A Simulation Solution Method for the Reachable Domain of Air-to-Surface Missile Terminal Guidance Phase

Abstract

The application discloses a simulation solving method for the reachable domain of the terminal guidance section of a space-to-surface missile, and comprises the following steps: obtaining the initial state and the original target state of the missile at the time when the missile enters the terminal guidance, and establishing a missile body coordinate system and an inertial coordinate system; selecting the search angle of a new target in the yaw direction and the pitch direction of the missile body coordinate system, and determining the initial position of the new target in the inertial coordinate system; performing integral iteration on the motion models of the missile and the new target, obtaining the final hit result, and recording the boundary of the reachable domain in the direction; updating the search angle of the new target in the yaw direction and the pitch direction of the missile, and forming the reachable domain of the terminal guidance section of the space-to-surface missile after traversal. The method considers the field of view range constraint of a seeker of the space-to-surface missile, narrows the search range of the reachable domain, and improves the solving efficiency. The solving process is irrelevant to the types and motion characteristics of the space-to-surface missile and the target, has good compatibility for different types of missiles and targets, and is a high-efficiency solving method with certain expansibility.

Description

Technical Field

[0001] This application belongs to the field of ballistic simulation technology, specifically a simulation solution method for the reachable domain of the terminal guidance phase of an air-to-surface missile. Background Technology

[0002] The reachability domain of an air-to-surface missile in its terminal guidance phase refers to the strike range that the air-to-surface missile can cover if it changes its target after entering the terminal guidance phase. As one of the important indicators for measuring the terminal strike capability of an air-to-surface missile, the reachability domain of its terminal guidance phase is related to a variety of factors, making it particularly important to be able to calculate it quickly and effectively.

[0003] Currently, there is limited research on the reachability domain of air-to-surface missiles during the terminal guidance phase. Although most existing attack range calculations employ simulation methods, they involve wide-area searches, making it difficult to balance calculation speed and accuracy. A method is needed that can quickly and effectively calculate the reachability domain of air-to-surface missiles during the terminal guidance phase. Summary of the Invention

[0004] To address the aforementioned problems in the existing technology, this application provides a simulation method for calculating the reachable domain of the terminal guidance phase of an air-to-surface missile. By considering the field-of-view constraints of the air-to-surface missile seeker to narrow the search range, it can quickly and effectively calculate the reachable domain of the terminal guidance phase of the air-to-surface missile.

[0005] To achieve the above objectives, this application adopts the following technical solution: a simulation calculation method for the reachable domain of an air-to-surface missile in the terminal guidance phase, comprising the following steps:

[0006] Obtain the initial state and original target state of the missile when it enters terminal guidance, and establish the missile body coordinate system and inertial coordinate system;

[0007] In the missile body coordinate system, select the search angles of the new target in the missile's yaw and pitch directions to determine the initial position of the new target in the inertial coordinate system;

[0008] The motion model of the missile and the new target is integrated and iterated to obtain the final hit result and record the reachable domain boundary of that orientation;

[0009] The search angles for new targets in the missile's yaw and pitch directions are updated, and the reachable domain of the air-to-surface missile's terminal guidance phase is formed after traversal.

[0010] The initial state includes the missile's altitude, pitch angle, yaw angle, and airspeed at the moment of terminal guidance, while the original target state includes the original target's velocity direction and magnitude.

[0011] The missile body coordinate system is established with the missile's center of mass as the origin, and the inertial coordinate system is established with the projection of the missile's initial position onto the horizontal plane as the origin.

[0012] Among them, the search angles for new targets in the yaw and pitch directions are constrained by the seeker locking angle, which requires that the ground target be within the seeker's field of view.

[0013] The initial position of the new target in the inertial coordinate system is determined by the search angle of the new target and the seeker locking distance constraint, which requires the ground target to be within the seeker's field of view.

[0014] In the process of integral iteration of the motion models of the missile and the new target, the new target moves according to the motion characteristics of its own model, and the missile tracks the target based on its own guidance law.

[0015] The search angles for new targets in the updated missile yaw and pitch directions, after traversal, form the reachable domain of the air-to-surface missile's terminal guidance phase, including:

[0016] Determine whether the search angles for new targets in the pitch direction have been traversed.

[0017] If not, continue updating the pitch search angle; if so, update the yaw search angle.

[0018] When the search angles for new targets in the yaw direction have been traversed, the maximum and minimum boundaries of the missile in each yaw direction are compared and obtained with the missile's initial position as the center.

[0019] This allows the maximum and minimum boundaries to form the reachable domain of the air-to-surface missile's terminal guidance phase in the polar coordinate system.

[0020] The beneficial effects of this application are:

[0021] This application provides a simulation method for calculating the reachable domain of an air-to-surface missile in its terminal guidance phase. It considers the field-of-view constraints of the air-to-surface missile seeker, narrows the search range of the reachable domain, and improves the calculation efficiency. The calculation process is independent of the type and motion characteristics of the air-to-surface missile and the target, and has good compatibility with different types of missiles and targets. It is an efficient simulation method for calculating the reachable domain of an air-to-surface missile in its terminal guidance phase with a certain degree of scalability. Attached Figure Description

[0022] Figure 1 This is a flowchart illustrating the method described in this application;

[0023] Figure 2 This is a flowchart of the reachability domain calculation method of the present invention;

[0024] Figure 3 This is a diagram showing the reachability domain solution results obtained based on the method of this invention in a specific example. Detailed Implementation

[0025] Embodiments of this application will now be described in more detail with reference to the accompanying drawings. While embodiments of this application are shown in the drawings, it should be understood that this application may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to make this application more thorough and complete, and to fully convey the scope of this application to those skilled in the art.

[0026] It should be understood that although the terms "first," "second," "third," etc., may be used in this application to describe various information, this information should not be limited to these terms. These terms are only used to distinguish information of the same type from one another. For example, without departing from the scope of this application, first information may also be referred to as second information, and similarly, second information may also be referred to as first information. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0027] In the description of this application, it should be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0028] Unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0029] like Figure 1 The method for simulating and calculating the reachable domain of an air-to-surface missile in its terminal guidance phase, as shown, includes the following steps:

[0030] S1. Obtain the initial state and original target state of the missile when it enters the terminal guidance moment, and establish the missile body coordinate system and inertial coordinate system.

[0031] Before the calculation, the reachability simulation parameters are set, including the seeker's field of view angle range. Field of view distance Angle search step size Simulation step size The search step size can be adjusted according to the simulation granularity requirements. and simulation step size .

[0032] The initial state of a missile includes its altitude at the moment it enters terminal guidance. Pitch angle Yaw angle ,airspeed .

[0033] The original target state includes the original target's velocity direction. and size .

[0034] Establish a missile body coordinate system with the missile's center of mass as the origin. An inertial coordinate system is established with the projection of the missile's initial position onto the horizontal plane as the origin. .

[0035] S2. Select the search angles of the new target in the missile's yaw and pitch directions in the missile coordinate system, and determine the initial position of the new target in the inertial coordinate system.

[0036] Based on the seeker lock angle constraint, the search angle for the new target in the yaw direction is selected. The seeker lock angle constraint requires that the ground target be within the seeker's field of view, i.e. Based on the aforementioned angle range, the search angle for the new target along the missile's yaw direction is selected in the missile's coordinate system. ;

[0037] Based on the seeker's locking angle constraint, the search angle for the new target in the pitch direction is selected. This can be derived from the geometric relationship between the seeker's field of view and the ground plane. Based on the aforementioned angle range, the search angle for the new target in the missile's pitch direction is selected in the missile's coordinate system. ;

[0038] Based on the seeker's locking range constraint, the initial position of the new target is determined. The seeker's locking range constraint requires that the ground target be within the seeker's field of view, i.e. Based on the above constraints, the new objective is determined to be... The initial position in the inertial coordinate system is: .

[0039] S3. Perform integral iteration on the motion model of the missile and the new target to obtain the final hit result and record the reachable domain boundary of that direction.

[0040] Based on the initial relative positions of the missile and the new target determined above, maneuvering and ballistic simulations of the new target are conducted: Integral iterations are performed on the motion models of the missile and the target, where the target moves according to the motion characteristics of its own model, and the missile tracks the target based on its own guidance law. The simulation iteration step size is [missing information]. Based on the final hit result of the simulation, record the reachable domain boundary of that location. .

[0041] S4. Update the search angles for new targets in the missile's yaw and pitch directions, and after traversing the range, form the reachable domain of the air-to-surface missile's terminal guidance phase.

[0042] Determine if the search angles for new targets in the pitch direction have been exhausted. If not, continue updating the pitch search angles; otherwise, update the yaw search angles. The angle search step size is... ;

[0043] If the search angles for new targets in the yaw direction have also been exhausted, then the maximum boundary in each yaw direction of the missile is obtained by comparison, centered on the missile's initial position. and minimum boundary The maximum and minimum reachable boundaries of the missile in each direction are presented using polar coordinates, ultimately forming the reachable domain of the air-to-surface missile in the terminal guidance phase.

[0044] After the above steps Figure 2 The diagram shows the reachability domain solution results obtained based on the method of this invention in a specific example.

[0045] In one instance, the parameters are solved. , , , The initial state of the missile and its original target at the moment of terminal guidance. , , , , , The reachable domain of the terminal guidance phase of an air-to-surface missile obtained based on the method of this invention is as follows: Figure 3 As shown, this invention solves the problem of calculating the reachable domain of the terminal guidance phase of an air-to-surface missile.

[0046] Finally, it should be noted that in this document, relationships such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "include," "contain," or any other variations are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus.

[0047] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0048] The various embodiments of this application have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or improvement of the technology in the market, or to enable others skilled in the art to understand the embodiments disclosed herein.

Claims

1. A method for solving the reachable domain of the terminal guidance phase of a surface-to-air missile, characterized in that, The method comprises the following steps: acquiring initial state and original target state of missile entering terminal guidance time, establishing missile body coordinate system and inertial coordinate system; selecting search angle of new target in yaw direction and pitch direction of the missile in the missile body coordinate system, determining initial position of the new target in the inertial coordinate system, the search angle of the new target in the yaw direction and the pitch direction is selected according to seeker locking angle constraint, the seeker locking angle constraint requires that the ground target is in the seeker field of view angle range, the initial position of the new target in the inertial coordinate system is determined according to the search angle of the new target and the seeker locking distance constraint, the seeker locking distance constraint requires that the ground target is in the seeker field of view distance; integrating and iterating the motion model of the missile and the new target to obtain the final hit result and record the reachable domain boundary, in the integrating and iterating the motion model of the missile and the new target, the new target carries out motion according to the motion characteristics of its own model, and the missile carries out tracking of the target based on its own guidance law; updating the search angle of the new target in the yaw direction and the pitch direction of the missile, and forming the reachable domain of the air-space missile terminal guidance segment after traversal.

2. The reachable domain simulation solution method for the midcourse guidance phase of a space-to-surface missile according to claim 1, characterized in that, The initial state comprises height, pitch angle, yaw angle and airspeed of the missile at the time of entering terminal guidance, and the original target state comprises velocity direction and size of the original target.

3. The simulation calculation method for the reachable domain of the terminal guidance phase of an air-to-surface missile as described in claim 1, characterized in that, The missile body coordinate system is established with the center of mass of the missile as the origin, and the inertial coordinate system is established with the projection of the initial position of the missile on the horizontal plane as the origin.

4. The simulation calculation method for the reachable domain of the terminal guidance phase of an air-to-surface missile as described in claim 1, characterized in that, The updating the search angle of the new target in the yaw direction and the pitch direction of the missile, and forming the reachable domain of the air-space missile terminal guidance segment after traversal comprises: judging whether the search angle of the new target in the pitch direction is traversed or not; if not, continue to update the pitch search angle, and if yes, update the yaw search angle; when the search angle of the new target in the yaw direction is traversed, taking the initial position of the missile as the center, comparing to obtain the maximum boundary and the minimum boundary of the missile in each yaw direction; making the maximum boundary and the minimum boundary form the reachable domain of the air-space missile terminal guidance segment in the polar coordinate system.

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