A synchronous slow flashing angle deception jamming method based on stealth cancellation

Abstract

The present invention provides a synchronous slow flicker angle deception jamming method based on cancellation stealth, which is used to solve the problem of low interference-to-signal ratio of traditional synchronous slow flicker jamming; including: building an RCS database of an aerial platform; obtaining beam information of a monopulse radar and configuration parameters of a dual aerial platform formation; generating a cancellation beam; generating an interference beam; timing control of the dual aerial platform formation transmitting the interference beam and the cancellation beam; judging whether to leave the attack range of an air defense missile. The method of the present invention has low cost, and only needs to add a software modulation beam on the basis of an existing jammer, and the method can eliminate the problem of low interference-to-signal ratio of flicker jamming.

Description

Technical Field

[0001] The invention belongs to the technical field of single pulse radar countermeasures and specifically relates to a synchronous slow flashing angle deception jamming method based on stealth cancellation. Background Art

[0002] The monopulse radar emits a pulse beam from multiple beams of the antenna at the same time, and measures the angle information of the target by comparing the phase and amplitude of the echo beams of each beam. It has the characteristics of high angle measurement accuracy, fast speed, and strong anti-interference ability. It is widely used as a tracking monopulse radar for fire control systems. When the monopulse radar stably tracks the target, the fire control system will launch an air defense missile, and the monopulse radar will guide the weapon to hit the target. This process is automatic.

[0003] Flicker jamming is an effective way to jam monopulse radar. In an air-to-ground combat scenario, two identical aerial platforms form a dual aerial platform formation and are captured by the monopulse radar of the ground fire control system. The dual aerial platform formation within the monopulse radar beam controls their respective jammers to alternately transmit beams to the monopulse radar. According to the frequency of alternation, it can be divided into fast flicker jamming and slow flicker jamming. According to the proportion of each jammer beam in the cycle, it can be divided into synchronous flicker jamming and asynchronous flicker jamming. Among them, only synchronous slow flicker jamming may cause monopulse radar to chase and swing. The chasing and swinging phenomenon refers to the tracking axis of the monopulse radar swinging back and forth between the two aerial platforms. The monopulse radar in the chasing and swinging state cannot stably track the target, so the fire control system cannot meet the conditions for launching air defense missiles, so that the interfered aerial platform can survive.

[0004] However, the disadvantage of the traditional synchronous slow flash of the monopulse radar is that the interference-to-signal ratio is unstable during combat. When the monopulse radar is irradiated from the head-on direction or the tail direction of the dual air platform formation, the interference-to-signal ratio is relatively large and can meet the interference requirements; but when irradiated from the side, the interference-to-signal ratio becomes smaller and changes dramatically, and the interference effect is unstable. The reason for the unstable interference-to-signal ratio during combat is that the RCS of the air platform varies greatly in different directions. Summary of the invention

[0005] The interference-to-signal ratio is the ratio of the interference power to the echo power received by the single-pulse radar. To maintain a sufficiently large interference-to-signal ratio, either increase the interference power or reduce the echo power. The idea of ​​the present invention is to use the cancellation stealth technology to reduce the echo power and thus increase the interference-to-signal ratio, meet the interference requirements, and solve the problem of low interference-to-signal ratio in traditional synchronous slow flicker interference. Therefore, the present invention provides a synchronous slow flicker angle deception interference method based on cancellation stealth, comprising the following steps:

[0006] Step 1: Build the RCS database of the aerial platform

[0007] The RCS database of the aerial platform needs to be constructed in advance; the two aerial platforms participating in the synchronous slow flicker interference are exactly the same. First, the three-dimensional geometric model of the aerial platform is obtained by computer-aided design technology; then the three-dimensional geometric model of the aerial platform is electromagnetically calculated using the moment method to obtain the RCS database of the aerial platform:

[0008]

[0009] Among them, f B (Hz) is the frequency, θ B (deg) is the pitch angle, ranging from [0, 180]; is the azimuth, in the range [0, 360); σ B (m 2 ) is the RCS of the airborne platform at this time; the coordinate system adopts the body coordinate system;

[0010] Step 2: Obtain the beam information of the monopulse radar and the configuration parameters of the dual air platform formation

[0011] In the configuration relationship of cancellation synchronous slow flash, M is the ground monopulse radar; A and B are the first and second aerial platforms respectively, and the three form a triangle in space; C is the midpoint of the line connecting A and B, and the distance between M and C is R; A′ is the energy center when the first aerial platform A transmits the interference beam and the second aerial platform B transmits the cancellation beam; B′ is the energy center when the first aerial platform A transmits the cancellation beam and the second aerial platform B transmits the interference beam; θ a is the angle of the first and second aerial platforms to the monopulse radar, that is, the angle with M as the vertex and MA and MB as the two sides; θ b is the pursuit angle, that is, the angle with M as the vertex and MA′ and MB′ as the two sides; θ c θ is the angle between the energy center and the airborne platform releasing interference to the monopulse radar, that is, the angle with M as the vertex and MA and MA′ as the two sides; e is the tracking angle error, that is, M is the vertex, MA′ and MB are the angles of the two sides;

[0012] The configuration parameters that need to be obtained include:

[0013] Position parameters: The straight-line distance between the monopulse radar and the midpoint of the dual air platform formation is R (m), and the horizontal distance between the midpoint of the dual air platform formation and the air defense missile position is D T (m), the angle θ of the dual air platform formation to the monopulse radar a (deg), the relative height between the dual aerial platforms and the air defense missile positions is H T (m);

[0014] Monopulse radar parameters: frequency fB (Hz), gain is G t (dB), transmission power P t (W), system loss L r , beam width θ 0.5 (deg), amplitude α0 (dBmV), antenna coefficient k H 、The impact of each link of the receiver on the interference-to-signal ratio t ;

[0015] Parameters of the first and second aerial platforms: It is approximately assumed that the angle parameters of the two aerial platforms are the same, that is, the elevation angle of the incident beam of the monopulse radar is θ B (deg), azimuth are Jammer system loss L of two air platforms j , Jammer gain G j , maximum interference power P jmax are the same; the suppression coefficient of the coordinated interference of two aerial platforms is K;

[0016] Step 3: Generate Cancellation Beam

[0017] First, calculate the RCS value σ of the aerial platform that generates the cancellation beam B ; Approximately assume that the angle parameters of the two aerial platforms are the same, using the pitch angle θ given in step 2 B and azimuth Bring it into the database created in step 1 to get This means that the RCS of the two air platforms is the same;

[0018] Therefore, the cancellation beam power emitted by the jammer of the first or second airborne platform is:

[0019]

[0020] Where α(dB) is the amplitude error, is the phase error;

[0021] Step 4: Generate Interference Beam

[0022] It is assumed that the two aerial platforms have the same angle parameters, and the pitch angle θ given in step 2 is used. B and azimuth Bring it into the database created in step 1 to get That is to say, the RCS of the two aerial platforms is the same; in addition, the suppression coefficient K is also required in the calculation process;

[0023] Therefore, the jammer beam power emitted by the first or second aerial platform is:

[0024]

[0025] Step 5: Timing control of the dual aerial platform formation transmitting jamming beams and cancellation beams

[0026] The beam timing controller is used to control the dual aerial platform formation to periodically transmit the cancellation beam and the interference beam; a flashing cycle includes two states, the first state: the first aerial platform transmits the interference beam while the second aerial platform transmits the cancellation beam; the second state: the first aerial platform transmits the cancellation beam while the second aerial platform transmits the interference beam; each state occupies 50% of the entire flashing cycle, and the two states are switched in turn;

[0027] Step 6: Determine whether to leave the air defense missile attack range

[0028] The judgment condition is

[0029]

[0030] In the formula, H min (m) and H max (m) are the minimum and maximum interception heights of air defense missiles, respectively, and D min (m) and D max (m) are the minimum and maximum horizontal interception distances of the air defense missile respectively; when both conditions are met at the same time, it means that the aerial platform is still within the attack range of the air defense missile, and continue to execute steps 2 to 5, otherwise the interference ends.

[0031] In one embodiment of the present invention, in step 5, the flashing period ranges from 1 s to 5 s.

[0032] The method of the present invention combines the stealth cancellation technology with the synchronous slow flicker interference, and utilizes the stealth cancellation technology to actively reduce the echo power in the illumination direction of the single pulse radar, thereby maintaining the interference-to-signal ratio required by the interference. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 A flow chart showing the technical solution of the present invention;

[0034] Figure 2 Showing the body coordinate system;

[0035] Figure 3 A diagram showing the configuration relationship for canceling synchronous slow flicker. DETAILED DESCRIPTION

[0036] The present invention will be described in detail below with reference to the accompanying drawings.

[0037] In order to achieve the above purpose, the present invention proposes a synchronous slow flicker angle deception jamming method based on cancellation stealth. The design idea is: in the traditional synchronous slow flicker jamming, there must be an aerial platform that only transmits the echo beam at the same time. The beam is passively transmitted under the influence of the RCS of the aerial platform and is usually uncontrollable. In the present invention, the cancellation stealth principle is utilized to allow the aerial platform that originally only transmits the echo beam to actively transmit the cancellation beam at the same time. In this way, the synthetic beam power received by the single-pulse radar is controllable, thereby achieving the purpose of reducing the interference-to-signal ratio.

[0038] The present invention provides a synchronous slow flashing angle deception interference method based on stealth cancellation, comprising the following steps:

[0039] Step 1: Build the RCS database of the aerial platform.

[0040] like Figure 1 As shown, the RCS database of the aerial platform needs to be constructed in advance for use in subsequent steps. The two aerial platforms involved in the synchronous slow flicker interference are exactly the same. First, a 3D geometric model of the aerial platform is obtained using computer-aided design technology (such as 3D design software CATIA from Dassault, France).

[0041] Then the moment method is used to perform electromagnetic calculations on the three-dimensional geometric model of the aerial platform. Roger F. Harrington introduced the moment method into computational electromagnetics in the 1960s to solve integral equations. The moment method is currently the most accurate numerical method. The RCS database of the aerial platform is obtained:

[0042]

[0043] Among them, f B (Hz) is the frequency, θ B (deg) is the pitch angle, ranging from [0, 180]. is the azimuth, in the range [0, 360). B (m 2 ) is the RCS of the airborne platform at this time. The coordinate system is based on Figure 2 Design,using the body coordinate system.

[0044] Step 2: Obtain the beam information of the monopulse radar and the configuration parameters of the dual air platform formation.

[0045] The configuration relationship for canceling synchronous slow flashing is as follows: Figure 3As shown in the figure, M is a ground monopulse radar; A and B are the first and second aerial platforms respectively, and the three form a triangle in space; C is the midpoint of the line connecting A and B, and the distance between M and C is R; A′ is the energy center when the first aerial platform A transmits an interference beam and the second aerial platform B transmits a cancellation beam; B′ is the energy center when the first aerial platform A transmits a cancellation beam and the second aerial platform B transmits an interference beam; θ a is the angle of the first and second aerial platforms to the monopulse radar, that is, the angle with M as the vertex and MA and MB as the two sides; θ b is the pursuit angle, that is, the angle with M as the vertex and MA′ and MB′ as the two sides; θ c θ is the angle formed by the energy center and the airborne platform releasing interference to the monopulse radar, that is, M is the vertex and MA and MA′ are the angles of the two sides (also M is the vertex and MB′ and MB are the angles of the two sides); e It is the tracking angle error, that is, M is the vertex, MA′ and MB are the angles of the two sides (also M is the vertex, MA and MB′ are the angles of the two sides).

[0046] The configuration parameters that need to be obtained include:

[0047] Position parameters: The straight-line distance between the monopulse radar and the midpoint of the dual air platform formation is R (m), and the horizontal distance between the midpoint of the dual air platform formation and the air defense missile position is D T (m), the angle θ of the dual air platform formation to the monopulse radar a (deg), the relative height between the dual aerial platforms and the air defense missile positions is H T (m).

[0048] Monopulse radar parameters: frequency f B (Hz), gain is G t (dB), transmission power P t (W), system loss L r , beam width θ 0.5 (deg), amplitude α0 (dBmV), antenna coefficient k H 、The impact of each link of the receiver on the interference-to-signal ratio t .

[0049] Parameters of the first and second aerial platforms: Because the distance between the two aerial platforms in the cancellation of synchronous slow flicker interference of the aerial platform to the ground monopulse radar is much smaller than the distance between the aerial platform and the ground monopulse radar, it is approximately assumed that the angle parameters of the two aerial platforms are the same, that is, the pitch angle of the incident beam of the monopulse radar is θ B (deg), azimuth are In addition, the jammer system loss of the two air platforms is L j, Jammer gain G j , maximum interference power P jmax are the same; the suppression coefficient of the coordinated interference of two aerial platforms is K.

[0050] Here, the six parameters related to the aerial platform are divided into three categories:

[0051] The first category includes two angle parameters, which refer to the pitch angle and azimuth angle of each platform. They are "approximately the same" because the distance between the two platforms is much smaller than the distance between the two platforms and the radar.

[0052] The second category includes three jammer parameters, which refer to the jammer system loss, jammer gain, and maximum jamming power of each platform. They are "exactly the same", which is required for this form of jamming.

[0053] The third category refers to the sixth parameter, suppression coefficient, which is different from the previous five parameters because the previous five parameters belong to a single aerial platform, while the suppression coefficient belongs to a certain interference method. The present invention is that the two platforms cooperate with each other and coordinate interference, and the suppression coefficient is relative to this dual-platform collaborative interference method.

[0054] Step 3: Generate cancellation beams.

[0055] like Figure 1 As shown, first calculate the RCS value σ of the aerial platform that generates the cancellation beam B Because the distance between the two aerial platforms in the cancellation of synchronous slow flicker interference of the aerial platform to the ground monopulse radar is much smaller than the distance between the aerial platform and the ground monopulse radar, it is approximately assumed that the angle parameters of the two aerial platforms are the same, and the pitch angle θ given in step 2 is used. B and azimuth Bring it into the database created in step 1 to get That is to say, the RCS of the two aerial platforms is the same.

[0056] Therefore, the cancellation beam power emitted by the jammer of the first or second airborne platform is:

[0057]

[0058] Where α(dB) is the amplitude error, is the phase error. The remaining parameters are given in step 2.

[0059] Step 4: Generate interference beam.

[0060] Similarly, because in the cancellation of synchronous slow flicker interference of the aerial platform to the ground monopulse radar, the distance between the two aerial platforms is much smaller than the distance between the aerial platform and the ground monopulse radar, it is approximately assumed that the angle parameters of the two aerial platforms are the same, and the pitch angle θ given in step 2 is used B and azimuth Bring it into the database created in step 1 to get That is to say, the RCS of the two aerial platforms is the same. In addition, the suppression coefficient K is also required in the calculation process, such as Figure 1 shown.

[0061] Therefore, the jammer beam power emitted by the first or second aerial platform is:

[0062]

[0063] Step 5: Timing control of the dual aerial platform formation transmitting interference beams and cancellation beams.

[0064] Figure 1 The beam timing controller is used to control the dual aerial platform formation to periodically transmit the cancellation beam and the interference beam. A flashing cycle includes two states. The first state: the first aerial platform transmits the interference beam while the second aerial platform transmits the cancellation beam; the second state: the first aerial platform transmits the cancellation beam while the second aerial platform transmits the interference beam. Each state occupies 50% of the entire flashing cycle, and the two states switch in turn. In one embodiment of the present invention, the flashing cycle ranges from 1s to 5s.

[0065] Step 6: Determine whether to leave the air defense missile attack range. The judgment condition is

[0066]

[0067] In the formula, H min (m) and H max (m) are the minimum and maximum interception heights of air defense missiles, respectively, and D min (m) and D max (m) are the minimum and maximum horizontal interception distances of the air defense missile. When both conditions are met, it means that the aerial platform is still within the attack range of the air defense missile, and continue to execute steps 2 to 5. Otherwise, the interference ends and the judgment branch is as follows: Figure 1 shown. Specific embodiments

[0069] Step 1: Build the RCS database of the aerial platform.

[0070] The two aerial platforms involved in the synchronous slow flicker interference are exactly the same. First, a three-dimensional geometric model of the aerial platform is established using the polygonal mesh modeling method. Then, the electromagnetic calculation of the three-dimensional geometric model of the aerial platform is performed using the moment method. The simulation parameters are: azimuth angle range is [0, 360) degrees, pitch angle range is [0, 90] degrees, and frequency is 2GHz, and the RCS database is obtained.

[0071] Step 2: Obtain the beam information of the monopulse radar and the configuration parameters of the dual air platform formation.

[0072] Position parameters: The straight-line distance R between the monopulse radar and the midpoint of the dual air platform formation is 45 km, the horizontal distance between the midpoint of the dual air platform formation and the air defense missile position is 43.87 km, and the angle θ between the dual air platform formation and the monopulse radar is a It is 1.17deg, and the relative height between the dual aerial platforms and the air defense missile positions is 10km.

[0073] Monopulse radar parameters: frequency f B is 2GHz, gain is G t is 50dB, the transmission power P t 200kW, system loss L r =1, beam width θ 0.5 is 2deg, the amplitude α0 is 60dbmV, and the antenna coefficient k H =1.02, the influence of each link of the receiver on the interference-to-signal ratio F t is 4.

[0074] Parameters of the first and second aerial platforms: Because the distance between the two aerial platforms in the cancellation of synchronous slow flicker interference of the aerial platform to the ground monopulse radar is much smaller than the distance between the aerial platform and the ground monopulse radar, it is approximately assumed that the angle parameters of the two aerial platforms are the same, that is, the pitch angle of the incident beam of the monopulse radar is θ B is 102.84deg, and the azimuth is is 12.30deg; in addition, the jammer system loss of the two air platforms is L j All are 1, jammer gain G j Both are 10dB, maximum interference power P jmax Both are 100W; the suppression coefficient K of the coordinated interference of dual aerial platforms is 20.

[0075] Step 3: Generate cancellation beams.

[0076] The RCS at this time is 18.53m obtained from the RCS database 2 . Cancel phase error is 4deg, and the amplitude error α is 1dB. The cancellation power emitted by the jammer is:

[0077]

[0078] Step 4: Generate interference beam.

[0079] The RCS at this time is 18.53m obtained from the RCS database 2 . Cancel phase error is 4deg, and the amplitude error α is 1dB. The interference power emitted by the jammer is:

[0080]

[0081] Step 5: Timing control of the dual aerial platform formation transmitting interference beams and cancellation beams.

[0082] The beam timing controller controls the dual aerial platform formation to periodically transmit the cancellation beam and the interference beam. A flashing cycle includes two states. The first state: the first aerial platform transmits the interference beam while the second aerial platform transmits the cancellation beam; the second state: the first aerial platform transmits the cancellation beam while the second aerial platform transmits the interference beam. Each state occupies 50% of the entire flashing cycle, and the two states switch in turn. The flashing cycle is 3s.

[0083] Step 6: Determine whether to leave the air defense missile attack range. The minimum interception altitude of air defense missiles is 300m, the maximum interception altitude is 20km, the minimum horizontal interception distance is 500m, and the maximum horizontal interception distance is 60km. The horizontal distance between the midpoint of the dual air platform formation and the air defense missile position is 43.87km, and the relative height between the dual air platforms and the air defense missile position is 10km. That is, the conditions for continued interference are met, so continue to execute steps 2 to 5.

[0084] If the traditional synchronous slow flicker interference is used, under the same suppression coefficient, the required interference power is 1550.79W, while the maximum power of the jammer is only 100W. Experiments show that compared with the traditional synchronous slow flicker, the cancellation synchronous slow flicker interference style of the present invention has a better interference effect, solves the problem of low interference-to-signal ratio of the traditional synchronous slow flicker interference, and can flexibly control the interference effect by actively transmitting interference beams and cancellation beams, and does not require the hardware upgrade of the air platform, saving costs.

[0085] The present invention combines the cancellation stealth technology with the synchronous slow flicker interference technology, and proposes a synchronous slow flicker angle deception interference method based on cancellation stealth. As a new interference style, it has the following advantages:

[0086] (1) Compared with the traditional synchronous slow flicker interference, the present invention fundamentally solves the problem of low interference-to-signal ratio. By using the cancellation stealth principle to reasonably design the cancellation beam, the RCS in the direction of the single pulse radar illumination can be reduced, which also reduces the echo power in this direction, thereby increasing the interference-to-signal ratio.

[0087] (2) The jamming method of the present invention is highly flexible, precise and controllable. Because the first and second aerial platforms actively radiate jamming beams and cancellation beams respectively, the power can be adjusted according to the actual jamming requirements. However, the traditional synchronous slow flash jamming cannot achieve flexible, precise and controllable jamming because it passively transmits echo beams.

[0088] (3) Low application cost. To solve the problem of low interference-to-signal ratio of synchronous slow flicker interference, in addition to the present invention, there is only one method that can achieve a similar effect, that is, the synchronous slow flicker interference of the stealth aerial platform. However, this method requires the use of the fourth-generation stealth aerial platform, and still has the problem of inflexible, imprecise and uncontrollable interference. Compared with this method, the method of the present invention has a cost advantage.

Claims

1. A synchronous slow flashing angle deception jamming method based on stealth cancellation, characterized in that: The steps include: Step 1: Build the RCS database of the aerial platform The RCS database of the aerial platform needs to be constructed in advance; the two aerial platforms participating in the synchronous slow flicker interference are exactly the same. First, the three-dimensional geometric model of the aerial platform is obtained by computer-aided design technology; then the three-dimensional geometric model of the aerial platform is electromagnetically calculated using the moment method to obtain the RCS database of the aerial platform: Among them, f B (Hz) is the frequency, θ B (deg) is the pitch angle, ranging from [0, 180]; is the azimuth, in the range [0, 360); σ B (m 2 ) is the RCS of the airborne platform at this time; the coordinate system adopts the body coordinate system; Step 2: Obtain the beam information of the monopulse radar and the configuration parameters of the dual air platform formation In the configuration relationship of cancellation synchronous slow flash, M is the ground monopulse radar; A and B are the first and second aerial platforms respectively, and the three form a triangle in space; C is the midpoint of the line connecting A and B, and the distance between M and C is R; A′ is the energy center when the first aerial platform A transmits the interference beam and the second aerial platform B transmits the cancellation beam; B′ is the energy center when the first aerial platform A transmits the cancellation beam and the second aerial platform B transmits the interference beam; θ a is the angle of the first and second aerial platforms to the monopulse radar, that is, the angle with M as the vertex and MA and MB as the two sides; θ b is the pursuit angle, that is, the angle with M as the vertex and MA′ and MB′ as the two sides; θ c θ is the angle between the energy center and the airborne platform releasing interference to the monopulse radar, that is, the angle with M as the vertex and MA and MA′ as the two sides; e is the tracking angle error, that is, M is the vertex, MA′ and MB are the angles of the two sides; The configuration parameters that need to be obtained include: Position parameters: The straight-line distance between the monopulse radar and the midpoint of the dual air platform formation is R (m), and the horizontal distance between the midpoint of the dual air platform formation and the air defense missile position is D T (m), the angle θ of the dual air platform formation to the monopulse radar a (deg), the relative height between the dual aerial platforms and the air defense missile positions is H T (m); Monopulse radar parameters: frequency f B (Hz), gain is G t (dB), transmission power P t (W), system loss L r , beam width θ 0.5 (deg), amplitude α0 (dBmV), antenna coefficient k H 、The impact of each link of the receiver on the interference-to-signal ratio t ; Parameters of the first and second aerial platforms: It is approximately assumed that the angle parameters of the two aerial platforms are the same, that is, the elevation angle of the incident beam of the monopulse radar is θ B (deg), azimuth are Jammer system loss L of two air platforms j , Jammer gain G j , maximum interference power P jmax are the same; the suppression coefficient of the coordinated interference of two aerial platforms is K; Step 3: Generate Cancellation Beam First, calculate the RCS value σ of the aerial platform that generates the cancellation beam B ; Approximately assume that the angle parameters of the two aerial platforms are the same, using the pitch angle θ given in step 2 B and azimuth Bring it into the database created in step 1 to get This means that the RCS of the two air platforms is the same; Therefore, the cancellation beam power emitted by the jammer of the first or second airborne platform is: Where α(dB) is the amplitude error, is the phase error; Step 4: Generate Interference Beam It is assumed that the two aerial platforms have the same angle parameters, and the pitch angle θ given in step 2 is used. B and azimuth Bring it into the database created in step 1 to get That is to say, the RCS of the two aerial platforms is the same; in addition, the suppression coefficient K is also required in the calculation process; Therefore, the jammer beam power emitted by the first or second aerial platform is: Step 5: Timing control of the dual aerial platform formation transmitting jamming beams and cancellation beams The beam timing controller is used to control the dual aerial platform formation to periodically transmit the cancellation beam and the interference beam; a flashing cycle includes two states, the first state: the first aerial platform transmits the interference beam while the second aerial platform transmits the cancellation beam; the second state: the first aerial platform transmits the cancellation beam while the second aerial platform transmits the interference beam; each state occupies 50% of the entire flashing cycle, and the two states are switched in turn; Step 6: Determine whether to leave the air defense missile attack range The judgment condition is In the formula, H min (m) and H max (m) are the minimum and maximum interception heights of air defense missiles, respectively, and D min (m) and D max (m) are the minimum and maximum horizontal interception distances of the air defense missile respectively; when both conditions are met at the same time, it means that the aerial platform is still within the attack range of the air defense missile, and continue to execute steps 2 to 5, otherwise the interference ends.

2. The synchronous slow flashing angle deception jamming method based on cancellation stealth as claimed in claim 1 is characterized in that: In step 5, the flashing period ranges from 1 s to 5 s.

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