Monopulse simulation method under local damage condition of darkroom array
By determining the central point in the region within the radar anechoic chamber, redefining the array region, and calculating the rotation command using preset angles and aircraft attitude angles, the problem of single-pulse simulation when the radar anechoic chamber array is partially damaged was solved, achieving accurate simulation results.
Patent Information
- Application Number
- CN202511004885.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-07-21
- Publication Date
- 2025-11-21
AI Technical Summary
When a part of the spherical array in a radar anechoic chamber is damaged, existing technologies struggle to achieve effective hardware-in-the-loop simulation, especially when time is of the essence and the undamaged portion cannot be used for normal single-pulse simulation.
By determining the center point in the region, the array region is redefined, and the rotation angle commands of the turntable and spherical array are calculated using preset angles and aircraft attitude angles, thus avoiding damaged array regions and achieving single-pulse simulation.
A correct and effective single-pulse simulation was achieved under the condition of partial damage to the radar anechoic chamber array, verifying the correctness and effectiveness of the method.
Smart Images
Figure CN120993772A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the field of aircraft guidance control simulation, and particularly relates to a single pulse simulation method under local damage of a darkroom array. BACKGROUND
[0002] During the design ground verification stage, an aircraft usually needs to be subjected to semi-physical simulation, and a radar darkroom needs to be used in the simulation system. The flight trajectory of the aircraft determines the part of the spherical array of the radar darkroom that needs to be used. When the local array in the spherical array that needs to be used happens to have radar antenna damage and the time is too urgent to be repaired, how to use the other undamaged parts to achieve the same semi-physical simulation effect is a problem to be solved. SUMMARY
[0003] The purpose of the present application is to provide a single pulse simulation method under local damage of a darkroom array, so as to realize normal single pulse simulation under damage of the darkroom array.
[0004] In order to achieve the above-mentioned task, the present application adopts the following technical scheme: A single pulse simulation method under local damage of a darkroom array, comprising: determining the array region needed to be used on the spherical array when the aircraft is subjected to semi-physical simulation in the radar darkroom, and the damaged array region on the spherical array; if the two regions intersect, then a region midpoint in the undamaged array region is re-determined, and a new array region with the same size as the array region needed to be used is determined based on the region midpoint; controlling the turntable of the fixed aircraft to rotate according to a preset angle, so that the region midpoint corresponds to the zero position of the turntable at the center of the radar darkroom, and the orientation of the single pulse radar seeker device carried on the aircraft avoids the damaged array region; calculating the rotation angle instruction of the turntable for executing a second rotation sequence according to the preset angle and the rotation angle instruction of the aircraft for executing a first rotation sequence; calculating the rotation angle instruction of the spherical array for executing a second rotation sequence according to the preset angle and the line of sight angle needed to be simulated by the aircraft during simulation; the turntable and the spherical array execute the corresponding rotation angle instructions respectively, so as to perform a single pulse simulation process.
[0005] Further, the preset angle comprises a horizontal preset angle of the turntable and a high-low preset angle . Let the coordinates of the region midpoint relative to the zero position coordinate system of the turntable be , and the preset angle calculation formula is: .
[0006] Further, according to the determined preset angle and the rotation angle instruction of the first rotation sequence executed by the aircraft on the turntable, the rotation angle instruction of the second rotation sequence executed by the turntable is calculated, including:
[0007] Wherein, the rotation angle instruction of the first rotation sequence contains pitch angle , yaw angle and roll angle ; the rotation angle instruction of the second rotation sequence contains pitch angle , yaw angle and roll angle . , , , , All are intermediate variables during calculation.
[0008] Further, the first rotation sequence is 321 rotation sequence, and the second rotation sequence is 231 rotation sequence.
[0009] Further, according to the preset angle and the line of sight angle to be simulated by the aircraft during simulation, the rotation angle instruction of the second rotation sequence executed by the spherical array is calculated, including:
[0010] Wherein, the rotation angle instruction of the second rotation sequence executed by the spherical array contains pitch angle instruction of the spherical array, yaw angle instruction ; the line of sight angle to be simulated by the aircraft during simulation includes the line of sight high-low angle of the aircraft during the first rotation sequence, line of sight azimuth angle . And are horizontal preset angle and high-low preset angle, , , , , All are intermediate variables.
[0011] A terminal device, comprising a processor, a memory and a computer program stored in the memory; when the processor executes the computer program, the single pulse simulation method under the local damage condition of the darkroom array is realized.
[0012] A computer readable storage medium, the medium stores a computer program; when the computer program is executed by the processor, the single pulse simulation method under the local damage condition of the darkroom array is realized.
[0013] Compared with the prior art, the present application has the following technical characteristics: The application provides a single pulse simulation method by presetting angles to avoid damaged arrays according to spatial angle relations; the preset angles and the attitude angle of the aircraft are used to calculate the turntable Euler angle command, and the preset angles and the line of sight angle are used to calculate the darkroom array angle command; the method is verified to be correct and effective through actual application. BRIEF DESCRIPTION OF DRAWINGS
[0014] Figure 1 is a flowchart of the method of the application; Figure 2 is a partial structure diagram of a spherical array in an embodiment of the application; Figure 3 is a comparison curve of the frame angle and the theoretical value in the case of avoiding damaged arrays in an embodiment of the application. DETAILED DESCRIPTION
[0015] The application provides a single pulse simulation method in the case of local damage of a darkroom array. First, the damaged array region and the undamaged array region on the spherical array are analyzed, and the size of the array region used in the semi-physical simulation is combined, so that the turntable at the center of the darkroom rotates according to the preset angle, thereby avoiding the orientation of the radar seeker device fixed on the turntable from the damaged region. Then, the rotation angle command of the turntable and the spherical array is determined based on the rotation angle command of the aircraft, so that the spatial angle relation between the spherical array and the radar seeker device is consistent with the theory. The flowchart is shown in Figure 1 , and the specific steps are as follows: Step 1, determine the array region required to be used on the spherical array when the aircraft is in the radar darkroom for semi-physical simulation, and the damaged array region on the spherical array. If the two regions intersect, then the region midpoint A in the undamaged array region is determined again, and a new array region with the same size as the required array region is established based on the region midpoint A. The new array region does not intersect with the damaged array region.
[0016] Step 2, control the turntable fixed with the aircraft to rotate according to the preset angle, so that the region midpoint A corresponds to the zero position of the turntable at the center of the radar darkroom, thereby avoiding the orientation of the single pulse radar seeker device carried on the aircraft from the damaged array region. The preset angle includes the horizontal preset angle and the high-low preset angle , and the calculation method is as follows: As shown in Figure 2 , since the originally required array region intersects with the remaining damaged array, the region midpoint A is selected in the undamaged array region and a new array region is established for semi-physical simulation. At this time, the new zero position of the turntable needs to be changed from the midpoint of the original array region to the region midpoint A. Let the coordinates of the region midpoint A relative to the zero position coordinate system of the turntable before the turntable is rotated be The preset angle calculation formula is:
[0017] Step 3: According to the determined preset angle and the rotation angle instruction of the first rotation sequence executed by the aircraft on the turntable, the rotation angle instruction of the second rotation sequence executed by the turntable is calculated, which is specifically as follows:
[0018] The first rotation sequence is the 321 rotation sequence, that is, the rotation sequence of rolling first, then yawing, and then pitching; the rotation angle instruction of the first rotation sequence includes the pitch angle , the yaw angle , and the roll angle ; the second rotation sequence is the 231 rotation sequence, that is, the rotation sequence of yawing first, then rolling, and then pitching; the rotation angle instruction of the second rotation sequence includes the pitch angle , the yaw angle , and the roll angle . , , , , are intermediate variables during calculation.
[0019] Step 4: According to the preset angle and the line-of-sight angle to be simulated by the aircraft during simulation, the rotation angle instruction of the second rotation sequence executed by the spherical array is calculated; the turntable and the spherical array execute the corresponding rotation angle instructions respectively, so as to perform the single-pulse simulation process.
[0020]
[0021] The rotation angle instruction of the second rotation sequence (the 231 rotation sequence) executed by the spherical array includes the pitch angle instruction , the yaw angle instruction of the spherical array; the line-of-sight angle to be simulated by the aircraft during simulation includes the line-of-sight elevation angle of the aircraft performing the first rotation sequence (the 321 rotation sequence), and the line-of-sight azimuth angle . and are the horizontal preset angle and the elevation preset angle in the preset angle, , , , , are intermediate variables.
[0022] Embodiment: An aircraft initial position is (0, 100, 0) m, flies at a constant speed (10, 0, 0) m / s, a fixed target position is (1100, 0, 10) m, the pitch angle of the aircraft changes with time t as (-5+0.5t) °, the yaw angle changes with time as (-0.5-0.035t) °, and the roll angle is 0 °. Assuming that the electric axis of the single-pulse radar director points to the target at any time, the theoretical frame angle (pitch frame angle , yaw frame angle ) can be calculated. Due to local damage of the darkroom array, the preset angle (horizontal preset angle °, high-low preset angle °) is needed, and the real frame angle (pitch frame angle , yaw frame angle ) obtained by testing by using the application is compared with the theoretical frame angle, as shown in Figure 3 , it can be seen that the two are completely coincident, proving the effectiveness and correctness of the scheme.
[0023] The above examples are only used to illustrate the technical solutions of the application, and not to limit them; although the application has been described in detail with reference to the foregoing examples, those skilled in the art should understand that they can still modify the technical solutions recorded in the foregoing examples, or make equivalent replacement for part of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the application, and should be included in the protection scope of the application.
Claims
1. A method for simulating a single pulse in the presence of partial damage to a darkroom array, comprising: The method comprises: determining the array area required to be used by the aircraft on the spherical array when performing a semi-physical simulation in a radar anechoic chamber, and a damaged array area on the spherical array; if the two intersect, then re-determining the area center in the undamaged array area, and determining a new array area consistent with the size of the required array area based on the area center; by controlling the turntable to rotate at a preset angle, so that the area center corresponds to the zero position of the turntable at the center of the radar anechoic chamber, and the orientation of the monopulse radar seeker device carried on the aircraft avoids the damaged array area; calculating the rotation angle instruction of the turntable for performing a second rotation sequence according to the determined preset angle and the rotation angle instruction of the aircraft for performing a first rotation sequence on the turntable; calculating the rotation angle instruction of the spherical array for performing a second rotation sequence according to the preset angle and the line-of-sight angle to be simulated by the aircraft during simulation; and the turntable and the spherical array perform rotation according to the corresponding rotation angle instructions, thereby performing a monopulse simulation process.
2. The method of claim 1, wherein, The preset angle includes a horizontal preset angle of the turntable and a high-low preset angle ; The coordinates of the center of the recording area relative to the zero coordinate system of the turntable are The preset angle calculation formula is: 。 3. The method of claim 1, wherein, The method comprises: Wherein, the rotation angle instruction of the first rotation sequence comprises a pitch angle , a yaw angle and a roll angle ; the rotation angle instruction of the second rotation sequence comprises a pitch angle , a yaw angle and a roll angle ; , , , , are intermediate variables in calculation.
4. The method of claim 1, wherein, the first rotation sequence is a 321 rotation sequence, and the second rotation sequence is a 231 rotation sequence.
5. The method of claim 1, wherein, The method comprises: The rotation angle instruction of the second rotation sequence executed by the spherical array includes a pitch angle instruction of the spherical array , a yaw angle instruction ; the line-of-sight angle that needs to be simulated by the aircraft during simulation includes a line-of-sight elevation angle of the aircraft performing the first rotation sequence , a line-of-sight azimuth angle ; and are a horizontal preset angle and an elevation preset angle, , , , , are intermediate variables. 6.A terminal device, comprising a processor, a memory, and a computer program stored in the memory; characterized in that, the first rotation sequence is a 321 rotation sequence, and the second rotation sequence is a 231 rotation sequence.
7. A computer readable storage medium having stored therein a computer program; characterized in that, The computer program is executed by the processor to implement the monopulse simulation method under the condition of local damage of the array of the anechoic chamber according to any one of claims 1-5.
8. A semi-physical simulation system, characterized by comprising: The computer program is executed by the processor to implement the monopulse simulation method under the condition of local damage of the array of the anechoic chamber according to any one of claims 1-5. The radar anechoic chamber in the simulation system adopts the monopulse simulation method under the condition of local damage of the array of the anechoic chamber according to any one of claims 1-5.