A method for simulating the arrival angle of a radiation source for an amplitude comparison direction finding system

Abstract

The present invention discloses a method for simulating the arrival angle of a radiation source for an amplitude comparison direction finding system, comprising the following steps: S1, determining the position coordinates and attitude angles; S2, performing coordinate transformation; S3, calculating the signal power received by each receiving antenna; S4, generating pulse description word data; S5, synthesizing the simulated signal of the arrival angle of the target radar. The present invention can flexibly and efficiently simulate the arrival angle signal of a six-degree-of-freedom moving target radar for an amplitude comparison direction finding system, bringing the simulation of complex test scenarios into the laboratory, and greatly reducing the test cost and development time.

Description

Technical Field

[0001] The present invention relates to a method for simulating the angle of arrival of a radiation source, and in particular to a method for simulating the angle of arrival of a radiation source for an amplitude comparison direction finding system, belonging to the technical field of electronic countermeasures. Background Art

[0002] Airborne radar warning equipment is an indispensable electronic countermeasure equipment on modern combat aircraft, mainly used to issue warning prompts for enemy radar threat signals, so that pilots can take corresponding actions and improve the survival ability of the aircraft during wartime. Therefore, it is necessary to evaluate the actual combat effectiveness of airborne radar warning equipment in the above environment, such as the evaluation of direction finding ability.

[0003] The radar warning equipment of the amplitude comparison direction finding system has multiple directional receiving antennas with different directions. For the signals radiated by the same spatial target radar, the signal powers received by each antenna will be different, and there is a certain mapping relationship between this difference and the angle of arrival of the signal. Therefore, according to its mapping relationship, by synthesizing coherent signals with different powers in multiple paths, the radar radiation signals of targets with different angles of arrival can be simulated.

[0004] At present, the conventional test equipment for the radar warning equipment of this system can only perform single fixed angle of arrival simulation tests or limited discrete angle of arrival simulation tests, and does not have the ability to simulate the continuous change of the angle of arrival in a dynamic scenario. In the actual combat process, both the aircraft and the target platform are moving. Therefore, the function of simulating the dynamic change of signals is required, and the existing research cannot meet the requirements of the dynamic electromagnetic scenario. The so-called dynamic electromagnetic scenario has two meanings. One is that the aircraft and the target platform are moving in three-dimensional space, and during the movement, their azimuth, distance, and attitude angles may change with time. The other is that the working mode of the target radar will change according to the specific battlefield situation. Both will affect the signals, resulting in the parameters of the signals intercepted by the antenna of the radar warning equipment being dynamically changed. The present invention can edit the simulation scenario according to the actual combat process and dynamically simulate the angle of arrival signals. Summary of the Invention

[0005] In order to solve the problem that the above technology can only perform single fixed angle of arrival simulation tests or limited discrete angle of arrival simulation tests, the present invention provides a method for simulating the angle of arrival of a radiation source for an amplitude comparison direction finding system, which can flexibly and efficiently simulate the target radar signals in a three-dimensional motion scenario, be closer to the actual application scenario, improve the test efficiency and reduce the test cost.

[0006] In order to solve the above technical problems, the technical solution adopted by the present invention is: a method for simulating the angle of arrival of a radiation source for an amplitude comparison direction finding system, including the following steps:

[0007] S1. Determine the position coordinates and attitude angles;

[0008] S2. Perform coordinate transformation;

[0009] S3. Calculate the signal power received by each receiving antenna;

[0010] S4. Generate pulse descriptor word data;

[0011] S5. Synthesize the arrival angle simulation signal of the target radar.

[0012] Preferably, the method specifically includes the following steps:

[0013] S1. Determine the position coordinates and attitude angles of the carrier aircraft and the target platform according to the set motion scenario;

[0014] S2. Perform coordinate transformation according to the position coordinates and attitude angle information of the carrier aircraft and the target platform, and respectively obtain the position coordinates of the target platform in the body coordinate system of the carrier aircraft and the position coordinates of the carrier aircraft in the target platform coordinate system;

[0015] S3. According to the above two position coordinates, combined with the directivity patterns of the receiving antennas of the radar warning device and the target radar antenna, the scanning mode of the target radar antenna, the signal frequency, and the transmitting power of the target radar in the set scenario, calculate the signal power received by each receiving antenna of the radar warning device.

[0016] S4. Generate pulse descriptor word data according to the power of the received signals of each receiving channel of the carrier aircraft radar warning device, combined with the target radar signal format in the set scenario;

[0017] S5. Inject the pulse descriptor word data into the vector signal source to synthesize the arrival angle simulation signals of each path of the target radar.

[0018] Preferably, in step S1, the motion scenario refers to a scenario in three-dimensional space where the carrier aircraft and the target platform can perform maneuvering actions in any direction and attitude angle and allows scene editing.

[0019] Preferably, in step S2, the coordinate transformation specifically includes the following steps:

[0020] S21. From the position coordinates (x r , y r , z r ) of the carrier aircraft and the position coordinates (x t , y t , z t ) of the target platform, obtain the target platform coordinate values (x t - x r , y t - y r , z t - z r), and combined with the three attitude angles of the carrier aircraft (yaw angle θ r , pitch angle β r and roll angle ), after rotating the coordinate system in the opposite direction by the same angle, the body coordinate system of the carrier aircraft can be obtained. According to the target platform coordinate values (x t -x r , y t -y r , z t -z r ) and the attitude angles of the carrier aircraft, the coordinate values of the target platform in the body coordinate system of the carrier aircraft can be calculated (x tr , y tr , z tr );

[0021] S22. From the position coordinates of the carrier aircraft (x r , y r , z r ) and the position coordinates of the target platform (x t , y t , z t ), the coordinate values of the carrier aircraft in the rectangular coordinate system with the target platform as the origin can be obtained (x r -x t , y r -y t , z r -z t ), and combined with the three attitude angles of the target platform (yaw angle θ t , pitch angle β t and roll angle ), after rotating the coordinate system in the opposite direction by the same angle, the target platform coordinate system can be obtained. According to the coordinate values of the carrier aircraft (x r -x t , y r -y t , z r -z t ) and the attitude angles of the target platform, the coordinate values of the carrier aircraft in the target platform coordinate system can be calculated (x rt , y rt , z rt ).

[0022] Preferably, in step S3, the method for calculating the signal power received by each receiving antenna specifically includes the following process:

[0023] S31. According to the position coordinates of the target platform in the body coordinate system of the carrier aircraft (x tr , y tr , z tr), the azimuth angle and pitch angle of the target platform relative to the carrier aircraft are obtained. Combining the pointing direction, directivity pattern, and gain of the receiving antenna, the receiving gains of the radar warning device's four receiving antennas for receiving the target radar signal are calculated respectively.

[0024] S32. According to the position coordinates (x rt , y rt , z rt ) of the carrier aircraft in the target platform coordinate system, the azimuth angle and pitch angle of the carrier aircraft relative to the target platform are obtained. Combining the pointing direction, directivity pattern, gain, and antenna scanning method of the target radar antenna, the radiation gain of the target radar in the direction of the carrier aircraft is calculated.

[0025] S33. According to the set target radar signal frequency and the relative distance from the carrier aircraft, the free space propagation loss is calculated. Combining the target radar transmit power, radiation gain, and the receiving gain of the carrier aircraft's radar warning device, the signal power received by each receiving antenna of the radar warning device is obtained.

[0026] Preferably, in the step S5, the method of injecting a pulse description word sequence into the vector signal source is adopted for synthesizing the arrival angle analog signal.

[0027] Preferably, the arrival angle includes the azimuth angle and the pitch angle, and it changes dynamically according to the set motion scenario.

[0028] The present invention calculates the parameters of the simulated signal of the moving target radar in three-dimensional space according to the set simulated motion scenario, generates the corresponding PDW data, and injects it into the vector signal source to synthesize 4-channel analog signals. Since the simulated scenario is editable, this method can flexibly and quickly simulate the signals of moving radiation sources in various scenarios under laboratory conditions, with a high simulation fidelity. At the same time, since the method of injecting PDW data into the vector signal source is adopted, the amount of data stored and transmitted is greatly compressed, and it can meet the requirements of high-pulse-density long-time simulation.

[0029] The present invention flexibly and efficiently simulates the radar signal of a six-degree-of-freedom moving target in three-dimensional space with a comparison amplitude direction finding system according to the set scenario, bringing the simulation of complex test scenarios into the laboratory, greatly reducing the test cost and development time.

[0030] The present invention proposes a method for simulating the radar signal of a moving target in an electronic countermeasure scenario, studies the mapping relationship between the spatial position and attitude of the target radar relative to the carrier aircraft and the RF signal power of each channel of the carrier aircraft, and synthesizes the simulated signal of the moving target radar in any motion scenario in the laboratory with a vector signal source, improving the simulation fidelity of the electronic countermeasure motion scenario and enhancing the test accuracy and efficiency of the radar warning device. Description of the Drawings

[0031] Figure 1This is the overall flowchart of the present invention.

[0032] Figure 2 This is the normalized directivity pattern (amplitude value) received by the four antennas of the radar warning device in the embodiment of the present invention.

[0033] Figure 3 This is the directivity pattern of the target radar antenna in the embodiment of the present invention.

[0034] Figure 4 This is the schematic diagram of the body coordinate system in the embodiment of the present invention.

[0035] Figure 5 This is the three-dimensional schematic diagram of amplitude comparison direction finding in the embodiment of the present invention.

[0036] Figure 6 This is the simulation result diagram of the power change trend of the signal received by receiving antenna 1 using this method.

[0037] Figure 7 This is the simulation result diagram of the power change trend of the signal received by receiving antenna 2 using this method.

[0038] Figure 8 This is the diagram of the power change trend of the RF analog signal of antenna 1 in the embodiment of the present invention.

[0039] Figure 9 This is the diagram of the power change trend of the RF analog signal of antenna 2 in the embodiment of the present invention.

[0040] Figure 10 This is the real-time spectrum diagram of the RF analog signal of antenna 1 in the embodiment of the present invention.

[0041] Figure 11 This is the real-time spectrum diagram of the RF analog signal of antenna 2 in the embodiment of the present invention. Detailed implementation manners

[0042] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0043] Embodiment

[0044] The signal simulation principle of the present invention is as follows:

[0045] According to the amplitude comparison direction finding principle, the radar warning device realizes direction finding by comparing the amplitudes of the two signals with the strongest power among the four received signals. Therefore, to test its direction finding performance, it is necessary to synthesize four radar coherent analog signals with specific amplitudes according to the mapping relationship between the spatial position and attitude of the target platform relative to the carrier aircraft in the set scenario and the RF signal amplitudes of each channel of the radar warning device receiver, and inject them into the corresponding channels of the receiver. The hardware implementation mainly consists of a control computer and a vector signal source. The control computer can edit the electronic countermeasure scenario, including the motion trajectories and attitude angles of the target platform and the carrier aircraft, the antenna installation angle, the scanning mode, and the radiation pattern, calculate the power values of each path according to the above parameters, generate the PDW data of the four receiver channel signals in combination with the operating mode and signal characteristics of the target radar, and finally transmit the PDW data of the four signals to the vector signal source in real time through the network cable to synthesize four RF analog signals and inject them into the corresponding receiving channels of the radar warning device to realize the detection of its working performance.

[0046] As Figure 1 shown, this simulation method takes the scenario editing information as input, such as setting parameters such as the initial position coordinates, attitude angles, motion speeds, simulation duration, antenna radiation pattern, antenna scanning mode, and transmission power of the carrier aircraft and the target platform. Since the target platforms are mainly divided into several categories such as air, sea, and land, among which the motion forms of the sea and land target platforms are relatively simple, mainly involving changes in position coordinates and azimuth angles, while the motion form of the air target platform is the most complex, involving not only changes in position coordinates but also changes in three attitude angles. Therefore, the following takes the most complex simulation scenario (air target platform, that is, the target platform is an aircraft) as an example for explanation. For the convenience of explanation, some specific settings need to be made for the simulation scenario.

[0047] Note: The scenario simulation of the sea and land target platforms can be obtained by simplifying the treatment of this embodiment. For example, the pitch angle and roll angle of the sea and land target platforms can be set to 0° or a specific value according to the actual simulation scenario.

[0048] (1) Antenna setting of the carrier aircraft radar warning device

[0049] Set the horizontal orientations of the four receiving antennas of the radar warning device on the carrier aircraft to 45°, 135°, 225°, and 315° respectively.

[0050] The radar warning device mainly measures the azimuth angle of the target and does not measure the pitch angle. Therefore, the shape of its antenna radiation pattern is wide on the left and right and narrow on the top and bottom. The power radiation patterns of its four receiving antennas are the same, and their projections on the horizontal plane and the vertical plane after normalization are both Gaussian functions (taking the common Gaussian function as an example). The mathematical expression of its projection on the horizontal plane is as follows:

[0051]

[0052] where θ is the azimuth angle; G(θ) is the power gain of the antenna in the θ direction, in dB; θ0 is the horizontal orientation of the antenna; θ r is the half-power beam width in the horizontal direction.

[0053] The mathematical expression of the projection on the vertical plane is as follows:

[0054]

[0055] where β is the elevation angle; G(β) is the power gain of the antenna in the β direction, in dB; β0 is the elevation orientation of the antenna; β r is the half-power beam width in the elevation direction.

[0056] Therefore, it is easy to obtain that the antenna power gain at the θ azimuth and the β elevation angle is:

[0057]

[0058] Taking the logarithm of the antenna power gain and converting it to dB units, then:

[0059]

[0060] Therefore, when the maximum received power gain of the antenna is G1 dB, the antenna power gain function can be obtained as:

[0061]

[0062] Since the half-power beam width of the receiving antenna in the horizontal direction is relatively large and the half-power beam width in the elevation direction is relatively small, so let θ r take π / 3, and β r take π / 9. The three-dimensional directivity of the 4 receiving antennas is as Figure 2 shown. (Note: x-axis (m), y-axis (m), z-axis (amplitude)).

[0063] (2) Target radar antenna setting

[0064] Set the initial horizontal orientation of the target radar transmitting antenna to the nose direction, that is, the 0° direction. At the same time, the antenna performs sector scanning within the XOY plane of the target platform, and the sector scanning angle range is (-π / 3, +π / 3), and the sector scanning angular velocity is 2π / s (the sector scanning period is 2 / 3 seconds). The elevation orientation is always the 0° direction.

[0065] The airborne radar (i.e., the target radar) requires very high angle measurement accuracy, so its beam width is very narrow, and the projections on the horizontal plane and the vertical plane after normalization are both Gaussian functions (taking the common Gaussian function as an example). Similarly, it can be obtained that when the maximum transmission gain is G2 dB, its antenna power gain at the θ azimuth and the β elevation angle is:

[0066]

[0067] where, θ is the azimuth angle; β is the elevation angle; G(θ, β) is the power gain of the antenna in the direction of (θ, β), with the unit of dB; G2 is the antenna gain, with the unit of dB; θ0 is the horizontal orientation of the antenna; β0 is the elevation orientation of the antenna; θ r is the half-power beam width in the horizontal direction; β r is the half-power beam width in the elevation direction. Since the half-power beam widths of the transmitting antenna in the horizontal and elevation directions are both relatively small, θ r and β r both take π / 18, and its three-dimensional directivity is as shown in Figure 3 .

[0068] For the convenience of calculation, when solving the gain of the transmitting and receiving antennas, the form of the aircraft body coordinate system is adopted, that is, as shown in Figure 4 , with the centroid of the aircraft as the origin, the head orientation of the longitudinal axis as the x-axis direction, the direction pointing to the right wing as the y-axis direction, and the direction pointing to the bottom of the aircraft as the z-axis direction.

[0069] As shown in Figure 5 , it is a schematic diagram of the positions and attitude angles of the carrier aircraft and the target platform (an aircraft in this embodiment) in three-dimensional space. On the left is the directivity pattern of the four receiving antennas of the carrier aircraft radar warning device, and on the right are the target platform and the target radar beam. It can be seen that the relative positions and respective attitude angles of the above two determine the magnitude of the power of the target radar radiation signal received by the four receiving antennas of the radar warning device.

[0070] Taking "finding the coordinates of the target platform in the carrier aircraft body coordinate system" as an example, the specific coordinate conversion method is described below. Note: The position coordinates and attitude angles (yaw angle, pitch angle, roll angle) are called six degrees of freedom.

[0071] Suppose the position coordinates and attitude angles of the carrier aircraft and the target platform at a certain moment in the ground coordinate system are respectively:

[0072] Carrier aircraft:

[0073] Target platform:

[0074] Then the conversion steps are as follows:

[0075] ① First, find the coordinates of the target platform relative to the carrier aircraft in the ground coordinate system: loca_rela = (x rel , y rel , z rel ) = (x t - x r , y t - yr, zt -z r )。

[0076] It can be seen that this relative coordinate is actually the coordinate of the target platform in a certain coordinate system with the origin at the centroid of the carrier aircraft and the directions of each coordinate axis being the same as those of the coordinate axes of the ground coordinate system.

[0077] Next, it is necessary to adjust the orientations of the three coordinate planes of this coordinate system one by one so that their orientations are consistent with the coordinate planes of the carrier aircraft body coordinate system, that is, the x-axis direction is the nose orientation, the y-axis direction is the cross-axis left-wing direction, and the z-axis direction is the vertical-axis direction pointing to the bottom of the aircraft.

[0078] ② Adjust the orientation of the xoy plane of the coordinate system so that the xoy plane rotates around the z-axis by the yaw angle θ of the carrier aircraft r , at this time the z coordinate remains unchanged, and the x and y coordinates change, and the coordinate (x1, y1, z1) of the target platform in this coordinate system is obtained. Among them, z1 = z r , x1 = (x rel ^2 + y rel ^2)^0.5 * cos(θ r ), y1 = (x rel ^2 + y rel ^2)^0.5 * sin(θ r ).

[0079] ③ Adjust the orientation of the zox plane of the coordinate system so that the zox plane rotates around the y-axis by the pitch angle β of the carrier aircraft r , at this time the y coordinate remains unchanged, and the z and x coordinates change, and the coordinate (x2, y2, z2) of the target platform in this coordinate system is obtained. Among them, y2 = y1, x2 = (x1^2 + z1^2)^0.5 * cos(β r ), z2 = (x1^2 + z1^2)^0.5 * sin(β r ).

[0080] ④ Adjust the orientation of the zoy plane of the coordinate system so that the zoy plane rotates around the x-axis by the roll angle of the carrier aircraft At this time the x coordinate remains unchanged, and the z and y coordinates change, and the coordinate (x3, y3, z3) of the target platform in this coordinate system is obtained. Among them, x3 = x2, y3 = (y2^2 + z2^2)^0.5 * cos(β r ), z3 = (y2^2 + z2^2)^0.5 * sin(β r ). At this time, the coordinate (x3, y3, z3) is the coordinate value of the target platform in the carrier aircraft body coordinate system, represented by (x tr , y tr , z tr ).

[0081] (3) Calculation of the signal power received by the radar warning device antenna

[0082] According to the principle of electromagnetic wave propagation, the signal power received by the antenna can be calculated by the following formula:

[0083] P re = P T + G T - L + G R (7)

[0084] Where, P re is the signal power received by the receiving antenna of the radar warning device, with the unit of dBm; P T is the transmitting power of the target radar, with the unit of dBm; G T is the transmitting gain of the target radar antenna, with the unit of dB; L is the free space propagation loss of the electromagnetic wave, with the unit of dB; G R is the receiving gain of the receiving antenna of the radar warning device, with the unit of dB.

[0085] Next, these parameters will be obtained step by step. According to the coordinate values obtained from the above coordinate transformation, the azimuth angle and elevation angle (θ re , β re ) of the carrier aircraft in the target platform coordinate system, and the azimuth angle and elevation angle (θ ra , β ra ) of the target platform in the carrier aircraft body coordinate system can be obtained respectively. Substituting them into Equation (5) and Equation (6) respectively, the transmitting gain GT of the target radar antenna and the receiving gains G R1 , G R2 , G R3 , G R4 of the 4 receiving antennas of the radar warning device can be obtained.

[0086] Where:

[0087]

[0088] In the above formula, θ0 is the horizontal orientation of the antenna, which changes according to the fan scan law.

[0089]

[0090]

[0091]

[0092]

[0093] The free space propagation loss of the electromagnetic wave is:

[0094] L = 32.45 + 20log(f) + 20log(d) (13)

[0095] Among them, f is the frequency of the signal, with the unit of MHz; d is the distance between the target radar antenna and the receiving antenna, with the unit of Km.

[0096] Finally, substituting the above parameters into Equation (7) can obtain the RF signal power values of the four channels of the carrier aircraft.

[0097] (4) Algorithm verification

[0098] Set the carrier aircraft to move in a uniform straight line, with the initial coordinates of (0m, 0m, 0m) and the speed of (90m / s, -120m / s, 62.5m / s); the target platform also moves in a uniform straight line, with the initial coordinates of (25000m, 8000m, 6000m) and the speed of (-240m / s, -80m / s, -60m / s); P T Take P as 68dBm (about 6000W), G2 as 33dB, G1 as 0dB, the carrier frequency f of the target radar signal is taken as 5GHz, the scanning mode of the target radar transmitting antenna is horizontal sector scanning, the sector scanning angle range is (-π / 3, +π / 3), the sector scanning angular velocity is 2π / s, and the simulation time is 60s.

[0099] The radar warning device realizes direction finding by comparing the amplitudes of the two signals with the strongest power among the four received signals. Therefore, the simulation of the arrival angles of the two signals with the strongest power is crucial. In addition, the two signals with the weakest power have little influence on the simulation accuracy of the arrival angles. In the above simulation scenario, after solving with this algorithm, it is found that receiving antennas 1 and 2 of the radar warning device are the two with stronger received signal power, as shown respectively in Figure 6 、 Figure 7 shown, where Figure 6 is the trend chart of the power of the signal received by receiving antenna 1 changing with time, Figure 7 is the trend chart of the power of the signal received by receiving antenna 2 changing with time; the other two signals are very weak, and the simulation situation is consistent with the expectation. Note: The abscissa is the time (s), and the ordinate is the received power determination (dBm).

[0100] (5) RF signal test and verification

[0101] According to the received signal power values of each channel obtained under the set scenario, PDW data generated by combining the target signal characteristics (taking the common linear frequency modulation pulse signal as an example) is transmitted to the vector signal source in real time through the network cable to synthesize four-channel RF analog signals.

[0102] Use a vector signal analyzer to test two of the strongest signals, and the test results are shown in Figure 8 、 Figure 9 shown, Figure 8It is the signal power trend chart of Antenna 1 channel. Figure 9 It is the signal power trend chart of Antenna 2 channel. From the trend charts of the power of two RF analog signals changing with time, it can be seen that the power values of the two RF signals are consistent with the simulation results of the above algorithm verification. From the test results, the signal parameters are consistent with the set values. At the same time, real-time spectrum analysis is carried out on the two signals, and the results are as Figure 10 , Figure 11 shown, which is consistent with the real-time spectrum of the linear frequency modulation pulse signal Figure 1 .

[0103] Finally, further verification experiments of various electronic countermeasure scenarios were carried out by using the actual installation of radar warning equipment. The experimental results are consistent with the expected effects, indicating that the method has a good effect on simulating moving radar target signals.

[0104] The above implementation manners are not limitations to the present invention, and the present invention is not limited to the above examples either. Changes, modifications, additions or substitutions made by those skilled in the art within the technical scope of the present invention also fall within the protection scope of the present invention.

Claims

1. A method for simulating the angle of arrival of a radiation source in an amplitude comparison direction finding system, characterized in that: The method includes the following steps: S1. Determine the position coordinates and attitude angles: Determine the position coordinates and attitude angles of the aircraft carrying the radar warning device, i.e., the carrier aircraft, and the position coordinates and attitude angles of the airborne, maritime or land-based target platform carrying the target radar according to the set motion scenario; S2. Perform coordinate transformation: Perform coordinate transformation according to the position coordinate and attitude angle information of the carrier aircraft and the target platform to obtain the position coordinates of the target platform in the body coordinate system of the carrier aircraft and the position coordinates of the carrier aircraft in the coordinate system of the target platform respectively; S3. Calculate the signal power received by each receiving antenna: According to the above two position coordinates, combined with the directivity patterns of the receiving antennas of the radar warning device and the target radar antenna in the set scenario, the scanning mode of the target radar antenna, the signal frequency, and the transmitting power of the target radar, calculate the signal power received by each receiving antenna of the radar warning device; S4. Generate pulse description word data: Generate pulse description word data according to the signal power received by each receiving channel of the radar warning device of the carrier aircraft, combined with the signal format of the target radar in the set scenario; S5. Synthesize the arrival angle simulation signal of the target radar: Inject the pulse description word data into the vector signal source to synthesize the arrival angle simulation signals of each path of the target radar.

2. The method for simulating the arrival angle of a radiation source for a specific amplitude comparison direction finding system according to claim 1, wherein: In the step S1, the motion scenario refers to a scenario in three-dimensional space where the carrier aircraft and the target platform can perform maneuvering actions in any direction and attitude angle and allows scene editing.

3. The method for simulating the arrival angle of a radiation source for the amplitude comparison direction finding system according to claim 1, wherein: In the step S2, the coordinate transformation specifically includes the following steps: S21. Given the carrier aircraft position coordinates (x r , y r , z r ) and the target platform position coordinates (x t , y t , z t ), the coordinate values of the target platform in the rectangular coordinate system with the carrier aircraft as the origin are obtained as (x t - x r , y t - y r , z t - z r ). Combining with the three attitude angles of the carrier aircraft (yaw angle θ r , pitch angle β r and roll angle ), after rotating the coordinate system in the opposite direction by the same angle respectively, the body coordinate system of the carrier aircraft can be obtained. According to the target platform coordinate values (x t - x r , y t - y r , z t - z r ) and the carrier aircraft attitude angles, the coordinate values of the target platform in the body coordinate system of the carrier aircraft can be calculated as (x tr , y tr , z tr ); S22. From the carrier aircraft position coordinates (x r , y r , z r ) and the target platform position coordinates (x t , y t , z t ), the carrier aircraft coordinate values (x r - x t , y r - y t , z r - z t ) in the rectangular coordinate system with the target platform as the origin are obtained. Combining with the three attitude angles (yaw angle θ t , pitch angle β t , and roll angle ) of the target platform, after rotating the coordinate system in the opposite direction by the same angle respectively, the target platform coordinate system can be obtained. According to the carrier aircraft coordinate values (x r - x t , y r - y t , z r - z t ) and the target platform attitude angles, the coordinate values (x rt , y rt , z rt ) of the carrier aircraft in the target platform coordinate system can be calculated.

4. The method for simulating the arrival angle of a radiation source for the amplitude comparison direction finding system according to claim 1, wherein: In the step S3, the method for calculating the signal power received by each receiving antenna specifically includes the following process: S31. Based on the target platform position coordinates (x tr , y tr , z tr ) in the carrier aircraft body coordinate system, obtain the azimuth angle and pitch angle of the target platform relative to the carrier aircraft, and combine the pointing, directivity pattern, and gain of the receiving antenna to calculate the receiving gains of the radar warning device's four receiving antennas for receiving the target radar signal respectively; S32. According to the position coordinates (x rt , y rt , z rt ) of the aircraft in the target platform coordinate system, obtain the azimuth angle and pitch angle of the aircraft relative to the target platform, and combine the pointing direction, directivity pattern, gain, and antenna scanning method of the target radar antenna to calculate the radiation gain of the target radar in the direction of the aircraft; S33. Calculate the free space propagation loss according to the set signal frequency of the target radar and the relative distance from the carrier aircraft, and combine the transmitting power of the target radar, the radiation gain, and the receiving gain of the radar warning device of the carrier aircraft to obtain the signal power received by each receiving antenna of the radar warning device.

5. The method for simulating the arrival angle of a radiation source for the amplitude comparison direction finding system according to claim 1, wherein: In the step S5, the synthesis of the arrival angle simulation signal adopts the method of injecting a pulse description word sequence into the vector signal source.

6. The method for simulating the angle of arrival of a radiation source for an amplitude comparison direction finding system according to any one of claims 1-5, characterized in that: The arrival angle includes the azimuth angle and the elevation angle, which change dynamically according to the set motion scenario.

Images