CN112965041A - Spherical phased array antenna wave control self-tracking difference array division method - Google Patents

Spherical phased array antenna wave control self-tracking difference array division method Download PDF

Info

Publication number
CN112965041A
CN112965041A CN202110183867.5A CN202110183867A CN112965041A CN 112965041 A CN112965041 A CN 112965041A CN 202110183867 A CN202110183867 A CN 202110183867A CN 112965041 A CN112965041 A CN 112965041A
Authority
CN
China
Prior art keywords
target
array
coordinate system
antenna
azimuth
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN202110183867.5A
Other languages
Chinese (zh)
Other versions
CN112965041B (en
Inventor
杜丹
王文政
扈景召
陈煜航
官劲
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Southwest Electronic Technology Institute No 10 Institute of Cetc
Original Assignee
Southwest Electronic Technology Institute No 10 Institute of Cetc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Southwest Electronic Technology Institute No 10 Institute of Cetc filed Critical Southwest Electronic Technology Institute No 10 Institute of Cetc
Priority to CN202110183867.5A priority Critical patent/CN112965041B/en
Publication of CN112965041A publication Critical patent/CN112965041A/en
Application granted granted Critical
Publication of CN112965041B publication Critical patent/CN112965041B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
    • G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
    • G01S7/41—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00 using analysis of echo signal for target characterisation; Target signature; Target cross-section
    • G01S7/415—Identification of targets based on measurements of movement associated with the target
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/66—Radar-tracking systems; Analogous systems
    • G01S13/72—Radar-tracking systems; Analogous systems for two-dimensional tracking, e.g. combination of angle and range tracking, track-while-scan radar
    • G01S13/723—Radar-tracking systems; Analogous systems for two-dimensional tracking, e.g. combination of angle and range tracking, track-while-scan radar by using numerical data
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/02—Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
    • G01S2013/0236—Special technical features
    • G01S2013/0245—Radar with phased array antenna
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
    • Y02D30/00—Reducing energy consumption in communication networks
    • Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks

Landscapes

  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Radar Systems Or Details Thereof (AREA)

Abstract

The wave control self-tracking difference array partitioning method for the spherical phased array antenna, disclosed by the invention, is simple and reliable, and consumes less hardware resources. The invention is realized by the following technical scheme: dividing the array into a plurality of sub-arrays by adopting a polar coordinate mode under a spherical phased array antenna coordinate system, taking polarity according to a clockwise or counterclockwise direction, rotating an azimuth angle to zero degree by taking a z axis as a center, and rotating a pitch angle to an x axis pointing target by taking a y axis as a center so that the x axis points to the target; based on a difference array division algorithm, calculating a rotation vector of a target pointing to a coordinate system in an original coordinate system under a rotated new coordinate system to obtain a spherical array difference division maximum pitch angle threshold value, and keeping a difference array pitch angle to be maximum; and establishing an equivalent antenna rotation model by utilizing the spherical array antenna to track the over-top target time difference array rotation characteristic, realizing beam coverage on a sensitive area by multi-feed source shaping, and completing the tracking of an antenna wave control angle tracking loop on the over-top target.

Description

Spherical phased array antenna wave control self-tracking difference array division method
The invention relates to a wave control self-tracking difference array division design method of a spherical phased array antenna, which is applied to the field of aerospace measurement and control.
Background
With the rapid increase of the number of satellites such as ocean/meteorological satellites, communication/navigation satellites and other low-orbit aircrafts, and the simultaneous measurement and control and cooperative management of a plurality of space targets by a ground measurement and control system at the same time, the load of the multi-target operation management and multi-target simultaneous measurement and control support capability of the measurement and control system is increased, which are problems difficult to solve by the traditional measurement and control. The array signal processing is a signal processing technology developed in recent decades, and compared with a traditional single directional sensor, the array signal processing has the advantages of flexible beam control, high signal gain, strong anti-interference capability, high spatial resolution capability and the like. In satellite communication, a key technology essential for guaranteeing normal satellite communication is to use a shaped antenna to perform beam synthesis in an airspace to suppress strong interference. One important solution is to estimate multiple interference directions in the shortest possible time and then null the problem well under conditions of high signal-to-noise ratio (SNR), sufficiently large fast beat number and incoherent sources. However, when these conditions are not met, the performance of these methods drops dramatically. The Maximum Likelihood (ML) method can theoretically solve the above-encountered problem, but requires a global search for multivariate nonlinear maxima, which is computationally unacceptable if exhaustive, especially when multi-dimensional and multi-modal. This problem is the bottleneck problem of the ML method for interference direction estimation. Many methods of maximizing the likelihood function have been proposed so far including alternative projection, expectation maximization, newton's iterative algorithm, and so on. However, the convergence speed of these methods depends on the choice of the initial value. Most global convergence iterative algorithms have very fast convergence performance in regions where the initial values are close to the global optimum point. However, if the initial value is not properly selected, the convergence speed decreases and easily falls into a local extreme point, resulting in a decrease in convergence accuracy. Large phased arrays have the advantage of large aperture, but also increase the complexity of the multi-receiver system. In this case, in order to reduce the number of receivers in engineering, it is important to perform sub-array division on the phased array.
The difference between the number of phased array antenna sub-arrays and the number of array elements in each sub-array can have a significant effect on the performance of the phased array system, such as the main lobe offset or the side lobe level increase, which can cause the lobe shape of the array antenna directional diagram to become asymmetric and increase the side lobe level. Phased array antennas can be divided into linear arrays, planar arrays, spherical arrays, conformal arrays and the like according to unit arrangement, and generally scan in one direction of an azimuth angle or a pitch angle, while antennas of the planar arrays and the like have one more degree of freedom and can scan in the two directions of the azimuth angle and the pitch angle at the same time. The most common linear array is a linear array in which the centers of the units are arranged in a straight line at equal intervals in sequence. The units of the linear array are also arranged at unequal intervals, and the centers of the units are not arranged on a straight line, such as on a circumference. A plurality of linear arrays are arranged on a plane at certain intervals to form a plane array, and if the centers of all units are arranged on a spherical surface, a spherical array is formed. The self-tracking technology of the phased array antenna to the space flight measurement and control target is a key technology applied to the field of space flight measurement and control. The self-tracking characteristic of the spherical phased array antenna to the measurement and control target is closely related to the difference array division, and when the spherical phased array antenna tracks the high-elevation over-top target, the same over-top tracking problem as that of the parabolic antenna used in the traditional measurement and control field can also occur. Because the higher the orbit height of the aircraft is, the higher the dynamic of the aircraft relative to a ground survey station is, and for an ultra-low orbit with the orbit height of less than 300 kilometers, the atmospheric resistance is very large, so that the orbit height attenuation speed is high, and more satellite fuel is required to be consumed to frequently perform orbit maintenance control, so that the service life of a satellite is limited, therefore, the dynamic characteristics of spherical array difference array division and a high elevation angle overhead target must be carefully designed and analyzed in the design of a spherical phased array antenna space measurement and control system, so as to avoid the problem of high elevation angle overhead tracking. In order to effectively utilize information energy and guarantee information transmission quality, a transmitting antenna is required to radiate electromagnetic waves only in a required direction as far as possible, a receiving antenna is also required to receive incoming waves only in a specified direction, and interference and noise in other directions are reduced as far as possible. The multi-beam spherical phased array generally divides thousands of array elements into a plurality of groups according to a specific rule, each group has a part of array elements, and the array elements are called sub-arrays. Usually, the number of sub-arrays must be balanced among the hardware complexity, the software computation and the expected performance of the system. After the array is divided into sub-arrays, the number of the sub-arrays is obviously less than that of array elements, each sub-array is used as a receiving channel, and then adaptive array processing is carried out on a sub-array level. Although sub-array level adaptive beamforming reduces the dimension of the adaptive weight vector (i.e. the degree of freedom of the system), the number of elements of a large phased array is very large and is far greater than the number of interference and noise to be suppressed, so that the sub-array division types are various. However, the larger the sub-array is, the larger the phase center distance is, so that the period distance of the grating lobe is shortened, and when the main lobe beam is scanned, the grating lobe moves into the main beam of the sub-array or falls into a high side lobe of the sub-array, which will seriously destroy the antenna performance of the array. And the scanning range of the antenna beam is also limited, and the scanning range is smaller as the number of the units included in the subarray is larger. The number of subarrays requires a trade-off between hardware complexity, computational cost and desired performance. The subarray division type is the basis of subarray level adaptive beam forming, namely a method for dividing the subarray. There are mainly 3 seed matrix division rules: uniform contiguous subarrays (regular non-overlapping subarrays), regular overlapping subarrays, non-uniform contiguous subarrays (irregular non-overlapping subarrays). The 'rule' means that the number of array elements in each subarray is the same, and the arrangement of the array elements in the subarrays is also the same; by "overlapping" is meant that the same array element is shared by different subarrays. The non-overlapping subarrays are easy to control in a microwave stage due to the fact that array elements are not shared, and engineering is easy to achieve; however, the regular sub-array has grating lobe and grating zero effect, which affects the adaptive beam forming effect. The irregular non-overlapping subarrays destroy the periodicity of array beams, so that the grating lobe and grating zero effect can be effectively overcome. Phased array radar usually adopts large aperture antenna, and the antenna contains a plurality of units, if need whole array element to do the DBF, the receiver needs a lot of passageways, to signal processing, also needs the data acquisition and the joint digital signal processing of a lot of passageways, not only the operation is very complicated and cost is too high, consequently carries out self-adaptation beam forming at antenna element level not too realistic. Now the array is divided into several sub-arrays, usually digital beam steering is performed at the sub-array level, and phase shifting is used to do this inside the sub-arrays. In large arrays, the subarray approach can greatly reduce hardware requirements and computational complexity, but adjacent subarray designs of the same size can result in high sidelobes, grating lobes, reduced gain, and offset of pointing angle. The interference from the grating lobe direction affects the detection and identification of the target signal, and the following methods are generally used to eliminate the influence of the grating lobe: one is to divide the subarrays randomly so that the spacing is not uniform. The method does not increase the complexity of the system, but is more complex than uniformly dividing random division, and no fixed principle can be found. And the second is a subarray overlapping division method which has a certain criterion and can also reduce the influence of grating lobes, but the system complexity is increased. In order to reduce the number of active elements and the cost, another method is to put the active and passive elements together and use density weighting. The density weighted antenna array is an unequal-spacing weighted antenna array, which approximates an ideal antenna aperture current distribution function by the variation of the spacing between active elements, and the excitation current amplitude of each antenna element is the same. Because the active array elements are randomly placed, the grating lobe problem is not serious under the condition of equal weighting of the subarray level.
Most radars now employ azimuth elevation type antenna mounts. In the radar self-tracking, the azimuth branch should add secant compensation in principle, and the compensation coefficient will increase gradually with the increase of elevation angle. Since the compensation coefficient tends to be infinite, the square error always exceeds the transverse error angular velocity and angular acceleration detected by the antenna feeder and the receiving system, and the angular velocity and the angular acceleration tend to be infinite, so that the following error is caused. And under the condition that the transverse error between the radar axis and the target is not changed, the higher the elevation angle is, the larger the error angle is, and when the elevation angle tends to track the target, the target cannot be followed by the system in the azimuth branch, so that the target is unlocked. The azimuth error angle tends to be infinite. Similarly, when the radar axis tracks the target, the ship continuously moves under the influence of wind and waves on the sea with constant transverse angular velocity and acceleration, the higher the elevation angle is, the azimuth motion is required, the larger the angular velocity and the angular acceleration of the ship-borne radar continuously and reversely moving along with the movement of the carrier are, and the radar is frequently reversed, continuously accelerated and decelerated, so that the angular velocity makes the radar have poor running stability. Noise amplification enables random errors of tracking to increase ideal feed sources of angular acceleration and error demodulation, errors solved by an acquisition circuit are strictly linear relation among azimuth branch, pitching offset voltage and transverse error angles in a radar self-tracking loop, and a secant compensation link is added in the radar self-tracking loop in a noise-free way, so that the transverse errors are changed into sounds. In practice, due to various interferences and noises, the ideal linearity is converted into an azimuth error, the azimuth error is sent to a servo driving system, a radar is driven to upwards superimpose a noise signal, and the noise moves in a direction with reduced error through a secant compensation link and is amplified, so that the higher the elevation angle is, the higher the noise entering an azimuth servo control loop is, for the same lateral error. The tracking system will affect the tracking performance of the high elevation arc-segment radar after adding secant compensation. The factors that the high elevation arc section influences the stable tracking of the radar, namely the servo system is more sensitive to the noise of an error demodulation and acquisition channel, so that the random tracking error is increased. When the survey ship is used for marine survey and control, due to the influence of factors such as bad sea conditions, a high-elevation arc segment is sometimes required to be tracked and controlled, and the high-elevation arc segment is always tracked in the tasks of the magic boat and Chang' e. The jitter is larger and larger along with the continuous increase of the elevation angle, and the jitter is maximum when the elevation angle reaches the maximum. The azimuth jitter exists because the azimuth-elevation type radar device tracks the antenna when tracking a high-elevation low-speed target. When the radar of the azimuth-elevation antenna pedestal generally tracks at a high elevation angle, the tracking performance of the radar is influenced by some factors and often cannot stably track a target. When the elevation angle of the target is below the m9n beamwidth) antenna main lobe is on the ground) when the received signal is the vector sum of the direct signal and the ground reflected signal) corresponds to angular flicker occurring between the target and its image) makes low elevation tracking difficult. The data of radar tracking shows that not only the dynamic lag affects the tracking performance of the radar at high elevation angle, but also the target is lost when the dynamic lag is serious. When the radar works at a high elevation angle, the motor, the drive and the antenna structure are all in a full-load working state, the target of the radar is lost, and due to ship shaking, the dead zone of the circuit is increased and the service life is greatly damaged, a reasonable random error tracking strategy caused by high elevation angle tracking error demodulation and more sensitive acquisition channel noise is very necessary. When the high elevation angle target is tracked, when the radar enters an arc segment with intense speed and elevation angle, the measurement and control task is tracked. After a changing area, a tracking "dead zone" is formed due to severe dynamic hysteresis of the radar. The tracking performance of the radar at high elevation angle is also influenced, and the tracking strategy of the target at a high speed relative to the observation station is also a main influence factor. When the radar is used for tracking a high elevation angle, the azimuth maximum tracking angular speed of the needle ship radar can be completed within at least the required time when the target passes the top, so that the equipment safety is guaranteed, effective data are obtained, and the high rotation of the radar is satisfactorily completed. At present, the research on digital multi-beam forming at home and abroad is generally based on a sub-array division structure of non-uniform, overlapped sub-arrays and crossed sub-arrays, and the digital multi-beam forming based on the uniform sub-array division of the multi-beam spherical phased array antenna is rarely researched. The multi-beam spherical phased array aerospace measurement and control system is just a multi-target measurement and control system which is suitable for the development of the demand.
Disclosure of Invention
The invention aims to provide a spherical phased array antenna wave control self-tracking difference array partitioning method with low hardware resource consumption, low cost and high reliability according to the characteristics of difference array partitioning in the application of a multi-beam spherical phased array antenna in the field of range measurement and control.
The technical scheme adopted by the invention for solving the technical problems is as follows: a spherical phased array antenna wave control self-tracking difference array dividing method is characterized in that: dividing an array into a plurality of sub-arrays by adopting a polar coordinate mode under a spherical phased array antenna coordinate system, dividing array elements with the same quantization value into one sub-array, wherein a spherical array antenna difference array is divided according to the azimuth and the elevation direction, a array plane azimuth difference array is divided according to a Z-axis tangent plane, an array plane elevation difference array is divided according to a mode orthogonal to the azimuth difference array, the polarity is taken according to the clockwise or counterclockwise clock direction, the position information of a space target is represented by an azimuth angle, a pitch angle and a target distance, a coordinate system is rotated by taking a Z-axis as a center, an azimuth angle psi is rotated to zero, a pitch angle phi is rotated by taking a y-axis as the center until the x-axis points to the target, and the x-axis points to the target; based on a spherical phased array antenna difference array division algorithm, under a new rotated coordinate system, calculating a rotation vector A of a target pointing to the coordinate system under an original coordinate system to obtain a maximum pitch angle threshold value of the spherical phased array antenna difference array division, according to the obtained pitch angle threshold value, when the division of the difference array exceeds a certain elevation angle, dividing the pitch angle of the difference array, and keeping the maximum pitch angle of the difference array on the threshold angle; and according to the antenna aperture and the given target tracking over-top characteristic analysis and simulation, obtaining the maximum pitch angle threshold of the target which is tracked over-top by the antenna and is not lost. The spherical phased array antenna is utilized to track the over-the-top target time difference array rotation characteristic, an equivalent antenna rotation model is established, digital beam control and in-subarray phase shifting are conducted on the subarray level, a difference array division high elevation angle maximum keeping method is adopted, beam coverage on a sensitive area is achieved through multi-feed source forming, and tracking of a wave control angle tracking loop of the spherical phased array antenna on the over-the-top target point is completed.
Compared with the prior art, the invention has the following beneficial effects:
the consumed hardware resource is small, and the cost is low. Is simple and reliable. The invention adopts a polar coordinate mode under a spherical phased array antenna coordinate system to divide the array into a plurality of sub-arrays and divide array elements with the same quantization value into one sub-array, thereby obtaining a directional diagram with low side lobes, having fewer sub-arrays and avoiding the occurrence of grating lobes and grating zeros. The spherical array antenna difference array division is divided according to the azimuth and the pitching direction, the array face azimuth difference array division is divided according to the tangent plane of the Z axis, the array face pitching difference array division is divided according to the orthogonal mode with the azimuth difference array, the maximum pitch angle threshold of the target which is tracked by the antenna and is not lost after the antenna passes the top can be obtained according to the analysis and simulation method of the target tracking over the top through the designed antenna aperture, the polarity is taken according to the clockwise or counterclockwise direction, the position information of the space target is represented by the azimuth angle, the pitch angle and the target distance, the coordinate system is rotated by taking the Z axis as the center, the azimuth angle psi is rotated to zero, the pitch angle phi is rotated to the target which is pointed by the X axis by taking the Y axis as the center, the target over the top tracking design is completed, the noise power output by the array is minimum, the flexibility is great, the beam pointing direction, the method has the advantages of enhancing the expected signal, inhibiting the interference signal, improving the resolution capability and the angle measurement precision of the space signal and the target, along with less resource occupation and simple and reliable method. The method has the advantages that complex equipment is not needed, only some changes in the wave control software tracking process are involved, the original spherical phased array antenna equipment is utilized, additional hardware is not added, the equipment quantity and the use of additional hardware are not needed, hardware resources and hardware cost are saved, the complexity of the system is greatly reduced, and the cost is saved.
The reliability is high. The method is based on the spherical phased array antenna difference array division algorithm, under the new rotated coordinate system, the rotation vector A of the target pointing coordinate system under the original coordinate system is calculated, the maximum pitch angle threshold value of the spherical phased array antenna difference array division is obtained, and the requirement on hardware and the calculation complexity are reduced. And according to the obtained pitch angle threshold, dividing the pitch angle of the difference array when the target exceeds a certain elevation angle, and keeping the maximum pitch angle of the difference array at the threshold angle. According to the obtained pitch angle threshold, a method of maximally maintaining a differential array pitch angle is adopted, so that the spherical phased array antenna can stably track the target in the process of passing the top of the aerospace craft, and the problem of target loss caused by overlarge steady-state tracking error of the target in the process of tracking the top-passing target at a high elevation angle and the tracked target is avoided by limiting the maximum elevation angle during division of the differential array.
According to the antenna aperture and the target tracking over-top characteristic analysis and simulation, the maximum pitch angle threshold of the antenna tracking over-top without losing the target is obtained. The spherical array antenna is utilized to track the overtop target time difference array rotation characteristic, an equivalent antenna rotation model is established, the spherical phased array antenna tracking is completed by adopting a difference array division high elevation maximum keeping method, the sum and difference wave beams obtained after division have good performance, the reliability is improved, the defects that adjacent subarray designs with the same size can cause high side lobes, grating lobes, gain reduction and deviation of a pointing angle are overcome, and the problem that the azimuth angle and the pitch angle are too large dynamically in the target high elevation overtop tracking process in a measurement and control system is solved.
The operation is simple, convenient and quick, and the automatic design is convenient. The invention keeps the equipment state of the original system, skillfully utilizes the characteristic of word multi-beam forming spherical array antenna differential array division, and carries out quantitative analysis on the wave control angle tracking dynamic performance of a target during over-top tracking, wherein the wave control angle tracking for high elevation angle limit of the divided spherical phased array antenna differential array is carried out on the basis of the analysis, and the maximum pitch angle threshold value of the differential array division can be obtained according to the indexes of the analyzed and designed antenna. In the subarray division of the digital beam forming, an optimal subarray division scheme is balanced in targets with mutually restricted detection probability, target angle estimation precision, side lobe level and the like, side lobes of a self-adaptive directional diagram are well improved, meanwhile, the interference of a subarray level self-adaptive digital beam forming jammer in the direction is obviously inhibited, and the requirement that the target is not lost when an antenna is in high elevation angle self-tracking can be met.
Drawings
The invention is further illustrated with reference to the figures and examples.
FIG. 1 is a schematic diagram of the differential array partitioning of a spherical phased array antenna of the present invention; wherein, fig. 1 is a schematic diagram of a coordinate system of a spherical phased array antenna; a schematic diagram of the difference array division of the spherical phased array antenna;
FIG. 2 is a schematic diagram of rotation of a spherical phased array antenna difference array partition when a tracked target passes over the top.
FIG. 3 is a schematic diagram of an equivalent model of a difference array partition when rotating over the top of a tracked target;
FIG. 4 is a simulation of the flight trajectory of an aerospace vehicle according to the present invention, wherein FIG. 4a is a graph illustrating the variation of the angle of a spherical phased array antenna tracking a satellite when the elevation angle is over the top of 73.5 degrees; fig. 4b is a diagram illustrating the variation curve of the angular velocity of the spherical phased array antenna tracking the satellite when the elevation angle is over the top of 73.5 degrees.
Detailed Description
See fig. 1. According to the invention, a polar coordinate mode is adopted under a spherical phased array antenna coordinate system, the array is divided into a plurality of sub-arrays, array elements with the same quantization value are divided into one sub-array, wherein the spherical array antenna difference array division is divided according to the azimuth and the pitch direction, the array surface azimuth difference array division is divided according to the Z-axis tangent plane, the array surface pitch difference array division is divided according to the orthogonal mode with the azimuth difference array, the polarity is taken according to the clockwise or counterclockwise direction, the azimuth angle, the pitch angle and the target distance are used for representing the position information of a space target, a coordinate system is rotated by taking the Z-axis as the center, the azimuth angle psi is rotated to zero degree, then the pitch angle is rotated by taking the y-axis as the center until the phi is directed to the target, and the x-axis; based on a spherical phased array antenna difference array division algorithm, under a new rotated coordinate system, calculating a rotation vector A of a target pointing to the coordinate system under an original coordinate system to obtain a maximum pitch angle threshold value of the spherical phased array antenna difference array division, according to the obtained pitch angle threshold value, when the division of the difference array exceeds a certain elevation angle, dividing the pitch angle of the difference array, and keeping the maximum pitch angle of the difference array on the threshold angle; and according to the antenna aperture and the given target tracking over-top characteristic analysis and simulation, obtaining the maximum pitch angle threshold of the target which is tracked over-top by the antenna and is not lost. The spherical phased array antenna is utilized to track the over-the-top target time difference array rotation characteristic, an equivalent antenna rotation model is established, digital beam control and in-subarray phase shifting are conducted on the subarray level, a difference array division high elevation angle maximum keeping method is adopted, beam coverage on a sensitive area is achieved through multi-feed source forming, and tracking of a wave control angle tracking loop of the spherical phased array antenna on the over-the-top target point is completed.
Applying a rotation matrix algorithm in the new rotated coordinate system, calculating the pointing coordinate and the target pointing coordinate in the original coordinate system, calculating a rotation angle and a rotation axis, and then calculating a corresponding rotation matrix by using a Rodrigue rotation formula to obtain a coordinate system rotation vector matrix A1:
Figure BDA0002942244440000061
wherein:
F11＝cosθEcosθA；F12＝cosθEsinθA；F13＝sinθE；
F21＝-sinθA；F22＝cosθA；F23＝0；
F31＝-sinθEcosθA；F32＝-sinθEsinθA；F33＝cosθE；
where F11 to F33 represent elements of the rotation vector matrix a1, θ E is the pitch angle of the target in the original coordinate system, and θ a is the azimuth angle of the target in the original coordinate system.
According to the target coordinate (x) under the original coordinate system1，y1，z1) Calculating target pointing coordinates in coordinate system transformation
Figure BDA0002942244440000071
Figure BDA0002942244440000072
Figure BDA0002942244440000073
Wherein: x is the number of1Is the normalized x-axis coordinate value, y, of the target in the original coordinate system1Is the normalized y-axis coordinate value, z, of the target in the original coordinate system1Is the normalized z-axis coordinate value of the target in the original coordinate system, thetae is the pitch angle of the target in the original coordinate system, and thetaa is the pitch angle of the target in the original coordinate system.
According to the projection of the target motion track on the spherical array to obtain (x)2，y2，z2)＝(x1，y1，z1)A1′
Figure BDA0002942244440000074
Figure BDA0002942244440000075
Wherein x is2Is the coordinate value, y, of the target in the new coordinate system of the spherical phased array antenna2Is the coordinate value of the target in the new coordinate system, z2Is the coordinate value of the target in the new coordinate system, phiTargetIs the target pitch angle psi in the new coordinate system after the spherical phased array antenna coordinate system is rotatedTargetIs the azimuth of the target in the new coordinate system after the coordinate system is rotated.
Calculating the coordinate (x) of the array element after the rotation of the coordinate system by using the rotation vector matrix A14，y4，z4)＝(x3，y3，z3)A1′
Wherein: x is the number of3,y3,z3Is the coordinate value of the array element in the original coordinate system, x4，y4，z4The coordinate values of the array elements in the new coordinate system after the coordinate system is rotated. Calculating the pitch angle array element phi of the array element under the new coordinate systemArray elementAnd azimuth psi of array element under new coordinate systemArray element
Figure BDA0002942244440000076
Figure BDA0002942244440000077
Wherein phi isTargetIs the pitch angle of the array element in the new coordinate system after the coordinate system is rotated, psiTargetThe azimuth angle of the array element in the new coordinate system after the coordinate system is rotated.
The difference array division strategy is that the azimuth difference array is divided according to the difference array division strategy: phi is aArray elementAt phiTarget～φTargetTaking the azimuth difference array positive value within +90 degrees; phi is aArray elementAt phiTarget～φTarget-taking azimuth difference array negative values within 90 °; the pitch difference array is divided according to the following strategies: phi is aArray elementIn phiTarget～φTargetTaking the positive value of the pitch difference array within +/-90 degrees; phi is aArray elementAt phiTarget～φTargetTaken as difference in pitch within-90 deg.)Array negative values.
See fig. 2. The spherical array antenna difference array division is divided according to the azimuth and the elevation direction, the array plane azimuth difference array division is divided according to the tangent plane of the Z axis, the polarity is taken according to the clockwise direction or the counterclockwise direction, the array plane elevation difference array division is divided according to the orthogonal mode with the array plane difference array division, the division mode can cause the rotation phenomenon of the difference array division when the antenna is at a high elevation angle, as shown in figure 2, the larger the antenna elevation angle is, the larger the rotation angular velocity of the difference array is.
See fig. 3. If the antenna azimuth direction is consistent with the target moving direction at the time 0, the antenna azimuth direction angular velocity component is Ω cos φ t at the time t, and the antenna pitching azimuth velocity is: Ω sin φ t. Dividing selection characteristics when the tracked target passes the top according to the difference array shown in figure 3, establishing an equivalent antenna rotation model by utilizing the rotation characteristics of the time difference array of the spherical array antenna for tracking the top-passing target, analyzing the dynamic characteristics of the target when the target passes the top, and setting the angular velocity of the target in the azimuth to be omega at the passing top according to the equivalent antenna rotation model, wherein the angular velocity of the target in the azimuth is omega at the passing top
The angular velocity component in the azimuth direction of the over-vertex antenna is: omega cos phi t-t＝0 (1)；
The angular velocity component in the elevation direction of the over-the-vertex antenna is: omega sin phi tt＝0＝0 (2)；
The angular acceleration component of the over-vertex antenna in the azimuth direction is as follows:
Figure BDA0002942244440000081
the angular acceleration component in the elevation direction of the over-vertex antenna is as follows:
Figure BDA0002942244440000082
according to a steady-state error analysis formula of wave control angle tracking and target angular acceleration:
Figure BDA0002942244440000083
wherein: r is angular acceleration, ωnFor the loop resonance frequency:
Figure BDA0002942244440000084
taking tracking loop bandwidth 2BL＝1HZThen:
Figure BDA0002942244440000085
substituting equation (4) results in: thetae pitch＝1.1236Ω2 (5)
Wherein R is angular acceleration/s, 2BLFor wave-controlled tracking of loop bandwidth, omeganAt the resonant frequency of the loop, Ω is the azimuthal velocity of the target at the over-peak.
According to the design index of the spherical antenna and the steady-state error analysis formula of the target angular acceleration, the maximum difference array division pitch angle threshold of the antenna for target over-top tracking is obtained, and according to the pitch angle threshold, the spherical phased array antenna tracking flow design is completed by adopting a difference array division high-elevation maximum holding method, wherein the process is as follows:
firstly, according to the designed beam width of the spherical array antenna, a steady-state error analysis formula (5) of a wave control tracking loop at an over-fixed point is used for obtaining the maximum pitch angle acceleration of a target tracked by the spherical array antenna. For example: assuming that the half-beam width of the antenna is 0.5 degrees, the maximum tolerable over-pointing azimuth velocity can be calculated to be 5.05 degrees/second according to the formula (5); and simulating the azimuth angle acceleration of the spherical array antenna under different over-vertex pitch angle conditions according to the track characteristics of the aerospace craft. In the simulation, the height of an aircraft orbit is set to be 300 kilometers, and the target orbit simulation experiment conditions are as follows: the height of the target track is 300 kilometers, and the target flying speed is 7.75 kilometers/second; radius of the earth: 6.37814 x 103 km; the method is obtained by simulating the flight trajectory of the spacecraft: when the satellite target crosses the top at an elevation angle of 73.5 degrees, the azimuth velocity is greater than 5 degrees/second, and the simulation result is shown in fig. 4. Therefore, according to the conclusion of the analysis, the designed spherical phased array antenna difference array division pitch angle threshold value is 73.5 degrees.
When the target exceeds a certain elevation angle, the pitch angle of the divided difference array is kept not to be increased, namely the steady state error of the wave control angle tracking loop of the spherical array antenna does not exceed the half beam width of the antenna, namely the wave control angle tracking loop of the spherical array antenna does not lose the target.
The above detailed description of the embodiments of the present invention, and the detailed description of the embodiments of the present invention used herein, is merely intended to facilitate the understanding of the methods and apparatuses of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.

Claims (10)

1. A spherical phased array antenna wave control self-tracking difference array dividing method is characterized in that: dividing an array into a plurality of sub-arrays by adopting a polar coordinate mode under a spherical phased array antenna coordinate system, dividing array elements with the same quantization value into one sub-array, wherein a spherical array antenna difference array is divided according to the azimuth and the elevation direction, a array plane azimuth difference array is divided according to a Z-axis tangent plane, an array plane elevation difference array is divided according to a mode orthogonal to the azimuth difference array, the polarity is taken according to the clockwise or counterclockwise clock direction, the position information of a space target is represented by an azimuth angle, a pitch angle and a target distance, a coordinate system is rotated by taking a Z-axis as a center, an azimuth angle psi is rotated to zero, a pitch angle phi is rotated by taking a y-axis as the center until the x-axis points to the target, and the x-axis points to the target; based on a spherical phased array antenna difference array division algorithm, under a new rotated coordinate system, calculating a rotation vector A of a target pointing to the coordinate system under an original coordinate system to obtain a maximum pitch angle threshold value of the spherical phased array antenna difference array division, according to the obtained pitch angle threshold value, when the division of the difference array exceeds a certain elevation angle, dividing the pitch angle of the difference array, and keeping the maximum pitch angle of the difference array on the threshold angle; according to the antenna aperture, according to the analysis and simulation of the given target tracking over-top characteristic, the maximum pitch angle threshold of the antenna tracking over-top without losing the target is obtained, the spherical array antenna is utilized to track the over-top target time difference array rotation characteristic, an equivalent antenna rotation model is established, digital beam control and intra-subarray phase shifting are carried out on the subarray level, a difference array division high elevation maximum keeping method is adopted, beam coverage on a sensitive area is realized through multi-feed source forming, and the tracking of the wave control angle tracking loop of the spherical phased array antenna on the target over-top is completed.
2. The spherical phased array antenna difference array partitioning and wave-controlled self-tracking method as claimed in claim 1, characterized in that: applying a rotation matrix algorithm in the new rotated coordinate system, calculating the pointing coordinate and the target pointing coordinate in the original coordinate system, calculating a rotation angle and a rotation axis, and then calculating a corresponding rotation matrix by using a Rodrigue rotation formula to obtain a coordinate system rotation vector matrix A1:
Figure FDA0002942244430000011
wherein:
F11＝cosθE cosθA；F12＝cosθE sinθA；F13＝sinθE；
F21＝-sinθA；F22＝cosθA；F23＝0；
F31＝-sinθE cosθA；F32＝-sinθE sinθA；F33＝cosθE；
where F11 to F33 represent elements of the rotation vector matrix a1, θ E is the pitch angle of the target in the original coordinate system, and θ a is the azimuth angle of the target in the original coordinate system.
3. The spherical phased array antenna difference array partitioning and wave-controlled self-tracking method as claimed in claim 1, characterized in that: according to the target coordinate (x) under the original coordinate system1，y1，z1) Calculating target pointing coordinates in coordinate system transformation
Figure FDA0002942244430000021
Figure FDA0002942244430000022
Figure FDA0002942244430000023
Wherein: x is the number of1Is the normalized x-axis coordinate value, y, of the target in the original coordinate system1Is the normalized y-axis coordinate value, z, of the target in the original coordinate system1Is the normalized z-axis coordinate value of the target in the original coordinate system, thetae is the pitch angle of the target in the original coordinate system, and thetaa is the pitch angle of the target in the original coordinate system.
4. The spherical phased array antenna difference array partitioning and wave-controlled self-tracking method as claimed in claim 1, characterized in that: according to the projection of the target motion track on the spherical array to obtain (x)2，y2，z2)＝(x1，y1，z1)A1′
Figure FDA0002942244430000024
Figure FDA0002942244430000025
Wherein x is2Is the coordinate value, y, of the target in the new coordinate system of the spherical phased array antenna2Is the coordinate value of the target in the new coordinate system, z2Is the coordinate value of the target in the new coordinate system, phiTargetIs the target pitch angle psi in the new coordinate system after the spherical phased array antenna coordinate system is rotatedTargetIs the azimuth of the target in the new coordinate system after the coordinate system is rotated.
5. The spherical surface of claim 1The phased array antenna difference array division and wave control self-tracking method is characterized in that: calculating the coordinate (x) of the array element after the rotation of the coordinate system by using the rotation vector matrix A14，y4，z4)＝(x3，y3，z3) A1' calculating the pitch angle of array element under new coordinate systemArray elementAnd azimuth psi of array element under new coordinate systemArray element
Figure FDA0002942244430000026
Figure FDA0002942244430000027
Wherein: x is the number of3,y3,z3Is the coordinate value of the array element in the original coordinate system, x4，y4，z4The coordinate values of the array elements in the new coordinate system after the rotation of the coordinate system,targetIs the pitch angle of the array element in the new coordinate system after the coordinate system is rotated, psiTargetThe azimuth angle of the array element in the new coordinate system after the coordinate system is rotated.
6. The spherical phased array antenna difference array partitioning and wave-controlled self-tracking method as claimed in claim 1, characterized in that: the azimuth difference array is divided according to a difference array division strategy: phi is aArray elementAt phiTarget～φTargetTaking the azimuth difference array positive value within +90 degrees; phi is aArray elementAt phiTarget～φTarget-taking azimuth difference array negative values within 90 °; the pitch difference array is divided according to the following strategies: phi is aArray elementIn phiTarget～φTargetTaking the positive value of the pitch difference array within +/-90 degrees; phi is aArray elementAt phiTarget～φTargetTaking the negative value of the pitch difference array within 90 deg..
7. The spherical phased array antenna difference array partitioning and wave-controlled self-tracking method as claimed in claim 1, characterized in that: dividing a spherical array antenna difference array according to the azimuth and the elevation direction, dividing a wavefront azimuth difference array according to a Z-axis tangent plane, and taking polarity according to a clockwise or counterclockwise clock direction, and dividing a wavefront elevation difference array according to a mode orthogonal to the wavefront elevation difference array division; if the antenna azimuth direction is consistent with the target moving direction at the time 0, the antenna azimuth direction angular velocity component is Ω cos φ t at the time t, and the antenna pitching azimuth velocity is: Ω sin φ t.
8. The spherical phased array antenna difference array partitioning and wave-controlled self-tracking method as claimed in claim 8, characterized in that: dividing selection characteristics when the tracked target passes the top according to the difference array, establishing an equivalent antenna rotation model by utilizing the rotation characteristics of the time difference array of the spherical array antenna for tracking the top-passing target, analyzing the dynamic characteristics of the target when the target passes the top, and setting the angular velocity of the target in the azimuth to be omega at the passing top according to the equivalent antenna rotation model, wherein the angular velocity of the target in the azimuth is omega at the passing top, and then the target passes the top
The angular velocity component in the azimuth direction of the over-vertex antenna is: omega cos phi t-t＝0 (1)；
The angular velocity component in the elevation direction of the over-the-vertex antenna is: omega sin phi tt＝0＝0 (2)；
The angular acceleration component of the over-vertex antenna in the azimuth direction is as follows:
Figure FDA0002942244430000031
the angular acceleration component in the elevation direction of the over-vertex antenna is as follows:
Figure FDA0002942244430000032
9. the spherical phased array antenna difference array partitioning and wave-controlled self-tracking method as claimed in claim 1, characterized in that: according to a steady-state error analysis formula of wave control angle tracking and target angular acceleration:
Figure FDA0002942244430000033
wherein: r is angular acceleration, ωnFor the loop resonance frequency:
Figure FDA0002942244430000034
taking tracking loop bandwidth 2BL＝1HZThen:
Figure FDA0002942244430000035
substituting equation (4) results in: thetae pitch＝1.1236Ω2 (5)
Wherein R is angular acceleration/s, 2BLFor wave-controlled tracking of loop bandwidth, omeganAt the resonant frequency of the loop, Ω is the azimuthal velocity of the target at the over-peak.
10. The spherical phased array antenna difference array partitioning and wave-controlled self-tracking method as claimed in claim 9, characterized in that: and according to the pitch angle threshold, adopting a difference array division high elevation maximum keeping method to complete the tracking process design of the spherical phased array antenna.
CN202110183867.5A 2021-02-10 2021-02-10 Differential array dividing method for wave control self-tracking of spherical phased array antenna Active CN112965041B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202110183867.5A CN112965041B (en) 2021-02-10 2021-02-10 Differential array dividing method for wave control self-tracking of spherical phased array antenna

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202110183867.5A CN112965041B (en) 2021-02-10 2021-02-10 Differential array dividing method for wave control self-tracking of spherical phased array antenna

Publications (2)

Publication Number Publication Date
CN112965041A true CN112965041A (en) 2021-06-15
CN112965041B CN112965041B (en) 2023-08-01

Family

ID=76284824

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202110183867.5A Active CN112965041B (en) 2021-02-10 2021-02-10 Differential array dividing method for wave control self-tracking of spherical phased array antenna

Country Status (1)

Country Link
CN (1) CN112965041B (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114927884A (en) * 2022-05-18 2022-08-19 中国电子科技集团公司第十研究所 Dynamic compensation method for improving performance of vehicle-mounted phased array antenna
CN115407804A (en) * 2022-10-31 2022-11-29 中国人民解放军63921部队 Tracking method, ground measurement and control equipment, terminal equipment and storage medium
CN115473047A (en) * 2022-08-12 2022-12-13 中国电子科技集团公司第二十九研究所 Overhead tracking method of VICTS antenna
CN115603051A (en) * 2022-11-29 2023-01-13 中国电子科技集团公司第十研究所（Cn） Calibration method for calibration area phase of multi-beam spherical phased array antenna
CN115629240A (en) * 2022-12-01 2023-01-20 北京航天驭星科技有限公司 Phased array antenna directional pattern on-orbit testing method and device, electronic equipment and medium
RU2794466C1 (en) * 2022-06-02 2023-04-19 Федеральное государственное унитарное предприятие "Ростовский-на-Дону научно-исследовательский институт радиосвязи" (ФГУП "РНИИРС") Method for surveying airspace by a pulse-doppler radar station with an active phased antenna array
CN116031664A (en) * 2023-03-20 2023-04-28 成都瑞迪威科技有限公司 Transmit-receive common aperture phased array antenna array method for inhibiting grating lobes

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0890849A1 (en) * 1997-07-10 1999-01-13 Imra Europe S.A. Acoustic lobe pattern combination method for improving mapping quality
US20090325598A1 (en) * 2008-06-30 2009-12-31 Guigne Jacques Y Method and system for determining position of a wireless electronic device within a volume
CN102353930A (en) * 2011-06-20 2012-02-15 中国人民解放军第二炮兵工程学院 Design method of high-precision direction-finding array structure
CN104980236A (en) * 2015-05-15 2015-10-14 中国科学院遥感与数字地球研究所 Method for testing tracing performance of low earth orbit satellite Ka-band data receiving system
CN106501770A (en) * 2016-10-26 2017-03-15 黑龙江大学 Based on near-field sources localization method in the far and near field width band mixing source of amplitude phase error array
CN108051803A (en) * 2017-10-25 2018-05-18 西南电子技术研究所（中国电子科技集团公司第十研究所） The method that multi-beam sphere phase array antenna tracking target crosses top
CN108061888A (en) * 2017-11-22 2018-05-22 西南电子技术研究所（中国电子科技集团公司第十研究所） Sphere phase array antenna is to the autotracking method of spacecraft dynamic object
CN110687531A (en) * 2019-09-28 2020-01-14 西南电子技术研究所（中国电子科技集团公司第十研究所） Method for improving self-tracking dynamic target real-time performance of digital multi-beam phased array antenna
CN111142099A (en) * 2020-01-06 2020-05-12 西南电子技术研究所（中国电子科技集团公司第十研究所） Method for solving blind target capture problem of spherical phased array antenna tracking over top
CN111220976A (en) * 2020-01-08 2020-06-02 西南电子技术研究所（中国电子科技集团公司第十研究所） Electric scanning self-tracking method of digital multi-beam phased array antenna for dynamic target

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0890849A1 (en) * 1997-07-10 1999-01-13 Imra Europe S.A. Acoustic lobe pattern combination method for improving mapping quality
US20090325598A1 (en) * 2008-06-30 2009-12-31 Guigne Jacques Y Method and system for determining position of a wireless electronic device within a volume
CN102353930A (en) * 2011-06-20 2012-02-15 中国人民解放军第二炮兵工程学院 Design method of high-precision direction-finding array structure
CN104980236A (en) * 2015-05-15 2015-10-14 中国科学院遥感与数字地球研究所 Method for testing tracing performance of low earth orbit satellite Ka-band data receiving system
CN106501770A (en) * 2016-10-26 2017-03-15 黑龙江大学 Based on near-field sources localization method in the far and near field width band mixing source of amplitude phase error array
CN108051803A (en) * 2017-10-25 2018-05-18 西南电子技术研究所（中国电子科技集团公司第十研究所） The method that multi-beam sphere phase array antenna tracking target crosses top
CN108061888A (en) * 2017-11-22 2018-05-22 西南电子技术研究所（中国电子科技集团公司第十研究所） Sphere phase array antenna is to the autotracking method of spacecraft dynamic object
CN110687531A (en) * 2019-09-28 2020-01-14 西南电子技术研究所（中国电子科技集团公司第十研究所） Method for improving self-tracking dynamic target real-time performance of digital multi-beam phased array antenna
CN111142099A (en) * 2020-01-06 2020-05-12 西南电子技术研究所（中国电子科技集团公司第十研究所） Method for solving blind target capture problem of spherical phased array antenna tracking over top
CN111220976A (en) * 2020-01-08 2020-06-02 西南电子技术研究所（中国电子科技集团公司第十研究所） Electric scanning self-tracking method of digital multi-beam phased array antenna for dynamic target

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
王文政等: ""全空域球面相控阵测控系统的一种过顶跟踪方法"", vol. 60, no. 60, pages 289 - 292 *

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114927884A (en) * 2022-05-18 2022-08-19 中国电子科技集团公司第十研究所 Dynamic compensation method for improving performance of vehicle-mounted phased array antenna
CN114927884B (en) * 2022-05-18 2023-06-23 中国电子科技集团公司第十研究所 Dynamic compensation method for improving performance of vehicle phased array antenna
RU2794466C1 (en) * 2022-06-02 2023-04-19 Федеральное государственное унитарное предприятие "Ростовский-на-Дону научно-исследовательский институт радиосвязи" (ФГУП "РНИИРС") Method for surveying airspace by a pulse-doppler radar station with an active phased antenna array
CN115473047A (en) * 2022-08-12 2022-12-13 中国电子科技集团公司第二十九研究所 Overhead tracking method of VICTS antenna
CN115407804A (en) * 2022-10-31 2022-11-29 中国人民解放军63921部队 Tracking method, ground measurement and control equipment, terminal equipment and storage medium
CN115603051A (en) * 2022-11-29 2023-01-13 中国电子科技集团公司第十研究所（Cn） Calibration method for calibration area phase of multi-beam spherical phased array antenna
CN115629240A (en) * 2022-12-01 2023-01-20 北京航天驭星科技有限公司 Phased array antenna directional pattern on-orbit testing method and device, electronic equipment and medium
CN116031664A (en) * 2023-03-20 2023-04-28 成都瑞迪威科技有限公司 Transmit-receive common aperture phased array antenna array method for inhibiting grating lobes

Also Published As

Publication number Publication date
CN112965041B (en) 2023-08-01

Similar Documents

Publication Publication Date Title
CN112965041B (en) Differential array dividing method for wave control self-tracking of spherical phased array antenna
CN106712866B (en) Communication-in-motion terminal station system and tracking method thereof
CN110515078B (en) Wave position design method for airspace coverage
US8604976B1 (en) Broad beam antenna design for a tilted phased array with platform motion
CN111624565B (en) Multi-area joint beam tracking method for large conformal phased array system
CN108508423A (en) Submatrix number based on special-shaped battle array and poor Monopulse estimation method
CN103630887B (en) The multi-beam sonar of a kind of Multibeam synthesis method and use the method
CN111830332B (en) Full-airspace curved-surface-array multi-calibration-area combined calibration method
CN112968286B (en) Beam control method and device, beam control equipment and beam controller
CN115061156A (en) Array antenna satellite navigation deception resisting method and system based on integrated navigation
CN117111117A (en) Multi-target tracking measurement and control method for full airspace dome phased array antenna
CN113252998B (en) Flatness optimization method for sum and difference beam signal levels of phased array antenna
CN110764059B (en) Method for transmitting and receiving vertical beam three-coordinate phased array radar
US10833757B1 (en) Systems and methods for mitigating adjacent satellite interference
CN206564605U (en) A kind of communication in moving end station system
CN112858994B (en) Amplitude comparison direction finding method based on uniform circular array
CN111813135B (en) Dual-coordinate system full-airspace array beam tracking method
CN116679306A (en) Extended aperture sonar imaging method based on coefficient correction
CN115963454A (en) Method for realizing phase frequency scanning monopulse antenna side lobe shadow masking wave beam
CN115037352A (en) Noise reduction method for satellite beam alignment enhancement
CN110376586A (en) A kind of distributed MIMO radar moving targets detection method based on chromatographic theory
CN115470660B (en) Spherical-cylindrical-area-array difference beam zero-depth optimization method and device
CN115825883B (en) Real-time direct signal interference suppression method for satellite-borne GNSS-S radar
Dianfei et al. Hemispherical coverage array antenna and performance analysis
CN113009518B (en) Multi-beam anti-interference method for satellite navigation signals

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant