An airborne bistatic radar configuration optimization design method, device and radar

Abstract

The present application relates to the technical field of radar signal processing, and provides a kind of airborne bistatic radar configuration optimization design method, device and radar.The method comprises: receiving input parameter;Wherein, input parameter includes single base radar maximum detection distance, the maximum detection distance of double base that needs to be reached;According to input parameter, determine double base baseline length;According to single base radar maximum detection distance and double base baseline length, determine aircraft height;Select airborne bistatic radar motion state as parallel configuration;Output the optimal configuration related parameter of airborne bistatic radar;Wherein, the parameter exported includes double base baseline length, double base height, double base flight direction.The present application can reach ideal double base detection power under given condition, and make the smoothness of clutter highest under the proposed airborne bistatic radar configuration, and the best suppression performance.

Description

Technical Field

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

[0002] Airborne bistatic radars offer excellent "four-way resistance" performance and can significantly extend their detection range compared to monostatic radars. This is especially true when the airborne platform utilizes unmanned early warning aircraft (AWACS), enabling effective long-range detection over the ocean. Their maneuverability and long endurance significantly enhance their detection capabilities over the ocean and beyond. Consequently, airborne bistatic radars are attracting increasing attention. However, when detecting low-altitude targets, bistatic radars inevitably receive clutter from the ground and ocean surfaces, and the range non-stationarity of this clutter is even more severe than that of monostatic radars. Airborne early warning radars typically employ space-time adaptive processing (STAP) technology to effectively suppress clutter. However, STAP's clutter suppression requires that the training samples meet the independent and identically distributed (IID) condition. In such cases, the non-stationary nature of clutter can lead to a sharp decline in STAP processor performance. Currently, there has been extensive research on clutter modeling and suppression methods for airborne bistatic radars. Some scholars have also studied the detection performance benefits of signal-level and data-level collaboration for bistatic and multistatic radars. However, the detection power of an airborne bistatic radar also depends on its motion state (i.e., configuration) and configuration. Poor motion state or configuration can significantly impact 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 this technical field. 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 solutions:

[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-baseline length L based on the input parameters of step 1;

[0009] Step 3: According to the maximum detection range R of the single-base radar in step 1 max Determine the aircraft height h using the double baseline 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, bistatic height h t 、h r , bistatic 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-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. The coordinates of the two foci 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, 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 .

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

[0022] The premise for the height design of transmitter and receiver is that the target is in the sight of 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 the formula (3) a .

[0026] Preferably, 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 pitch 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 angle 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 bistatic 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 When fixed, the slant range from the clutter block to the receiver is:

[0029]

[0030] in,

[0031]

[0032] Therefore, we further get:

[0033]

[0034] Further calculations are 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 the following formula:

[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). By analyzing the range-Doppler trajectory of the received echo under each motion state, the motion state when the clutter is most stable 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 clutter stability 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 bistatic 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 for implementing the airborne bistatic radar configuration optimization design method described in the first aspect, the device comprising:

[0043] 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, the instructions being executed by the processor to perform 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 a memory to execute the method of the first aspect.

[0046] In a fifth aspect, a computer program product comprising instructions is provided, which, when executed on a computer or a processor, causes the computer or the processor to execute the method of 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 based on detection power; then determines the height of the carrier aircraft based on the constraints of the common view area coverage detection range of the airborne bistatic radars; and finally determines the configuration of the airborne bistatic radar based on the stability characteristics and suppression effect of the clutter received by the receiver. Thus, the ideal bistatic detection power can be achieved under given conditions, and the clutter stability is maximized and the suppression performance is best under the proposed airborne bistatic radar configuration. BRIEF DESCRIPTION OF THE DRAWINGS

[0049] 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. Those skilled in the art can also derive other drawings based on these drawings without inventive effort.

[0050] Figure 1 1 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 1 is a schematic diagram of the projection of an airborne bistatic radar on the ground in a method for optimizing the configuration of an airborne bistatic radar provided by an embodiment of the present invention;

[0052] Figure 31 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 1 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 Schematic diagram of geometric relationships of an airborne bistatic radar according to an airborne bistatic radar configuration optimization design method provided by an embodiment of the present invention;

[0055] Figure 6 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 1 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 1 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 solutions and advantages of the present invention more clearly understood, the present invention will be further described in detail below with reference to 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 meaning open inclusion, that is, "including, but not limited to". In the description of the specification, the terms "one embodiment", "some embodiments", "exemplary embodiments", "example", "specific example" or "some examples" and the like are intended to indicate that the 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 for descriptive purposes only, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. 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, "multiple" means 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 description purposes of the same type of individuals, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated.

[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 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 range R of the single-base radar in step 1 max Determine the aircraft height h using the double baseline length L in step 2 a .

[0069] Step 4: Select the parallel configuration for the airborne bistatic radar. The parallel configuration is selected by analyzing the clutter model of the airborne bistatic radar. It can be considered that the clutter is more stable in 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, bistatic height h t 、h r , bistatic 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. An airborne bistatic radar with ideal detection power is constructed according to the optimal configuration-related parameters and parallel configuration.

[0071] Since the configuration of an airborne bistatic radar is a prerequisite for achieving its ideal detection power, and changing the configuration of the airborne bistatic radar can significantly reduce the radar's range non-stationarity, thereby improving the clutter suppression performance of the STAP processor, 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 based on their detection power; then determines the height of the carrier aircraft based on the constraints of the common view area coverage detection range of the airborne bistatic radars; and finally, determines the airborne bistatic radar configuration based on the receiver's reception clutter stationarity and suppression effect. This method achieves ideal bistatic detection power under given conditions and maximizes clutter stationarity and suppression performance under the proposed airborne bistatic radar configuration.

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

[0073]

[0074] Wherein, x is the abscissa of the point on the Cassini oval, and y is the ordinate 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 is determined according to formula (2), that is, the dual-base baseline length L.

[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] The length of the double-base baseline is calculated to be

[0080] In actual use, the airborne bistatic radar is a positive side-looking array that adopts a one-transmit-one-receive working mode. The receiver is located in 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 embodiment, the maximum detection range R of the single-base radar in step 1 is max Determine the aircraft height h using the double baseline length L in step 2 a , specifically 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 the 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 pitch 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 angle is defined as a positive value when it rotates clockwise along the Y axis, 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 bistatic 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 When fixed, the slant range from the clutter block to the receiver is:

[0089]

[0090] in,

[0091]

[0092] Therefore, we further get:

[0093]

[0094] Further calculations are 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 the following formula:

[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 Indicates 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 with the strongest clutter stability 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 (ie δ t =180°、δ r =180°) when receiving the echo at the distance - Doppler trajectory, Figure 6(b) The motion state is dual-base parallel flight (ie, δ t =90°、δ r =90°) when receiving the echo at the distance - Doppler trajectory, Figure 6 (c) The motion state is bi-base vertical flight (i.e. δ t =90°、δ r =180°) when receiving the echo's 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 clutter stability 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 , bistatic 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 of the ground, 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] Example 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 line connecting the two-base radar is the X-axis, the midpoint of the line is the origin of the coordinate system, 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 FIG. 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 in 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 and the transmitter at the rear. The height of the transmitter and receiver are the same, that is, h t =h r =h a , the length of the double base baseline is L.

[0103] This embodiment provides a method for optimizing the design of an airborne bistatic radar configuration. 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 line and the X axis is and R′ max Indicates the forward detection distance relative to the transmitter, at this time:

[0108]

[0109] When the transmitter position is fixed, given the maximum detection range of the bistatic radar, the distance ahead of the receiver, that is, the baseline length L of the bistatic, 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 base stations 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 aircraft 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 pitch 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 bistatic 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 When fixed, 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 Indicates 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 clutter stability is the strongest. Therefore, this embodiment selects the dual-base parallel flight configuration.

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

[0125] This embodiment first determines the distance between airborne bistatic radars based on their detection power; then determines the height of the carrier aircraft based on the constraints of the common view area coverage of the airborne bistatic radars; and finally determines the configuration of the airborne bistatic radars based on the receiver's clutter reception stability and suppression effect. This allows the airborne bistatic radars to achieve ideal bistatic detection power under given conditions, while also maximizing clutter stability and achieving optimal clutter suppression performance.

[0126] Example 3:

[0127] like Figure 8 FIG. 1 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 bus connection is taken as an example.

[0129] The memory 22, as a non-volatile computer-readable storage medium, 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 high-speed random access memory and non-volatile memory, such as at least one disk storage device, flash memory device, or other non-volatile solid-state memory device. In some embodiments, the memory 22 may optionally include a memory remotely located relative to the processor 21, and such remote memory may be connected to the processor 21 via a network. Examples of such networks 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 , perform the airborne bistatic radar configuration optimization design method in the above-mentioned embodiment 1.

[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 content can be found in the description of the method embodiment of the present invention and will not be repeated here.

[0133] Those skilled in the art will understand that all or part of the steps in the various methods of the embodiments can be completed by instructing related hardware through a program, and the program can be stored in a computer-readable storage medium, which may include: read-only memory (ROM), 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 scope of protection 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-baseline length L based on the input parameters of step 1; Step 3: According to the maximum detection range R of the single-base radar in step 1 max Determine the aircraft height h using the double baseline 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, bistatic height h t 、h r , bistatic 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 airborne bistatic radar configuration optimization design method according to claim 1, characterized in that: Determining the double-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 coordinates of the two foci 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 airborne bistatic radar configuration optimization design method according to claim 2, characterized in that: The double baseline length 4. The airborne bistatic radar configuration optimization design method according to claim 2, characterized in that: The airborne bistatic radar is a positive side-view array, which adopts a one-transmit-one-receive working mode. The height of the transmitter and receiver is the same, that is, h t =h r =h a .

5. The airborne bistatic radar configuration optimization design method according to claim 1, characterized in that: According to the maximum detection range R of the single-base radar in step 1 max Determine the aircraft height h using the double baseline length L in step 2 a , specifically including: The premise for the height design of transmitter and receiver is that the target is in the sight of 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 airborne bistatic radar configuration optimization design method 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 pitch 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 bistatic 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 When fixed, the slant range from the clutter block to the receiver is: in, Therefore, we further get: Further calculations are 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 the following formula: 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). By analyzing the range-Doppler trajectory of the received echo under each motion state, the motion state when the clutter is most stable 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 clutter stability 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, wherein: 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 , bistatic 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 according to any one of claims 1 to 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 perform the airborne bistatic radar configuration optimization design method according to 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 to 7.

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