CN114136151B - Device and method for parallel setting of correction projectile parameters of multi-barrel rocket projectile - Google Patents
Device and method for parallel setting of correction projectile parameters of multi-barrel rocket projectile Download PDFInfo
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- CN114136151B CN114136151B CN202111150677.XA CN202111150677A CN114136151B CN 114136151 B CN114136151 B CN 114136151B CN 202111150677 A CN202111150677 A CN 202111150677A CN 114136151 B CN114136151 B CN 114136151B
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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
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/03—Cooperating elements; Interaction or communication between different cooperating elements or between cooperating elements and receivers
- G01S19/08—Cooperating elements; Interaction or communication between different cooperating elements or between cooperating elements and receivers providing integrity information, e.g. health of satellites or quality of ephemeris data
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/14—Receivers specially adapted for specific applications
- G01S19/18—Military applications
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04J—MULTIPLEX COMMUNICATION
- H04J3/00—Time-division multiplex systems
- H04J3/02—Details
- H04J3/06—Synchronising arrangements
- H04J3/0635—Clock or time synchronisation in a network
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L12/00—Data switching networks
- H04L12/02—Details
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
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Abstract
The invention discloses a device and a method for parallelly setting correction projectile parameters of a multi-barrel rocket projectile, which comprises the steps of acquiring satellite ephemeris data in real time and judging the validity of the satellite ephemeris data; acquiring and forwarding the position data of the gun carrier to a data resolving computer in real time, and receiving the data information of the rocket projectile and the bullet path, which is sent by the data resolving computer and is resolved according to the target information and the position data of the gun carrier; judging the validity of the rocket projectile ballistic data; if the satellite ephemeris data and the rocket projectile ballistic data are both effective, performing data fusion on the satellite ephemeris data and the rocket projectile ballistic data in a dynamic packaging mode and packaging the data into rocket correction projectile setting parameters; and the selected pipe number rocket is corrected and loaded in parallel according to the loading parameters; and receiving and analyzing the setting state information returned by the rocket correction projectile with the selected pipe number, and judging whether parameter setting is finished or not. The invention solves the problem that the conventional rocket gun has long time for correcting the missile parameter serial loading in a parallel loading mode.
Description
Technical Field
The invention relates to the technical field of multi-rocket launcher launching control, in particular to a multi-rocket launcher correction projectile parameter parallel setting device and method.
Background
The multi-tube rocket gun is an effective weapon capable of providing large-area instantaneous intensive fire power, has the characteristics of sudden, intensive and violent fire power, simple and light structure and strong maneuverability, is different from conventional cannonballs and missiles, is a weapon which depends on saturation attack to strike enemy troops in quantity, but has poor concentration.
The rocket gun correction projectile is a rocket projectile with simple trajectory correction capability added on the basis of an uncontrolled rocket projectile, improves the accuracy of an attack target, has an autonomous positioning function, and needs to fix satellite information data and projectile path data before launching. At present, the parameter setting of the rocket gun correction projectile generally adopts a multi-tube serial one-by-one setting method, and the setting method consumes long time.
Disclosure of Invention
The invention aims to solve the technical problem that the parameter setting of the existing rocket gun correction projectile generally adopts a multi-tube serial one-by-one setting method, and the setting method has the problem of long time consumption. The invention aims to provide a multi-tube rocket gun correction projectile parameter parallel loading device and method, which improve the loading mode of shortening rocket gun correction projectile parameters and solve the problem that the parameter serial loading time of the existing rocket gun correction projectile is long, namely, the loading time is shortened, the battle preparation time of a rocket gun weapon system is shortened, and the battlefield vitality of the rocket gun weapon system is improved.
The invention is realized by the following technical scheme:
in a first aspect, the invention provides a multi-rocket launcher missile parameter correcting parallel setting device, which comprises: the Beidou antenna, the power amplifier, the time service communication module, the power supply module, the data processing module and the setting data communication module;
the Beidou antenna is used for acquiring satellite signals, and the satellite signals comprise satellite ephemeris data and gun carrier position data;
the power amplifier is used for performing power amplification processing on satellite ephemeris data and gun carriage position data acquired from the Beidou antenna to obtain satellite signals subjected to power amplification processing;
the Beidou antenna is used for receiving satellite signals, transmitting the received satellite signals to the setting data communication module through the time service communication module through the power amplifier, and transmitting satellite ephemeris data and gun-carriage position data to the data processing module;
the data processing module is used for forwarding the gun carriage position data to a data resolving computer of a weapon system and receiving data information of the rocket projectile and the bullet channel data sent by the data resolving computer of the weapon system and resolved according to target information and the gun carriage position data; fusing and packaging the rocket projectile trajectory data and the satellite ephemeris data into rocket correction projectile installation fixed parameters; according to the rocket correction projectile setting parameters, parallelly finishing parameter setting and system time service of multi-tube rocket correction projectiles (rocket projectiles with various tube numbers such as 12-tube rocket projectiles or 40-tube rocket projectiles);
the setting data communication module is used for carrying out data transmission communication of the multi-tube rocket correction projectile;
and the power supply module is used for providing electric energy for the modules.
The invention can be used for similar products or other products, is not limited to 12-tube rocket guns, is also suitable for rocket guns with various tube numbers such as 40 tubes and the like, and is also suitable for rocket correction projectiles and missiles with various calibers.
When parameters are set, the Beidou antenna transmits received satellite signals (including satellite ephemeris data, gun carriage position data and the like) to a set data communication module through a time service communication module through a power amplifier, and transmits the satellite ephemeris data and the gun carriage position data to a data processing module; the data processing module transmits the position data of the gun carriage to the weapon system data resolving computer; and the data processing module receives data information of rocket projectile ballistic data which is sent by a weapon system solution computer and is resolved according to target information and gun carriage position data, completes data fusion of setting parameters by combining the rocket projectile ballistic data and satellite ephemeris data, and completes parameter setting and system time service of 12 rocket-launched correction projectiles in parallel.
After the parallel loading method is used for a weapon system, the problem that the existing rocket gun modified projectile parameter serial loading time is long can be solved through a parallel loading mode, the fighting preparation time of the rocket gun weapon system is shortened, and the battlefield vitality of the rocket gun weapon system is improved.
Furthermore, the data processing module fuses and packages the rocket projectile ballistic data and the satellite ephemeris data into rocket correction projectile fixed parameters, and the rocket correction projectile parameter frame data package is completed in a dynamic package mode; wherein: the dynamic group package is that the data processing module dynamically sets the launching number, the launching sequence and the launching channel in the number 1-12 rocket launching correcting projectile according to the requirements issued by the element resolving computer and under the principle of following the safe launching rule.
Furthermore, the rocket correction projectile parameter frame comprises satellite ephemeris data of the rocket correction projectile, rocket projectile ballistic data, a rocket correction projectile specific tube number, a fuze installation mode and a check bit, wherein the check bit is a check bit calculated according to parameter data.
Furthermore, parameter setting and system time service of multi-tube rocket correction projectiles (rocket projectiles with various tube numbers such as 12-tube rocket projectiles or 40-tube rocket projectiles and the like) are completed in parallel in the data processing module; wherein, the secondary parameter setting mode is adopted for setting.
Furthermore, the data processing module is further configured to perform validity judgment on the received satellite ephemeris data and perform validity judgment on the rocket projectile ballistic data.
Furthermore, the data processing module adopts a Cortex A9 structure 4-core 800MHz operation processor, and can simultaneously complete state detection, information interaction and parameter setting of 12-tube rocket projectiles; or other processors with comparable processing capabilities.
Further, the loading data communication module is provided with a 12-channel RS422 data loading interface which is related to a communication interface selected by the rocket correction projectile.
In a second aspect, the invention also provides a multi-rocket launcher correction projectile parameter parallel setting method, which is applied to the multi-rocket launcher correction projectile parameter parallel setting device and comprises the following steps:
acquiring satellite ephemeris data in real time, and judging the validity of the satellite ephemeris data;
acquiring and forwarding the position data of the gun carrier to a data resolving computer in real time, and receiving the data information of the rocket projectile and the bullet path, which is sent by the data resolving computer and is resolved according to the target information and the position data of the gun carrier; judging the validity of the rocket projectile ballistic data;
if the satellite ephemeris data and the rocket projectile ballistic data are both effective, performing data fusion on the satellite ephemeris data and the rocket projectile ballistic data in a dynamic packaging mode and packaging the data into rocket correction projectile setting parameters; according to the rocket correction projectile setting parameters and the requirements set by a computer calculated according to the data elements, a setting data communication module is controlled, and the rocket correction projectile setting parameters are subjected to selected pipe number rocket correction projectile setting in parallel through an RS422 interface (at most 12 rocket correction projectile parameters can be set in parallel);
and receiving and analyzing the loading state information returned by the rocket correction projectile with the selected pipe number, and judging whether parameter loading is finished.
Further, the satellite ephemeris data and rocket projectile ballistic data are subjected to data fusion in a dynamic package mode and packaged into rocket correction projectile setting parameters; the method specifically comprises the following steps:
the method comprises the steps that satellite ephemeris data are adopted in the front, rocket projectile trajectory data are adopted in the rear, dynamic package is carried out according to different projectile launching tasks, rocket correction projectile parameter frame data package is completed, the rocket correction projectile parameter frame comprises the satellite ephemeris data of a rocket correction projectile, the rocket projectile trajectory data, a rocket correction projectile specific tube number, a fuze mounting mode and a check bit, and the check bit is a check bit which is resolved according to the parameter data;
the parallel rocket correction missile setting of the selected pipe number through the RS422 interface according to the rocket correction missile setting parameters specifically comprises the following steps:
and (3) loading 12 frames of rocket correction projectile parameter data into a 12-frame rocket correction projectile loading computer in parallel through a loading data communication module.
Further, the receiving and analyzing of the loading state information returned by the rocket correction projectile with the selected pipe number judges whether parameter loading is finished; the method specifically comprises the following steps:
and (4) the time required for completing parameter setting is not more than 30s, if all the rocket correcting bullets are not successfully set for the first time, the rocket correcting bullets which are not successfully set are subjected to secondary setting, the rocket correcting bullets are completely set whether all the rocket correcting bullets are successfully set for the second time, and a setting result is returned.
Compared with the prior art, the invention has the following advantages and beneficial effects:
1. according to different missions, the method completes rocket correction projectile parameter data package in a dynamic package mode, wherein a rocket correction projectile parameter frame comprises specific tube numbers of the rocket correction projectile, a fuze setting mode and check bits for resolving according to parameter data. The dynamic group package mainly refers to that the data processing module 5 can dynamically set the launching number, the launching sequence and the launching channel in the 1-12 rocket launching correcting projectile according to the requirements issued by the element resolving computer 8 and the principle of following the safe launching rule; and carrying out the selected pipe number rocket correction projectile setting on the rocket correction projectile setting parameters in parallel.
2. The invention can be used for similar products or other products, is not limited to 12-tube rocket guns, is also suitable for rocket guns with various tube numbers such as 40 tubes and the like, and is also suitable for rocket correction projectiles and missiles with various calibers.
3. After the parallel loading method is used for a weapon system, the problem that the existing rocket gun modified projectile parameter serial loading time is long can be solved through a parallel loading mode, the fighting preparation time of the rocket gun weapon system is shortened, and the battlefield vitality of the rocket gun weapon system is improved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principles of the invention. In the drawings:
FIG. 1 is a working principle diagram of a multi-rocket launcher correction projectile parameter parallel setting device of the invention.
FIG. 2 is a flow chart of a multi-rocket launcher correction projectile parameter parallel setting method of the invention.
Reference numbers and corresponding part names:
the system comprises a Beidou antenna 1, a power amplifier 2, a time service communication module 3, a power supply module 4, a data processing module 5, a data communication module 6, a rocket correction projectile 7-12 and an 8-data resolving computer.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and the accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not used as limiting the present invention.
Example 1
As shown in fig. 1, the invention relates to a multi-rocket launcher correction projectile parameter parallel setting device, comprising: the Beidou antenna 1, the power amplifier 2, the time service communication module 3, the power supply module 4, the data processing module 5 and the setting data communication module 6;
the Beidou antenna 1 is used for acquiring satellite signals (digital signals), and the satellite signals comprise satellite ephemeris data and gun carriage position data;
the power amplifier 2 is used for performing power amplification processing on satellite ephemeris data and gun carriage position data acquired from the Beidou antenna 1 to obtain a satellite signal subjected to power amplification processing;
the time service communication module 3 is used for acquiring a time service signal (analog signal), the Beidou antenna 1 transmits the received satellite signal to the setting data communication module 6 through the time service communication module 3 by the power amplifier 2, and transmits the satellite ephemeris data and the gun carriage position data to the data processing module 5;
the data processing module 5 is configured to forward the gun carriage position data to the data element calculating computer 8 of the weapon system, and receive data information of the rocket projectile lane sent by the data element calculating computer 8 of the weapon system and calculated according to the target information and the gun carriage position data; fusing and packaging the rocket projectile ballistic data and the satellite ephemeris data into rocket correction projectile mounting fixed parameters; according to the rocket correction projectile setting parameters, parallelly finishing parameter setting and system time service of multi-tube rocket correction projectiles (rocket projectiles with various tube numbers such as 12-tube rocket projectiles or 40-tube rocket projectiles);
the fixed data communication module 6 is used for carrying out data transmission communication of the multi-rocket correcting projectile;
and the power supply module 4 is used for supplying electric energy to the modules.
The invention can be used for similar products or other products, is not limited to 12-tube rocket guns, is also suitable for rocket guns with various tube numbers such as 40 tubes and the like, and is also suitable for rocket correcting missiles and missiles with various calibers.
For further explaining the embodiment, in the data processing module 5, the rocket projectile trajectory data and the satellite ephemeris data are fused and packaged into rocket correction projectile setting parameters, and a dynamic packaging manner is adopted to complete rocket correction projectile parameter frame data packaging; wherein: the dynamic group package is that the data processing module 5 dynamically sets the launching quantity, the launching sequence and the launching channel in the 1-12 number launching rocket correcting bombs according to the requirements issued by the element resolving computer 8 and under the principle of following the safe launching rule.
Specifically, the rocket correction projectile parameter frame comprises satellite ephemeris data of the rocket correction projectile, rocket projectile trajectory data, a rocket correction projectile body pipe number, a fuse setting mode and a check bit, wherein the check bit is a check bit which is calculated according to the parameter data.
To further explain the embodiment, the data processing module 5 completes parameter setting and system time service of a multi-tube (rocket cannons with various tube numbers such as 12-tube rocket cannons or 40-tube rocket cannons) rocket correction bomb in parallel; and the second time of the secondary loading is finished regardless of whether all the loads are successful or not, and the loading is finished and the loading result is returned. In specific implementation, the time required by the parallel installation of the invention is between 12s and 15 s.
For further explanation of the embodiment, the method is further configured to perform validity judgment on the received satellite ephemeris data, and perform validity judgment on the rocket projectile trajectory data.
For further explanation of this embodiment, the data processing module 5 adopts a Cortex A9 architecture 4-core 800MHz arithmetic processor, and can simultaneously complete state detection, information interaction, and parameter setting of a 12-tube rocket projectile; or other processors with comparable processing capabilities.
For further illustration of the present embodiment, the loading data communication module 6 has 12 RS422 data loading interfaces, which are associated with communication interfaces selected for rocket correction projectiles.
When parameters are loaded and timed, the Beidou antenna 1 transmits received satellite signals (including satellite ephemeris data, gun carriage position data and the like) to a loading data communication module 6 through a time service communication module 3 through a power amplifier 2, and transmits the satellite ephemeris data and the gun carriage position data to a data processing module 5; the data processing module 5 transmits the position data of the gun carriage to the weapon system data resolving computer 8; the data processing module 5 receives data information of rocket projectile trajectory data, which is sent by a weapon system data resolving computer 8 and is resolved according to target information and gun carriage position data, completes data fusion of setting parameters by combining the rocket projectile trajectory data and satellite ephemeris data, and completes 12 parameter setting and system time service of the rocket correction projectile in parallel.
After the invention is used for a weapon system, the problem of long time for correcting the missile parameter serial loading of the traditional rocket gun can be solved, the combat preparation time of the rocket gun weapon system is shortened, and the battlefield vitality of the rocket gun weapon system is improved.
Key points and protection points of the invention: (1) the setting data communication module 6 is provided with 12 paths of RS422 data setting interfaces;
(2) the data processing module 5 adopts a Cortex A9 structure 4-core 800MHz operation processor;
(3) and according to the difference of each projectile launching task, completing rocket correction projectile parameter data packaging in a dynamic packaging mode, wherein a rocket correction projectile parameter frame comprises a specific tube number of the rocket correction projectile, a fuze setting mode and a check bit for resolving according to parameter data. The dynamic group package mainly refers to that the data processing module 5 can dynamically set the launching number, the launching sequence and the launching channel in the 1-12 rocket launching correcting projectile according to the requirements issued by the element resolving computer 8 and the principle of following the safe launching rule; carrying out the selected pipe number rocket correction projectile setting on the rocket correction projectile setting parameters in parallel;
(4) and (5) setting by adopting a secondary parameter setting mode.
The invention can be used for similar products or other products, is not limited to 12-tube rocket guns, is also suitable for rocket guns with various tube numbers such as 40 tubes and the like, and is also suitable for rocket correction projectiles and missiles with various calibers.
Example 2
As shown in fig. 2, the present embodiment is different from embodiment 1 in that the present embodiment provides a method for parallel setting of corrected projectile parameters of a multi-rocket launcher, the method is applied to a device for parallel setting of corrected projectile parameters of a multi-rocket launcher in embodiment 1, and the method includes:
acquiring satellite ephemeris data in real time, and judging the validity of the satellite ephemeris data;
acquiring and forwarding gun carrier position data to a data element resolving computer in real time, and receiving rocket projectile lane data information which is resolved according to target information and gun carrier position data and sent by the data element resolving computer; judging the validity of the rocket projectile ballistic data;
if the satellite ephemeris data and the rocket projectile ballistic data are both effective, performing data fusion on the satellite ephemeris data and the rocket projectile ballistic data in a dynamic packaging mode and packaging the data into rocket correction projectile setting parameters; according to the rocket correction projectile setting parameters and the requirements set by a computer calculated according to the data elements, a setting data communication module 6 is controlled, and the rocket correction projectile setting parameters are subjected to selected pipe number rocket correction projectiles 7 in parallel through an RS422 interface (at most 12 rocket correction projectile parameters can be set in parallel);
and receiving and analyzing the loading state information returned by the rocket correction projectile with the selected pipe number, and judging whether parameter loading is finished.
For further explanation of this embodiment, the satellite ephemeris data and rocket projectile trajectory data are subjected to data fusion by using a dynamic package method and packaged into rocket correction projectile setting parameters; the method specifically comprises the following steps:
the method comprises the steps that satellite ephemeris data are adopted in the front, rocket projectile trajectory data are adopted in the rear, dynamic package is carried out according to different projectile launching tasks, rocket correction projectile parameter frame data package is completed, the rocket correction projectile parameter frame comprises the satellite ephemeris data of a rocket correction projectile, the rocket projectile trajectory data, a rocket correction projectile specific tube number, a fuze mounting mode and a check bit, and the check bit is a check bit which is resolved according to the parameter data;
the parallel loading of the selected pipe number rocket correction projectile 7 through the RS422 interface according to the rocket correction projectile loading parameters specifically comprises the following steps:
12 frames of rocket correction projectile parameter data are parallelly installed in a 12-rocket correction projectile onboard computer through a loading data communication module 6.
For further explanation of this embodiment, the receiving and analyzing the loading status information returned by the rocket correction projectile with the selected pipe number determines whether parameter loading is completed; the method specifically comprises the following steps:
and (4) the time required for finishing parameter setting is not more than 30s, if the first time is not completed successfully, the second time of setting is carried out on the rocket correction bomb which is not successfully set, the second time of setting is finished whether all the settings are successful or not, and a setting result is returned.
To further explain the present embodiment, the satellite ephemeris data validity determination is specifically performed as follows:
the data processing module 5 sets 1 satellite data length effective identifier satellite ValidLen and assigns a value of 0; the data processing module 5 sets 1 satellite number identifier satellite validnum capable of receiving satellite signals and assigns a value of 0; the data processing module 5 sets 1 satellite data verification valid identifier SatelliteValidCHk and assigns a value of 0; the data processing module 5 compares the byte number identifier of the data length of the received time service communication module 3 with the actually received data length, and if the length is consistent, the SatelliteValidLen is assigned with 0x01; if the number of the satellite particles received by the data processing module 5 through the time service communication module 3 is not less than 5, the satellite ValidNum is assigned with 0x01; the data processing module 5 carries out check bit calculation on satellite data output by the time service communication module 3 to generate a check bit, the check bit is compared with a self check bit in the received satellite data, and if the generated check bit is consistent with the self check bit, the satellite ValidChk is assigned with 0x01; satellite ephemeris data is valid if three strips, satelliteValidLen = =0x01, satelliteValidNum = =0x01, satelliteValidChk = =0x01, are satisfied simultaneously.
To further explain this embodiment, the effectiveness judgment is performed on the rocket projectile trajectory data, which specifically includes:
the data processing module 5 carries out check bit resolving on the rocket projectile trajectory data output by the primitive resolving computer 8 to generate check bits, the check bits are compared with self check bits of the received rocket projectile trajectory data, if the generated check bits are consistent with the self check bits, the rocket projectile trajectory data are judged to be valid, and if not, the rocket projectile trajectory data are judged to be invalid.
After the method is used for a weapon system, the problem of long time for correcting the missile parameters of the existing rocket gun in serial loading can be solved by a parallel loading and setting mode, the fighting preparation time of the rocket gun weapon system is shortened, and the battlefield vitality of the rocket gun weapon system is improved.
As will be appreciated by one skilled in the art, embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the application. It will be understood that each flow and/or block of the flowchart illustrations and/or block diagrams, and combinations of flows and/or blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are merely exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (10)
1. A multi-rocket launcher correction projectile parameter parallel setting device is characterized by comprising: the Beidou antenna (1), the power amplifier (2), the time service communication module (3), the power supply module (4), the data processing module (5) and the setting data communication module (6);
the Beidou antenna (1) is used for acquiring satellite signals, and the satellite signals comprise satellite ephemeris data and gun carrier position data;
the power amplifier (2) is used for performing power amplification processing on satellite ephemeris data and gun carriage position data acquired from the Beidou antenna (1) to obtain satellite signals subjected to power amplification processing;
the time service communication module (3) is used for acquiring a time service signal, the Beidou antenna (1) transmits the received satellite signal to the setting data communication module (6) through the power amplifier (2) and the time service communication module (3), and transmits satellite ephemeris data and gun carriage position data to the data processing module (5);
the data processing module (5) is used for forwarding the position data of the gun carrier to the data element resolving computer (8) of the weapon system and receiving data information of the rocket projectile channel sent by the data element resolving computer (8) of the weapon system and resolved according to the target information and the position data of the gun carrier; fusing and packaging the rocket projectile ballistic data and the satellite ephemeris data into rocket correction projectile mounting fixed parameters; according to the rocket correction projectile setting parameters, parameter setting and system time service of the multi-tube rocket correction projectile are completed in parallel;
and the setting data communication module (6) is used for carrying out data transmission communication of the multi-rocket correction projectile.
2. The multi-rocket launcher projectile parameter parallel loading and setting device according to claim 1, wherein said data processing module (5) fuses and packages said rocket projectile trajectory data and said satellite ephemeris data into rocket projectile parameter frame data packets by means of dynamic packaging; wherein: the dynamic group package is that the data processing module (5) dynamically sets the launching quantity, the launching sequence and the launching channel in the 1-12 rocket launching correction projectile according to the requirements issued by the element resolving computer (8) and under the principle of following the safe launching rule.
3. The multi-barrel rocket gun correction projectile parameter parallel setting device according to claim 2, wherein the rocket correction projectile parameter frame comprises satellite ephemeris data of a rocket correction projectile, rocket projectile ballistic data, a rocket correction projectile specific tube number, a fuze setting mode and a check bit, and the check bit is a check bit calculated according to parameter data.
4. The parallel multi-rocket launcher correction projectile parameter setting device according to claim 1, wherein the data processing module (5) completes parameter setting and system time service of the multi-rocket launcher correction projectile in parallel; wherein, the secondary parameter setting mode is adopted for setting.
5. The multi-rocket launcher correction projectile parameter parallel setting device according to claim 1, wherein the data processing module (5) is further configured to perform validity judgment on the received satellite ephemeris data and to perform validity judgment on rocket projectile ballistic data.
6. The multi-rocket launcher correction projectile parameter parallel setting device according to claim 1, wherein the data processing module (5) adopts a Cortex A9 architecture 4-core 800MHz arithmetic processor, and completes state detection, information interaction and parameter setting of 12-tube rocket projectiles at the same time.
7. A multi-rocket launcher correction projectile parameter parallel loading apparatus according to claim 1, wherein said loading data communication module (6) has 12 RS422 data loading interfaces.
8. A multi-rocket launcher correction projectile parameter parallel setting method, which is applied to a multi-rocket launcher correction projectile parameter parallel setting device as claimed in any one of claims 1 to 7, and which comprises:
acquiring satellite ephemeris data in real time, and judging the validity of the satellite ephemeris data;
acquiring and forwarding gun carrier position data to a data element resolving computer in real time, and receiving rocket projectile lane data information which is resolved according to target information and gun carrier position data and sent by the data element resolving computer; judging the validity of the rocket projectile ballistic data;
if the satellite ephemeris data and the rocket projectile ballistic data are both effective, performing data fusion on the satellite ephemeris data and the rocket projectile ballistic data in a dynamic packaging mode and packaging the data into rocket correction projectile setting parameters; and the selected pipe number rocket correction missile-setting is carried out in parallel through an RS422 interface according to the rocket correction missile-setting parameters;
and receiving and analyzing the loading state information returned by the rocket correction projectile with the selected pipe number, and judging whether parameter loading is finished.
9. The method for parallel setting of the correction projectile parameters of the multi-rocket launcher according to claim 8, wherein the satellite ephemeris data and rocket projectile trajectory data are subjected to data fusion by adopting a dynamic package mode and are packaged into rocket correction projectile setting parameters; the method specifically comprises the following steps:
the method comprises the following steps of dynamically packaging a rocket correction projectile parameter frame data according to different missions after satellite ephemeris data are adopted, rocket projectile ballistic data are adopted, a rocket projectile ballistic data frame data package is completed, the rocket correction projectile parameter frame comprises the satellite ephemeris data of a rocket correction projectile, the rocket projectile ballistic data, a rocket correction projectile specific tube number, a fuze mounting mode and a check bit, and the check bit is a check bit which is calculated according to the parameter data;
the parallel rocket correction missile setting of the selected pipe number through the RS422 interface according to the rocket correction missile setting parameters specifically comprises the following steps:
and (3) parallelly loading 12 frames of rocket correction projectile parameter data into a 12-rocket correction projectile on-board computer through a loading data communication module.
10. The method for parallel setting of the parameters of the multi-rocket launcher correction projectile according to claim 8, wherein the receiving and analyzing the setting status information returned by the rocket correction projectile with the selected tube number judges whether the parameter setting is completed; the method specifically comprises the following steps:
and (4) the time required for finishing parameter setting is not more than 30s, if the first time is not completed successfully, the second time of setting is carried out on the rocket correction bomb which is not successfully set, the second time of setting is finished whether all the settings are successful or not, and a setting result is returned.
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