Method for constructing parameterized air-to-air missile model

Abstract

The present invention discloses a parameterized air-to-air missile model construction method, comprising the following steps: S1, obtaining the relative motion relationship between the missile and the target at the current moment, and generating the guidance instruction at the current moment; S2, generating the missile heading at the current moment according to the guidance instruction at the current moment; S3, generating the simulated trajectory of the missile at the current moment based on the current missile heading, aerodynamic data and dynamic model; S4, repeating S1 to S3, obtaining the simulated trajectory of the missile at different moments, and combining them into a complete simulated trajectory of the missile; S5, obtaining the control parameters of the missile pilot according to the complete simulated trajectory, and then obtaining the missile simulation model. The parameterized air-to-air missile model construction method disclosed by the present invention can be simulated according to the actual aerodynamic shape of the missile, and is more in line with the actual situation of the missile.

Description

Technical Field

[0001] The invention relates to a parameterized air-to-air missile model construction method, belonging to the guidance control field. Background Art

[0002] There are two main problems in the current construction of air-to-air missile models: First, the missile itself is not the focus of research, so the model construction has been simplified to varying degrees. For example, the three-degree-of-freedom modeling method is used to ignore the impact of posture changes. For air combat simulation environments that take into account the tactical level, it is urgent to pursue an effective and realistic air-to-air missile simulation system. Therefore, the simplified missile model cannot fully reflect the impact of missile performance on the combat process, and it is impossible to derive more detailed and accurate tactical strategies.

[0003] Secondly, in the existing six-degree-of-freedom nonlinear detailed modeling of missiles, the simulation system is designed in general and in detail, and the missile is divided into several subsystems for mathematical modeling using a modular design method. The simulated air-to-air missile can meet the requirements of the tactical simulation level for the missile's meticulousness, and usually has a certain degree of versatility. Its versatility refers to the repeatability of the modeling process. Its design method and design process can be used to simulate other missiles with different performance. However, in terms of application in air combat simulation environments, it takes a long time to generate a missile again, which cannot meet the needs of quickly generating performance-biased missiles in simulation, and fails to achieve the establishment of a truly parametric missile model.

[0004] Therefore, it is necessary to further study the air-to-air missile model construction method to solve the above problems. Summary of the invention

[0005] In order to overcome the above problems, the inventors conducted in-depth research and designed a parameterized air-to-air missile model construction method, which includes the following steps:

[0006] S1, obtaining the current relative motion relationship between the projectile and the target, and generating the current guidance command;

[0007] S2, generating the missile heading at the current moment according to the guidance instruction at the current moment;

[0008] S3, generating a simulated trajectory of the missile at the current moment based on the current missile heading, aerodynamic data and dynamic model;

[0009] S4, repeat S1 to S3 to obtain the simulated trajectory of the missile at different times, and combine them into a complete simulated trajectory of the missile;

[0010] S5. According to the complete simulation trajectory, the missile pilot control parameters are obtained, and then the missile simulation model is obtained.

[0011] In a preferred embodiment, in S3, the aerodynamic data received by the missile is deflected, and the aerodynamic data includes aerodynamic coefficients and aerodynamic matrices.

[0012] In a preferred embodiment, the pneumatic data deflection includes the following sub-steps:

[0013] S31, obtaining a reference aerodynamic coefficient curve and a reference aerodynamic torque curve;

[0014] S32, deflecting the reference aerodynamic coefficient curve and the reference aerodynamic moment curve to obtain a deflected aerodynamic coefficient curve and a deflected aerodynamic moment curve;

[0015] S33, substituting the attack angle in the missile heading into the deflection aerodynamic coefficient curve and the deflection aerodynamic moment curve respectively, to obtain the corresponding aerodynamic coefficient and aerodynamic matrix, and using them as the aerodynamic data after deflection.

[0016] In a preferred embodiment, in S1, a proportional guidance method is used to generate guidance instructions.

[0017] In a preferred embodiment, in S3, the simulation is a six-degree-of-freedom trajectory simulation.

[0018] In a preferred embodiment, feature points are selected on the simulated trajectory obtained in S4.

[0019] In a preferred embodiment, in S5, the autopilot is a two-circuit overload autopilot.

[0020] In a preferred embodiment, in S5, the required parameters of the two-loop overload autopilot are obtained by calculating the characteristic points on the simulated trajectory obtained in S4, and are expressed as:

[0021]

[0022]

[0023]

[0024]

[0025] Among them, a α It is expressed as the missile pitch rotation angular acceleration generated by unit angle of attack, a δ Indicates the magnitude of the missile pitch rotation angular acceleration generated by the unit rudder angle, b α It is expressed as the angular velocity of the missile velocity vector generated by the unit angle of attack, b δ Indicates the magnitude of the angular velocity of the missile velocity vector generated by a unit rudder angle; is the static stability moment, q is the dynamic pressure, S is the characteristic area of ​​the missile, is the operating torque, P is the thrust, c y is the lift coefficient, is the rudder lift coefficient, L is the missile characteristic length, J z is the moment of inertia.

[0026] In a preferred embodiment, a plurality of characteristic points are selected on the simulated trajectory as segmentation points to obtain segmentation control parameters of the autopilot, wherein the characteristic points are selected based on the speed inflection point and / or the flight altitude inflection point.

[0027] The beneficial effects of the present invention include:

[0028] (1) Compared with the traditional missile modeling ideas, the parameterized air-to-air missile model construction ideas provided by the present invention have stronger versatility and can truly realize the real-time generation of parameter-differentiated missile models;

[0029] (2) The parameterized air-to-air missile model provided by the present invention can be simulated according to the actual aerodynamic shape of the missile, which is more in line with the actual situation of the missile. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 A schematic flow chart of a parameterized air-to-air missile model construction method according to a preferred embodiment of the present invention is shown;

[0031] Figure 2 A schematic diagram of a Mach number-angle of attack interpolation relationship curve in a parameterized air-to-air missile model construction method according to a preferred embodiment of the present invention is shown;

[0032] Figure 3 The lift coefficient curve after deflection according to Example 1 of the present invention is shown;

[0033] Figure 4 The drag coefficient curve after deflection in Example 1 of the present invention is shown;

[0034] Figure 5 The uncontrolled full-ballistic deflection velocity curve according to Example 1 of the present invention is shown;

[0035] Figure 6 The graph shows the variation curve of the miss amount in Example 1 of the present invention. DETAILED DESCRIPTION

[0036] The present invention will be further described in detail below through the accompanying drawings and embodiments. Through these descriptions, the characteristics and advantages of the present invention will become more clear and distinct.

[0037] The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Although various aspects of the embodiments are shown in the drawings, the drawings are not necessarily drawn to scale unless otherwise noted.

[0038] According to a parameterized air-to-air missile model construction method provided by the present invention, Figure 1 As shown, the following steps are included:

[0039] S1, obtaining the current relative motion relationship between the projectile and the target, and generating the current guidance command;

[0040] S2, generating the missile heading at the current moment according to the guidance instruction at the current moment;

[0041] S3, generating a simulated trajectory of the missile at the current moment based on the current missile heading, aerodynamic data and dynamic model;

[0042] S4, repeat S1 to S3 to obtain the simulated trajectory of the missile at different times, and combine them into a complete simulated trajectory of the missile;

[0043] S5. According to the complete simulation trajectory, the missile pilot control parameters are obtained, and then the missile simulation model is obtained.

[0044] According to the present invention, S1-S3 is one of the commonly used means in missile simulation, and its specific process is not described in detail in the present invention.

[0045] In a preferred embodiment, in S1, a proportional guidance method is used to generate guidance instructions.

[0046] The proportional guidance method can be expressed as:

[0047]

[0048] Among them, a c Represents the guidance command, N is the proportional guidance coefficient, V r represents the missile speed, and q represents the missile-target line-of-sight angle.

[0049] Different from the traditional missile simulation, in the present invention, in S3, the aerodynamic data received by the missile is deflected, and the aerodynamic data includes aerodynamic coefficients and aerodynamic matrices.

[0050] Aerodynamic data refers to the force and torque generated by the relative motion between the missile and the air. In traditional missile models, the influence of air changes on the missile is not considered, that is, different missiles are assumed to have the same aerodynamic shape. In the present invention, by biasing the aerodynamic data, the missile has different aerodynamic shapes during the simulation process. The simulation can be performed according to the actual aerodynamic shape of the missile, thereby obtaining a simulation effect that is more in line with reality.

[0051] In a preferred embodiment, the pneumatic data deflection includes the following sub-steps:

[0052] S31, obtaining a reference aerodynamic coefficient curve and a reference aerodynamic torque curve;

[0053] S32, obtaining a pull-off coefficient, and using the pull-off coefficient to pull off a reference aerodynamic coefficient curve and a reference aerodynamic torque curve to obtain a pull-off aerodynamic coefficient curve and a pull-off aerodynamic torque curve;

[0054] S33, substituting the attack angle in the missile heading into the deflection aerodynamic coefficient curve and the deflection aerodynamic moment curve respectively, to obtain the corresponding aerodynamic coefficient and aerodynamic matrix, and using them as the aerodynamic data after deflection.

[0055] Specifically, in S31, the aerodynamic force is decomposed into three components along the velocity coordinate system, namely, drag force X, lift force Y and lateral force Z:

[0056]

[0057] Where q is the dynamic pressure and S is the missile characteristic area. x 、c y 、c z are dimensionless proportional coefficients, namely the drag coefficient, lift coefficient and lateral force coefficient, c x 、c y 、c z The three values ​​are simulated by CFD to obtain the Mach number-angle of attack interpolation relationship curve, which is used as the benchmark aerodynamic coefficient value curve, such as Figure 2 As shown,

[0058] Furthermore, in the same way, the Mach number-aerodynamic torque value relationship curve is obtained through CFD simulation and used as the reference aerodynamic torque curve.

[0059] In the present invention, there is no particular limitation on the method for obtaining the pull-bias coefficient in S32. For example, the pull-bias coefficient can be obtained according to the aerodynamic shape of the missile, or the pull-bias coefficient can be determined according to the aerodynamic requirements of the missile to be simulated.

[0060] Furthermore, the pulling deviation is achieved by pulling the inflection point of the lift / drag coefficient curve and generating a Bezier curve according to the starting / end point and the inflection point of the curve.

[0061] According to the present invention, a simulation trajectory is obtained by deflecting the aerodynamic data received by the missile, and then the autopilot control parameters are obtained through the simulation trajectory, and the final missile simulation model is obtained based on the control parameters. Compared with the simulation model obtained by mathematical modeling in a traditional way, the model obtained by the present invention can realize the change of the aerodynamic parameters of the missile, and the control system makes corresponding changes according to the aerodynamic parameters, truly realizing real-time generation of parameter differentiation, and the obtained simulation model is more universal.

[0062] In a preferred embodiment, in S3, the simulation is a six-degree-of-freedom trajectory simulation.

[0063] Six-degree-of-freedom simulation can meet the requirements of tactical simulation level for missile detail, thereby obtaining more accurate simulation data, and further improving the accuracy of the final missile simulation model.

[0064] According to the present invention, in S5, the autopilot is preferably a two-circuit overload autopilot.

[0065] The two-circuit overload pilot is a classic missile pilot, and its structure is not described in detail in the present invention.

[0066] According to the present invention, in S5, the required parameters of the two-circuit overload autopilot are obtained by calculating the characteristic points on the simulated trajectory obtained in S4, and are expressed as:

[0067]

[0068]

[0069]

[0070]

[0071] Among them, a α It is expressed as the missile pitch rotation angular acceleration generated by unit angle of attack, a δ Indicates the magnitude of the missile pitch rotation angular acceleration generated by the unit rudder angle, b α It is expressed as the angular velocity of the missile velocity vector generated by the unit angle of attack, b δ Indicates the magnitude of the angular velocity of the missile velocity vector generated by a unit rudder angle; is the static stability moment, q is the dynamic pressure, S is the characteristic area of ​​the missile, is the operating torque, P is the thrust, c y is the lift coefficient, is the rudder lift coefficient, L is the missile characteristic length, J zThe required parameters change according to the aerodynamic parameters. Compared with the existing missile modeling methods, it can truly realize the real-time generation of parameter-differentiated missile models.

[0072] In a preferred embodiment, a plurality of characteristic points are selected on the simulated trajectory as segmentation points to obtain segmentation control parameters of the autopilot, wherein the characteristic points are selected based on the speed inflection point and / or the flight altitude inflection point.

[0073] For example, the characteristic points are: the initial state of the missile, the maximum speed point of the missile, any point in the missile's ascending stage, the highest position point of the missile, the highest speed point of the missile, the second highest speed point of the missile, any point in the missile's descending stage, and the missile's end point.

[0074] Example

[0075] Example 1

[0076] Three missiles with different aerodynamic shapes are simulated. The pull coefficients k of the three missiles are 1.2, 1.4, and 1.6 respectively. The simulation model is obtained by the following steps:

[0077] S1, obtaining the current relative motion relationship between the projectile and the target, and generating the current guidance command;

[0078] S2, generate the current missile heading according to the current guidance command,

[0079] S3, generating a simulated trajectory of the missile at the current moment based on the current missile heading, aerodynamic data and dynamic model;

[0080] S4, repeat S1 to S3 to obtain the simulated trajectory of the missile at different times, and combine them into a complete simulated trajectory of the missile;

[0081] S5. According to the complete simulation trajectory, the missile pilot control parameters are obtained, and then the missile simulation model is obtained.

[0082] In S3, the aerodynamic data received by the missile is deflected, wherein the aerodynamic data includes aerodynamic coefficients and aerodynamic matrices.

[0083] The pneumatic data deflection comprises the following sub-steps:

[0084] S31, obtaining a reference aerodynamic coefficient curve and a reference aerodynamic torque curve;

[0085] S32, deflecting the reference aerodynamic coefficient curve and the reference aerodynamic moment curve to obtain a deflected aerodynamic coefficient curve and a deflected aerodynamic moment curve, wherein the lift coefficient curve after deflection is as follows: Figure 3 As shown in the figure, the drag coefficient curve after deflection is as follows Figure 4 shown.

[0086] S33, the attack angle in the missile heading is substituted into the deflection aerodynamic coefficient curve and the deflection aerodynamic moment curve, and the corresponding aerodynamic coefficient and aerodynamic matrix are obtained, which are used as the aerodynamic data after deflection.

[0087] In S1, the proportional guidance method is used to generate guidance instructions, which can be expressed as

[0088] In S3, the simulation is a six-degree-of-freedom trajectory simulation.

[0089] In S4, the full trajectory results are obtained as follows Figure 5 shown.

[0090] In S5, the pilot is a two-circuit overload pilot. Multiple characteristic points are selected on the simulated trajectory as segmentation points to obtain the segmentation control parameters of the pilot, and the characteristic points are the initial state of the missile, the maximum speed point of the missile, any point in the missile ascending stage, the highest position point of the missile, the highest speed point of the missile, the second highest speed point of the missile, any point in the missile descending stage, and the end point of the missile.

[0091] The required parameters of the two-loop overload autopilot are obtained by calculating the characteristic points on the simulated trajectory obtained in S4 and are expressed as:

[0092]

[0093]

[0094]

[0095]

[0096] The missile simulation model obtained in S5 is used to perform target interception simulation, and the initial conditions of the simulation are set as shown in Table 1.

[0097] Table 1

[0098] Missile initial position (0,10000,0) Missile initial speed (340,0,0) Target initial position (20000,10000,0) Target initial speed (-120,150，0)

[0099] The change of the miss amount after simulation is as follows Figure 6 shown.

[0100] Depend on Figure 6 It can be seen that as the drag coefficient deviation increases, the time it takes for the missile to hit the target increases significantly, especially when the distance between the missile and the target is shortened at the end of the trajectory and the missile needs to maneuver. At this time, the influence of the drag coefficient deviation is obvious, that is, the simulation results can reflect the differences in actual flight processes of missiles with different aerodynamic shapes.

[0101] In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front", "rear", etc. indicate positions or positional relationships based on the working state of the present invention, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", "third", and "fourth" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0102] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0103] The present invention has been described above in conjunction with preferred embodiments, but these embodiments are only exemplary and serve only as an illustration. On this basis, the present invention may be subjected to a variety of substitutions and improvements, all of which fall within the scope of protection of the present invention.

Claims

1. A method for constructing a parameterized air-to-air missile model, characterized in that: The following steps are involved: S1, obtaining the current relative motion relationship between the projectile and the target, and generating the current guidance command; S2, generating the missile heading at the current moment according to the guidance instruction at the current moment; S3, generating a simulated trajectory of the missile at the current moment based on the current missile heading, aerodynamic data and dynamic model; S4, repeat S1 to S3 to obtain the simulated trajectory of the missile at different times, and combine them into a complete simulated trajectory of the missile; S5. According to the complete simulation trajectory, the missile pilot control parameters are obtained, and then the missile simulation model is obtained. In S3, the aerodynamic data received by the missile is deflected, wherein the aerodynamic data includes aerodynamic coefficients and aerodynamic matrices. The pneumatic data deflection comprises the following sub-steps: S31, obtaining a reference aerodynamic coefficient curve and a reference aerodynamic torque curve; S32, deflecting the reference aerodynamic coefficient curve and the reference aerodynamic moment curve to obtain a deflected aerodynamic coefficient curve and a deflected aerodynamic moment curve; S33, the attack angle in the missile heading is substituted into the pull-off aerodynamic coefficient curve and the pull-off aerodynamic moment curve, respectively, to obtain the corresponding aerodynamic coefficient and aerodynamic matrix, which are used as the aerodynamic data after pull-off. In S31, the aerodynamic force is decomposed into three components along the velocity coordinate system, namely drag force X, lift force Y and lateral force Z: Where q is the dynamic pressure, S is the characteristic area of ​​the missile; c x 、c y 、c z are dimensionless proportional coefficients, namely the drag coefficient, lift coefficient and lateral force coefficient, c x 、c y 、c z The three numerical values ​​are simulated through CFD simulation to obtain the Mach number-angle of attack interpolation relationship curve, which is used as the benchmark aerodynamic coefficient value curve.

2. The parameterized air-to-air missile model construction method according to claim 1, characterized in that: In S1, the proportional guidance method is used to generate guidance instructions.

3. The parameterized air-to-air missile model construction method according to claim 1, characterized in that: In S3, the simulation is a six-degree-of-freedom trajectory simulation.

4. The parameterized air-to-air missile model construction method according to claim 3, characterized in that: Feature points are selected on the simulated trajectory obtained in S4.

5. The parameterized air-to-air missile model construction method according to claim 4, characterized in that: In S5, the autopilot is a two-circuit overload autopilot.

6. The parameterized air-to-air missile model construction method according to claim 5, characterized in that: In S5, the required parameters of the two-loop overload autopilot are calculated by the characteristic points on the simulated trajectory obtained in S4 and are expressed as: Among them, a α It is expressed as the missile pitch rotation angular acceleration generated by unit angle of attack, a δ Indicates the missile pitch rotation angular acceleration generated by unit rudder angle, b α It is expressed as the angular velocity of the missile velocity vector generated by the unit angle of attack, b δ It indicates the angular velocity of the missile velocity vector generated by the unit rudder angle; is the static stability moment, q is the dynamic pressure, S is the characteristic area of ​​the missile, is the operating torque, P is the thrust, c y is the lift coefficient, is the rudder lift coefficient, L is the missile characteristic length, J z is the moment of inertia.

7. The parameterized air-to-air missile model construction method according to claim 6, characterized in that: A plurality of characteristic points are selected on the simulated trajectory as segmentation points to obtain segmentation control parameters of the autopilot, wherein the characteristic points are selected based on the speed inflection point and / or the flight altitude inflection point.

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