CN111324964A - Method for rapidly evaluating hit rate of missile on targets with different characteristics - Google Patents
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Abstract
The invention discloses a method for quickly evaluating the hit rate of a missile on targets with different characteristics, which comprises the following steps: s1, establishing a missile trajectory model according to the initial missile launching random deviation, the missile engine thrust eccentric random deviation, the missile body mass uneven random deviation, the trajectory wind deviation, the missile manufacturing and mounting errors and the atmospheric environment random deviation; s2, the guided missile carries out simulation movement, and the space position of the guided missile relative to the target is calculated in real time according to the trajectory detector of the guided missile; s3, judging whether the missile warhead acts or not by the missile control system based on the space position relative to the target, if so, entering S4, and otherwise, repeatedly executing S2; s4, calculating damage characteristics of the warhead of the missile at the current spatial position of the missile; s5, analyzing and calculating the damage condition of the target according to the damage characteristic and the target vulnerability of the missile warhead; and S6, obtaining the missile hit rate according to the target damage condition.
Description
Technical Field
The invention relates to the technical field of military aerospace simulation, in particular to a method for quickly evaluating hit rates of missiles on targets with different characteristics.
Background
One of the most important indicators for measuring missile systems is the probability of a missile destroying a target. The general algorithm considers the missile shooting precision, and mainly considers various random deviations such as missile mass deviation, geometric dimension deviation, initial speed firing angle deviation, wind interference deviation, engine thrust impulse deviation and the like according to an ideal motion equation of the missile. A deviation-based ballistic model of various missiles is established, modeling and sampling statistics are carried out on related parameters, simulation is carried out on the basis of a Monte Carlo algorithm, and results are analyzed. However, the analysis is only performed on the trajectory model of the missile, that is, the probability that the trajectory meets the target in space, and the probability that the missile actually damages the target also needs to consider factors such as the damage characteristic of a warhead, the motion characteristic of the target, and the damage characteristic of the target, so that the single consideration of the trajectory characteristic of the missile is inaccurate.
Generally, for missile hit rate analysis, uncertainty is mainly considered through a missile trajectory model, data such as warhead characteristics and target characteristics are also lacked for probability analysis of a real missile destruction target, the probability of the missile destruction target is an important index for measuring the quality of a missile system and is also a final measurement index for optimizing the missile system by an engineer, and the engineer can be quickly and accurately guided to design the missile system by quickly obtaining the damage characteristics of the missile to the target.
Disclosure of Invention
Aiming at the problems and the defects in the prior art, the invention provides a method for rapidly evaluating the hit rate of a missile on targets with different characteristics.
The invention solves the technical problems through the following technical scheme:
the invention provides a method for rapidly evaluating the hit rate of a missile on targets with different characteristics, which is characterized by comprising the following steps of:
s1, establishing a missile trajectory model according to the initial missile launching random deviation, the missile engine thrust eccentric random deviation, the missile body mass uneven random deviation, the trajectory wind deviation, the missile manufacturing and mounting errors and the atmospheric environment random deviation;
s2, the guided missile carries out simulation movement, and the space position deviation of the guided missile relative to the target are calculated in real time according to the trajectory detector of the guided missile;
s3, judging whether the missile warhead acts or not by the missile control system based on the space position relative to the target, if so, entering a step S4, and otherwise, repeatedly executing the step S2;
s4, calculating damage characteristics of the warhead of the missile at the current spatial position of the missile;
s5, analyzing and calculating the damage condition of the target according to the damage characteristic and the target vulnerability of the missile warhead;
and S6, obtaining the missile hit rate according to the target damage condition.
Preferably, the projectile warhead damage characteristics include fragment damage characteristics, shock wave damage characteristics and other damage characteristics;
the damage characteristic probability of the missile to the target is as follows:
wherein i is a variety of damage characteristics, PsThe probability of various damage characteristics.
Preferably, the probability of the damage characteristic of the shock wave is as follows:
in the formula, delta P is the overpressure of the shock wave; delta Pinf、ΔPsupThe lower limit and the upper limit of the target difference and overpressure range of the warhead shock wave damage are respectively set, and different target characteristics are provided according to different targets;
the probability of fragment damage characteristics is as follows:
in the formula, ErThe specific kinetic energy of the fragment, E is the lowest specific kinetic energy to puncture the target armor.
On the basis of the common knowledge in the field, the above preferred conditions can be combined randomly to obtain the preferred embodiments of the invention.
The positive progress effects of the invention are as follows:
the invention introduces the missile trajectory characteristic, the warhead characteristic and the target characteristic into a missile hit rate analysis system, thereby solving the following problems:
(1) the missile hit rate quick evaluation method can quickly obtain the hit rates of different warheads to different targets, so that the trajectory efficiency is systematically evaluated, the method for theoretically predicting the missile hit rate is realized, and the design of a missile system is guided.
(2) The missile hit rate is estimated in the early stage, so that the test cost can be greatly saved, and some inconvenient tests or tests which cannot be carried out can be estimated.
(3) The damage characteristic of the warhead is obtained by means of simulation, test and theoretical calculation, and the warhead is optimized based on the missile hit rate.
(4) The target vulnerability can be obtained by means of simulation, test and theoretical calculation, and the battle bucket can be optimized based on the missile hit rate and the target vulnerability.
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FIG. 1 is a flow chart of a method for rapidly evaluating the hit rate of a missile on targets with different characteristics according to a preferred embodiment of the invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
As shown in fig. 1, the present embodiment provides a method for quickly evaluating hit rates of different targets by a missile, which includes the following steps:
and S1, establishing a missile trajectory model according to the initial missile launching random deviation, the missile engine thrust eccentricity random deviation, the missile body mass unevenness random deviation, the trajectory wind deviation, the missile manufacturing and mounting errors and the atmospheric environment random deviation.
And S2, simulating the missile, and calculating the space position of the missile relative to the target and the space position deviation in real time according to the trajectory detector of the missile.
S3, the missile control system judges whether the missile warhead acts based on the space position relative to the target, if so, the step S4 is carried out, and if not, the step S2 is repeatedly carried out.
And S4, calculating the damage characteristic of the warhead of the missile at the current spatial position of the missile.
Wherein the damage characteristics of the missile warhead include fragment damage characteristics, shock wave damage characteristics and other damage characteristics;
the damage characteristic probability of the missile to the target is as follows:
wherein i is a variety of damage characteristics, PsThe probability of various damage characteristics.
The probability of the damage characteristic of the shock wave is as follows:
in the formula, delta P is the overpressure of the shock wave; delta Pinf、ΔPsupThe lower limit and the upper limit of the target difference and overpressure range of the warhead shock wave damage are respectively set, and different target characteristics are provided according to different targets;
the probability of fragment damage characteristics is as follows:
in the formula, ErThe specific kinetic energy of the fragment, E is the lowest specific kinetic energy to puncture the target armor.
The damage probability calculation formula of the multiple missiles:
in the formula, WiThe damage probability of the ith missile to the target is shown, and n represents the number of launched missiles.
And S5, analyzing and calculating the damage condition of the target according to the damage characteristic and the target vulnerability of the missile warhead.
And S6, obtaining the missile hit rate according to the target damage condition.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.
Claims (3)
1. A method for rapidly evaluating the hit rate of a missile on targets with different characteristics is characterized by comprising the following steps:
s1, establishing a missile trajectory model according to the initial missile launching random deviation, the missile engine thrust eccentric random deviation, the missile body mass uneven random deviation, the trajectory wind deviation, the missile manufacturing and mounting errors and the atmospheric environment random deviation;
s2, the guided missile carries out simulation movement, and the space position deviation of the guided missile relative to the target are calculated in real time according to the trajectory detector of the guided missile;
s3, judging whether the missile warhead acts or not by the missile control system based on the space position relative to the target, if so, entering a step S4, and otherwise, repeatedly executing the step S2;
s4, calculating damage characteristics of the warhead of the missile at the current spatial position of the missile;
s5, analyzing and calculating the damage condition of the target according to the damage characteristic and the target vulnerability of the missile warhead;
and S6, obtaining the missile hit rate according to the target damage condition.
2. The method for rapidly evaluating the hit rate of a missile on targets with different characteristics as claimed in claim 1, wherein the damage characteristics of the missile warhead comprise fragmentation damage characteristics, shock wave damage characteristics and other damage characteristics;
the damage characteristic probability of the missile to the target is as follows:
wherein i is a variety of damage characteristics, PsThe probability of various damage characteristics.
3. The method for rapidly evaluating the hit rate of the missile on the targets with different characteristics according to claim 2, wherein the probability of damage characteristics of the shock wave is as follows:
in the formula, delta P is the overpressure of the shock wave; delta Pinf/ΔPsupThe lower limit and the upper limit of the target difference and overpressure range of the warhead shock wave damage are respectively set, and different target characteristics are provided according to different targets;
the probability of fragment damage characteristics is as follows:
in the formula, ErThe specific kinetic energy of the fragment, E is the lowest specific kinetic energy to puncture the target armor.
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Cited By (1)
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| CN112784437A (en) * | 2021-02-04 | 2021-05-11 | 中国人民解放军63863部队 | System for evaluating damage efficiency of air-defense missile to helicopter target |
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| CN105910495A (en) * | 2016-05-09 | 2016-08-31 | 哈尔滨工业大学 | Missile weapon system design method aiming at efficiency on basis of performance indexes |
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| CN112784437A (en) * | 2021-02-04 | 2021-05-11 | 中国人民解放军63863部队 | System for evaluating damage efficiency of air-defense missile to helicopter target |
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Application publication date: 20200623 |