Device and method for verifying single-machine positioning capability of electronic warfare equipment

Abstract

The invention provides an electronic warfare equipment stand-alone positioning capability verification device and method, the device comprises a flight platform, and electronic warfare equipment, an inertial navigation simulator and display control equipment which are carried on the flight platform, and the flight platform flies around a radiation source target; wherein the electronic warfare equipment is used for acquiring reconnaissance data of a radiation source target and completing positioning, a positioning algorithm is built in the electronic warfare equipment, and the positioning algorithm is used for performing positioning calculation on the radiation source target according to the reconnaissance data and inertial navigation data; the inertial navigation simulator is used for providing real-time inertial navigation data and a radiation source target position; and the display control equipment is used for verifying the positioning settlement result of the electronic warfare equipment by using the radiation source target position provided by the inertial navigation simulator. According to the invention, verification of the single-machine positioning capability of the electronic warfare equipment is realized in a desktop environment, on one hand, the test verification efficiency is improved, on the other hand, a scene required by positioning can be flexibly and conveniently simulated, and manpower and material resource consumption of flight test verification is saved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of airborne electronic warfare, and in particular to an electronic warfare equipment single-machine positioning capability verification device and method. BACKGROUND

[0002] Acquiring accurate position information of a radiation source target is a key for airborne electronic warfare equipment to perceive an electromagnetic situation, avoid threat targets and generate electromagnetic intelligence, and directly affects the exertion of combat effectiveness. Single-machine positioning methods of airborne electronic warfare equipment mainly include cross positioning and fast positioning. Regardless of which positioning method, electronic warfare equipment needs to continuously detect radiation source target signals, and a positioning angle is formed by platform movement to solve the positioning result. Therefore, the positioning of a radiation source target needs conditions such as detecting radiation source target signals, acquiring platform inertial navigation data and forming a positioning angle by platform movement. Traditional methods are difficult to construct the required conditions for positioning in a desktop environment, and therefore can only verify the positioning performance of equipment in a test flight. On the one hand, the test flight verification consumes huge manpower and material resources, and on the other hand, it is limited by test target and test flight airspace, and can only verify specific scenarios, and it is difficult to fully verify the boundaries of the positioning performance. SUMMARY

[0003] Embodiments of the present application provide an electronic warfare equipment single-machine positioning capability verification device and method, which are used to solve the problems in the background art.

[0004] Other characteristics and advantages of the present application will become apparent from the following detailed description, or will be learned by practice of the present application.

[0005] According to a first aspect of embodiments of the present application, an electronic warfare equipment single-machine positioning capability verification device is provided, comprising a flight platform, and electronic warfare equipment, an inertial navigation simulator and a display and control device carried on the flight platform, the flight platform flies around a radiation source target; wherein The electronic warfare equipment is used to acquire reconnaissance data of the radiation source target and complete positioning, the electronic warfare equipment is built-in with a positioning algorithm, the positioning algorithm is used to position and solve the radiation source target according to the reconnaissance data and inertial navigation data; The inertial navigation simulator is used to provide real-time inertial navigation data and a radiation source target position; The display and control device is used to verify the positioning result of the electronic warfare equipment by using the radiation source target position provided by the inertial navigation simulator.

[0006] According to an embodiment of the present application, the positioning algorithm comprises: The distance between the flight platform and the radiation source target is calculated according to the flight time of the flight platform, the change angle of the heading angle and the flight data; Combining the direction-finding angle of the radiation source target by the electronic warfare equipment and the position information of the flight platform, the position of the radiation source target is calculated.

[0007] According to one embodiment of the present application, the formula for calculating the distance of the flight platform from the radiation source target is:

[0008] wherein R is the distance of the flight platform from the radiation source target, is the flight speed of the flight platform, is the flight time of the flight platform, is the change angle of the heading angle.

[0009] According to one embodiment of the present application, the process for obtaining the real-time inertial navigation data and the position of the radiation source target comprises: loading the inertial navigation model in the inertial navigation simulator from the inertial navigation model; setting the initial position, speed, radiation source distance and inertial navigation data rate of the flight platform in the inertial navigation simulator according to the test verification condition requirement, and calculating the position of the radiation source target and the real-time inertial navigation data by the inertial navigation model.

[0010] According to one embodiment of the present application, the inertial navigation model comprises:

[0011] wherein, is the function for calculating the position of the flight platform at B from the position of the radiation source target , the heading angle , the distance R, and the height difference between the radiation source target and the flight platform; is the height of the flight platform at point A, is the time for the flight platform from point A to point B, is the flight speed of the flight platform. According to one embodiment of the present application, the direction-finding calibration is performed in real time during the flight of the flight platform around the radiation source target; the direction-finding calibration comprises: making the direction-finding angle of the electronic warfare equipment to the radiation source target stable at 90 degrees.

[0012] According to one embodiment of the present application, the radiation source target is simulated by a signal source, and the signal source is configured by the display control device according to the parameters of the radiation source target, and the power of the signal source is adjusted so that the electronic warfare equipment can normally receive signals.

[0013] According to one embodiment of the present application, the electronic warfare equipment further comprises pre-processing the data of the signal source to generate a reconnaissance signal.

[0014] According to one embodiment of the present application, the electronic warfare equipment further comprises pre-processing the data of the signal source to generate a reconnaissance signal. ​

[0015] According to a second aspect of the present application, an electronic warfare equipment single-machine positioning capability verification method is provided, which is implemented based on the electronic warfare equipment single-machine positioning capability verification device of the first aspect, and specifically comprises the following steps: An inertial navigation model is loaded in the inertial navigation simulator, and the initial position, speed, radiation source distance and inertial navigation data rate parameters of the flight platform are set in the inertial navigation simulator according to the test verification condition requirements; the position of the radiation source target calculated by the inertial navigation simulator is output to the display control device, and the real-time inertial navigation data of the flight platform is sent to the electronic warfare equipment; The signal source is configured by the display control device according to the parameter information of the radiation source target; and the flight of the flight platform is controlled at the same time; The electronic warfare equipment receives the signal of the signal source and processes it into reconnaissance data, and then combines the inertial navigation data output by the inertial navigation simulator to perform positioning calculation on the radiation source target, and outputs the positioning result to the display control device; The display control device displays the positioning result of the radiation source target, and combines the position of the radiation source target output by the inertial navigation simulator to evaluate the accuracy of the positioning result.

[0016] According to an embodiment of the present application, the flight platform flies around the signal source, and the direction-finding angle of the signal source by the electronic warfare equipment is always 90 degrees.

[0017] Compared with the prior art, the beneficial effects of the above technical solution are: 1. The electronic warfare equipment single-machine positioning capability verification is realized in a desktop environment, which greatly improves the test verification efficiency on the one hand, and flexibly and conveniently simulates the radiation source target, flight path of the flight platform and test airspace and other scenes required for positioning on the other hand, thereby saving the huge manpower and material consumption of flight test verification; 2. The present application can quickly and simply construct various boundary conditions according to verification requirements, fully test and verify the single-machine positioning performance of the electronic warfare equipment, and avoid the problem that the verification is insufficient due to limited conditions in flight test verification. BRIEF DESCRIPTION OF DRAWINGS

[0018] The accompanying drawings, which are incorporated into and form part of the specification, illustrate embodiments consistent with the present application and, together with the specification, serve to explain the principles of the application. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor on the basis of these drawings.

[0019] Figure 1 The electronic warfare equipment single-machine positioning capability verification device schematic diagram proposed for the embodiments of the present application.

[0020] Figure 2This is a schematic diagram of a desktop verification model for the single-unit positioning capability of electronic warfare equipment according to an embodiment of this application.

[0021] Figure 3 This is a schematic diagram of the inertial navigation model according to an embodiment of this application.

[0022] Figure 4 This is a schematic diagram of the structure of an electronic device provided in an embodiment of this application. Detailed Implementation

[0023] The embodiments of this application are described in detail below, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar modules or modules having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this application, and should not be construed as limiting this application. Rather, the embodiments of this application include all variations, modifications, and equivalents falling within the spirit and scope of the appended claims.

[0024] Example 1 To verify the equipment's positioning capabilities, please refer to... Figure 1 This application proposes an electronic warfare equipment single-unit positioning capability verification device, including a flight platform and electronic warfare equipment, inertial navigation simulator and display and control equipment mounted on the flight platform. During verification, the flight platform flies around the radiation source target.

[0025] Specifically, electronic warfare equipment is mainly used to acquire reconnaissance data of radiation source targets and complete their location. In this embodiment, the electronic warfare equipment has a built-in location algorithm, which is used to calculate the location of the radiation source target based on reconnaissance data and inertial navigation data. The inertial navigation simulator is mainly used to provide real-time inertial navigation data and the location of the radiation source target. The display and control equipment is mainly used to verify the location calculation results of the electronic warfare equipment using the radiation source target location provided by the inertial navigation simulator.

[0026] In this embodiment, the specific implementation process of the positioning algorithm in electronic warfare equipment is given: First, the distance between the flight platform and the radiation source target is calculated based on the flight time, the change angle of the heading angle of the flight platform and the flight data; then, the position of the radiation source target is calculated by combining the direction finding angle of the radiation source target of the electronic warfare equipment and the position information of the flight platform.

[0027] To further illustrate the implementation process of the positioning algorithm proposed in this embodiment, the following is a detailed explanation. Figure 2 The desktop verification model for the single-unit positioning capability of electronic warfare equipment is described in detail.

[0028] The radiation source target is located at point P. An airborne platform equipped with electronic warfare gear, centered on the radiation source target, is at a distance of... The flight platform flies at a constant speed along a circle with radius R. The line of sight between the flight platform and the radiation source rotates at an angular velocity The angle between the line connecting the flight platform and the radiation source and the flight direction of the flight platform is The angle between the line connecting the flight platform and the radiation source and the flight direction of the flight platform is The following relationship can be obtained according to the principle of dynamics: (1) According to equation (1), the distance R between the flight platform and the radiation source target can be obtained as: (2) The flight platform moves at a constant speed from point A to point B, and the flight path is a circle with the radiation source target as the center, so the following relationship exists: (3) In time , the flight platform moves from point A to point B, and the change angle of the flight direction of the flight platform is When the time is very short, the angular velocity can be obtained as: (4) Substituting equations (3) and (4) into equation (2), we obtain: (5) From the above analysis, according to the flight time of the flight platform, the change angle of the flight direction, and the flight speed , the distance R between the flight platform and the radiation source target can be calculated, and then the position of the radiation source target can be calculated by combining the direction-finding angle of the electronic warfare equipment to the radiation source target and the position information of the flight platform.

[0029] In this embodiment, the inertial navigation simulator provides real-time inertial navigation data and the position of the radiation source target through the internal inertial navigation model. Specifically, first, load the inertial navigation model in the inertial navigation simulator according to the test verification condition requirements, set the initial position, speed, radiation source distance, and inertial navigation data rate of the flight platform in the inertial navigation simulator, and calculate the position of the radiation source target and real-time inertial navigation data through the inertial navigation model.

[0030] For reference Figure 3 , in this embodiment, a specific inertial navigation model diagram is given, in which point A is the initial point of the flight platform movement, the flight direction angle of the aircraft is , the position coordinates are , the flight speed is , the distance between the flight platform and the radiation source target is R, and the height difference is Then, according to the earth coordinate model, the coordinates of the radiation source target can be obtained is: (6) In the above formula, is a function of the position of the radiation source target A, the heading angle the distance R and the height difference . The position of the radiation source target O is calculated.

[0031] After time t, the aircraft moves from point A to point B, and the heading angle of the aircraft at point B can be calculated as: (7) Because the aircraft platform flies around the target, the distance from the target at point B is R, and the height difference from the target is , the position of the aircraft platform at point B can be calculated as: is: (8) In the above formula, is a function of the position of the radiation source target A, the heading angle the distance R and the height difference . The position of the aircraft at point B is calculated. By substituting equation (7) into equation (8), we get: (9) In summary, by setting the initial position of the aircraft platform, the distance and height difference between the aircraft platform and the target, and the speed of the aircraft platform, the heading angle and position of the aircraft platform at any time can be calculated, and real-time inertial navigation information can be obtained.

[0032] It should be particularly noted that in the present embodiment, the direction finding calibration is performed in real time during the flight of the aircraft platform around the radiation source target; the direction finding calibration includes: making the direction finding angle of the electronic warfare equipment to the radiation source target stable at 90 degrees.

[0033] In actual application, the radiation source target is simulated by a signal source, and the signal source is configured by the display control device according to the parameters of the radiation source target, and the power of the signal source is adjusted so that the electronic warfare equipment can normally receive signals.

[0034] In one embodiment, the electronic warfare equipment further includes pre-processing of the data of the signal source, generating a reconnaissance signal, and the positioning algorithm completes the positioning result calculation according to the reconnaissance signal.

[0035] Compared with the traditional scheme, the electronic warfare equipment single machine positioning capability verification device proposed in the present embodiment has the following advantages: 1. The desktop environment realizes the single machine positioning capability verification of electronic warfare equipment, which greatly improves the test verification efficiency, and flexibly and conveniently simulates the required radiation source target, aircraft platform flight path and test airspace and other scenes, saving the huge manpower and material consumption of test flight verification; 2. The application can quickly and simply construct various boundary conditions according to verification requirements, fully test and verify the single machine positioning performance of electronic warfare equipment, and avoid the problem of insufficient verification due to limited conditions in test flight verification.

[0036] Embodiment 2 Based on the embodiment 1, the embodiment provides a single machine positioning capability verification method of electronic warfare equipment, which is realized based on the single machine positioning capability verification device of electronic warfare equipment in the embodiment 1, and specifically includes the following steps: S100, loading an inertial navigation model in an inertial navigation simulator, setting the initial position, speed, radiation source distance and inertial navigation data rate parameters of the flight platform in the inertial navigation simulator according to the test verification condition requirements, calculating the position of the radiation source target by the inertial navigation simulator and outputting the position to a display control device, and sending the real-time inertial navigation data of the flight platform to the electronic warfare equipment; S200, configuring a signal source by the display control device according to the parameter information of the radiation source target; and controlling the flight of the flight platform; S300, the display control device controls the normal work of the electronic warfare equipment, the electronic warfare equipment receives the signal of the signal source and processes it into reconnaissance data, then combines the inertial navigation data output by the inertial navigation simulator to perform positioning calculation on the radiation source target, and outputs the positioning result to the display control device; S400, the display control device displays the positioning result of the radiation source target, and combines the position of the radiation source target output by the inertial navigation simulator to evaluate the accuracy of the positioning result.

[0037] In S200, when the flight platform is controlled to fly, the flight platform flies around the signal source and performs direction finding calibration, so that the direction finding angle of the electronic warfare equipment to the signal source always remains 90 degrees.

[0038] Based on the same technical concept, the embodiment of the application further provides an electronic device, which can realize the single machine positioning capability verification method of electronic warfare equipment provided by the above-mentioned embodiments of the application. In one embodiment, the electronic device is realized as a display control device, as shown in Figure 4 The electronic device can include: at least one processor, and a memory connected with the at least one processor, and the specific connection medium between the processor and the memory in the embodiment of the application is not limited, Figure 4 for example, the connection between the processor and the memory through a bus. The bus is connected Figure 4The connection between the other components is indicated by a thick line, which is only illustrative and not limited. The bus can be divided into an address bus, a data bus, a control bus, etc. For convenience, Figure 4 The bus is indicated by a thick line, but it does not mean that there is only one bus or one type of bus. Alternatively, the processor can also be called a controller, and the name is not limited.

[0039] In the embodiment of the application, the memory stores instructions executable by the at least one processor, and the at least one processor can execute the electronic warfare equipment single-machine positioning capability verification method flow discussed above by executing the instructions stored in the memory. The processor can realize Figure 4 The functions of each module in the device shown.

[0040] The processor is the control center of the device, and can connect each part of the control device through various interfaces and lines. By running or executing the instructions stored in the memory and calling the data stored in the memory, the device processes data and performs various functions, thereby monitoring the device as a whole.

[0041] In an alternative design, the processor can include one or more processing units, and the processor can integrate an application processor and a modem processor, wherein the application processor mainly processes the operating system, user interface and application program, etc., and the modem processor mainly processes wireless communication. It can be understood that the above-mentioned modem processor can also not be integrated into the processor. In some embodiments, the processor and the memory can be implemented on the same chip, and in some embodiments, they can also be implemented on separate chips respectively.

[0042] The processor can be a general-purpose processor, such as a CPU, a digital signal processor, an application-specific integrated circuit, a field programmable gate array, or other programmable logic device, a discrete gate or transistor logic device, a discrete hardware component, which can realize or execute the methods, steps and logic block diagrams disclosed in the embodiments of the application. The general-purpose processor can be a microprocessor or any conventional processor. The steps of the electronic warfare equipment single-machine positioning capability verification method flow disclosed in the embodiments of the application can be directly embodied as execution completed by a hardware processor, or executed by a combination of hardware and software modules in the processor.

[0043] The memory, as a non-volatile computer readable storage medium, can be used to store non-volatile software programs, non-volatile computer executable programs and modules. The memory can include at least one type of storage medium, for example, can include flash memory, hard disk, multimedia card, card type memory, random access memory (RAM), static random access memory (SRAM), programmable read-only memory (PROM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), magnetic memory, magnetic disk, optical disk, etc. The memory is any other medium capable of carrying or storing desired program code in the form of instructions or data structures and capable of being accessed by a computer, but is not limited thereto. The memory in the embodiments of the application can also be a circuit or any other device capable of realizing the storage function, used for storing program instructions and / or data.

[0044] By designing and programming the processor, the code corresponding to the electronic warfare equipment single machine positioning capability verification method flow introduced in the foregoing embodiments can be fixed into the chip, so that the chip can execute the steps of the method of the foregoing embodiments when running. How to design and program the processor is a technology known to those skilled in the art, and will not be described here.

[0045] and at least one display for human-computer interaction and display of a corresponding interface.

[0046] Based on the same inventive concept, the embodiments of the present application also provide a storage medium storing computer instructions, when the computer instructions run on a computer, the computer instructions make the computer execute the electronic warfare equipment single machine positioning capability verification method flow discussed above.

[0047] In some optional embodiments, the present application also provides that each aspect of the electronic warfare equipment single machine positioning capability verification method flow can also be realized in the form of a program product, which includes program codes, when the program product runs on the device, the program codes are used to make the control device execute the steps of the electronic warfare equipment single machine positioning capability verification method flow according to various exemplary embodiments of the present application described in the specification.

[0048] It should be noted that, although several units or sub-units of the apparatus are mentioned in the above detailed description, such division is merely exemplary and not mandatory. Indeed, according to an embodiment of the application, the features and functionalities of two or more units described above can be embodied in one unit. Conversely, the features and functionalities of one unit described above can be further divided into units embodied by several units. Moreover, although the operations of the method of the application are described in a particular, sequential order, this is not necessarily the case. Indeed, certain of the steps can be performed in a different order than that described, or can be performed concurrently. Additionally or alternatively, certain steps can be omitted, combined, or further divided into multiple steps.

[0049] Those skilled in the art will appreciate that embodiments of the application can be devised for a method, a system, or a computer program product. Accordingly, the present application can be embodied in the form of an entirely hardware embodiment, an entirely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present application can take the form of a computer program product on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROMs, optical storage devices, etc.) embodying computer readable program code.

[0050] The present application is described in reference to the flowchart illustrations and / or block diagrams of the methods, apparatus (systems) and computer program products according to embodiments of the application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general purpose computer, special purpose computer, embedded processing system or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart illustrations and / or block diagrams block or blocks. Figure 1 one or more functions specified in the flowchart illustrations and / or block diagrams block or blocks. Figure 1 one or more functions specified in the flowchart illustrations and / or block diagrams block or blocks.

[0051] The program code can be written in any combination of one or more programming languages, including an object oriented programming language such as Java, C++, or the like, and conventional procedural programming languages, such as the "C" programming language or similar programming languages. The program code can execute entirely on the user's computing device, partly on the user's computing device, as a stand-alone software package, partly on the user's computing device and partly on a remote computing device or entirely on the remote computing device or server.

[0052] In situations where the remote computing device is involved, the remote computing device can be connected to the user computing device through any kind of network, including a local area network (LAN) or a wide area network (WAN), or can be connected to an external computing device (e.g., using an Internet service provider to connect through the Internet).

[0053] These computer program instructions can also be stored in a computer readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer readable memory produce an article of manufacture including instructions which implement the flow Figure 1 The functions specified in the flow or flows and / or blocks Figure 1 The functions specified in the flow or flows and / or blocks

[0054] These computer program instructions can also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the flow Figure 1 The functions specified in the flow or flows and / or blocks Figure 1 The functions specified in the flow or flows and / or blocks

[0055] The above only is the preferred embodiment of the present application, and is not intended to limit the present application. Any modification, equivalent replacement, improvement, etc. within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. An electronic warfare equipment single unit positioning capability verification device, characterized in that, The electronic warfare equipment is used for acquiring reconnaissance data of the radiation source target and completing positioning, the electronic warfare equipment is internally provided with a positioning algorithm, and the positioning algorithm is used for positioning the radiation source target according to the reconnaissance data and inertial navigation data. The positioning algorithm comprises the following steps: The distance between the flight platform and the radiation source target is calculated according to the flight time, the heading angle change angle and the flight data of the flight platform; The position of the radiation source target is calculated by combining the direction finding angle of the radiation source target and the position information of the flight platform.

2. The electronic warfare equipment single unit positioning capability verification device of claim 1, wherein, The calculation formula of the distance between the flight platform and the radiation source target is as follows: The acquisition process of the real-time inertial navigation data and the position of the radiation source target comprises the following steps: An inertial navigation model is loaded in the inertial navigation simulator according to the test verification condition requirement; 3. The electronic warfare equipment single unit positioning capability verification device of claim 2, wherein, The initial position, the speed, the radiation source distance and the inertial navigation data rate of the flight platform are set in the inertial navigation simulator, and the position of the radiation source target and the real-time inertial navigation data are calculated through the inertial navigation model. Wherein, R is the distance between the flight platform and the radiation source target, V is the flight speed of the flight platform, T is the flight time of the flight platform, is the change angle of the heading angle.

4. The electronic warfare equipment single unit positioning capability verification device according to claim 1 or 2, characterized in that, The inertial navigation model comprises the following steps: During the flight of the flight platform around the radiation source target, the direction finding calibration is performed in real time. The direction finding calibration comprises the following steps: the direction finding angle of the electronic warfare equipment to the radiation source target is stabilized to 90 degrees.

5. The electronic warfare equipment single unit positioning capability verification device of claim 4, wherein, The radiation source target adopts a signal source simulation, the signal source is configured according to the parameter of the radiation source target by the display control device, and the power of the signal source is adjusted so that the electronic warfare equipment can normally receive signals. wherein, is the target position of the radiation source, is the heading angle, is the distance R, the height difference between the radiation target source and the flight platform, calculates the position of the flight platform at B, is a function of time; is the height of the flight platform at point A, is the time of the flight platform from point A to point B, is the flight speed of the flight platform.

6. The electronic warfare equipment single unit positioning capability verification apparatus of claim 1, wherein, The electronic warfare equipment further comprises preprocessing the data of the signal source to generate reconnaissance signals. The electronic warfare equipment single-machine positioning capability verification device is realized according to any one of claims 1 to 8, and specifically comprises the following steps:

7. The electronic warfare equipment single unit positioning capability verification apparatus of claim 1, wherein, An inertial navigation model is loaded in the inertial navigation simulator, the initial position, the speed, the radiation source distance and the inertial navigation data rate parameters of the flight platform are set in the inertial navigation simulator according to the test verification condition requirement, the position of the radiation source target is calculated by the inertial navigation simulator and output to the display control device, and the real-time inertial navigation data of the flight platform is sent to the electronic warfare equipment; 8. The electronic warfare equipment single unit positioning capability verification apparatus of claim 1, wherein, The signal source is configured according to the parameter information of the radiation source target by the display control device, and the flight platform is controlled to fly; 9. An electronic warfare equipment single unit positioning capability verification method, characterized in that, The electronic warfare equipment receives the signals of the signal source and processes them into reconnaissance data, then the radiation source target is positioned according to the inertial navigation data output by the inertial navigation simulator, and the positioning result is output to the display control device; The display control device displays the positioning result of the radiation source target, and the accuracy of the positioning result is evaluated according to the position of the radiation source target output by the inertial navigation simulator. The flight platform flies around the signal source, and the direction finding angle of the electronic warfare equipment to the signal source is always 90 degrees. ​ ​ 10. The method of claim 9, wherein: ​

Images