CN116663239B - Missile escape area attack distance calculation method based on golden section method - Google Patents
Missile escape area attack distance calculation method based on golden section method Download PDFInfo
- Publication number
- CN116663239B CN116663239B CN202310446601.4A CN202310446601A CN116663239B CN 116663239 B CN116663239 B CN 116663239B CN 202310446601 A CN202310446601 A CN 202310446601A CN 116663239 B CN116663239 B CN 116663239B
- Authority
- CN
- China
- Prior art keywords
- missile
- aircraft
- maximum
- calculating
- angle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 58
- 238000004364 calculation method Methods 0.000 title claims abstract description 31
- 230000008859 change Effects 0.000 claims abstract description 66
- 239000000446 fuel Substances 0.000 claims abstract description 15
- 238000004088 simulation Methods 0.000 claims abstract description 6
- 230000009471 action Effects 0.000 claims abstract description 4
- 230000009194 climbing Effects 0.000 claims description 23
- 230000008569 process Effects 0.000 claims description 6
- 230000001133 acceleration Effects 0.000 claims description 3
- 239000000295 fuel oil Substances 0.000 claims description 2
- 230000014509 gene expression Effects 0.000 claims description 2
- 238000004422 calculation algorithm Methods 0.000 description 4
- 238000013459 approach Methods 0.000 description 3
- 238000013528 artificial neural network Methods 0.000 description 3
- 238000013135 deep learning Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses a missile escape area attack distance calculation method based on a golden section method, which comprises the following steps of: s1, establishing a state model of a missile and an aircraft; s2, updating the states of the missile and the aircraft; s3, setting a missile tracking guidance law; s4, updating the state quantity at the moment of missile launching; s5, calculating the maximum fuel consumption of the missile and the maximum change rate of each state quantity of the missile; s6, updating the flight state of the missile and the aircraft under the action of tracking guidance law, and tracking the aircraft by the missile; s7, performing real-time approximate calculation on the attack distance parameter of the non-escapable area of the missile by using a golden ratio searching method, and realizing online simulation calculation on the attack distance parameter of the missile. The method considers attack distance parameter calculation under the flight performance of the missile and the target aircraft, has certain universality and can be suitable for missiles and target aircraft of different models. Therefore, the method is suitable for popularization and application.
Description
Technical Field
The invention belongs to the technical field of guidance, and particularly relates to a missile escape area attack distance calculation method based on a golden section method.
Background
With the development of airborne missile weapons, the attack performance of missiles has a greater and greater influence on the wins and losses of modern short-distance air combat and medium-distance air combat. In the actual air combat process of the aircraft, the attack range of the airborne missile can change in real time along with the air combat situation, and is particularly related to time-varying states of the flying speed, the altitude, the azimuth angle, the entering angle and the like of the two aircrafts, so that the maneuvering decision method of the aircraft air combat with better decision effect must consider the time-varying characteristics of the missile attack area. The air-to-air missile non-escapable area refers to an area where the enemy plane cannot escape from missile attack no matter what mode is adopted for maneuvering after the missile is launched by the plane, and has important significance in air combat practice. The judgment condition of the success or failure of the air combat is that one aircraft is in the missile attack area of other aircraft, so that the real-time calculation of the parameters of the missile attack area, especially the non-escapable area of the missile, is a key point for analyzing the missile attack performance, and is a basis for designing the maneuvering decision method of the air combat of the aircraft.
The existing missile attack area calculation method can be roughly divided into a polynomial fitting method, a neural network, golden section searching, deep learning and other methods. The missile attack area calculation method based on polynomial fitting, neural network and deep learning is limited by missile attack area offline data, has better instantaneity but poorer applicability, and needs to be retrained when the types of the enemy aircraft and the my aircraft missile change. The existing missile attack area calculation method based on golden section search is more researched in a two-dimensional attack area, the target motion type is simpler, and escape maneuver which can be actually adopted by a target aircraft cannot be considered.
Disclosure of Invention
The invention aims to provide a missile escape area attack distance calculation method based on a golden section method, which mainly solves the problems that the existing calculation method is poor in universality, cannot be suitable for the situation that an enemy plane adopts escape maneuver, is poor in instantaneity and the like.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows:
a missile escape area attack distance calculation method based on a golden section method comprises the following steps:
s1, establishing a state model of a missile and an aircraft;
s2, establishing a three-degree-of-freedom guidance model of the missile and the aircraft, and updating the states of the missile and the aircraft;
s3, setting a missile tracking guidance law which shortens the missile climbing angle, the track angle and the speed change rate of the missile;
s4, updating the state quantity at the moment under the missile according to the missile tracking guidance law, the change rate of each state of the missile and the set state updating step length of the current state of the missile;
s5, calculating the maximum fuel consumption of the missile and the maximum change rate of each state quantity of the missile according to the missile tracking guidance law;
s6, updating the flight state of the missile and the aircraft under the action of tracking guidance law, and tracking the aircraft by the missile;
s7, based on the missile tracking guidance law, real-time approximate calculation is carried out on the missile attack distance parameter of the non-escapable area of the missile by utilizing a golden ratio searching method, so that the missile attack distance parameter is simulated and calculated on line.
Further, in the step S1, the state expression of the missile and the aircraft is:
wherein, subscript M represents missile, subscript E represents escaped aircraft, V represents speed, χ represents track angle, γ represents climb angle, and (x, y, h) represents position coordinates.
Further, in step S2, the update mode of the three-degree-of-freedom guidance model for the states of the missile and the aircraft is as follows:
wherein,indicating the rate of change of speed>Indicating the track angle change rate,/, for>Represents the rate of change of the climbing angle,/-)>Represents the abscissa position change rate,/>Representing the rate of change of the ordinate position,>represents the change rate of the vertical coordinate position, n x For tangential overload control, n y For lateral overload control, n z G is the normal overload control quantity and g is the gravitational acceleration.
Further, in step S3, the missile tracking control rate setting process is as follows:
s31, calculating a position difference vector d of the missile and the aircraft according to the current states of the aircraft and the missile M ：
d M ＝[x E -x M ，y E -y M ，h E -h M ] T (3)；
S32, calculating an included angle χ between the position difference vector and the horizontal plane d Included angle gamma with vertical plane d The method comprises the following steps:
s33, passing the track angle change rate of the missile at the current momentAnd climbing angle change rate->The track angle and the climbing angle at the next moment are close to the included angle χ of the horizontal plane of the position difference vector at the current moment d Included angle gamma with vertical plane d And (3) making:
in the method, in the process of the invention,the maximum positive and negative change rate of the yaw angle and the maximum positive and negative change rate of the climbing angle of the missile are related to the available overload of the missile, and delta t is the step length of updating the states of the missile and the aircraft;
s34, assuming that the missile accelerates to the maximum speed after launching, namely the change rate of the current moment of the missile speedThe method meets the following conditions:
further, in step S5, the maximum fuel consumption of the missile is calculated by:
calculating the fuel quantity consumed by the missile after the current maneuver, namely:
wherein m, ρ, s, C D The missile mass, the air density, the missile cross-sectional area and the missile air resistance coefficient are respectively; the maximum fuel consumption of the missile is as follows:
i.e. if the missile keeps the maximum speed of inorganization to fly flat, the maximum fuel consumption can ensure that the missile at t max Continuous flight over time.
Further, in step S5, calculating the maximum rate of change of each state quantity of the missile includes:
calculating the maximum positive and negative change rate of the missile track angle:
wherein n is zmax For maximum normal overload control quantity, n zmin Is the maximum value of normal overload control quantity;
calculating the maximum positive and negative change rate of the missile climbing angle:
wherein n is ymax For maximum lateral overload control, n ymin Is the maximum value of the lateral overload control quantity;
calculating the maximum rate of change of the missile speed:
wherein n is xmax Is the maximum value of the lateral overload control quantity.
Further, in step S6, when the missile tracks the aircraft, whether the missile hits the aircraft is determined by the following conditions: before the fuel oil quantity is exhausted, the distance D between the missile and the target at a certain moment is less than or equal to e, and e is the allowable off-target quantity of the missile.
Further, in step S7, the step of performing real-time approximate calculation on the attack distance parameter of the non-escapable region of the missile by the golden ratio search method includes:
s71: firstly, taking a target aircraft as a center, determining an initial interval guess [ a ] of the maximum attack distance of a missile nonsuperimposable area 0 ，b 0 ]；
S72: calculation of golden section Point R g ＝a 0 +0.618(b 0 -a 0 )；
S73: performing hit judgment on the dividing points, and judging whether the missile hits the target according to the miss distance and the ballistic simulation ending limiting condition; if hit the target, let a i ＝R g ，b i ＝b i-1 The method comprises the steps of carrying out a first treatment on the surface of the No make a i ＝a i-1 ，b i ＝R g The method comprises the steps of carrying out a first treatment on the surface of the Re-cycling the calculation until |a is satisfied i -b i I is less than the boundary of the set point.
Compared with the prior art, the invention has the following beneficial effects:
the three-degree-of-freedom guidance model based on the missile and the aircraft considers attack distance parameter calculation under the flight performance of the missile and the target aircraft, has certain universality and can be suitable for different types of missiles and target aircraft; based on the designed missile tracking guidance law and the designed aircraft escape guidance law, the golden section search can be utilized to simulate and calculate the missile attack distance parameters on line. The method and the device realize the rapid calculation of the attack distance of missiles with different flight performances to the non-escapable areas of the target aircrafts with different performances in real time under the air combat dynamic environment.
Drawings
FIG. 1 is a schematic flow chart of the method of the present invention.
FIG. 2 is a diagram of a missile and aircraft trajectory following and escaping guidance laws in accordance with an embodiment of the present invention.
Fig. 3 is a graph of a variation trend of a maximum attack distance of a missile non-escapable region in the embodiment of the present invention.
Detailed Description
The invention will be further illustrated by the following description and examples, which include but are not limited to the following examples.
Examples
As shown in FIG. 1, the method for calculating the attack distance of the non-escapable region of the missile based on the golden section method disclosed by the invention is characterized in that the maximum attack distance of the attack region of the missile is actually related to the state of the aircraft on the my side, the state of the aircraft on the enemy side (such as the altitude difference of the two aircraft, the speed, the azimuth angle, the entry angle and the like), the performance parameters of the missile on the air-air side (such as the maneuvering overload capacity, the maximum Mach number of flight and the upper limit of the flight time and the like), therefore, the maximum attack distance D of the non-escapable region of the missile is established on the assumption that the performance parameters of the missile on the me side and the flight performance parameters of the enemy side are known MKmax And calculating the maximum attack distance of the missile in the current double-machine state in real time according to the change rule of the double-machine state.
Firstly, a state model of a missile and an aircraft is established, which are respectively expressed as:
wherein, subscript M represents missile, subscript E represents escaped aircraft, V represents speed, χ represents track angle, γ represents climb angle, and (x, y, h) represents position coordinates.
The states of the missiles and the aircrafts are updated by the following three-degree-of-freedom guidance models of the missiles and the aircrafts.
Wherein,indicating the rate of change of speed>Indicating the track angle change rate,/, for>Represents the rate of change of the climbing angle,/-)>Represents the abscissa position change rate,/>Representing the rate of change of the ordinate position,>represents the change rate of the vertical coordinate position, n x For tangential overload control, n y For lateral overload control, n z G is the normal overload control quantity and g is the gravitational acceleration.
In order to realize the tracking of the missile on the target aircraft, a missile guidance law which can shorten the missile climbing angle, the track angle and the speed change rate of the missile from the aircraft is designed, namely, three overload control amounts can be reversely calculated according to the formula of the climbing angle, the yaw angle and the speed change rate in the formula (2); in an actual simulation program, taking a missile as an example, six states of the missile and six states of an enemy plane are input, so that the change rates of the climbing angle, the yaw angle and the speed at the moment under the missile can be obtained, and the corresponding overload instruction is obtained. Calculating a position difference vector d of the missile and the aircraft according to the current states of the aircraft and the missile M ：
d M ＝[x E -x M ，y E -y M ，h E -h M ] T (3)；
Then calculating the included angle χ between the position difference vector and the horizontal plane d Included angle gamma with vertical plane d The method comprises the following steps:
in order to enable the missile to approach the distance between the missile and the enemy escaping aircraft at the next moment, the track angle change rate of the missile at the current momentAnd climbing angle change rate->The track angle and the climbing angle at the next moment are close to the included angle χ of the horizontal plane of the position difference vector at the current moment d Included angle gamma with vertical plane d And (3) making:
in the method, in the process of the invention,the maximum positive and negative change rate of the yaw angle and the maximum positive and negative change rate of the climbing angle of the missile are related to the available overload of the missile, and delta t is the step length of the state update of the missile and the aircraft. The missile can fly towards the enemy aircraft at the moment through the method, so that the enemy aircraft can be tracked. Assuming that the missile accelerates after launching up to maximum speed, i.e. the rate of change of the current moment of the missile speed +.>The method meets the following conditions:
the tracking guidance law of the missile is determined, and the state quantity at the moment under the missile can be updated according to the calculated change rates and the current state of the missile and the set state updating step length. According to the current track angle, the climbing angle, the maximum angle change rate and the position vector connecting line with the target machine of the missile, the missile can approach the target.
After giving the tracking guidance law of the missile, the fuel quantity consumed by the missile after the current maneuver can be calculated, namely:
wherein m, ρ, s, C D The missile mass, the air density, the missile cross-sectional area and the missile air resistance coefficient are respectively; the maximum fuel consumption of the missile is as follows:
i.e. if the missile keeps the maximum speed of inorganization to fly flat, the maximum fuel consumption can ensure that the missile at t max Continuous flight over time.
After the missile tracking guidance law is designed, the tangential overload control quantity n of the missile can be obtained according to the missile driving capability and the accelerating capability xM Lateral overload control quantity n of missile yM Normal overload control quantity n of missile zM The maximum positive and negative change rates of the missile track angle are respectively calculated as follows:
wherein n is zmax For maximum normal overload control quantity, n zmin Is the maximum value of normal overload control quantity;
calculating the maximum positive and negative change rate of the missile climbing angle:
wherein n is ymax For maximum lateral overload control, n ymin Is the maximum value of the lateral overload control quantity;
calculating the maximum rate of change of the missile speed:
wherein n is xmax Is the maximum value of the lateral overload control quantity.
The target aircraft has an escape guidance law similar to the missile tracking guidance law, and is different from the missile tracking guidance law in that the change rate of the track angle of the aircraft at the current moment of the aircraft is changed in order to pull the aircraft away from the missile at the next momentAnd climbing angle change rate->The included angle χ of the horizontal plane of the position difference vector of the next moment of the aircraft track angle and the climb angle away from the current moment d Included angle gamma with vertical plane d The aircraft track angle, climb angle, and speed maximum rate of change calculations are similar to missile-related calculations.
The missile and the aircraft update the flight state under the action of tracking guidance law and escaping guidance law, the missile tracks the aircraft, the aircraft escapes in a maneuvering way, and the guided missile and the aircraft escape at the maximum speed after steering and tail placement. Whether the missile hits the aircraft or not is judged by the following conditions: before the fuel quantity is exhausted (representing that the maximum controllable time of the missile is exceeded), the distance Dve between the missile and the target at a certain moment exists, and e is the allowable off-target quantity of the missile.
And finally, based on the missile guidance law and the aircraft escape guidance law, performing real-time approximate calculation on the attack distance parameters of the non-escapable areas of the missiles by using a golden ratio searching method.Firstly, taking a target aircraft as a center, determining an initial interval guess [ a ] of the maximum attack distance of a missile nonsuperimposable area 0 ，b 0 ]Calculating golden section point R g ＝a 0 +0.618(b 0 -a 0 ) The method comprises the steps of carrying out a first treatment on the surface of the Then hit judgment is carried out at the dividing point position, and whether the missile hits the target or not is judged according to the miss distance and the ballistic simulation ending limiting condition, so that the target is marked as a i ＝R g ，b i ＝b i-1 The method comprises the steps of carrying out a first treatment on the surface of the No make a i ＝a i-1 ，b i ＝R g The method comprises the steps of carrying out a first treatment on the surface of the Re-cycling the calculation until |a is satisfied i -b i I is less than the boundary epsilon of the set point.
Compared with a missile attack area distance parameter calculation method based on polynomial fitting, a neural network and deep learning, the three-degree-of-freedom guidance model based on the missiles and the aircrafts takes into consideration attack distance parameter calculation under the flight performances of the missiles and the target aircrafts, has certain universality and can be suitable for missiles and target aircrafts of different models; based on the designed missile tracking guidance law and the designed aircraft escape guidance law, the golden section search can be utilized to simulate and calculate the missile attack distance parameters on line.
Taking AIM-120 missiles used by F16 fighter as an example, the missile performance parameters are shown in Table 1. The simulation environment is Matlab2019a.
TABLE 1 missile performance parameters
The performance parameters of the target aircraft are: maximum speed 200m/s, maximum tangential overload 1, maximum lateral overload and maximum normal overload of + -3 and maximum climb angle of 60 deg..
In order to verify the missile tracking guidance law and the aircraft escape guidance law, the state of the missile when being launched and the initial state of the target aircraft are set as follows:
x M ＝[300,0,0,3000,1000,3000] T ，x E ＝[300,60,0,1000,13500,4000] T
as can be seen from the flight path diagram 2 of the missile and the target aircraft, the moment of the my missile under the pursuit guidance law approaches the target aircraft, the target aircraft under the escape guidance law escapes after turning and tail placement, and the attack condition is achieved after the missile off-target quantity is achieved along with the gradual reduction of the distance between the missile and the target aircraft.
In order to verify a missile non-escaped area attack distance real-time calculation algorithm based on the golden section search method, the change trend of the missile non-escaped area attack distance under different relative heights, different relative speeds and different entry angles of the missile and the target aircraft is solved, as shown in fig. 3. Therefore, when the missile is launched, the greater the altitude, the greater the speed and the better the entering angle of the missile relative to the target aircraft, the greater the maximum attack distance of the non-escapable area of the missile is also increased, the attack distance change caused by the altitude advantage is more obvious, the actual characteristic of the missile attack area distance change is met, and the effectiveness of the algorithm is verified. In addition, the solving time of the algorithm in the Matlab simulation environment is not more than 0.026s at maximum, and the algorithm real-time performance is good.
The above embodiment is only one of the preferred embodiments of the present invention, and should not be used to limit the scope of the present invention, but all the insubstantial modifications or color changes made in the main design concept and spirit of the present invention are still consistent with the present invention, and all the technical problems to be solved are included in the scope of the present invention.
Claims (7)
1. A missile escape area attack distance calculation method based on a golden section method is characterized by comprising the following steps:
s1, establishing a state model of a missile and an aircraft;
s2, establishing a three-degree-of-freedom guidance model of the missile and the aircraft, and updating the states of the missile and the aircraft;
s3, setting a missile tracking guidance law, wherein the missile tracking guidance law comprises a missile climbing angle, a track angle and a speed change rate, and the missile climbing angle, the track angle and the speed change rate are used for enabling the missile to shorten the distance between the missile and an aircraft;
the missile tracking control rate setting process comprises the following steps:
s31, calculating a position difference vector d of the missile and the aircraft according to the current states of the aircraft and the missile M ：
d M ＝[x E -x M ,y E -y M ,h E -h M ] T (3)；
S32, calculating an included angle χ between the position difference vector and the horizontal plane d Included angle gamma with vertical plane d The method comprises the following steps:
s33, passing the track angle change rate of the missile at the current momentAnd climbing angle change rate->The track angle and the climbing angle at the next moment are close to the included angle χ of the horizontal plane of the position difference vector at the current moment d Included angle gamma with vertical plane d And (3) making:
in the method, in the process of the invention,for maximum positive and negative change of yaw angle of guided missileThe maximum positive and negative change rate of the rate and the climbing angle is related to the available overload of the missile, and delta t is the step length of the state update of the missile and the aircraft;
s34, assuming that the missile accelerates to the maximum speed after launching, namely the change rate of the current moment of the missile speedThe method meets the following conditions:
s4, updating the state quantity at the moment under the missile according to the missile tracking guidance law, the change rate of each state of the missile and the set state updating step length of the current state of the missile;
s5, calculating the maximum fuel consumption of the missile and the maximum change rate of each state quantity of the missile according to the missile tracking guidance law;
s6, updating the flight state of the missile and the aircraft under the action of tracking guidance law, and tracking the aircraft by the missile;
s7, based on the missile tracking guidance law, real-time approximate calculation is carried out on the missile attack distance parameter of the non-escapable area of the missile by utilizing a golden ratio searching method, so that the missile attack distance parameter is simulated and calculated on line.
2. The method for calculating the attack distance of the missile non-escape area based on the golden section method according to claim 1, wherein in the step S1, the state expressions of the missile and the aircraft are:
wherein, subscript M represents missile, subscript E represents escaped aircraft, V represents speed, χ represents track angle, γ represents climb angle, and (x, y, h) represents position coordinates.
3. The method for calculating the attack distance of the missile non-escapable area based on the golden section method according to claim 2, wherein in the step S2, the three-degree-of-freedom guidance model updates the states of the missile and the aircraft in the following manner:
wherein,indicating the rate of change of speed>Indicating the track angle change rate,/, for>Represents the rate of change of the climbing angle,/-)>Represents the abscissa position change rate,/>Representing the rate of change of the ordinate position,>represents the change rate of the vertical coordinate position, n x For tangential overload control, n y For lateral overload control, n z G is the normal overload control quantity and g is the gravitational acceleration.
4. A method for calculating an attack distance of a missile non-escape area based on the golden section method according to claim 3, wherein in step S5, the maximum fuel consumption of the missile is calculated by:
calculating the fuel quantity consumed by the missile after the current maneuver, namely:
wherein m, ρ, s, C D The missile mass, the air density, the missile cross-sectional area and the missile air resistance coefficient are respectively; the maximum fuel consumption of the missile is as follows:
i.e. if the missile keeps the maximum speed of inorganization to fly flat, the maximum fuel consumption can ensure that the missile at t max Continuous flight over time.
5. The method for calculating the attack distance of a missile non-escaped area based on the golden section method according to claim 4, wherein in step S5, calculating the maximum rate of change of each state quantity of the missile includes:
calculating the maximum positive and negative change rate of the missile track angle:
wherein n is zmax For maximum normal overload control quantity, n zmin Is the minimum value of normal overload control quantity;
calculating the maximum positive and negative change rate of the missile climbing angle:
wherein n is ymax For maximum lateral overload control, n ymin Is the minimum value of the lateral overload control quantity;
calculating the maximum rate of change of the missile speed:
wherein n is xmax Is the maximum value of the tangential overload control quantity.
6. The method for calculating the attack distance of a missile non-escapable region based on the golden section method according to claim 5, wherein in step S6, when the missile tracks the aircraft, whether the missile hits the aircraft is judged by the following conditions: before the fuel oil quantity is exhausted, the distance D between the missile and the target at a certain moment is less than or equal to e, and e is the allowable off-target quantity of the missile.
7. The method for calculating the attack distance of the non-escaped area of the missile according to claim 6, wherein in the step S7, the method for searching the golden ratio performs real-time approximate calculation on the attack distance parameter of the non-escaped area of the missile, which comprises the following steps:
s71: firstly, taking a target aircraft as a center, determining an initial interval guess [ a ] of the maximum attack distance of a missile nonsuperimposable area 0 ,b 0 ]；
S72: calculation of golden section Point R g ＝a 0 +0.618(b 0 -a 0 )；
S73: performing hit judgment on the dividing points, and judging whether the missile hits the target according to the miss distance and the ballistic simulation ending limiting condition; if hit the target, let a i ＝R g ，b i ＝b i-1 The method comprises the steps of carrying out a first treatment on the surface of the No make a i ＝a i-1 ，b i ＝R g The method comprises the steps of carrying out a first treatment on the surface of the Re-cycling the calculation until |a is satisfied i -b i I is less than the boundary of the set point.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310446601.4A CN116663239B (en) | 2023-04-24 | 2023-04-24 | Missile escape area attack distance calculation method based on golden section method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310446601.4A CN116663239B (en) | 2023-04-24 | 2023-04-24 | Missile escape area attack distance calculation method based on golden section method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116663239A CN116663239A (en) | 2023-08-29 |
| CN116663239B true CN116663239B (en) | 2024-01-05 |
Family
ID=87717950
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310446601.4A Active CN116663239B (en) | 2023-04-24 | 2023-04-24 | Missile escape area attack distance calculation method based on golden section method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116663239B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6244536B1 (en) * | 1997-11-26 | 2001-06-12 | The United States Of America As Represented By The Secretary Of The Air Force | Air to air homing missile guidance |
| CN106020215A (en) * | 2016-05-09 | 2016-10-12 | 北京航空航天大学 | Near-distance air combat automatic decision-making method based on single-step prediction matrix gaming |
| CN107132765A (en) * | 2017-06-01 | 2017-09-05 | 烟台南山学院 | A kind of angle-of-attack based on trajectory planning and attack time control method |
| CN108534785A (en) * | 2018-03-22 | 2018-09-14 | 北京控制工程研究所 | A kind of air enters guided trajectory Adaptive Planning method |
| CN111898201A (en) * | 2020-07-08 | 2020-11-06 | 西北工业大学 | High-precision autonomous attack guiding method for fighter in air combat simulation environment |
| CN112685886A (en) * | 2020-12-25 | 2021-04-20 | 曾喆昭 | Precise and rapid terminal guidance method based on coupled PI (proportional integral) stabilization rule |
| CN114610057A (en) * | 2022-02-25 | 2022-06-10 | 北京航空航天大学 | Design method for maneuvering penetration strategy of high-Mach aircraft |
| CN115238450A (en) * | 2022-06-07 | 2022-10-25 | 西北工业大学 | Simulation calculation method for launching attack area during advancing of guided rocket projectile |
| CN115950310A (en) * | 2022-12-14 | 2023-04-11 | 西北工业大学 | Attack time and angle constraint guidance method of time-varying speed aircraft |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8195345B2 (en) * | 2010-08-05 | 2012-06-05 | King Fahd University Of Petroleum & Minerals | Method of generating an integrated fuzzy-based guidance law for aerodynamic missiles |
| CN111221352B (en) * | 2020-03-03 | 2021-01-29 | 中国科学院自动化研究所 | Control system based on cooperative game countermeasure of multiple unmanned aerial vehicles |
-
2023
- 2023-04-24 CN CN202310446601.4A patent/CN116663239B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6244536B1 (en) * | 1997-11-26 | 2001-06-12 | The United States Of America As Represented By The Secretary Of The Air Force | Air to air homing missile guidance |
| CN106020215A (en) * | 2016-05-09 | 2016-10-12 | 北京航空航天大学 | Near-distance air combat automatic decision-making method based on single-step prediction matrix gaming |
| CN107132765A (en) * | 2017-06-01 | 2017-09-05 | 烟台南山学院 | A kind of angle-of-attack based on trajectory planning and attack time control method |
| CN108534785A (en) * | 2018-03-22 | 2018-09-14 | 北京控制工程研究所 | A kind of air enters guided trajectory Adaptive Planning method |
| CN111898201A (en) * | 2020-07-08 | 2020-11-06 | 西北工业大学 | High-precision autonomous attack guiding method for fighter in air combat simulation environment |
| CN112685886A (en) * | 2020-12-25 | 2021-04-20 | 曾喆昭 | Precise and rapid terminal guidance method based on coupled PI (proportional integral) stabilization rule |
| CN114610057A (en) * | 2022-02-25 | 2022-06-10 | 北京航空航天大学 | Design method for maneuvering penetration strategy of high-Mach aircraft |
| CN115238450A (en) * | 2022-06-07 | 2022-10-25 | 西北工业大学 | Simulation calculation method for launching attack area during advancing of guided rocket projectile |
| CN115950310A (en) * | 2022-12-14 | 2023-04-11 | 西北工业大学 | Attack time and angle constraint guidance method of time-varying speed aircraft |
Non-Patent Citations (4)
| Title |
|---|
| Xiaoxiong Liu,et al..A Multi-UCAV Cooperative Decision-Making Method Based on an MAPPO Algorithm for Beyond-Visual-Range Air Combat.《aerospace》.2022,全文. * |
| 中距空空导弹不可逃逸区工程应用解算方法;游航航 等;《战术导弹技术》;全文 * |
| 基于目标逃逸机动预估的空空导弹可发射区;王杰 等;《北京航空航天大学学报》;全文 * |
| 改进BAS-TIMS算法在空战机动决策中的应用;嵇慧明;余敏建;乔新航;杨海燕;张帅文;;国防科技大学学报(04);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116663239A (en) | 2023-08-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111551080B (en) | Guidance method for attack time control | |
| CN106352738B (en) | More bullet cooperative guidance methods based on output-consistence | |
| CN105204512B (en) | A kind of six degree of freedom UCAV short range combat method based on simplified model game playing by machine | |
| CN110412874B (en) | Multi-missile cooperative guidance law design method for maneuvering target and time delay communication | |
| CN103090728A (en) | Tail angle restraining guidance method based on sliding mode control | |
| CN110717245B (en) | Design method of quasi-gliding trajectory based on falling angle and falling speed constraints | |
| CN111898201B (en) | High-precision autonomous attack guiding method for fighter in air combat simulation environment | |
| CN114003050B (en) | Active defense guidance method of three-body countermeasure strategy based on differential game | |
| CN112859921B (en) | Three-dimensional simultaneous attack robust cooperative guidance law design method | |
| CN113282061A (en) | Unmanned aerial vehicle air game countermeasure solving method based on course learning | |
| CN114063644B (en) | Unmanned fighter plane air combat autonomous decision-making method based on pigeon flock reverse countermeasure learning | |
| CN111176315B (en) | Variant cruise missile control method based on L1 adaptive control | |
| CN115951695A (en) | Dynamic tactical control domain resolving method based on three-party game in air combat simulation environment | |
| CN113139331A (en) | Air-to-air missile situation perception and decision method based on Bayesian network | |
| CN113741186B (en) | Double-aircraft air combat decision-making method based on near-end strategy optimization | |
| CN116663239B (en) | Missile escape area attack distance calculation method based on golden section method | |
| CN114815878B (en) | Hypersonic aircraft collaborative guidance method based on real-time optimization and deep learning | |
| Wang et al. | Study on fuzzy neural sliding mode guidance law with terminal angle constraint for maneuvering target | |
| CN117806171B (en) | Intelligent cooperative game maneuvering method for ultra-high-speed aircraft carrying defenses | |
| CN110687801A (en) | Self-adaptive integral sliding mode three-dimensional guidance law design method based on forward guidance | |
| CN113110576B (en) | Self-adaptive fixed time convergence cooperative guidance method capable of realizing continuous switching | |
| CN116579118B (en) | Online quick calculation method for three-dimensional dynamic emission area for combat in short-distance air combat | |
| CN117891271B (en) | Three-dimensional collaborative guidance method for high-speed aircraft in consideration of time and angle constraints | |
| CN118149657A (en) | Constant time convergence guidance rocket projectile angle constraint guidance law design method | |
| CN116430900B (en) | Game track planning method of hypersonic warhead based on deep reinforcement learning |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |