A method for simulating single-pulse in case of partial damage of a dark chamber array

Abstract

The application discloses a single pulse simulation method under local damage of a darkroom array, comprising the following steps: determining an array area required by an aircraft when performing a semi-physical simulation in a radar darkroom on a spherical array, a damaged array area on the spherical array, and selecting a new array area; rotating a turntable for fixing the aircraft according to a preset angle, so that a midpoint of the area corresponds to a zero position of the turntable at a center of the radar darkroom, and an orientation of a single pulse radar guiding device carried on the aircraft avoids the damaged array area; calculating a rotation angle instruction of a second rotation sequence of the turntable according to the determined preset angle and a rotation angle instruction of a first rotation sequence of the aircraft on the turntable; calculating a rotation angle instruction of a second rotation sequence of the spherical array according to the preset angle and a line of sight angle required by the aircraft when simulating; and the turntable and the spherical array perform the rotation according to the corresponding rotation angle instructions, so that a single pulse simulation process is performed.

Description

Technical Field

[0001] This invention relates to the field of aircraft guidance and control simulation, specifically to a single-pulse simulation method for local damage to an anechoic chamber array. Background Technology

[0002] During the ground verification phase of aircraft design, hardware-in-the-loop simulation is usually required. The simulation system uses a radar anechoic chamber. The flight trajectory of the aircraft determines the location of the spherical array in the radar anechoic chamber that needs to be used. When a part of the spherical array that needs to be used happens to have a damaged radar antenna and there is no time to repair it, how to use other undamaged parts to achieve the same hardware-in-the-loop simulation effect is a problem to be solved. Summary of the Invention

[0003] The purpose of this invention is to provide a single-pulse simulation method for local damage to an anechoic chamber array, so as to achieve normal single-pulse simulation under the condition of anechoic chamber array damage.

[0004] To achieve the above objectives, the present invention employs the following technical solution: A single-pulse simulation method for localized damage to an anechoic chamber array includes: Determine the array area required for the aircraft on the spherical array during the hardware-in-the-loop simulation in the radar anechoic chamber, as well as the damaged array area on the spherical array; if the two intersect, redetermine the midpoint of the undamaged array area, and based on the midpoint, determine a new array area of ​​the same size as the required array area. By controlling the turntable of the fixed aircraft to rotate at a preset angle, the center of the region corresponds to the zero position of the turntable at the center of the radar anechoic chamber, and the orientation of the monopulse radar guidance device on the aircraft avoids the damaged array area. Based on the predetermined preset angle and the rotation angle command of the aircraft on the turntable for executing the first rotation sequence, calculate the rotation angle command of the turntable for executing the second rotation sequence. Based on the preset angle and the line-of-sight angle that the aircraft needs to simulate during the simulation, the rotation angle command for the second rotation sequence of the spherical array is calculated; the turntable and the spherical array execute the corresponding rotation angle command respectively, thereby performing a single-pulse simulation process.

[0005] Furthermore, the preset angle includes the horizontal preset angle of the turntable. and height preset angle ; Let the coordinates of the point in the region relative to the zero coordinate system of the turntable be . The formula for calculating the preset angle is: .

[0006] Furthermore, based on the determined preset angle and the rotation angle command for the aircraft to execute the first rotation sequence on the turntable, the rotation angle command for the turntable to execute the second rotation sequence is calculated, including:

[0007] The rotation angle command in the first rotation sequence includes the pitch angle. Yaw angle and roll angle The second rotation angle command includes the pitch angle. Yaw angle and roll angle ; , , , , These are all intermediate variables used in the calculation.

[0008] Furthermore, the first transposition is a 321 transposition, and the second transposition is a 231 transposition.

[0009] Further, based on the preset angle and the line-of-sight angle that the aircraft needs to simulate during the simulation, the rotation angle command for the spherical array to execute the second rotation sequence is calculated, including:

[0010] Among them, the rotation angle command for the second rotation sequence of the spherical array includes the pitch angle command of the spherical array. Yaw angle command The line-of-sight angles that need to be simulated during the simulation of the aircraft include the elevation angle of the line of sight during the first turn of the aircraft. Azimuth of line of sight ; and For horizontal preset angle and vertical preset angle, , , , , All are intermediate variables.

[0011] A terminal device includes a processor, a memory, and a computer program stored in the memory; when the processor executes the computer program, it implements a single-pulse simulation method for local damage to the anechoic chamber array.

[0012] A computer-readable storage medium storing a computer program; when executed by a processor, the computer program implements a single-pulse simulation method for local damage to the anechoic chamber array.

[0013] Compared with the prior art, the present invention has the following technical features: This invention proposes the idea of ​​achieving single-pulse simulation by presetting angles through spatial angular relationships to avoid damaged arrays; it calculates turntable Euler angle commands using preset angles and aircraft attitude angles, and calculates anechoic chamber array angle commands using preset angles and line-of-sight angles; the correctness and effectiveness of this method have been verified through practical application. Attached Figure Description

[0014] Figure 1 This is a flowchart illustrating the method of the present invention; Figure 2 This is a partial structural schematic diagram of a spherical array in one embodiment of the present invention; Figure 3 This is a curve comparing the frame angle with the theoretical value in one embodiment of the present invention, where the damaged array is avoided. Detailed Implementation

[0015] This invention provides a single-pulse simulation method for localized damage to an anechoic chamber array. First, by analyzing the damaged and undamaged areas of the spherical array, and considering the size of the array area used in the hardware-in-the-loop simulation, the turntable at the center of the anechoic chamber is rotated at a preset angle, ensuring that the radar guidance device fixed on the turntable avoids the damaged area. Then, based on the aircraft's rotation angle command, the rotation angle commands for the turntable and the spherical array are determined, ensuring that the spatial angular relationship between the spherical array and the radar guidance device is consistent with theory. The flowchart is shown below. Figure 1 As shown, the specific steps are as follows: Step 1: Determine the array area to be used on the spherical array when the aircraft is in a semi-physical simulation in the radar anechoic chamber, and the damaged array area on the spherical array; if the two intersect, then redetermine the center point A in the undamaged array area, and establish a new array area with the same size as the required array area based on the center point A; the new array area does not intersect with the damaged array area.

[0016] Step 2: By controlling the turntable of the fixed aircraft to rotate at a preset angle, point A in the region corresponds to the zero position of the turntable at the center of the radar anechoic chamber, thereby ensuring that the orientation of the monopulse radar guidance device mounted on the aircraft avoids the damaged array area. The preset angle includes the horizontal preset angle of the turntable. and height preset angle The calculation method is as follows: like Figure 2 As shown, since the original array region intersects with the remaining parts of the damaged array, a new array region is re-established by selecting region point A within the undamaged array region for hardware-in-the-loop simulation. At this point, the new zero point of the turntable needs to be changed from the midpoint of the original array region to region point A. Let the coordinates of region point A relative to the turntable's zero-position coordinate system before the turntable rotates be... The formula for calculating the preset angle is:

[0017] Step 3: Based on the determined preset angle and the rotation angle command of the aircraft executing the first rotation sequence on the turntable, calculate the rotation angle command of the turntable executing the second rotation sequence, as follows:

[0018] The first turn sequence is a 321 turn sequence, which is a turn sequence of roll, yaw, and pitch; the rotation angle command for the first turn sequence includes the pitch angle. Yaw angle and roll angle The second turn sequence is 231, meaning yaw first, then roll, and finally pitch; the turn angle commands in the second turn sequence include pitch angle. Yaw angle and roll angle ; , , , , These are all intermediate variables used in the calculation.

[0019] Step 4: Calculate the rotation angle command for the second rotation sequence of the spherical array based on the preset angle and the line-of-sight angle that the aircraft needs to simulate during the simulation; the turntable and the spherical array execute the corresponding rotation angle command respectively, thereby performing a single-pulse simulation process.

[0020]

[0021] Among them, the rotation angle command for the second rotation sequence (231 rotation sequence) of the spherical array includes the pitch angle command of the spherical array. Yaw angle command The line-of-sight angles that need to be simulated during the simulation of the aircraft include the elevation angles of the line of sight during the first turn (321 turn). Azimuth of line of sight ; and These are the horizontal preset angle and the vertical preset angle. , , , , All are intermediate variables.

[0022] Example: An aircraft has an initial position of (0, 100, 0) m and flies at a constant speed of (10, 0, 0) m / s. The target position is (1100, 0, 10) m. The aircraft's pitch angle changes with time t as (-5 + 0.5t)°, its yaw angle changes with time as (-0.5 - 0.035t)°, and its roll angle is 0°. Assuming the electrical axis of the monopulse radar seeker is always pointing towards the target, its theoretical frame angle (pitch frame angle) can be calculated. Yaw frame angle Due to localized damage to the anechoic chamber array, a preset angle (horizontal preset angle) is required. °, Preset height angle Using this invention for testing, the true frame angle (pitch frame angle) is obtained. Yaw frame angle Compare with the theoretical framework angle, such as Figure 3 As shown, the two completely overlap, proving the effectiveness and correctness of this solution.

[0023] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application, and should all be included within the protection scope of this application.

Claims

1. A single-pulse simulation method for localized damage to an anechoic chamber array, characterized in that, include: Determine the array area required on the spherical array when the aircraft is simulated in a radar anechoic chamber, as well as the damaged array area on the spherical array; If the two intersect, the midpoint of the region is redefined in the undamaged array region, and a new array region with the same size as the required array region is determined based on the midpoint of the region. By controlling the turntable of the fixed aircraft to rotate at a preset angle, the center point of the region corresponds to the zero position of the turntable at the center of the radar anechoic chamber, and the orientation of the monopulse radar guidance device on the aircraft avoids the damaged array area; the preset angle includes the horizontal preset angle of the turntable. and height preset angle ; Let the coordinates of the point in the region relative to the zero coordinate system of the turntable be . The formula for calculating the preset angle is: ； Based on the predetermined preset angle and the rotation angle command for the aircraft to execute the first rotation sequence on the turntable, calculate the rotation angle command for the turntable to execute the second rotation sequence, including: ； The rotation angle command in the first rotation sequence includes the pitch angle. Yaw angle and roll angle The second rotation angle command includes the pitch angle. Yaw angle and roll angle ; , , , , These are all intermediate variables used in the calculation; Based on the preset angle and the line-of-sight angle that the aircraft needs to simulate during the simulation, the rotation angle command for the spherical array to execute the second rotation sequence is calculated, including: Among them, the rotation angle command for the second rotation sequence of the spherical array includes the pitch angle command of the spherical array. Yaw angle command The line-of-sight angles that need to be simulated during the simulation of the aircraft include the elevation angle of the line of sight during the first turn of the aircraft. Azimuth of line of sight ; and For horizontal preset angle and vertical preset angle, , , , , All are intermediate variables; The turntable and spherical array execute the corresponding rotation angle commands to perform a single-pulse simulation process.

2. The single-pulse simulation method for localized damage to an anechoic chamber array according to claim 1, characterized in that, The first transposition is 321 transposition, and the second transposition is 231 transposition.

3. A terminal device, comprising a processor, a memory, and a computer program stored in the memory; characterized in that, When the processor executes a computer program, it implements the single-pulse simulation method for local damage to the anechoic chamber array as described in any one of claims 1 or 2.

4. A computer-readable storage medium storing a computer program; characterized in that, When the computer program is executed by the processor, it implements the single-pulse simulation method for local damage to the anechoic chamber array as described in any one of claims 1 or 2.

5. A hardware-in-the-loop simulation system, characterized in that, The radar anechoic chamber in this simulation system employs a single-pulse simulation method for local damage to the anechoic chamber array as described in any one of claims 1 or 2.

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