missile

Abstract

The present application discloses a missile, including: a missile body, a seeker and an onboard computer, which is fixedly installed in the inner cavity of the missile body through the onboard computer, wherein an electrical connection socket is provided on the missile body, and two or more identification sockets are provided on the electrical connection socket, and the two or more identification sockets are respectively located at different positions of the socket and correspond to different types of seekers, and a category pin for characterizing the category of the seeker is provided on the seeker, and the seeker is sleeved with the missile body, and the category pin corresponds to the corresponding identification socket, and the onboard computer includes an identification module, and the identification module is used to obtain the position of the category pin, and identify the category of the seeker according to the position of the category pin, and call the corresponding missile flight parameters according to the identification result. Rapid docking between the missile body and the seeker and simple identification of the seeker type are achieved, and the missile is automatically adapted to different types of seekers, which significantly improves the adaptability of the missile to battlefield conditions.

Description

Technical Field

[0001] The present disclosure relates to the field of missile design and manufacturing, and in particular to a missile. Background Art

[0002] The traditional domestic missile seeker heads are not replaceable during the combat preparation stage. During use, the troops cannot replace the seeker heads according to battlefield weather, astronomical phenomena and target conditions. During a battle, the quantity and type of ammunition carried by the troops can only be planned according to prior estimates, and the situation on the battlefield is often unpredictable. Therefore, it often happens that the type of missile cannot be well adapted to the target, reducing combat efficiency. Summary of the invention

[0003] In view of this, the present disclosure proposes a missile, comprising: a missile body, a seeker, and an onboard computer;

[0004] The onboard computer is fixedly installed in the inner cavity of the missile body;

[0005] Wherein, the projectile body is provided with an electrical connection socket, and the electrical connection socket is provided with more than two identification sockets, and the more than two identification sockets are respectively located at different positions of the socket and correspond to different types of guide heads;

[0006] The seeker is provided with a category pin for characterizing the category of the seeker;

[0007] The seeker is sleeved with the missile body, and the category pin corresponds to the corresponding identification socket; the missile-borne computer includes an identification module;

[0008] The identification module is used to obtain the position of the category pin, identify the category of the seeker according to the position of the category pin, and call corresponding missile flight parameters according to the identification result.

[0009] In a possible implementation manner, the electrical connection socket is arranged on an end surface of the projectile body facing the guide head.

[0010] In a possible implementation, the identification socket includes a first identification socket, a second identification socket, and a third identification socket;

[0011] The first identification jack is a television image identification jack;

[0012] The second identification socket is an infrared image identification socket;

[0013] The third identification socket is a laser semi-active identification socket.

[0014] In a possible implementation, a mounting portion is provided at the end surface of the projectile connected toward the guide head;

[0015] The mounting portion is circular;

[0016] The mounting portion is integrally formed with the elastic body;

[0017] The electrical connection socket is embedded in the fixing hole provided on the mounting portion and is fixedly connected to the side wall of the fixing hole.

[0018] In a possible implementation, the projectile body includes a sleeve section;

[0019] The sleeve section extends to the outside of the projectile and is suitable for being inserted into the guide head and fixedly connected to the guide head.

[0020] In a possible implementation, a rotational connection portion is provided at the connection between the guide head and the projectile body, and the rotational connection portion is sleeved on the projectile body and can rotate around the projectile body;

[0021] An electrical connection plug is provided on the end surface of the guide head facing the projectile;

[0022] The electrical connection plug is provided with an electrical interface for fixing and installing the category pin, and the position of the electrical interface corresponds to the position of the identification socket;

[0023] Wherein, the electrical interface is provided with the type of pins; and

[0024] Different positions of the electrical interface on the electrical connection plug represent different types of the guide head.

[0025] In a possible implementation manner, the screw-on portion and the guide head are integrally formed, and the electrical connection plug and the guide head are integrally formed.

[0026] In a possible implementation, the category pin includes any one of a television image pin, an infrared image pin, and a laser semi-active pin.

[0027] In a possible implementation, the identification module includes a state acquisition unit, a position determination unit, and a category determination unit;

[0028] The state acquisition unit is configured to acquire the current power-on state of each of the identification sockets;

[0029] The position determination unit is configured to determine the current position of the category pin on the seeker according to the current power-on state of the identification jack;

[0030] The category determination unit is configured to determine the category of the seeker according to the current position of the category pin.

[0031] In a possible implementation, the identification module further includes a flight parameter acquisition unit;

[0032] The flight parameter acquisition unit is configured to determine and call the flight parameters matching the category of the seeker as the current flight parameters of the missile based on the determined category of the seeker and referring to the seeker category and flight parameter mapping data table.

[0033] It is fixedly installed in the inner cavity of the missile body through the missile-borne computer, wherein the missile body is provided with an electrical connection socket, and the electrical connection socket is provided with more than three identification sockets, which are respectively located at different positions of the socket and correspond to different types of seekers, and the seeker is provided with a category pin for characterizing the category of the seeker, the seeker is sleeved with the missile body, and the category pin corresponds to the corresponding identification socket, and the missile-borne computer includes an identification module, which is used to obtain the position of the category pin, and identify the category of the seeker according to the position of the category pin, and call the corresponding missile flight parameters according to the identification result. Rapid docking between the missile body and the seeker and simple identification of the seeker type are achieved, and the missile is automatically adapted to different types of seekers, which significantly improves the adaptability of the missile to battlefield conditions.

[0034] Further features and aspects of the present disclosure will become apparent from the following detailed description of exemplary embodiments with reference to the attached drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate exemplary embodiments, features, and aspects of the disclosure and, together with the description, serve to explain the principles of the disclosure.

[0036] Figure 1 A schematic diagram showing a missile according to an embodiment of the present disclosure;

[0037] Figure 2 A top view of a missile showing an embodiment of the present disclosure;

[0038] Figure 3 A schematic diagram showing an electrical connection socket of a missile according to an embodiment of the present disclosure;

[0039] Figure 4 A first schematic diagram showing an electrical connection plug of a missile according to an embodiment of the present disclosure;

[0040] Figure 5 A second schematic diagram showing an electrical connection plug of a missile according to an embodiment of the present disclosure;

[0041] Figure 6 A third schematic diagram showing an electrical connection plug of a missile according to an embodiment of the present disclosure;

[0042] Figure 7 A flow chart showing an identification module of an onboard computer of a missile according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0043] Various exemplary embodiments, features and aspects of the present disclosure will be described in detail below with reference to the accompanying drawings. The same reference numerals in the accompanying drawings represent elements with the same or similar functions. Although various aspects of the embodiments are shown in the accompanying drawings, the drawings are not necessarily drawn to scale unless otherwise specified.

[0044] The word “exemplary” is used exclusively herein to mean “serving as an example, example, or illustration.” Any embodiment described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments.

[0045] In addition, in order to better illustrate the present disclosure, numerous specific details are given in the following specific embodiments. It should be understood by those skilled in the art that the present disclosure can also be implemented without certain specific details. In some examples, methods, means, components and circuits well known to those skilled in the art are not described in detail in order to highlight the subject matter of the present disclosure.

[0046] Figure 1 FIG. 1 is a schematic diagram of a missile 100 according to an embodiment of the present disclosure. Figure 1 and Figure 2 As shown, the missile 100 comprises:

[0047] The missile body 110, the seeker head 120 and the missile-borne computer 130, wherein the missile-borne computer 130 is fixedly installed in the inner cavity of the missile body 110, wherein the missile body 110 is provided with an electrical connection socket 140, and the electrical connection socket 140 is provided with more than two identification sockets, which are respectively located at different positions of the socket and correspond to different categories of the seeker head 120, and the seeker head 120 is provided with a category pin for characterizing the category of the seeker head 120, the seeker head 120 is socketed with the missile body 110, and the category pin corresponds to the corresponding identification socket, and the missile-borne computer 130 includes an identification module, which is used to obtain the position of the category pin, identify the category of the seeker head 120 according to the position of the category pin, and call the corresponding missile flight parameters according to the identification result.

[0048] The missile-borne computer 130 is fixedly installed in the inner cavity of the missile body 110, wherein the missile body 110 is provided with an electrical connection socket 140, and the electrical connection socket 140 is provided with more than two identification sockets, which are respectively located at different positions of the socket and correspond to different types of seekers 120, and the seeker 120 is provided with a category pin for characterizing the category of the seeker 120, and the seeker 120 is sleeved with the missile body 110, and the category pin corresponds to the corresponding identification socket, and the missile-borne computer 130 includes an identification module, which is used to obtain the position of the category pin, and identify the category of the seeker 120 according to the position of the category pin, and call the corresponding missile flight parameters according to the identification result. The rapid docking of the missile body 110 and the seeker 120 and the simple and identifiable type of the seeker 120 are realized, and the missile automatically adapts to different types of seekers 120, which significantly improves the adaptability of the missile to battlefield conditions.

[0049] Specifically, in a possible implementation, see Figure 3 The first identification jack 141, the second identification jack 142 and the third identification jack 143 are located at different positions respectively. The first identification jack 141 is a TV image recognition jack, the second identification jack 142 is an infrared image recognition jack, and the third identification jack 143 is a laser semi-active recognition jack. The TV image recognition jack, the infrared image recognition jack and the laser semi-active recognition jack are all located at the opening of the inner cavity of the projectile body 110. For example, the onboard computer is electrically connected to the electrical connection socket 140, and is electrically connected to the television image recognition socket, the infrared image recognition socket and the laser semi-active socket through the electrical connection socket 140 respectively. The television image recognition socket, the infrared image recognition socket and the laser semi-active recognition socket are all located at the opening of the inner cavity of the projectile 110. The television image recognition socket, the infrared image recognition socket and the laser semi-active recognition socket are all circular. A mounting portion is provided at the opening of the inner cavity of the projectile 110 (i.e., the end face of the projectile 110 facing the guide head 120). The mounting portion is circular and is integrally formed with the projectile 110. The mounting portion is provided with a mounting hole, wherein the television image recognition socket is the first recognition socket, the infrared image recognition socket is the second recognition socket, and the laser semi-active socket is the third recognition socket. Among them, the three different types of seeker heads 120 have the same power supply method, and the electrical connection sockets connected to the missile body 110 are of the same size and have the same number of reserved category pin positions. Among them, three category pin positions are set for the seeker head 120 category, and the category pin position of each seeker head 120 is different. The category pin position of the same type of seeker head 120 is fixed; after the seeker head 120 is powered on, the on-board computer automatically identifies the type of seeker head 120 according to the different positions of the category pins, and its logic judgment module automatically calls the guidance control program and model parameters corresponding to the seeker head 120.

[0050] It should be noted that the control program in the onboard computer of the missile disclosed in the present invention can be implemented by conventional technical means in the art, which will not be described in detail here.

[0051] Furthermore, in a possible implementation, the seeker 120 also includes three types, and these three types of seekers 120 are respectively a television image seeker, an infrared image seeker and a laser semi-active seeker. Correspondingly, the television image seeker includes a television image plug, a television image category pin is provided on the television image plug, and the television image category pin is fixedly installed in the television image seeker; the infrared image seeker includes an infrared image plug, an infrared image plug is provided with an infrared image category pin, and the infrared image category pin is fixedly installed in the infrared image seeker; the laser semi-active seeker includes a laser semi-active plug, a laser semi-active plug is provided with a laser semi-active category pin, and the laser semi-active category pin is fixedly installed in the laser semi-active seeker.

[0052] Furthermore, in a possible implementation, a screw-on portion is provided at the connection between the guide head 120 and the projectile body 110, and the screw-on portion is sleeved on the projectile body 110 and can rotate around the projectile body. An electrical connection plug is provided on the end face of the guide head 120 facing the projectile body 110, and an electrical interface for fixing and installing a category pin is provided on the electrical connection plug, and the position of the electrical interface corresponds to the position of the identification socket, wherein a category pin is inserted into the electrical interface, and different positions of the electrical interface on the electrical connection plug represent different categories of the guide head 120.

[0053] Here, it should be noted that after the rotational connection portion of the seeker 120 is sleeved on the sleeve section of the projectile 110, it can be slightly rotated around the sleeve section, and the seeker 120 is fixedly connected to the projectile 110 by the micro-rotation, thereby ensuring that the seeker 120 is fixed to the projectile 110. Among them, those skilled in the art can understand that the sleeve micro-rotation connection between the seeker 120 and the projectile 110 can be achieved by conventional technical means in the art, which will not be described in detail here.

[0054] For further information, see Figure 4 In a possible implementation, the guide head 120 is a television image guide head, and a screw-on portion is provided at the opening of the television image guide head, and the screw-on portion is integrally formed with the television image guide head. An electrical connection plug is provided on the end surface of the television image guide head facing the body 110 (i.e., the rear end of the television image guide head), and the upper left corner of the electrical connection plug is an electrical interface corresponding to the television image category pin, and the television image category pin is plugged into the electrical interface.

[0055] For further information, see Figure 5In a possible implementation, the seeker 120 is an infrared image seeker, and a screw-on portion is provided at the opening of the infrared image seeker, and the screw-on portion is integrally formed with the infrared image seeker. An electrical connection plug is provided on the end surface of the infrared image seeker facing the projectile 110, and an electrical interface corresponding to the infrared image category pin is located in the middle of the upper side of the electrical connection plug, and the infrared image category pin is plugged into the electrical interface.

[0056] For further information, see Figure 6 In a possible implementation, the seeker 120 is a laser semi-active seeker, and a screw-on portion is provided at the opening of the laser semi-active seeker. The screw-on portion and the laser semi-active seeker are integrally formed. An electrical connection plug is provided on the end surface of the laser semi-active seeker facing the projectile 110. The upper right corner of the electrical connection plug is an electrical interface corresponding to the laser semi-active category pin, and the laser semi-active category pin is plugged into the electrical interface.

[0057] It should be noted that see Figure 3 , Figure 4 , Figure 5 and Figure 6 On the electrical connection socket 140 and the electrical connection plug, in addition to the first identification jack 141, the second identification jack 142, the third identification jack 143 and the electrical interfaces corresponding to each category of pins, there are also jacks and electrical interfaces for other purposes, which can be set using conventional technical means in the field and will not be described in detail here.

[0058] When the category pin of the corresponding seeker 120 is inserted into the corresponding socket, it means that the power is on. At this time, the onboard computer automatically identifies the type of seeker 120 according to the different positions of the category pin, and its logic judgment module automatically calls the guidance control program and model parameters corresponding to the seeker 120. Specifically, the identification module first obtains the status of each electrical connection socket 140, and the status of each electrical connection socket 140 can identify the power on and off status of the identification socket therein, and then obtains the position of the category pin according to the level status of each identification socket in the electrical connection socket 140. If one of the identification sockets is identified as being powered on, the position of the category pin corresponding to this identification socket can be determined, and then the category of the seeker 120 is obtained according to the position of the category pin, that is, the category of the seeker 120 corresponding to the position recorded in the built-in storage is obtained. Each category of the seeker 120 corresponds to a unique position identifier, and then the identifier of the category pin in the seeker 120 is obtained. The flight parameters corresponding to the category pin can be obtained according to the identifier. Similarly, each category pin has a one-to-one mapped flight parameter in the built-in storage of the onboard computer 130. The flight parameter is used as a control parameter, that is, the parameter information to be executed.

[0059] In one possible implementation, see Figure 7 First, execute step S100 to collect the information of the pin, and then make a judgment, that is, execute step S200 to determine whether the pin in jack No. 1 is at a high level. If the pin in jack No. 1 is not at a high level, execute step S300 to determine whether the pin in jack No. 2 is at a high level. If the pin in jack No. 2 is not at a high level, execute step S400 to determine whether the pin in jack No. 3 is at a high level. If the pin in jack No. 3 is not at a high level, execute step S500 to perform a fault self-check program. Further, if it is determined that the pin in jack No. 1 is at a high level, execute step S001 to call the missile control program corresponding to the television image seeker. If it is determined that the pin in jack No. 2 is at a high level, execute step S002 to call the missile control program corresponding to the infrared image seeker. If it is determined that the pin in jack No. 3 is at a high level, execute step S003 to call the missile control program corresponding to the laser semi-active seeker.

[0060] Furthermore, in a possible implementation, the projectile 110 includes a sleeve section, which extends to the outside of the projectile 110 and is suitable for being inserted into the seeker 120 and fixedly connected to the seeker 120. For example, a sleeve connection design is adopted between the projectile 110 and the seeker 120. During the connection process, the category pin of the seeker 120 is first aligned with the socket of the projectile 110 and inserted, and then the part is screwed into and tightened along the thread of the seeker 120 until the mark on the projectile 110 is aligned with the phase mark of the seeker 120. The seeker 120 and the missile body 110 are simply connected by a sleeve fast mechanical interface and an electrical socket, and a seeker 120 category pin is reserved in the seeker 120 socket, so that the rapid connection between the missile body 110 and the seeker 120 and the type of the seeker 120 can be easily identified. In addition, the missile-borne computer is electrically connected to the electrical connection socket through a bus. When the seeker 120 is connected to the missile body 110, that is, when the category pin is electrically connected to the corresponding connection socket, the seeker 120 type logic judgment module in the missile-borne computer can automatically identify the seeker 120 and can automatically call the control program and model parameters corresponding to the type of the seeker 120, so that the missile can automatically adapt to different types of seekers 120, which significantly improves the adaptability of the missile to battlefield conditions. In addition, the aerodynamic shape of the missile disclosed in the present invention has a compact overall layout, increases the lift-to-drag ratio, improves the control efficiency of the missile, and reduces the rolling interference torque caused by the deflection of the rudder wing, so that the missile disclosed in the present invention is suitable for subsonic flight at 0.1 to 0.9 Ma.

[0061] It should be noted that the weight of the missile disclosed herein is no more than 15 kg, and it is an aerodynamic shape structure of a small missile launched in a canister form.

[0062] Furthermore, in a possible implementation, the inner cavity of the projectile 110 is provided with a mounting tube, wherein the shape and size of the mounting tube are consistent with the appearance of the onboard computer, the onboard computer is fixedly installed in the mounting tube, the onboard computer and the mounting tube can be connected by screw connection, and a first support rod and a second support rod are provided between the mounting tube and the inner cavity of the projectile 110, the first support rod and the second support rod are both integrally formed with the projectile 110, and the first support rod and the second support rod can be screwed or welded to the mounting tube.

[0063] In another possible implementation, a first bearing is installed at the tail of the missile body 110, and a plurality of tail fins are arranged on the first bearing. The tail fins are rectangular, and one end (the short side end) of the tail fins is welded to the bearing, and the angles between the tail fins are equal. For example, see Figure 1 The tail of the projectile 110 is equipped with a first bearing, and four tail fins are installed on the bearing. Each tail fin has the same size, shape and material. The four tail fins are all rectangular, and the angle between each tail fin is a right angle. Among them, the tail fin is rectangular, and one side of the short side of the tail fin is fixedly connected to the first bearing, and the connection method can be welding. The tail fin adopts a large aspect ratio and free rotation. The free tail fin eliminates the rolling interference torque of the projectile 110 caused by the deflection of the rudder wing, and further increases the trajectory change capability of the projectile 110.

[0064] Furthermore, in a possible implementation, an engine is installed in the inner cavity of the missile body 110, the engine is close to the tail of the missile body 110, a second bearing is installed on the outer side of the missile body 110, a plurality of rudder wings are arranged on the second bearing, the rudder wings are trapezoidal, one end of the rudder wing is welded to the bearing, and the angles between the rudder wings are equal. For example, see Figure 1 A second bearing is installed on the outer side of the middle part of the missile body 110, and four rudder wings are installed on the second bearing. The size, shape and material of each rudder wing are the same. The four rudder wings are all trapezoidal, and the angle between each rudder wing is a right angle. The direction of the rudder wing and the tail wing are consistent. Among them, the rudder wing of the present invention adopts a small aspect ratio. The small aspect ratio of the rudder wing not only increases the lift-to-drag ratio of the missile body 110, but also has a higher aerodynamic efficiency at a large angle of attack. The rudder shaft is located in front of the center of mass to ensure that the control force and torque are beneficial to the control of the missile body 110. The distance from the center of mass is small, and the center of mass direct driving force can be generated, which further increases the trajectory change capability of the missile body 110. The missile disclosed in the present invention is suitable for the aerodynamic shape of a small missile launched by a barrel and flying at a subsonic speed, including a combined aerodynamic shape of a rudder wing at the front of the missile body and a tail wing at the rear of the missile body. The ratio of the span length of the rudder wing to the chord length is 1:6.2. The tail wing is mounted on a freely rotatable bearing, and the overall shape is an "×-×" duck-type aerodynamic layout.

[0065] It should be noted that, although the missiles disclosed in the present invention are described above by taking the above embodiments as examples, those skilled in the art will appreciate that the present invention should not be limited thereto. In fact, the user can flexibly set the missiles according to personal preferences and / or actual application scenarios, as long as the desired functions are achieved.

[0066] In this way, the missile-borne computer 130 is fixedly installed in the inner cavity of the missile body 110, wherein the missile body 110 is provided with an electrical connection socket 140, and the electrical connection socket 140 is provided with more than two identification sockets, which are respectively located at different positions of the socket and correspond to different types of seekers 120, and the seeker 120 is provided with a category pin for characterizing the category of the seeker 120, and the seeker 120 is sleeved with the missile body 110, and the category pin corresponds to the corresponding identification socket, and the missile-borne computer 130 includes an identification module, which is used to obtain the position of the category pin, and identify the category of the seeker 120 according to the position of the category pin, and call the corresponding missile flight parameters according to the identification result. Rapid docking of the missile body 110 and the seeker 120 and simple identification of the type of the seeker 120 are achieved, and the missile automatically adapts to different types of seekers 120, which significantly improves the adaptability of the missile to battlefield conditions.

[0067] The embodiments of the present disclosure have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The selection of terms used herein is intended to best explain the principles of the embodiments, practical applications, or technical improvements in the market, or to enable other persons of ordinary skill in the art to understand the embodiments disclosed herein.

Claims

1. A missile, characterized in that: include: missile body, seeker and onboard computer; The onboard computer is fixedly installed in the inner cavity of the missile body; Wherein, the projectile body is provided with an electrical connection socket, and the electrical connection socket is provided with more than two identification sockets, and the more than two identification sockets are respectively located at different positions of the socket and correspond to different types of guide heads; The seeker is provided with a category pin for characterizing the category of the seeker; The seeker is sleeved with the missile body, and the category pin corresponds to the corresponding identification socket; the missile-borne computer includes an identification module; The identification module is used to obtain the position of the category pin, identify the category of the seeker according to the position of the category pin, and call the corresponding missile flight parameters according to the identification result; A screw connection portion is provided at the connection between the guide head and the projectile body, and the screw connection portion is sleeved on the projectile body and can rotate around the projectile body; An electrical connection plug is provided on the end surface of the guide head facing the projectile; The electrical connection plug is provided with an electrical interface for fixing and installing the category pin, and the position of the electrical interface corresponds to the position of the identification socket; Wherein, the electrical interface is provided with the type of pins; and Different positions of the electrical interface on the electrical connection plug represent different types of the seeker; The electrical connection socket is arranged on the end surface of the projectile body facing the guide head.

2. The missile according to claim 1, characterized in that: The identification sockets include a first identification socket, a second identification socket and a third identification socket; The first identification jack is a television image identification jack; The second identification socket is an infrared image identification socket; The third identification socket is a laser semi-active identification socket.

3. The missile according to claim 2, characterized in that: A mounting portion is provided at the end surface of the projectile body connected to the guide head; The mounting portion is circular; The mounting portion is integrally formed with the elastic body; The electrical connection socket is embedded in the fixing hole provided on the mounting portion and is fixedly connected to the side wall of the fixing hole.

4. The missile according to claim 1, characterized in that: The projectile body includes a sleeve section; The sleeve section extends to the outside of the projectile and is suitable for being inserted into the guide head and fixedly connected to the guide head.

5. The missile according to claim 1, characterized in that: The screw-on portion is integrally formed with the guide head, and the electrical connection plug is integrally formed with the guide head.

6. The missile according to any one of claims 1 to 5, characterized in that: The category pins include any one of a television image pin, an infrared image pin and a laser semi-active pin.

7. The missile according to any one of claims 1 to 5, characterized in that: The identification module includes a state acquisition unit, a position determination unit and a category determination unit; The state acquisition unit is configured to acquire the current power-on state of each of the identification sockets; The position determination unit is configured to determine the current position of the category pin on the seeker according to the current power-on state of the identification jack; The category determination unit is configured to determine the category of the seeker according to the current position of the category pin.

8. The missile according to claim 1, characterized in that: The identification module also includes a flight parameter acquisition unit; The flight parameter acquisition unit is configured to determine and call the flight parameters matching the category of the seeker as the current flight parameters of the missile based on the determined category of the seeker and referring to the seeker category and flight parameter mapping data table.

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