A CN 201910917270A CN 110727218 A CN110727218 A CN 110727218A
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0423—Input/output
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F1/00—Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannons; Harpoon guns
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/24—Pc safety
- G05B2219/24215—Scada supervisory control and data acquisition
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- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides launching control equipment and a launching control method suitable for launching a double-launched missile, wherein the launching control equipment comprises the following steps: the system comprises a first transceiver module, a second transceiver module, a DSP processor module, a gating module and an upper computer module; the first transceiver module is connected with the DSP processor module; the upper computer module and the DSP module are connected in series through a second transceiver module; the gating module is respectively connected with the DSP module and the upper computer module in series, and outputs the information of any information channel or any plurality of information channels to the upper computer module according to the gating instruction and the real-time information output by the upper computer module. The invention has reasonable design and convenient use, has the information channel gating function, particularly the video gating function in the missile launching process, and is favorable for controlling the missile launching in the missile weapon system with the optical imaging guide device.
Description
Technical Field
The invention relates to the field of automatic control, in particular to launching control equipment and a launching control method suitable for launching a double-launched missile, and particularly relates to the launching control equipment for the double-launched missile with a video gating function.
Background
The missile launching control equipment is an important component of a missile weapon system, receives an instruction of an upper computer and executes various operations related to missile launching. Missile launch control equipment generally comprises communication circuitry, missile power-up circuitry, and missile launch circuitry. Typically, the missile has only an electrical interface with the launch control device. In a missile weapon system with an optical imaging guide device, a missile needs to upload a video signal to an upper computer through a control device, and the multi-missile control device needs to have a video channel selection function.
Patent document 107037750a discloses a missile launching control method based on TMS320F28335, which includes: step 1: establishing a missile launching control system based on a TMS320F28335 chip; step 2: acquiring binding parameters and control commands of management equipment in the missile launching control system through a CAN (controller area network) bus, and feeding parameter binding results and execution results of execution equipment back to the management equipment; and step 3: and configuring an input/output port of the execution equipment control module according to the parameter binding result, and setting a power supply mode and a launching flow matched with the type of the missile to be launched. The patent does not have an information channel gating function, particularly a video gating function; are not conducive to controlling missile launch in a missile weapons system with optical imaging guidance.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide launching control equipment and a launching control method suitable for launching a double-launched missile.
The invention provides launching control equipment suitable for launching a double-launched missile, which comprises: the system comprises a first transceiver module, a second transceiver module, a DSP processor module, a gating module and an upper computer module; the first transceiver module is connected with the DSP processor module;
the upper computer module and the DSP module are connected in series through a second transceiver module; the gating module is respectively connected with the DSP module and the upper computer module in series, and outputs the information of any information channel or any plurality of information channels to the upper computer module according to the gating instruction and the real-time information output by the upper computer module.
Preferably, the video gating module includes: gating the controller; the gating controller is externally connected with a direct current power supply, and the gating controller is grounded.
Preferably, the first transceiver module comprises: a bus transceiver module, the bus transceiver module comprising: a CAN bus circuit and a bus transceiver; the number of the CAN bus circuits is two; the number of the bus transceivers is two; the DSP processor module comprises: a bus controller; the bus transceiver is externally connected with a direct current power supply, and the bus transceiver is grounded.
Preferably, the second transceiver module comprises: a second circuit, a second transceiver; the second transceiver is connected with the DSP processor through a second circuit; the upper computer module comprises fire control equipment; the second circuit includes: RS422 circuit.
Preferably, the method further comprises the following steps: a power supply control module; the power supply control module is connected with the DSP processor module in parallel; the power control module includes: the missile control system comprises a missile energizing circuit, a thermal battery activating circuit, an engine ignition circuit and a relay; the missile electrifying circuit, the thermal battery activating circuit and the engine ignition circuit are respectively connected with the relay in parallel.
Preferably, the gating module is a video gating module; the video gating module is respectively connected with the DSP module and the upper computer module in series, and the video gating module outputs video information of any information channel or any plurality of information channels to the upper computer module according to a video gating instruction and real-time information.
According to the launching control method suitable for launching the double-launched missile provided by the invention, launching control equipment suitable for launching the double-launched missile is adopted, and the following steps are executed:
and a transmitting communication step: the launching control equipment suitable for launching the double-launched missiles is in communication connection with the upper computer module through the second transceiver; the missile launching module is in communication connection with the bus transceiver;
executing a transmitting step: the launching control equipment suitable for launching the double-launched missiles powers up the missile launching module and is in communication connection with the missile launching module and the upper computer module at the same time, and the missile launching module executes missile launching;
a gating step: the launching control equipment suitable for launching the double-launched missiles selects and outputs the information of any one information channel or any plurality of information channels according to the real-time information and the gating instruction output by the upper computer module.
Preferably, the second transceiver comprises: RS422 serial port; the bus transceiver includes: CAN bus transceiver.
Preferably, the launching step is performed while powering up the two missiles, and the two missiles are launched in sequence.
Preferably, the real-time information is a PAL video signal.
Compared with the prior art, the invention has the following beneficial effects:
1. the dual-missile launching control device is reasonable in design and convenient to use, and can work independently or cooperatively;
2. the missile launching process has an information channel gating function, particularly a video gating function;
3. control of missile launch in a missile weapons system with optical imaging guidance is facilitated.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic diagram of the principles of the present invention;
FIG. 2 is a schematic diagram of a RS422 communication circuit according to an embodiment of the invention;
FIG. 3 is a schematic diagram of a CAN bus circuit according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of the missile power-up and launch circuitry in an embodiment of the invention;
fig. 5 is a schematic diagram of a video gating circuit in an embodiment of the invention.
In the figure:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, 2, 3, 4 and 5, the launching control device for launching the dual-missile according to the invention comprises: the system comprises a first transceiver module, a second transceiver module, a DSP processor module, a gating module and an upper computer module; the first transceiver module is connected with the DSP processor module; specifically, in one embodiment, the DSP processor module 5 employs a TMS320F28335PGFA chip as the core controller of the entire device.
The upper computer module and the DSP module are connected in series through a second transceiver module; the gating module is respectively connected with the DSP module and the upper computer module in series, and outputs the information of any information channel or any plurality of information channels to the upper computer module according to the gating instruction and the real-time information output by the upper computer module. Preferably, the video gating module includes: gating the controller; the gating controller is externally connected with a direct current power supply, and the gating controller is grounded. Preferably, the first transceiver module comprises: a bus transceiver module, the bus transceiver module comprising: a CAN bus circuit and a bus transceiver; the number of the CAN bus circuits is two; the number of the bus transceivers is two; the DSP processor module comprises: a bus controller; the bus transceiver is externally connected with a direct current power supply, and the bus transceiver is grounded. Specifically, in one embodiment, the CAN bus circuits 21, 22 utilize two CAN bus controllers on board the DSP processor, and the circuits are shown in fig. 2, with the TJA1050T being used externally as the bus transceiver. The pin 3 of TJA1050T is connected with a +5V direct current power supply, and the pin 2 is connected with a power ground; pins 1 and 4 are respectively connected with CANTXA and CANRXA of the DSP processor; pins 7 and 6 are respectively connected with CAN _ H and CAN _ L of the missile CAN bus transceiver through 5-ohm resistors, and 120-ohm matching resistors are bridged between the CAN _ H and the CAN _ L; meanwhile, CAN _ H and CAN _ L are respectively connected with a power ground through a filter resistor of 30 pF; the pin 8 is connected with the power ground.
The second transceiver module comprises: a second circuit, a second transceiver; the second transceiver is connected with the DSP processor through a second circuit; the upper computer module comprises fire control equipment; the second circuit includes: RS422 circuit. Specifically, in one embodiment, the RS422 circuit 3 uses a MAX1490EBEPG chip as a transceiver to implement the communication between the DSP processor and the RS422 of the upper computer, and the circuit thereof is as shown in fig. 3. The MAX1490EBEPG chip is isolated from the DSP serial port communication interfaces SCITXDB and SCIRXDB through a U-SN74HC86D exclusive-OR gate chip.
Preferably, the method further comprises the following steps: a power supply control module; the power supply control module is connected with the DSP processor module in parallel; the power control module includes: the missile control system comprises a missile energizing circuit, a thermal battery activating circuit, an engine ignition circuit and a relay; the missile electrifying circuit, the thermal battery activating circuit and the engine ignition circuit are respectively connected with the relay in parallel. Specifically, in one embodiment, the missile energizing circuit, the thermal battery activation circuit and the engine ignition circuit adopt the same principle form, namely a DSP processor GPIO port controls corresponding relay action, and the circuit thereof is shown in figure 4. When the device receives a corresponding output instruction of an upper computer, the level Input of a GPIO pin of the DSP processor is set low, the level is increased and driven by SN74LVC07AD to conduct a PS2801-4 photoelectric coupler, a Darlington triode ULN2803ADWR is controlled to be conducted, then a relay is controlled to be attracted, and finally a missile power supply, a thermal battery activation power supply and an engine ignition power supply are switched on.
Preferably, the gating module is a video gating module; the video gating module is respectively connected with the DSP module and the upper computer module in series, and the video gating module outputs video information of any information channel or any plurality of information channels according to a video gating instruction and real-time information. Specifically, in one embodiment, the video strobe circuit 4 employs a MAX4311 as the strobe controller, the circuit of which is shown in FIG. 5. When the device receives a video gating instruction of an upper computer, the GPIO corresponding to the DSP processor outputs an address input AV _ addr serving as MAX 4311. AV1+ and AV2+ correspond to the two paths of input video signals respectively, and AV _ out is a video signal for controlling output. When the AV _ addr is in a high level, selecting the video channel AV1 to output; when AV _ addr is low, the video channel AV2 is selected for output.
The launching control device suitable for launching the double-launched missile provided by the invention can be understood as one embodiment of the launching control method suitable for launching the double-launched missile provided by the invention by a person skilled in the art. Namely, the launching control method suitable for launching the double-launched missile can be realized by adopting the corresponding step flow of the launching control equipment suitable for launching the double-launched missile.
A launching control method suitable for launching of a double-launched missile, which is characterized in that the launching control device suitable for launching of a double-launched missile of any one of claims 1 to 6 is adopted, and the following steps are executed:
and a transmitting communication step: the launching control equipment suitable for launching the double-launched missiles is in communication connection with the upper computer module through the second transceiver; the missile launching module is in communication connection with the bus transceiver;
executing a transmitting step: the launching control equipment suitable for launching the double-launched missiles powers up the missile launching module and is in communication connection with the missile launching module and the upper computer module at the same time, and the missile launching module executes missile launching;
a gating step: the launching control equipment suitable for launching the double-launched missiles selects and outputs the information of any one information channel or any plurality of information channels to the upper computer module according to the real-time information and the gating instruction output by the upper computer module.
The second transceiver comprises: RS422 serial port; the bus transceiver includes: a CAN bus transceiver; preferably, the launching step is executed while the two missiles are powered up, and the two missiles are launched in sequence; the real-time information is a PAL video signal. The invention has reasonable design and convenient use, has the information channel gating function, particularly the video gating function in the missile launching process, and is favorable for controlling the missile launching in the missile weapon system with the optical imaging guide device.
Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, units provided by the present invention as pure computer readable program code, the system and its various devices, modules, units provided by the present invention can be fully implemented by logically programming method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system and various devices, modules and units thereof provided by the invention can be regarded as a hardware component, and the devices, modules and units included in the system for realizing various functions can also be regarded as structures in the hardware component; means, modules, units for performing the various functions may also be regarded as structures within both software modules and hardware components for performing the method.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A launch control apparatus adapted for dual-launch missile launching, comprising: the system comprises an upper computer module, a first transceiver module, a second transceiver module, a DSP processor module and a gating module;
the first transceiver module is connected with the DSP processor module;
the upper computer module and the DSP module are connected in series through a second transceiver module;
the gating module is respectively connected with the DSP module and the upper computer module in series, and outputs the information of any information channel or any plurality of information channels to the upper computer module according to the gating instruction and the real-time information output by the upper computer module.
2. The launch control apparatus adapted for twin-missile launching as recited in claim 1, wherein the video gating module comprises: gating the controller;
the gating controller is externally connected with a direct current power supply, and the gating controller is grounded.
3. The launch control apparatus adapted for twin-missile launching according to claim 1, wherein the first transceiver module comprises: a bus transceiver module, the bus transceiver module comprising: a CAN bus circuit and a bus transceiver;
the number of the CAN bus circuits is two;
the number of the bus transceivers is two;
the DSP processor module comprises: a bus controller;
the bus transceiver is externally connected with a direct current power supply, and the bus transceiver is grounded.
4. The launch control apparatus adapted for twin-missile launching according to claim 1, wherein the second transceiver module comprises: a second circuit, a second transceiver;
the second transceiver is connected with the DSP processor through a second circuit;
the upper computer module comprises fire control equipment;
the second circuit includes: RS422 circuit.
5. The launch control apparatus adapted for twin-missile launching according to claim 1, further comprising: a power supply control module; the power supply control module is connected with the DSP processor module in parallel;
the power control module includes: the missile control system comprises a missile energizing circuit, a thermal battery activating circuit, an engine ignition circuit and a relay; the missile electrifying circuit, the thermal battery activating circuit and the engine ignition circuit are respectively connected with the relay in parallel.
6. The launch control apparatus adapted for twin-missile launching as recited in claim 1, wherein the gating module is a video gating module;
the video gating module is respectively connected with the DSP module and the upper computer module in series, and the video gating module outputs video information of any information channel or any plurality of information channels to the upper computer module according to a video gating instruction and real-time information.
7. A launch control method suitable for launching a double-launched missile, characterized in that, by using the launch control device suitable for launching a double-launched missile of any one of claims 1 to 6, the following steps are executed:
and a transmitting communication step: the launching control equipment suitable for launching the double-launched missiles is in communication connection with the upper computer module through the second transceiver; the missile launching module is in communication connection with the bus transceiver;
executing a transmitting step: the launching control equipment suitable for launching the double-launched missiles powers up the missile launching module and is in communication connection with the missile launching module and the upper computer module at the same time, and the missile launching module executes missile launching;
a gating step: the launching control equipment suitable for launching the double-launched missiles outputs the information of any one information channel or any plurality of information channels according to the real-time information and the gating instruction output by the upper computer module.
8. The launch control method adapted for twin-missile launching as recited in claim 7, wherein the second transceiver comprises: RS422 serial port;
the bus transceiver includes: CAN bus transceiver.
9. The launch control method adapted for dual-missile launching as in claim 7, wherein the launching step is performed while powering up the two missiles and the two missile launches are performed sequentially.
10. The fire control method of a two-missile launcher suitable for two-missile launching as claimed in claim 7, wherein the real-time information is a PAL video signal.
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| CN201910917270.1A CN110727218A (en) | 2019-09-26 | 2019-09-26 | Launching control equipment and method suitable for launching double-launched missiles |
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| CN201910917270.1A CN110727218A (en) | 2019-09-26 | 2019-09-26 | Launching control equipment and method suitable for launching double-launched missiles |
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Cited By (1)
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| CN111397439A (en) * | 2020-03-16 | 2020-07-10 | 上海机电工程研究所 | Portable guided missile firepower control equipment |
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