CN113093601A - Close-range aviation firepower support system and method - Google Patents
Close-range aviation firepower support system and method Download PDFInfo
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- CN113093601A CN113093601A CN202110343624.3A CN202110343624A CN113093601A CN 113093601 A CN113093601 A CN 113093601A CN 202110343624 A CN202110343624 A CN 202110343624A CN 113093601 A CN113093601 A CN 113093601A
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- 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
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- 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
- G01S19/38—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system
- G01S19/39—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system the satellite radio beacon positioning system transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
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Abstract
The invention provides a close-range aviation firepower support system and a close-range aviation firepower support method, and relates to the technical field of information. The system comprises measuring equipment, main control equipment and command equipment, wherein the measuring equipment is used for measuring target information of a target and sending the target information to the main control equipment, and the target information comprises a target distance and a target direction; the main control equipment is used for obtaining three-dimensional coordinates according to target information, generating a firepower support simple command according to the three-dimensional coordinates and sending the firepower support simple command to the command equipment, the command equipment is used for confirming the firepower support simple command and distributing different airplanes according to the firepower support simple command, and the different airplanes strike firepower on a target according to the target three-dimensional coordinates. The fire fighting robot can quickly and accurately hit fire to a target, improves the information exchange efficiency on a battlefield, and improves the short-distance aviation fire support capability.
Description
Technical Field
The invention relates to the technical field of information, in particular to an aviation fire power support system and an aviation fire power support method.
Background
The aviation firepower support is a combat action of an aviation soldier for supporting army and navy naval vessel formation and carrying out air assault on enemies, and is an important component of air support. The main categories include direct support and indirect support, in which direct support is an air assault on a target close to the leading force, and the effect of direct support is directly utilized by the forces being aided, and the effect of "near air support" of the army is similar to that of the force. In attack combat, it is common to carry out the attack after the ground force has initiated the impact. In defense combat, it begins when an enemy forces an attack. In the landing and airborne combat, the landing and the airborne landing are started simultaneously, and the combat mission is finished. Indirect support is an air assault on a target far from the leading army, the effect of which cannot be directly utilized by the aided army, but which plays a positive role in the battle progress, and the "long-distance air support" of the army is similar to this.
The current aviation support steps are complex, and the full information flow aiming at the short-distance aviation thermal power support action is not realized.
Disclosure of Invention
The invention aims to provide a short-distance aviation fire power support system and a short-distance aviation fire power support method, which can quickly and accurately carry out fire power striking on a target and improve the information exchange efficiency on a battlefield and the short-distance aviation fire power support capability.
The embodiment of the invention is realized by the following steps:
in a first aspect, an embodiment of the present invention provides a short-distance aviation thermal power support system, including a measurement device, a main control device, and a command device, wherein the measurement device is configured to measure target information of a target and transmit the target information to the main control device, the target information includes a target distance and an orientation, the main control device is configured to obtain three-dimensional coordinates according to the target information, generate a thermal power support command according to the three-dimensional coordinates, and transmit the thermal power support command to the command device, the command device is configured to confirm the thermal power support command, allocate different airplanes according to the thermal power support command, and perform thermal power striking on the target according to the three-dimensional coordinates by the different airplanes.
In some embodiments of the present invention, the close-range aviation thermal power support system further includes a plurality of pilot terminals, the command device transmits the thermal power support command to the plurality of pilot terminals, and the plurality of pilot terminals are configured to control different airplanes to perform thermal power striking on a target according to the thermal power support command.
In some embodiments of the present invention, the measuring device includes a laser range finder, and the laser range finder is communicatively connected to the main control device.
In some embodiments of the present invention, the short-range aviation power support system further includes a beidou navigation system, the measuring device measures target information through the beidou navigation system and sends the target information to the main control device, and any two of the main control device, the command device, and the pilot terminal communicate through the beidou navigation system.
In a second aspect, an embodiment of the present application provides a short-range aviation power support method, including step S1, in which a measurement device measures target information of a target and transmits the target information to a main control device, where the target information includes a target distance and an orientation;
s2: the main control equipment obtains three-dimensional coordinates according to the target information, generates a fire power support simple command according to the three-dimensional coordinates and sends the fire power support simple command to the command equipment;
s3: the command device is configured to confirm the fire power support command, assign different airplanes according to the fire power support command, and strike the fire power of the target by the different airplanes according to the three-dimensional coordinates.
In some embodiments of the present invention, the close-range aviation thermal power assistance method further includes a plurality of pilot terminals, the command device transmits the thermal power assistance profile to the plurality of pilot terminals, and the plurality of pilot terminals respectively control different airplanes to perform thermal power attack on a target according to the thermal power assistance profile.
In some embodiments of the present invention, the target information includes an attack direction of the target, a target elevation and a target category; the fire support profile includes one or more of the target information, flight information of different aircraft, attack information, ammunition information, weather information, and a fire application code.
In some embodiments of the invention, the flight information includes an offset range, a departure direction, and an angle of the aircraft; the attack information comprises any one or more of attack directions and starting point distances of different airplanes; the ammunition information comprises proposed ammunition and quantity, missile guiding mode and laser coding; the meteorological information comprises cloud base height and visibility.
In some embodiments of the present invention, the commander generates contact information and fire information based on the fire support order, transmits the fire information to different airplanes based on the contact information, and performs fire striking based on the fire information by different airplanes.
In some embodiments of the present invention, the method for supporting short-range aviation power further includes a beidou navigation system, the measuring device measures target information through the beidou navigation system and sends the target information to the main control device, and any two of the main control device, the command device, and the pilot terminal communicate through the beidou navigation system.
Compared with the prior art, the embodiment of the invention has at least the following advantages or beneficial effects:
in a first aspect, an embodiment of the present invention provides a short-distance aviation thermal power support system, including a measurement device, a main control device, and a command device, wherein the measurement device is configured to measure target information of a target and transmit the target information to the main control device, the target information includes a target distance and an orientation, the main control device is configured to obtain three-dimensional coordinates according to the target information, generate a thermal power support command according to the three-dimensional coordinates, and transmit the thermal power support command to the command device, the command device is configured to confirm the thermal power support command, allocate different airplanes according to the thermal power support command, and perform thermal power striking on the target according to the three-dimensional coordinates by the different airplanes.
With respect to the first aspect: the invention aims to provide a close-range aviation firepower support system which comprises a measuring device, a main control device and a plurality of pilot terminals. The target information is measured by the measuring equipment and then sent to the main control equipment, so that the target position and the related information can be obtained in real time, the target information required in the battle can be mastered more accurately, and the fighting efficiency is improved. The main control equipment calculates to obtain the three-dimensional coordinates according to the target information, so that the target position can be accurately represented, and further, the target can be subjected to fire striking more accurately. The main control equipment generates a firepower support simple command according to the three-dimensional coordinates and then sends the firepower support simple command to the command equipment, and the command equipment confirms the firepower support simple command, so that the firepower support simple command is ensured to be correct, and the accuracy of the firepower support simple command and the information exchange efficiency on a battlefield are improved. The command equipment distributes different airplanes according to the firepower support simple order, and the different airplanes strike the targets according to the three-dimensional coordinates, so that the quick and accurate striking target is realized, and the near-distance aviation firepower support capability is improved.
In a second aspect, an embodiment of the present application provides a short-range aviation power support method, including step S1, in which the measurement device measures target information of the target and transmits the target information to the main control device, the target information including the target distance, the azimuth, and a pitch angle with respect to the measurement device;
s2: the main control device obtains the three-dimensional coordinates according to the target information, generates the fire support simple command according to the three-dimensional coordinates and sends the fire support simple command to the command device;
s3: the command device is configured to confirm the fire power support command, and assign different airplanes based on the fire power support command, wherein the different airplanes have the three-dimensional coordinates to perform fire power striking on the target.
With respect to the second aspect: an object of the present invention is to provide a method for assisting near-field aviation thermal power, which operates in the same manner and has the same advantageous effects as those of the first aspect, and therefore, a repeated description thereof is not necessary.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Fig. 1 is a flowchart of a method for supporting short-range aviation power according to an embodiment of the present invention;
fig. 2 is a schematic diagram of a short-range aviation power support system according to an embodiment of the present invention.
Icon: 1-measuring equipment, 2-main control equipment, 3-pilot terminal and 4-command equipment.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present application, presented in the accompanying drawings, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In the description of the present application, it should be noted that the terms "upper", "lower", "inner", "outer", and the like indicate orientations or positional relationships based on orientations or positional relationships shown in the drawings or orientations or positional relationships conventionally found in use of products of the application, and are used only for convenience in describing the present application and for simplification of description, but do not indicate or imply that the referred devices or elements 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.
In the description of the present application, it is also to be noted that, unless otherwise explicitly specified or limited, the terms "disposed" and "connected" are to be interpreted broadly, e.g., as being either fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
Some embodiments of the present application will be described in detail below with reference to the accompanying drawings. The embodiments described below and the individual features of the embodiments can be combined with one another without conflict.
Example 1
Referring to fig. 1 to 2, fig. 2 shows a short-distance aviation thermal power support system according to an embodiment of the present application, which includes a measurement device 1, a main control device 2, and a command device 4, wherein the measurement device 1 is configured to measure target information of a target and transmit the target information to the main control device 2, the target information includes a target distance and an orientation, the main control device 2 is configured to obtain three-dimensional coordinates according to the target information, generate a thermal power support command according to the three-dimensional coordinates, and transmit the thermal power support command to the command device 4, the command device 4 is configured to confirm the thermal power support command, allocate different airplanes according to the thermal power support command, and fire-hit the target by the different airplanes according to the three-dimensional coordinates.
In detail, in the above embodiment, the measuring device 1 may be one or more of detection devices such as military satellites, radars, or sonars. The target information can be obtained by the measuring device 1, so that the target situation can be more clearly known in the battle, and the battle plan can be more conveniently made. The target information includes a target distance and an orientation, wherein the target distance refers to a straight-line distance from the measuring device 1 to a target point measured by the measuring device 1, and the orientation is an orientation relative to the measuring device 1, for example, any direction in the east, west, south and north directions of the measuring device 1, and is not limited in detail herein. The target information may also include the pitch angle of the target relative to the measuring device 1, thereby facilitating accurate target height through target distance and pitch angle calculations. In this embodiment, available information that can be measured by the conventional measuring apparatus 1, such as an image of the target, weather conditions of a place where the target is located, and the like, may be included in the target information. After the target information is measured, the measuring device 1 may send the target information to the main control device 2 through satellite communication, radio station, or the like.
The main control device 2 is an existing known intelligent terminal with computing capability, and the main control device 2 inputs the target information into a preset computing model after receiving the target information, so that a three-dimensional coordinate of the target is obtained through computing, and the target position can be accurately represented by building the three-dimensional coordinate of the target through computing. The main control device 2 generates a fire support simple command according to the three-dimensional coordinates of the target, wherein the fire support simple command is a simplified command, which may include various information, such as the number of enemy targets, the devices required by the party to fight, battlefield conditions, etc. in the present embodiment, the fire support simple command generated according to the three-dimensional coordinates of the target may include the orientation of the target, the height of the target, etc. by generating the format of the fire support simple command from the information, in a complicated fighting environment, the complicated information may be simplified and standardized, so that the fighter can more quickly and clearly understand the information transmitted by the command. The main control device 2 can transmit the generated fire support simple command to the commander 4 by a wireless communication method such as satellite communication or radio station, and when the fire support simple command is received by the commander 4, the contents of the fire support simple command are confirmed to ensure that the fire support simple command is correct, thereby improving the accuracy of the fire support simple command. After confirming the fire support command, the commander 4 distributes different numbers and different types of airplanes to fire the target according to the content of the fire support command, so that fire support can be given to ground troops in the air, an air-ground combined combat system is formed, and the combat effect is improved, wherein the different types of airplanes refer to different bombers or fighters.
In some embodiments of the present invention, the close-range aviation thermal power support system further includes a plurality of pilot terminals 3, the command device 4 transmits the thermal power support command to the plurality of pilot terminals 3, and the plurality of pilot terminals 3 are configured to control different airplanes to perform thermal power striking on the target according to the thermal power support command.
In the above embodiment, the pilot terminal 3 may also be an intelligent device with computing power. The command device 4 can send the firepower support simple command to the pilot terminals 3 through wireless communication modes such as satellite communication, radio stations and the like, and different pilots execute the take-off task of the airplane according to the commands received by the different pilot terminals 3, so that different airplanes can be distributed to perform firepower striking. In this embodiment, the fire support command may also be sent directly to the plurality of pilot terminals 3 through the main control device 2, so that different airplanes may be guided to fire striking directly through the main control device 2, which is only one implementation manner, and is not unique.
In some embodiments of the present invention, the measuring device 1 includes a laser range finder, and the laser range finder is communicatively connected to the main control device 2.
In the above embodiment, the laser distance measuring instrument is a conventionally known one, and has the advantages of light weight, small volume, simple operation and high distance measuring precision. The laser range finder can be applied to a reconnaissance plane and can also be used by being held by a fighter. The laser range finder can be a three-dimensional laser range finder, and the target distance and the pitch angle of the target relative to the laser range finder can be conveniently and accurately measured through the laser range finder, so that the target height can be obtained, and the target is positioned in a three-dimensional space. Optionally, the laser range finder may be in communication connection with the main control device 2 through satellite communication or mobile communication, so that target information may be transmitted to the main control device 2 in real time. The measurement device 1 and the main control device 2 in the above embodiments may perform full duplex communication, so that after the main control device 2 receives the target information, information can be fed back to the measurement device 1 in time to confirm whether the target information is received in real time. The command device 4 and the main control device 2 can also be in full-duplex communication, and the combat situation can be fed back in real time.
In some embodiments of the present invention, the short-range aviation power support system further includes a beidou navigation system, the measuring device 1 measures target information through the beidou navigation system and sends the target information to the main control device 2, and any two of the main control device 2, the command device 4, and the pilot terminal 3 communicate through the beidou navigation system.
In detail, the measuring device 1 can be positioned through a Beidou navigation system, the main control device 2 obtains the reference longitude and latitude and the elevation of the measuring device 1 through the Beidou navigation system and uses the reference longitude and latitude and the elevation as the reference for calculating the three-dimensional coordinate of the target, and then the three-dimensional coordinate of the target can be accurately calculated on the basis that the measuring device 1 measures the distance and the direction of the target. Any two of the main control equipment 2, the command equipment 4 and the pilot terminal 3 carry out short message communication through the Beidou navigation system, wherein the short message communication refers to that bidirectional information transmission is directly carried out through satellite signals, and in places where ordinary signals in deserts, oceans and the field cannot cover, any two of the main control equipment 2, the command equipment 4 and the pilot terminal 3 can carry out bilateral communication through the Beidou navigation system in real time, so that communication obstacles are avoided. After the main control device 2 generates the fire support simple command, the fire support simple command can be sent to the command device 4 through the short message communication function of the beidou navigation system, the command device 4 can also be sent to the plurality of pilot terminals 3 through the beidou navigation system, and the plurality of pilot terminals 3 can also feed back battlefield conditions to the command device 4 and the main control device 2 in real time through the short message communication function. In this embodiment, the beidou navigation system can also transmit the weather condition to order commander or flight crew master the weather condition in target area in real time.
Example 2
Referring to fig. 1 to 2, fig. 1 shows a method for supporting short-distance aviation power according to an embodiment of the present application, including step S1, in which a measurement device 1 measures target information of a target and transmits the target information to a main control device 2, where the target information includes a target distance and a target direction;
s2: the main control device 2 obtains three-dimensional coordinates according to the target information, generates a fire power support simple command according to the three-dimensional coordinates, and transmits the fire power support simple command to the command device 4;
s3: the command device 4 is configured to confirm the thermal power support command, assign different airplanes according to the thermal power support command, and strike thermal power on a target by the different airplanes according to the three-dimensional coordinates.
The principle and advantageous effects of the above embodiment are the same as those of embodiment 1, and a repeated description thereof is not necessary.
In some embodiments of the present invention, the close-range aviation thermal power assistance method further includes a plurality of pilot terminals 3, the command device 4 transmits the thermal power assistance command to the plurality of pilot terminals 3, and the plurality of pilot terminals 3 control different airplanes to perform thermal power striking on the target according to the thermal power assistance command.
The principle and advantageous effects of the above embodiment are the same as those of embodiment 1, and a repeated description thereof is not necessary.
In some embodiments of the present invention, the target information includes an attack direction of the target, a target elevation and a target category; the fire support profile includes one or more of the target information, flight information of different aircraft, attack information, ammunition information, weather information, and a fire application code.
In detail, the attack direction of the target refers to the direction in which the aircraft attacks the target, such as from a 45-degree direction. The target elevation is the height of the target relative to the sea level, which is automatically calculated by the main control device 2 according to the pitch angle of the target relative to the measuring device 1, which is obtained by the measuring device 1, the target categories are classified into a major category and a minor category, wherein the major category can be classified into vehicles, airplanes, ships, buildings and personnel, and the minor category is subdivided on the basis of the major category, for example, the vehicles can be classified into tanks, armored cars, troop cars, ordinary vehicles and the like. The fire support profile includes one or more of the target information, flight information of different aircraft, attack information, ammunition information, and weather information. Therefore, various information can be integrated and simplified through a firepower support simple command and then sent to the pilot terminals 3 through the main control equipment 2, the information transmission efficiency is improved, and an aviation army can quickly know the target and the battlefield situation, so that the target can be quickly and accurately hit. In this implementation, the firepower application password is used for the command device 4 or the main control device 2 to verify the authority to start firepower striking, and the firepower application password is set, so that the safety of firepower striking is ensured.
In some embodiments of the invention, the flight information includes an offset range, a departure direction, and an angle of the aircraft; the attack information comprises any one or more of attack directions and starting point distances of different airplanes; the ammunition information comprises proposed ammunition and quantity, missile guiding mode and laser coding; the meteorological information comprises cloud base height and visibility.
In detail, the flight information includes the offset range, the departure direction, and the angle of the aircraft. The offset range of the airplane means that the airplane can be offset on the left side or the right side after entering an attack route, and the actual selection can be carried out according to the deployment position of air defense fire power of an enemy. The departure direction and angle refer to the direction and angle of departure of the airplane from the battlefield after the attack is finished, for example, the airplane departs from the battlefield from the left 120 degrees, because other directions may have enemy air-defense weapons, so as to avoid the front contact with enemy air-defense firepower as much as possible. The offset range, departure direction and angle of the aircraft can be selected according to the actual enemy fire deployment, and are only exemplary and not limited thereto.
In detail, the attack information includes any one or more of attack directions and starting point distances of different airplanes. The attack direction is the direction from the attack starting point of the airplane to the target, and the starting point distance refers to the distance from the attack starting point to the target, wherein the starting point distance is not absolute because the range of the target is different in size and can be set according to the size of the target range and the actual situation. In this embodiment, the attack information may further include necessary descriptions, where the necessary descriptions refer to descriptions that are convenient for understanding and for the rear personnel to grasp the situation ahead, and may be related information of the target supplemented according to the battlefield situation, for example, when the target is a ground building, the necessary descriptions such as the structural material of the target may be added, and are not specifically limited herein.
In detail, the ammunition information includes the proposed ammunition and the number, laser-guided bomb guidance mode and the code thereof. It is recommended that ammunition and the amount of ammunition be deployed according to target information acquired by the measuring device 1, for example, when the target volume is large, ammunition with larger power or a larger amount of ammunition can be deployed, and when the target volume is small, ammunition with less power or a smaller amount of ammunition can be deployed. The guided missile can be guided by infrared guidance, radar guidance, laser guidance and other guidance modes, the code is the only code of the laser guided missile, and the laser guided bomb can be guided by the laser guidance equipment through the code.
In detail, the meteorological information includes cloud base height, visibility and meteorological conditions. The cloud base height is the vertical distance between the cloud base and the ground surface, and can be obtained through a portable meteorological instrument and the like or roughly estimated. Visibility refers to the distance visible in the horizontal direction and can be estimated approximately from the visible distance. The cloud base height and visibility are used for assisting rear commanders and pilots to master the battlefield meteorological conditions. The above-mentioned meteorological information may also contain necessary descriptions, and the necessary descriptions herein refer to descriptions for facilitating understanding and facilitating the rear personnel to grasp the front situation, such as wind direction, thunder and lightning, and the like, and are not limited specifically herein.
In some embodiments of the present invention, the commander 4 generates contact information and fire information based on the fire support commander, and the commander 4 transmits the fire information to different airplanes based on the contact information, and the airplanes hit fire based on the fire information.
Specifically, the commander 4 receives the fire support command issued by the master controller 2, and then confirms the fire support command by the commander in accordance with actual conditions such as battlefield, airplane, ammunition, and the like, forms the final fire information, and sets the related contact information. The contact information may be the call sign of the onboard radio on different airplanes, and the contact information may also include the call sign of the ground scout radio station. And the command equipment 4 contacts with different airplanes according to the contact information, so that the safety of the information is ensured. In this embodiment, pilot terminal 3 can obtain the contact information of command device 4, and carries out the communication liaison with ground scout personnel according to the ground scout personnel radio station call sign in the contact information, has promoted integration operation level. The firepower information is firepower striking information formed after a commander confirms a firepower support order, and can be sent to different pilot terminals 3 through the commander 4 and the main control device 2, wherein the commander 4 can send the firepower information to different airplanes according to communication information of the different airplanes included in the contact information, so that different numbers or types of airplanes use specified ammunition to strike a target.
In some embodiments of the present invention, the short-range aviation power support method further includes a beidou navigation system, the measuring device 1 measures target information through the beidou navigation system and sends the target information to the main control device 2, and any two of the main control device 2, the command device 4, and the pilot terminal 3 communicate through the beidou navigation system.
The principle and advantageous effects of the above embodiment are the same as those of embodiment 1, and a repeated description thereof is not necessary.
In the embodiments provided in the present application, it should be understood that the disclosed apparatus and method may be implemented in other ways. The apparatus embodiments described above are merely illustrative, and for example, the flowchart and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of apparatus, methods and computer program products according to various embodiments of the present application. In this regard, each block in the flowchart or schematic diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
In addition, functional modules in the embodiments of the present application may be integrated together to form an independent part, or each module may exist separately, or two or more modules may be integrated to form an independent part.
The functions, if implemented in the form of software functional modules and sold or used as a stand-alone product, may be stored in a computer readable storage medium. Based on such understanding, the technical solution of the present application or portions thereof that substantially contribute to the prior art may be embodied in the form of a software product stored in a storage medium and including instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present application. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
In summary, the present application provides a close-range aviation thermal support system and method, which includes a measurement device 1, a main control device 2, a pilot terminal 3, and a command device 4. The target information is measured by the measuring equipment 1 and then sent to the main control equipment 2, so that the target position and related information can be obtained in real time, the target information required in the battle can be mastered more accurately, and the fighting efficiency is improved. The main control device 2 calculates to obtain a three-dimensional coordinate according to the target information, so that the target position can be accurately represented, and further, the target can be subjected to fire striking more accurately. The main control device 2 generates a fire support simple command according to the three-dimensional coordinates and transmits the fire support simple command to the command device 4, and the command device 4 confirms the fire support simple command, thereby ensuring that the fire support simple command is correct, and improving the accuracy of the fire support simple command and the information exchange efficiency on the battlefield. The command equipment 4 distributes different airplanes according to the firepower support simple order, and the different airplanes strike the targets according to the three-dimensional coordinates, so that the quick and accurate striking target is realized, and the near-distance aviation firepower support capability is improved.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
It will be evident to those skilled in the art that the present application is not limited to the details of the foregoing illustrative embodiments, and that the present application may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the application being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Claims (10)
1. A close-range aviation fire support system is characterized by comprising a measuring device, a main control device and a command device;
the measuring equipment is used for measuring target information of a target and sending the target information to the main control equipment, wherein the target information comprises a target distance and a target direction;
the main control equipment is used for obtaining three-dimensional coordinates according to the target information, generating a firepower support simple command according to the three-dimensional coordinates and sending the firepower support simple command to the command equipment;
the command equipment is used for confirming the fire power support simple command, distributing different airplanes according to the fire power support simple command, and carrying out fire power striking on the target by the different airplanes according to the three-dimensional coordinates.
2. The close range aviation thermal power support system according to claim 1, further comprising a plurality of pilot terminals, the command device transmitting the thermal power support profile to the plurality of pilot terminals, the plurality of pilot terminals being configured to control different aircraft to perform thermal power strikes on targets respectively according to the thermal power support profile.
3. The close-range airborne fire support system of claim 1, wherein said measurement device comprises a laser range finder communicatively coupled to said master control device.
4. The close-range aircraft fire support system of claim 2, further comprising a beidou navigation system, wherein the measuring device measures target information through the beidou navigation system and transmits the target information to the main control device, and any two of the main control device, the command device and the pilot terminal communicate through the beidou navigation system.
5. A close-range aviation thermal power support method is characterized by comprising the following steps of S1, measuring target information of a target by a measuring device and sending the target information to a main control device, wherein the target information comprises a target distance and a target direction;
s2: the main control equipment obtains three-dimensional coordinates according to the target information, generates a firepower support simple command according to the three-dimensional coordinates and sends the firepower support simple command to the command equipment;
s3: the command equipment is used for confirming the fire power support simple command, distributing different airplanes according to the fire power support simple command, and carrying out fire power striking on the target by the different airplanes according to the three-dimensional coordinates.
6. The close range aviation thermal power assist method according to claim 5, further comprising a plurality of pilot terminals, wherein the command device transmits the thermal power assist command to the plurality of pilot terminals, and the plurality of pilot terminals control different airplanes to perform thermal power striking on the target in accordance with the thermal power assist command.
7. The near field aviation power support method according to claim 5, wherein the target information includes an attack direction of the target, a target elevation, and a target category; the fire support profile includes any one or more of the target information, flight information of a plurality of aircraft, attack information, ammunition information, weather information, and a fire application password.
8. The close-range airborne fire support method according to claim 7, wherein the flight information includes an offset range, a departure direction, and an angle of the aircraft; the attack information comprises attack directions and starting point distances of a plurality of airplanes; the ammunition information comprises the type and the number of ammunition, a guided missile guiding mode and laser codes; the meteorological information comprises cloud base height and visibility.
9. The method for assisting near-distance aviation fire as set forth in claim 8, wherein the command device generates contact information and fire information based on the fire support commander, the command device transmits the fire information to different airplanes based on the contact information, and the different airplanes perform fire fighting based on the fire information.
10. The close range aviation power support method according to claim 6, further comprising a beidou navigation system, wherein the measuring device measures target information through the beidou navigation system and transmits the target information to the main control device, and any two of the main control device, the command device, and the pilot terminal communicate through the beidou navigation system.
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