A multi-constraint fire control method based on shift matching for a carrier platform

Abstract

A kind of carrier platform multi-constraint fire control method based on shift matching, which can be applied to infrared image terminal guidance type precision guided weapon in complex battlefield environment. The launch azimuth angle, launch height and launch speed data information of guided weapon are obtained through the flight carrier platform as the input of fire control algorithm design. The shift matching algorithm is used to perform shift matching operation on the launch angle, launch height and launch speed at the launch time in the fire control software. The fire control solution under the multi-constraint condition of infrared imaging type precision guided weapon is obtained. Good operational effect of aerial guided weapon can be achieved in complex battlefield environment. The release restriction under the operational background of aerial guided weapon is fully considered.

Description

TECHNICAL FIELD

[0001] The present application relates to a carrier platform multi-constraint fire control method based on shift matching, and belongs to the technical field of aviation guided weapon fire control. BACKGROUND

[0002] The infrared imaging type precision guided weapon belongs to a kind of composite guided aviation precision guided weapon, and especially for the specific use scene of air-to-ground infrared imaging type precision guided weapon, the combat scene that the weapon encounters such as mountain obstruction in flight process or the combat scene that the weapon needs to bypass enemy interception area in flight process, thus there are specific restrictions on the fire control solution and launch of the weapon. Based on this background, when the infrared imaging type precision guided weapon carries out target attack, a multi-constraint fire control algorithm is needed for specific combat scene, so that the launch constraint of the weapon can be carried out in the fire control algorithm through the design and planning of combat task according to the needs of combat scene, the flight height, flight speed and attack range specified by the weapon are realized, the fire control launch window is realized, the infrared imaging type precision guided weapon involved is launched and attacked according to the constraint conditions, and the effectiveness of weapon attack is ensured.

[0003] In the fire control system of the existing precision guided weapon, in the range of flight speed, flight height and attack area that the weapon cannot be launched, the method adopted is to directly consider avoiding the condition range in the fire control system when designing the weapon fire control system, that is, to directly avoid the limited fire control constraint condition by adopting a conservative design method in the design. This processing method is simple and direct, but the disadvantage is that the fire control system is too conservative, which is not conducive to the flexible and effective use of the weapon system. SUMMARY

[0004] The technical problem solved by the present application is that when the flight speed, flight height and attack area of the weapon are limited in the specific use of the traditional precision guided weapon, the conservative design method is adopted to avoid the limited condition to realize the fire control system calculation, which causes the problem of insufficient flexibility and effectiveness of the weapon system in use, and a carrier platform multi-constraint fire control method based on shift matching is proposed.

[0005] The present application solves the above technical problems by the following technical scheme:

[0006] A carrier platform multi-constraint fire control method based on shift matching, comprising:

[0007] Measuring the current heading angle of the carrying platform, and obtaining the real-time heading angle of the guided weapon in the mounted state according to the heading angle;

[0008] Measuring the current flight height of the carrying platform, and obtaining the real-time flight height of the guided weapon in the mounted state according to the flight height;

[0009] The current flight speed of the platform is measured, and the real-time flight speed under the guidance weapon mounting state is obtained according to the flight speed;

[0010] The real-time heading angle, the real-time flight height and the real-time flight speed under the guidance weapon mounting state are loaded into the preset constraint condition of the fire control system, and the constraint limitation of the battlefield environment is converted into constraint input variables under the constraint condition;

[0011] The range of each constraint input variable is determined, the fire control system under the preset constraint condition of the fire control system is calculated, and the fire control delivery window parameters under the constraint condition are obtained.

[0012] The specific method for converting the real-time heading angle under the guidance weapon mounting state into a constraint input variable is:

[0013] The range of the heading angle under the guidance weapon mounting state is determined, the heading angle range is segmented and constrained, and the interval number after the segmented constraint is determined according to the current heading angle.

[0014] The specific method for converting the real-time flight height under the guidance weapon mounting state into a constraint input variable is:

[0015] The range of the flight height under the guidance weapon mounting state is determined, the flight height range is segmented and constrained, and the interval number after the segmented constraint is determined according to the current flight height.

[0016] The specific method for converting the real-time flight speed under the guidance weapon mounting state into a constraint input variable is:

[0017] The range of the flight speed under the guidance weapon mounting state is determined, the flight speed range is segmented and constrained, and the interval number after the segmented constraint is determined according to the current flight speed.

[0018] The preset constraint condition of the fire control system includes the heading angle constraint, the flight height constraint and the flight speed constraint, the constraint heading angle, the constraint flight height and the constraint flight speed are determined respectively under the condition of simultaneously satisfying the heading angle constraint, the flight height constraint and the flight speed constraint, the heading direction allowed delivery amount, the minimum flight height and the minimum flight speed are calculated as the fire control delivery window parameters under the constraint condition.

[0019] In the heading angle constraint, the heading angle interval is represented by binary number 0 or 1 and is divided, 0 represents the prohibited launching interval of the constrained heading angle, and 1 represents the interval of the allowed launching of the heading angle, N constraint heading angle values are set as the judgment threshold, the binary constraint heading angle in the interval form is taken as the heading angle input of the fire control calculation, the shift operation is performed from the rightmost bit to the left, and the logic operation is performed by performing the logic AND operation of the binary values corresponding to the intervals and 0x01, the cycle budget is performed according to the number of heading angle intervals, until all heading angle intervals are calculated, and the allowed launching range of the heading direction is calculated.

[0020] In the flight height constraint, one constraint flight height is set as the judgment threshold, each flight height interval is represented by binary number 0 or 1, the binary values of the constraint flight heights corresponding to the flight height intervals are determined when the flight height is constrained, the binary values of the constraint flight heights are subjected to the binary logic AND operation of 0x01, only when the result value is 0, the binary values of the constraint flight heights are shifted to the left, until the result is 1, the shift calculation is stopped, and the number of intervals with the calculated value of 0 is the number of constrained flight height intervals, so that the minimum flight height is calculated.

[0021] In the flight speed constraint, one constraint flight speed is set as the judgment threshold, each flight speed interval is represented by binary number 0 or 1, the binary values of the constraint flight speeds corresponding to the flight speed intervals are determined when the flight speed is constrained, the binary values of the constraint flight speeds are subjected to the binary logic AND operation of 0x01, only when the result value is 0, the binary values of the constraint flight speeds are shifted to the left, until the result is 1, the shift calculation is stopped, and the number of intervals with the calculated value of 0 is the number of constrained flight speed intervals, so that the minimum flight speed is calculated.

[0022] When the heading direction allowed launching amount is 1, the aerial guided weapon launching is allowed under the current heading angle constraint, and when the heading direction allowed launching amount is 0, the aerial guided weapon launching is not allowed under the current heading angle constraint.

[0023] A carrier platform multi-constraint fire control medium, the carrier platform multi-constraint fire control medium stores a fire control program, and the fire control program is executed by a processor to realize the steps of the above method.

[0024] Compared with the prior art, the present application has the following advantages:

[0025] The application provides a carrier platform multi-constraint fire control method based on shift matching, which is used for the specific use scene of air-to-ground infrared imaging type precision guided weapons, sets multiple constraint limits for the region of the launching direction angle, the weapon launching speed and the weapon launching height in the fire control algorithm, thereby solving the problem of the insufficient flexibility and effectiveness of the weapon system in use due to the flight speed, flight height and attack region range limits of the weapon on the fire control system, and achieving the multi-constraint fire control launching calculation in the complex combat environment, the use flexibility and effectiveness of the precision guided weapon system, and the performance of the weapon in use is greatly improved. BRIEF DESCRIPTION OF DRAWINGS

[0026] Figure 1 A carrier platform multi-constraint fire control method principle diagram is provided for the application.

[0027] Figure 2 A carrier platform multi-constraint fire control method flow chart is provided for the application.

[0028] Figure 3 A fire control algorithm heading angle constraint example schematic diagram is provided for the application. DETAILED DESCRIPTION

[0029] A carrier platform multi-constraint fire control method based on shift matching is provided, which is used for the specific use scene of air-to-ground infrared imaging type precision guided weapons, sets multiple constraint limits for the region of the launching direction angle, the weapon launching speed and the weapon launching height in the fire control algorithm, thereby achieving the fire control launching calculation under the multi-constraint condition, and the specific steps are as follows:

[0030] The current heading angle of the carrying platform is measured, and the real-time heading angle under the guided weapon mounting state is obtained according to the heading angle.

[0031] The current flight height of the carrying platform is measured, and the real-time flight height under the guided weapon mounting state is obtained according to the flight height.

[0032] The current flight speed of the carrying platform is measured, and the real-time flight speed under the guided weapon mounting state is obtained according to the flight speed.

[0033] The real-time heading angle, the real-time flight height and the real-time flight speed under the guided weapon mounting state are loaded into the constraint condition preset by the fire control system, and the constraint limits of the battlefield environment are converted into constraint input variables under the constraint condition.

[0034] The range of each constraint input variable is determined, the fire control system calculation under the constraint condition preset by the fire control system is carried out, and the fire control launching window parameters under the constraint condition are obtained.

[0035] The specific method for converting the real-time heading angle in the guided weapon mounting state into a constraint input variable is as follows:

[0036] The heading angle range in the guided weapon mounting state is determined, the heading angle range is segmented and constrained, and the number of intervals after the segmented constraint is determined according to the current heading angle;

[0037] The specific method for converting the real-time flight height in the guided weapon mounting state into a constraint input variable is as follows:

[0038] The flight height range in the guided weapon mounting state is determined, the flight height range is segmented and constrained, and the number of intervals after the segmented constraint is determined according to the current flight height;

[0039] The specific method for converting the real-time flight speed in the guided weapon mounting state into a constraint input variable is as follows:

[0040] The flight speed range in the guided weapon mounting state is determined, the flight speed range is segmented and constrained, and the number of intervals after the segmented constraint is determined according to the current flight speed.

[0041] The constraint conditions preset by the fire control system include heading angle constraint, flight height constraint, and flight speed constraint. In the case of simultaneously satisfying the heading angle constraint, the flight height constraint, and the flight speed constraint, the constrained heading angle, the constrained flight height, and the constrained flight speed are determined respectively, the heading direction allowed launch amount, the minimum flight height, and the minimum flight speed are calculated, and the fire control launch window parameters under the constraint conditions are calculated.

[0042] In the heading angle constraint, the heading range is divided into multiple intervals, each heading angle interval is represented by a binary number 0 or 1, wherein 0 represents a prohibited launch interval of the heading angle under constraint, and 1 represents an interval of the heading angle allowed to launch. One or more constrained heading intervals are set as a judgment threshold, and the corresponding binary constrained heading angle in the interval form is taken as the heading angle input for fire control calculation, and a shift and a logical operation are performed, wherein the shift operation is a successive shift from the rightmost low bit to the left, and the logical operation is a logical AND (&) operation of the binary value corresponding to the interval and 0x01. The heading direction allowed launch range is calculated by performing loop budget according to the number of heading angle intervals, until the entire heading angle interval calculation is completed. For example, Figure 3 as shown in the following table:

[0043] In the flight height constraint, a constraint flight height is set as a judgment threshold, each flight height interval is represented by binary number 0 or 1, the binary value of the constraint flight height corresponding to each flight height interval is determined when there is a flight height constraint, the binary value of the constraint flight height is subjected to a binary logical AND (&) operation with 0x01, only when the result value is 0, the binary value of the constraint flight height is shifted to the left, the number of bits of the shift is the number of the flight height intervals that are constrained, and the minimum flight height is calculated according to the binary value after the shift and the number of times of the shift;

[0044] In the flight speed constraint, a constraint flight speed is set as a judgment threshold, each flight speed interval is represented by binary number 0 or 1, the binary value of the constraint flight speed corresponding to each flight speed interval is determined when there is a flight speed constraint, the binary value of the constraint flight speed is subjected to a binary logical AND (&) operation with 0x01, only when the result value is 0, the binary value of the constraint flight speed is shifted to the left, the number of bits of the shift is the number of the flight speed intervals that are constrained, and the minimum flight speed is calculated according to the binary value after the shift and the number of times of the shift;

[0045] When the value of the allowed launch amount of the heading direction interval is 1, the aerial guided weapon is allowed to be launched under the constraint of the current heading angle interval, and when the value of the allowed launch amount of the heading direction is 0, the aerial guided weapon is not allowed to be launched under the constraint of the current heading angle.

[0046] When the binary value of the constraint flight height corresponding to each flight height interval and the binary value of the constraint flight speed corresponding to each flight speed interval are subjected to a logical AND (&) operation with 0x01 in the order from right to left and from low bit to high bit, when the result value is 0, the input binary value of the flight height interval is continuously shifted to the left for the next logical AND operation, and the shift is stopped when the result is 1, the number of bits of the shift is the number of intervals with the value 0, which is the number of the intervals that are constrained, so that the minimum flight speed and flight height constrained by the fire control system are obtained.

[0047] The following is further described according to a specific embodiment:

[0048] In the current embodiment, the guided weapon is mounted on the carrier platform, the heading angle φ, flight speed v, flight height h and other information are obtained, and the constraint conditions involved in the specific task scene are combined to convert the constraint limitation of the battlefield environment into constraint input variables under the constraint conditions, and the specific process is as follows:

[0049] The current heading angle φ1 of the carrier platform is measured by the inertial device of the carrier platform, the heading information φ1 of the aerial guided weapon when it is mounted on the carrier platform is obtained according to the heading angle of the carrier platform, and the flight height h1 of the aerial guided weapon and the flight speed v1 of the aerial guided weapon are also obtained.

[0050] Based on the real-time flight heading angle φ1, flight height h1 and flight speed information v1 in the aviation guided weapon mounting, the real-time flight data is loaded, and the actual battlefield environment multiple constraint limits are converted into the design input variables of the fire control algorithm combined with the constraint conditions;

[0051] According to the range of each constraint quantity, the shift matching algorithm is adopted, the fire control calculation under multiple constraint conditions is carried out through shift operation and logical matching, the parameters under multiple constraint conditions are obtained, and the fire control delivery window is displayed.

[0052] As shown in Figure 1 , in the embodiment, it is assumed that the current (specific point) flight state aircraft flight data is: flight heading angle φ = 1.2°, flight height: h = 7500m, flight speed: v = 230m / s;

[0053] The specific constraint conditions in the embodiment are:

[0054] (1) Weapon heading direction delivery range: [0°, 40°], [60°, 120°], [140°, 220°], [240°, 340°];

[0055] (2) Weapon delivery height: h > 6000m;

[0056] (3) Weapon delivery speed: v > 200m / s.

[0057] The flow of the multiple constraint fire control algorithm is shown in Figure 2 , which specifically includes the following steps:

[0058] Step one: after the fire control system starts to work, the current heading angle φ2 = 1.2° of the mounted platform is measured by the inertial device of the mounted aircraft platform, and the heading angle information φ2 = 1.2° of the aviation guided weapon mounting is obtained according to the heading angle of the mounted aircraft platform;

[0059] Step two: the current flight height h2 = 7500m of the mounted platform is measured by the inertial device of the mounted aircraft platform, and the flight height h2 = 7500m of the aviation guided weapon mounting is obtained according to the flight height of the mounted aircraft platform;

[0060] Step three: the current flight speed v2 = 230m / s of the mounted platform is measured by the inertial device of the mounted aircraft platform, and the flight speed v2 = 230m / s of the aviation guided weapon mounting is obtained according to the flight speed of the mounted aircraft platform;

[0061] Step four: based on the real-time flight heading angle φ2, flight height h2 and flight speed information v2 obtained in the preceding steps, load the real-time flight data, and perform data processing, wherein the release heading angle is divided into 18 intervals with an average interval of 20°, i.e., interval 1: [0°, 20°), interval 2: [20°, 40°), …, and interval 18: [340°, 360°]. According to the release heading angle constraint condition 1, the corresponding intervals 3: [40°, 60°), 7: [120°, 140°), 12: [220°, 240°) and 17: [320°, 340°) are non-release areas, and the corresponding heading angle constraint input value in the fire control system is: 0b101111011110111011. The flight height range is divided into 8 intervals with an average interval of 1000 meters, i.e., interval 1: [4000, 5000), interval 2: [5000, 6000), …, and interval 8: [11000, 12000]. According to the constraint condition 2, the release height constraint corresponds to interval 2, i.e., below 6000 meters is a non-release area for weapons, and the release height constraint input value in the fire control system is: 0b11111100. The flight speed range is divided into 8 intervals with an average interval of 20 meters / second, i.e., interval 1: [140, 160), interval 2: [160, 180), …, and interval 8: [280, 300]. According to the constraint condition 3, it corresponds to interval 3, and the release speed constraint input value in the fire control system is: 0b11111000.

[0062] Step five: according to the specific range of each constraint designed in step four, a shift matching algorithm is used to perform fire control calculation under multiple constraint conditions through shift operation and logical matching, and a fire control release window under multiple constraint conditions is obtained. In the shift matching operation in the fire control algorithm, the matching logic operation is performed in sequence from left to right with 0x01, wherein the calculation result of the corresponding positions of the 3rd, 7th, 12th and 17th intervals is 0, which represents that the release is not allowed in this area of the heading direction, and the corresponding calculation result of the other intervals is 1, which represents that the release is allowed in these areas of the heading direction. Similarly, the shift matching operation of the flight height and the flight speed is the same as the operation process of the heading direction, and the actual simulation effect of the multiple constraint embodiments in the fire control algorithm of the present application is obtained. In the fire control system, the multiple constraint fire control algorithm proposed in the present application is used, the green area in the simulation is the release area allowed by the fire control calculation, and the weapon can be released and attacked; the red area is a restricted area, and the weapon cannot be released and attacked.

[0063] Although the present application has been disclosed with reference to the preferred embodiments, it is not intended to limit the present application to the preferred embodiments. Any person skilled in the art, without departing from the spirit and scope of the present application, can make possible changes and modifications to the technical solutions of the present application by using the disclosed methods and technical contents. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application, without departing from the technical solutions of the present application, shall fall within the protection scope of the technical solutions of the present application.

[0064] The contents not described in detail in the specification of the present application are the known technologies of the person skilled in the art.

Claims

1. A shift-matching based multi-constraint fire control method for a carrier platform, characterized in that The method comprises the following steps: measuring the current heading angle of the carrying platform, and obtaining the real-time heading angle of the carrying platform in the state of mounting the guided weapon according to the heading angle; measuring the current flight height of the carrying platform, and obtaining the real-time flight height of the carrying platform in the state of mounting the guided weapon according to the flight height; measuring the current flight speed of the carrying platform, and obtaining the real-time flight speed of the carrying platform in the state of mounting the guided weapon according to the flight speed; loading the real-time heading angle, the real-time flight height and the real-time flight speed of the carrying platform in the state of mounting the guided weapon into the preset constraint condition of the fire control system, and converting the constraint limitation of the battlefield environment into constraint input variables under the constraint condition; determining the range of each constraint input variable, and performing fire control system calculation under the preset constraint condition of the fire control system by using a shift matching algorithm to obtain the fire control release window parameters under the constraint condition; the preset constraint condition of the fire control system comprises a heading angle constraint, a flight height constraint and a flight speed constraint, and the constraint heading angle, the constraint flight height and the constraint flight speed are determined respectively under the condition that the heading angle constraint, the flight height constraint and the flight speed constraint are all satisfied, and the heading direction allowed release amount, the minimum flight height and the minimum flight speed are calculated as the fire control release window parameters under the constraint condition; the step of converting the constraint limitation of the battlefield environment into constraint input variables under the constraint condition specifically comprises: determining the range of the heading angle in the state of mounting the guided weapon, segmenting the range of the heading angle, and determining the number of intervals after segmentation according to the current heading angle; determining the range of the flight height in the state of mounting the guided weapon, segmenting the range of the flight height, and determining the number of intervals after segmentation according to the current flight height; determining the range of the flight speed in the state of mounting the guided weapon, segmenting the range of the flight speed, and determining the number of intervals after segmentation according to the current flight speed; each interval is represented by a binary number 0 or 1.

2. The multi-constraint fire control method for a carrying platform based on shift matching according to claim 1, wherein: in the heading angle constraint, the intervals of the heading angle are represented by binary numbers 0 or 1 and are divided, 0 represents a prohibited release interval of the heading angle under constraint, and 1 represents an interval allowed to release under the heading angle, N constraint heading angle values are set as judgment thresholds, the binary constraint heading angle in the form of intervals is taken as the heading angle input of the fire control calculation, and shift and logic operations are performed, wherein the shift operation is a shift from the rightmost low bit to the left, and the logic operation is a logic "and" operation of the binary values corresponding to the intervals and 0x01, and the operation is circularly operated according to the number of intervals of the heading angle until all the intervals of the heading angle are calculated.

3. The multi-constraint fire control method for a carrying platform based on shift matching according to claim 2, wherein: In the flight height constraint, a constraint flight height is set as a judgment threshold, each flight height interval is represented by binary number 0 or 1, binary values of the constraint flight height corresponding to each flight height interval are determined when there is a flight height constraint, the binary values of the constraint flight height are subjected to binary logical AND operation with 0x01, only when the result value is 0, the binary values of the constraint flight height are shifted to the left until the result is 1, and the shift number is the interval number of the calculated value 0, which is the number of the constrained flight height intervals, thereby the minimum flight height is calculated.

4. The multi-constraint fire control method based on shift matching of a carrier platform according to claim 3, characterized in that: In the flight speed constraint, a constraint flight speed is set as a judgment threshold, each flight speed interval is represented by binary number 0 or 1, binary values of the constraint flight speed corresponding to each flight speed interval are determined when there is a flight speed constraint, the binary values of the constraint flight speed are subjected to binary logical AND operation with 0x01, only when the result value is 0, the binary values of the constraint flight speed are shifted to the left until the result is 1, and the shift number is the interval number of the calculated value 0, which is the number of the constrained flight speed intervals, thereby the minimum flight speed is calculated.

5. The multi-constraint fire control method based on shift matching of a carrier platform according to claim 4, characterized in that: When the allowed launch amount in the heading direction is 1, the aerial guided weapon is allowed to be launched under the constraint of the current heading angle, and when the allowed launch amount in the heading direction is 0, the aerial guided weapon is not allowed to be launched under the constraint of the current heading angle.

6. A platform multi-constrained fire control medium having stored therein a fire control program, the platform multi-constrained fire control medium comprising: The fire control program is executed by the processor to realize the steps of the method according to any one of claims 1 to 5.

Images