Airborne bistatic radar configuration optimization design method and device and radar

Abstract

The invention relates to the technical field of radar signal processing, and provides an airborne bistatic radar configuration optimization design method, an airborne bistatic radar configuration optimization design device and a radar. The method comprises the steps of receiving input parameters; wherein the input parameters comprise a single-base radar maximum detection distance and a double-base maximum detection distance which needs to be reached; determining a double-base baseline length according to the input parameters; determining the height of the aerial carrier according to the maximum detection distance of the single-base radar and the length of the double-base baseline; selecting the motion state of the airborne bistatic radar as a parallel configuration; outputting the optimal configuration related parameters of the airborne bistatic radar; wherein the output parameters comprise the double-base baseline length, the double-base height and the double-base flight direction. According to the invention, ideal bistatic detection power can be achieved under given conditions, and the stability of clutters is the highest and the suppression performance is the best under the proposed airborne bistatic radar configuration.

Description

Technical Field

[0001] The present invention relates to the field of radar signal processing technology, and in particular to an airborne bistatic radar configuration optimization design method, device and radar. Background Art

[0002] Airborne bistatic radar has excellent "four-anti" performance, and compared with airborne single-base radar, airborne bistatic radar can greatly expand the detection range, especially when the airborne platform uses unmanned early warning aircraft, it can effectively realize far-sea detection, and has the advantages of flexibility and long endurance, which greatly improves the detection capability of far sea and far area. Therefore, airborne bistatic radar has received more and more attention. However, when airborne bistatic radar detects low-altitude targets, it will inevitably receive clutter from the ground and sea surface, and the distance non-stationarity of clutter is more serious than that of single-base radar. Airborne early warning radar usually uses space-time adaptive processing (Space-Time Adaptive Processing, referred to as: STAP) technology to effectively suppress clutter, but the prerequisite for STAP to achieve clutter suppression is that the training samples meet the independent and identically distributed (Independent and Identically Distributed, referred to as: IID) condition. At this time, the non-stationary characteristics of clutter will cause the performance of STAP processor to drop sharply. At present, there have been many studies on the clutter modeling and suppression methods of airborne bistatic radars, and some scholars have also studied the detection performance benefits brought by the signal-level coordination and data-level coordination of bistatic / multistatic radars. However, the detection power of airborne bistatic radars also depends on their motion state (i.e., configuration) and configuration. When their motion state or configuration is not good, it is very likely to affect their detection accuracy and subsequent clutter suppression performance.

[0003] In view of this, overcoming the defects of the prior art is an urgent problem to be solved in the field of this technology. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a method, a device and a radar for optimizing the configuration of an airborne bistatic radar, so as to design an optimal airborne bistatic radar.

[0005] The present invention adopts the following technical solution:

[0006] In a first aspect, the present invention provides a method for optimizing the configuration of an airborne bistatic radar, comprising:

[0007] Step 1: Receive input parameters; the input parameters include the maximum detection range R of the single-base radar max , the maximum detection distance R′ of the dual-base that needs to be achieved max ;

[0008] Step 2: Determine the double base baseline length L according to the input parameters of step 1;

[0009] Step 3: According to the maximum detection distance R of the single-base radar in step 1 max Determine the aircraft height h by using the double base line length L in step 2 a ;

[0010] Step 4: Select the airborne bistatic radar motion state as parallel configuration;

[0011] Step 5: Output the optimal configuration parameters of the airborne bistatic radar; the output parameters include the bistatic baseline length L, the bistatic height h t 、h r , dual-base flight direction δ t , δ r ; Among them, h t is the height of the transmitter, h r is the height of the receiver, δ t is the flight direction of the transmitter, δ r is the flight direction of the receiver.

[0012] Preferably, determining the double base baseline length L according to the input parameters of step 1 specifically includes:

[0013] The detection power of the bistatic radar is the Cassini oval line, and the two focal coordinates of the Cassini oval line are (-c, 0) and (c, 0), respectively, c = L / 2, then the standard equation of the oval line is expressed as:

[0014]

[0015] Wherein, x is the abscissa of the point on the Cassini oval, and y is the ordinate of the point on the Cassini oval;

[0016] The intersection of the Cassini oval and the X-axis is and R′ max Expressing the forward detection distance relative to the transmitter, the following formula is used:

[0017]

[0018] When the transmitter position is fixed, at a given dual-base maximum detection distance R′ max Then, the double base baseline length L is determined according to formula (2).

[0019] Preferably, the double base line length

[0020] Preferably, the airborne bistatic radar is a positive side-view array, adopts a one-transmit-one-receive working mode, and the height of the transmitter and the receiver are the same, that is, h t =h r =h a .

[0021] Preferably, the maximum detection distance R of the single-base radar in step 1 max Determine the aircraft height h by using the double base line length L in step 2 a , including:

[0022] The premise for the height design of the transmitter and receiver is that the target is in the line of sight of both transmitter and receiver at the same time, that is, the common view area completely covers the detection range;

[0023] When the heights of the two bases are equal, the length of the common view area on the X axis is Therefore, when the common view area completely covers the detection range, the following formula is obtained:

[0024]

[0025] Determine the aircraft height h according to formula (3): a .

[0026] Preferably, the selecting the airborne bistatic radar motion state as a parallel configuration specifically includes:

[0027] Establish the clutter model of airborne bistatic radar, assuming that the radar antennas are all placed facing sideways, δ t , δ r are the azimuth angles of the flight direction of the transmitting and receiving platform aircraft relative to the baseline direction, and the azimuth and elevation angles of a certain clutter block on the ground relative to the transmitter are θ t and The azimuth and elevation angles relative to the receiver are θ r and Define that when the azimuth rotates clockwise along the Y axis, it is a positive value, otherwise it is a negative value; R t and R r are the distances from the transmitter and receiver to the clutter block, respectively. Then the dual-base distance and R s =R t +R r ;

[0028] According to the double-base geometric relationship, when the receiver points to θ r , bistatic distance and R s In the case of fixed position, the slant range from the clutter block to the receiver is:

[0029]

[0030] in,

[0031]

[0032] Therefore, we further get:

[0033]

[0034] Further calculation is performed to obtain the cone angle ψ of the clutter block relative to the transmitter t and the cone angle ψ relative to the receiver r , then the Doppler frequency of the received echo is expressed as follows:

[0035]

[0036] in, f d is the Doppler frequency of the received echo, λ is the radar operating wavelength, v t and v r denote the speed of the transmitter and receiver respectively, δ t and δ r Represent the flight directions of the transmitter and receiver respectively;

[0037] Then, the main lobe clutter Doppler frequency of each range unit is calculated according to formula (7), and the range-Doppler trajectory of the received echo under each motion state is analyzed, and the motion state when the clutter stability is the strongest is taken as the optimal motion state of the airborne bistatic radar;

[0038] Among them, when the two bases are flying in parallel, that is, δ t =90°、δ r =90°, and when the main lobe of the receiver points to the normal direction, the stability of the clutter is the strongest, so the motion state of the airborne bistatic radar is a parallel configuration.

[0039] Preferably, the output of the optimal configuration-related parameters of the airborne bistatic radar specifically includes:

[0040] Output double base height h t 、h r ; Among them, h t =h r =h a ;

[0041] The output parameters include the double-base baseline length L and the double-base flight direction δ t , δ r .

[0042] In a second aspect, the present invention further provides an airborne bistatic radar configuration optimization design device, which is used to implement the airborne bistatic radar configuration optimization design method described in the first aspect, and the device comprises:

[0043] At least one processor; and a memory in communication with the at least one processor; wherein the memory stores instructions executable by the at least one processor, and the instructions are executed by the processor to execute the airborne bistatic radar configuration optimization design method described in the first aspect.

[0044] In a third aspect, the present invention further provides a non-volatile computer storage medium, wherein the computer storage medium stores computer executable instructions, and the computer executable instructions are executed by one or more processors to complete the method described in the first aspect.

[0045] In a fourth aspect, a chip is provided, comprising: a processor and an interface, for calling and running a computer program stored in the memory from a memory, and executing the method of the first aspect.

[0046] According to a fifth aspect, a computer program product comprising instructions is provided. When the instructions are executed on a computer or a processor, the computer or the processor executes the method according to the first aspect.

[0047] In a sixth aspect, the present invention further provides an airborne bistatic radar designed using the airborne bistatic radar configuration optimization design method described in the first aspect.

[0048] The present invention first determines the distance between airborne bistatic radars according to the detection power; then determines the height of the carrier according to the constraint of the common view area coverage detection range of the airborne bistatic radar; finally determines the configuration of the airborne bistatic radar according to the stability characteristic and suppression effect of the clutter received by the receiver, so that the ideal bistatic detection power can be achieved under given conditions, and the stability of the clutter is the highest and the suppression performance is the best under the proposed airborne bistatic radar configuration. BRIEF DESCRIPTION OF THE DRAWINGS

[0049] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0050] Figure 1 It is a flow chart of a method for optimizing the configuration of an airborne bistatic radar provided by an embodiment of the present invention;

[0051] Figure 2 It is a schematic diagram of the projection of an airborne bistatic radar on the ground in a configuration optimization design method of an airborne bistatic radar provided by an embodiment of the present invention;

[0052] Figure 3It is a schematic diagram of a common coverage area of ​​an airborne bistatic radar in a configuration optimization design method of an airborne bistatic radar provided by an embodiment of the present invention;

[0053] Figure 4 It is a schematic diagram of a bistatic parallel configuration of an airborne bistatic radar configuration optimization design method provided by an embodiment of the present invention;

[0054] Figure 5 It is a schematic diagram of the geometric relationship of an airborne bistatic radar in a configuration optimization design method of an airborne bistatic radar provided by an embodiment of the present invention;

[0055] Figure 6 It is the main lobe clutter range-Doppler trajectory under three configurations in an airborne bistatic radar configuration optimization design method provided by an embodiment of the present invention;

[0056] Figure 7 It is a flow chart of a method for optimizing the configuration of an airborne bistatic radar provided by an embodiment of the present invention;

[0057] Figure 8 It is a schematic diagram of the architecture of an airborne bistatic radar configuration optimization design device provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0058] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0059] Unless the context requires otherwise, throughout the specification and claims, the term "including" is to be interpreted as open inclusion, that is, "including, but not limited to". In the description of the specification, the terms "one embodiment", "some embodiments", "exemplary embodiments", "examples", "specific examples" or "some examples" and the like are intended to indicate that specific features, structures, materials or characteristics associated with the embodiment or example are included in at least one embodiment or example of the present disclosure. The schematic representation of the above terms does not necessarily refer to the same embodiment or example. In addition, the specific features, structures, materials or characteristics may be included in any one or more embodiments or examples in any appropriate manner, that is, although they may be carried in the embodiments or examples of the above terms due to reasons such as the order and position of appearance, it is not limited to that they can be carried in combination by one embodiment or example.

[0060] In the description of the present invention, the terms "first" and "second" are used only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of indicated technical features. Thus, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the embodiments of the present disclosure, unless otherwise specified, the meaning of "multiple" is two or more. In addition, for example, the description may also use the method of adding "A" and "B" at the end to describe the same type of nouns as two independent individuals. In this case, the corresponding features defined as "A" and "B" are only used to distinguish the same type of individuals for description purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of indicated technical features.

[0061] In the description of the present invention, the expression "A and / or B" (where A and B are used to formally represent specific characteristic contents) will be involved, and the corresponding expressions include the following three combinations: only A, only B, and a combination of A and B.

[0062] As used herein, "about," "substantially," or "approximately" includes the stated value and an average value that is within an acceptable range of deviation from the particular value as determined by one of ordinary skill in the art taking into account the measurements in question and the errors associated with the measurement of the particular quantity (i.e., the limitations of the measurement system).

[0063] In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0064] Embodiment 1:

[0065] Embodiment 1 of the present invention provides a method for optimizing the configuration of an airborne bistatic radar. Figure 1 As shown, including:

[0066] Step 1: Receive input parameters; the input parameters include the maximum detection range R of the single-base radar max , the maximum detection distance R′ of the dual-base that needs to be achieved max .

[0067] Step 2: Determine the double base baseline length L based on the input parameters of step 1.

[0068] Step 3: According to the maximum detection distance R of the single-base radar in step 1 max Determine the aircraft height h by using the double base line length L in step 2 a .

[0069] Step 4: Select the airborne bistatic radar motion state as a parallel configuration; wherein, the parallel configuration is selected by establishing an airborne bistatic radar clutter model for analysis, and it can be considered that the clutter is more stable under the parallel configuration.

[0070] Step 5: Output the optimal configuration parameters of the airborne bistatic radar; the output parameters include the bistatic baseline length L, the bistatic height h t 、h r , dual-base flight direction δ t , δ r ; Among them, h t is the height of the transmitter, h r is the height of the receiver, δ t is the flight direction of the transmitter, δ r is the flight direction of the receiver. According to the optimal configuration related parameters and parallel configuration, an airborne bistatic radar with ideal detection power is constructed.

[0071] Since the configuration of the airborne bistatic radar is a prerequisite for it to achieve ideal detection power, and by changing the configuration mode of the airborne bistatic radar, the radar's distance non-stationary characteristics can be significantly reduced, thereby improving the clutter suppression performance of the STAP processor. Therefore, this embodiment provides an airborne bistatic radar configuration optimization design method to provide theoretical and key technical support for the development of airborne bistatic radars. Specifically: this embodiment first determines the distance between the airborne bistatic radars according to the detection power; then determines the height of the carrier according to the constraint of the common view area coverage detection range of the airborne bistatic radar; finally, determines the configuration of the airborne bistatic radar according to the stability characteristics and suppression effect of the clutter received by the receiver, so that the ideal bistatic detection power can be achieved under given conditions, and the clutter stability is the highest and the suppression performance is the best under the proposed airborne bistatic radar configuration.

[0072] The step of determining the bistatic baseline length L according to the input parameters of step 1 specifically includes: the detection power of the bistatic radar is the Cassini oval line, the two focal coordinates of the Cassini oval line are (-c, 0) and (c, 0), c=L / 2, and the standard equation of the oval line is expressed as:

[0073]

[0074] Wherein, x is the horizontal coordinate of the point on the Cassini oval, and y is the vertical coordinate of the point on the Cassini oval.

[0075] The intersection of the Cassini oval and the X-axis is and R′ max Expressing the forward detection distance relative to the transmitter, the following formula is used:

[0076]

[0077] When the transmitter position is fixed, at a given dual-base maximum detection distance R′ max Then, the distance ahead of the receiver, i.e., the double-base baseline length L, is determined according to formula (2).

[0078] The X-axis may be understood as an extension line formed by connecting the projection points of the transmitter and the receiver on the ground.

[0079] It is calculated that the length of the double base baseline is

[0080] In actual use, the airborne bistatic radar is a positive side-looking array, adopting a one-transmit-one-receive working mode. The receiver is located in the front to receive the echo signal, and the transmitter is located in the rear. The transmitter and receiver are at the same height.

[0081] In an optional implementation, the maximum detection distance R of the single-base radar in step 1 max Determine the aircraft height h by using the double base line length L in step 2 a , including:

[0082] The premise for the height design of transmitter and receiver is that the target is in the line of sight of both transmitter and receiver at the same time, that is, the common view area completely covers the detection range.

[0083] When the heights of the two bases are equal, the length of the common view area on the X axis is Here, · represents a multiplication operation, so when the common view area completely covers the detection range, the following formula is obtained:

[0084]

[0085] Determine the aircraft height h according to formula (3): a .

[0086] In some embodiments, selecting the airborne bistatic radar motion state as a parallel configuration specifically includes:

[0087] Establish the clutter model of airborne bistatic radar, assuming that the radar antennas are all placed facing sideways, δ t , δ r are the azimuth angles of the flight direction of the transmitting and receiving platform aircraft relative to the baseline direction, and the azimuth and elevation angles of a certain clutter block on the ground relative to the transmitter are θ t and The azimuth and elevation angles relative to the receiver are θ r and Define that when the azimuth rotates clockwise along the Y axis, it is a positive value, otherwise it is a negative value; Rt and R r are the distances from the transmitter and receiver to the clutter block, respectively. Then the dual-base distance and R s =R t +R r ; The Y-axis can be understood as an axis that is relatively perpendicular to the X-axis on the plane where the ground is located.

[0088] According to the double-base geometric relationship, when the receiver points to θ r , bistatic distance and R s In the case of fixed position, the slant range from the clutter block to the receiver is:

[0089]

[0090] in,

[0091]

[0092] Therefore, we further get:

[0093]

[0094] Further calculation is performed to obtain the cone angle ψ of the clutter block relative to the transmitter t and the cone angle ψ relative to the receiver r , then the Doppler frequency of the received echo is expressed as follows:

[0095]

[0096] in, f d is the Doppler frequency of the received echo, λ is the radar operating wavelength, v t and v r denote the speed of the transmitter and receiver respectively, δ t and δ r Represent the flight directions of the transmitter and receiver respectively.

[0097] Then, the main lobe clutter Doppler frequency of each range unit is calculated according to formula (7). According to the main lobe clutter Doppler frequency of each range unit, the range-Doppler trajectory of the received echo can be constructed. By analyzing the range-Doppler trajectory of the received echo under various motion states (also called main lobe clutter range-Doppler trajectory), the motion state when the clutter stability is the strongest is taken as the optimal motion state of the airborne bistatic radar; among them, Figure 6 As shown, Figure 6 (a) The motion state is double-base collinear flight (i.e., δ t =180°, δ r =180°) when receiving the echo distance-Doppler trajectory, Figure 6(b) The motion state is double-base parallel flight (i.e., δ t =90°、δ r =90°) when receiving the echo distance-Doppler trajectory, Figure 6 (c) The motion state is double-base vertical flight (i.e., δ t =90°、δ r =180°) when receiving the echo range-Doppler trajectory, it can be seen that when the two bases are flying in parallel, that is, δ t =90°、δ r =90°, and when the main lobe of the receiver points to the normal direction, the stability of the clutter is the strongest, so the motion state of the airborne bistatic radar is a parallel configuration.

[0098] The output of the optimal configuration related parameters of the airborne bistatic radar specifically includes: outputting the bistatic height h t 、h r ; Output parameters: double base baseline length L, double base height h t 、h r , dual-base flight direction δ t , δ r .

[0099] It should be noted here that the X-axis and Y-axis described in this embodiment are described with reference to the plane where the ground is located, that is, the X-axis is obtained by connecting the projection points of the transmitter and the receiver on the ground, and the Y-axis is an axis on the ground perpendicular to the X-axis.

[0100] Embodiment 2:

[0101] The present invention is based on the method described in Example 1, combined with specific application scenarios, and uses technical descriptions in related scenarios to illustrate the implementation process of the present invention in characteristic scenarios.

[0102] The projection of the airborne bistatic radar involved in this embodiment on the ground is as follows: Figure 2 As shown, the bistatic radar connecting line is the X-axis, the midpoint of the connecting line is the coordinate origin, the baseline length is L, and the maximum detection distance is R′ max , which represents the forward detection distance relative to the transmitter; the geometric relationship diagram of the common coverage area Ac involved in the present invention is as follows Figure 3 As shown in the figure, the two circles represent the line-of-sight range of the transmitter and the receiver respectively, and the shaded part Ac represents the common coverage area, referred to as the common view area; the geometric relationship diagram of the airborne bistatic radar used in the present invention is shown in Figure 4 As shown; the double-base parallel configuration of the present invention is as shown Figure 5As shown, the flight direction of the two bases is parallel flight, and the beams point to the same direction; it is assumed that the airborne bistatic radars are all positive side-view arrays, using a one-transmit-one-receive working mode, with the receiver forward to receive the echo signal, the transmitter located at the rear, and the height of the transmitter and the receiver being the same, that is, h t =h r =h a , the length of the double base baseline is L.

[0103] This embodiment provides an airborne bistatic radar configuration optimization design method as follows: Figure 7 As shown, the following steps are included:

[0104] Step 11: Input parameters include the maximum detection range R of the single-base radar max , the maximum detection distance R′ of the dual base that needs to be achieved max .

[0105] Step 12: The detection power of the bistatic radar is the Cassini oval. The coordinates of the two foci of the oval are (-c, 0) and (c, 0), respectively. c = L / 2. The standard equation of the oval can be expressed as:

[0106]

[0107] Therefore, the intersection of the oval and the X-axis is and R′ max Represents the forward detection distance relative to the transmitter, at this time:

[0108]

[0109] When the transmitter position is fixed, given the maximum detection distance of the bistatic radar, the distance ahead of the receiver, that is, the baseline length L of the bistatic radar, can be determined according to formula (2).

[0110] Step 13: The premise of transmitter and receiver height design is that the target must be in the line of sight of both transmitter and receiver at the same time, that is, the common coverage area, referred to as the common view area. When the heights of the two bases are equal, the length of the common view area on the X axis is Therefore, when the common view area completely covers the detection range, we have:

[0111]

[0112] Therefore, the flight altitude of the bistatic radar carrier can be determined according to formula (3).

[0113] Step 14: First, establish the clutter model of the airborne bistatic radar, assuming that the radar antennas are all placed facing sideways, δ t , δ rare the azimuth angles of the flight direction of the transmitting and receiving platform aircraft relative to the baseline direction, and the azimuth and elevation angles of a certain clutter block on the ground relative to the transmitter are θ t and The azimuth and elevation angles relative to the receiver are θ r and The present invention defines that when the azimuth angle rotates clockwise along the Y axis, it is a positive value, otherwise it is a negative value. t and R r are the distances from the transmitter and receiver to the clutter block, respectively. Then the dual-base distance and R s =R t +R r .

[0114] According to the double-base geometric relationship, when the receiver points to θ r , bistatic distance and R s In the case of fixed position, the slant range from the clutter block to the receiver is:

[0115]

[0116] in,

[0117]

[0118] Therefore, we further get:

[0119]

[0120] The cone angle ψ of the clutter block relative to the transmitter and receiver can be further calculated: t and ψ r , then the Doppler frequency of the received echo can be expressed as:

[0121]

[0122] in, f d is the Doppler frequency of the received echo, λ is the radar operating wavelength, v t and v r denote the speed of the transmitter and receiver respectively, δ t and δ r Represent the flight directions of the transmitter and receiver respectively.

[0123] Then, the main lobe clutter Doppler frequency of each range unit is calculated according to formula (7). By analyzing the range-Doppler trajectory, it can be found that when the two bases are flying in parallel and the main lobe of the receiver points in the normal direction, the stability of the clutter is the strongest. Therefore, this embodiment selects the two-base parallel flight configuration.

[0124] Step 15: The output parameters include the double base baseline length L, double base height h t 、h r , dual-base flight direction δ t , δ r .

[0125] This embodiment first determines the distance between the airborne bistatic radars according to the detection power; then determines the height of the carrier according to the constraint of the common view area coverage detection range of the airborne bistatic radar; finally determines the configuration of the airborne bistatic radar according to the stability characteristics and suppression effect of the clutter received by the receiver, so that the airborne bistatic radar can achieve the ideal bistatic detection power under given conditions; and achieve the highest stability of clutter and the best suppression performance.

[0126] Embodiment 3:

[0127] like Figure 8 , which is a schematic diagram of the structure of an airborne bistatic radar configuration optimization design device according to an embodiment of the present invention. The airborne bistatic radar configuration optimization design device according to this embodiment includes one or more processors 21 and a memory 22. Figure 8 A processor 21 is taken as an example.

[0128] The processor 21 and the memory 22 may be connected via a bus or other means. Figure 8 The example of connecting through bus is taken in the following.

[0129] The memory 22 is a non-volatile computer-readable storage medium that can be used to store non-volatile software programs and non-volatile computer executable programs, such as the airborne bistatic radar configuration optimization design method in Example 1. The processor 21 executes the airborne bistatic radar configuration optimization design method by running the non-volatile software programs and instructions stored in the memory 22.

[0130] The memory 22 may include a high-speed random access memory, and may also include a non-volatile memory, such as at least one disk storage device, a flash memory device, or other non-volatile solid-state storage devices. In some embodiments, the memory 22 may optionally include a memory remotely arranged relative to the processor 21, and these remote memories may be connected to the processor 21 via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0131] The program instructions / modules are stored in the memory 22, and when executed by the one or more processors 21, the airborne bistatic radar configuration optimization design method in the above-mentioned embodiment 1 is executed.

[0132] It is worth noting that the information interaction, execution process, etc. between the modules and units within the above-mentioned devices and systems are based on the same concept as the processing method embodiment of the present invention. The specific contents can be found in the description of the method embodiment of the present invention and will not be repeated here.

[0133] A person skilled in the art may understand that all or part of the steps in the various methods of the embodiments may be completed by instructing related hardware through a program, and the program may be stored in a computer-readable storage medium, and the storage medium may include: a read-only memory (ROM), a random access memory (RAM), a disk or an optical disk, etc.

[0134] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for optimizing the configuration of an airborne bistatic radar, characterized in that: include: Step 1: Receive input parameters; the input parameters include the maximum detection range R of the single-base radar max , the maximum detection distance R′ of the dual-base that needs to be achieved max ; Step 2: Determine the double base baseline length L according to the input parameters of step 1; Step 3: According to the maximum detection distance R of the single-base radar in step 1 max Determine the aircraft height h by using the double base line length L in step 2 a ; Step 4: Select the airborne bistatic radar motion state as parallel configuration; Step 5: Output the optimal configuration parameters of the airborne bistatic radar; the output parameters include the bistatic baseline length L, the bistatic height h t 、h r , dual-base flight direction δ t , δ r ; Among them, h t is the height of the transmitter, h r is the height of the receiver, δ t is the flight direction of the transmitter, δ r is the flight direction of the receiver.

2. The method for optimizing the configuration of an airborne bistatic radar according to claim 1, characterized in that: Determining the double-base baseline length L according to the input parameters of step 1 specifically includes: The detection power of the bistatic radar is the Cassini oval line, and the two focal coordinates of the Cassini oval line are (-c, 0) and (c, 0), respectively, c = L / 2, then the standard equation of the oval line is expressed as: Wherein, x is the abscissa of the point on the Cassini oval, and y is the ordinate of the point on the Cassini oval; The intersection of the Cassini oval and the X-axis is and R′ max Expressing the forward detection distance relative to the transmitter, the following formula is used: When the transmitter position is fixed, at a given dual-base maximum detection distance R′ max Then, the double base baseline length L is determined according to formula (2).

3. The method for optimizing the configuration of an airborne bistatic radar according to claim 2, characterized in that: The double base line length 4. The method for optimizing the configuration of an airborne bistatic radar according to claim 2, characterized in that: The airborne bistatic radar is a positive side-viewing array, adopting a one-transmit-one-receive working mode, with the transmitter and receiver at the same height, i.e. h t =h r =h a .

5. The method for optimizing the configuration of an airborne bistatic radar according to claim 1, characterized in that: According to the maximum detection distance R of the single-base radar in step 1 max Determine the aircraft height h by using the double base line length L in step 2 a , specifically including: The premise for the height design of the transmitter and receiver is that the target is in the line of sight of both transmitter and receiver at the same time, that is, the common view area completely covers the detection range; When the heights of the two bases are equal, the length of the common view area on the X axis is Therefore, when the common view area completely covers the detection range, the following formula is obtained: Determine the aircraft height h according to formula (3): a .

6. The method for optimizing the configuration of an airborne bistatic radar according to claim 1, characterized in that: The selecting of the airborne bistatic radar motion state as a parallel configuration specifically includes: Establish the clutter model of airborne bistatic radar, assuming that the radar antennas are all placed facing sideways, δ t , δ r are the azimuth angles of the flight direction of the transmitting and receiving platform aircraft relative to the baseline direction, and the azimuth and elevation angles of a certain clutter block on the ground relative to the transmitter are θ t and The azimuth and elevation angles relative to the receiver are θ r and The azimuth is defined as a positive value when it rotates clockwise along the Y axis, otherwise it is a negative value; R t and R r are the distances from the transmitter and receiver to the clutter block, respectively. Then the dual-base distance and R s =R t +R r ; According to the double-base geometric relationship, when the receiver points to θ r , bistatic distance and R s In the case of fixed position, the slant range from the clutter block to the receiver is: in, Therefore, we further get: Further calculation is performed to obtain the cone angle ψ of the clutter block relative to the transmitter t and the cone angle ψ relative to the receiver r , then the Doppler frequency of the received echo is expressed as follows: in, f d is the Doppler frequency of the received echo, λ is the radar operating wavelength, v t and v r denote the speed of the transmitter and receiver respectively, δ t and δ r Represent the flight directions of the transmitter and receiver respectively; Then, the main lobe clutter Doppler frequency of each range unit is calculated according to formula (7), and the range-Doppler trajectory of the received echo under each motion state is analyzed, and the motion state when the clutter stability is the strongest is taken as the optimal motion state of the airborne bistatic radar; Among them, when the two bases are flying in parallel, that is, δ t =90°、δ r =90°, and when the main lobe of the receiver points to the normal direction, the stability of the clutter is the strongest, so the motion state of the airborne bistatic radar is a parallel configuration.

7. The method for optimizing the configuration of an airborne bistatic radar according to claim 1, characterized in that: The output of the optimal configuration related parameters of the airborne bistatic radar specifically includes: Output parameters: double base baseline length L, double base height h t 、h r , dual-base flight direction δ t , δ r .

8. A non-volatile computer storage medium, characterized in that: The computer storage medium stores computer executable instructions, which are executed by one or more processors to complete the airborne bistatic radar configuration optimization design method as described in any one of claims 1-7.

9. An airborne bistatic radar configuration optimization design device, characterized in that: include: at least one processor; And, a memory communicatively connected to the at least one processor; wherein the memory stores instructions executable by the at least one processor, and the instructions are executed by the processor to execute the airborne bistatic radar configuration optimization design method described in any one of claims 1-7.

10. An airborne bistatic radar, characterized in that: The airborne bistatic radar is designed using the configuration optimization design method of any one of claims 1-7.

Images