JPH1089897A - Guided airframe system - Google Patents

Abstract

PROBLEM TO BE SOLVED: To improve the interference treating capacity of a guided airframe itself by a method wherein tracking is switched so as to track by a signal from a wide band receiver when a guiding signal is judged that it is not stable and the airframe is guided so as to aim an interfering wave source while a guidance error and a destroying effect at the estimated rendezvous point are estimated and evaluated in a ground device. SOLUTION: An ECCM circuit 14 compares the levels of an objective signal, received and treated by a main antenna 9, with the level of a interfering signal and when the level of the interfering signal is higher than that of the target signal, the circuit 14 transmits the signal to a signal treating circuit 21. Radio wave in UHF-millimeter wave band is received by a wide band antenna 19 at all times, a signal is attenuated or amplified and demodulated by a wide band receiver 20 while a signal process control circuit 21 judges whether a receiving level is not lower than a preset value or not and whether tracking is to be switched from target to a jammer by a signal from the ECCM circuit 14 or not, then, the tracking process of the signal processing unit 13 is switched to the receiving signal of the wide band receiver 20. On the other hand, a destroying probability at the estimated rendezvous point is operated from an evaluating and deciding circuit 3 and a guidance operation evaluation circuit 4.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention detects and tracks a target,
BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a guided flying vehicle system composed of a ground device that performs guidance calculation and fires a guided flying vehicle and a guided flying vehicle that tracks a target and autonomously guides a target.

[0002]

2. Description of the Related Art When a guided flying object is obstructed, an ECCM (Electr
ic Counter Counter Measur
In the processing of the jamming signal in the element circuit, large power jamming and complicated fraud jamming are limited and cannot be handled, so that the purpose of finally destroying the target with a predetermined probability cannot be achieved.

[0003] In a state in which the guided flying object is tracking the target and autonomously guiding, even if the guided flying object is obstructed, the ground equipment determines whether the guided flying object is obstructed. Since there was no means, there was no countermeasure for the entire guided flying vehicle system including ground equipment.

First, FIG. 15 shows a state diagram of a guided flying object, a ground device, a target, and a jammer when a radio wave is interrupted while the guided flying object is launched and performing autonomous guidance. The target 50 being tracked by the guided flying object 23 is located in the area supported by the interference of the jammer A51, and the guided flying vehicle is being jammed by both the target 50 itself and the jammer A51, The ground device 8 has no means for determining whether or not the guidance flying object 23 is obstructed. Also,
Although the radar device 1 of the ground device 8 is also subject to radio interference from the jammer B52, it is determined whether or not the guided flying object 23 is being disturbed, or whether the interference received by the ground device 8 and the frequency or power level are different. It does not have any means for determining whether the disturbance is of the same nature. Therefore, the guided flying object 23 is
It is necessary to perform signal processing of jamming radio waves within the range of the capability of the built-in ECCM circuit, and flight is controlled by a noisy guidance signal, which causes a large guidance error. In the figure, 53, 54, and 55 indicate the interference areas of the respective jammers, and 56 and 57 indicate the antenna beams of the guided flying object and the radar device.

FIG. 16 is a block diagram of a conventional guided flying vehicle system including a guided flying vehicle and a ground device. The ground device 8 includes the radar device 1 and the shooting control device 6
And a launcher 7. Based on target information (position, distance, and speed) obtained from the radar device 1 that detects and tracks a target (not shown), the firing / guidance calculation unit 2 of the shooting control device 6 calculates firing parameters and launches 7, and the information is preset to the guided flying object 23. Further, the shooting / guidance calculation unit 2 calculates an optimum firing time, and
To launch. When the launch instruction is issued, the propulsion device 18 of the guidance flying object 23 ignites and starts flying. The shooting / guidance calculation unit 2 calculates a guidance command signal for medium-term guidance using target information that changes from time to time, and sends it to the radar device 1. The guided flying object 23 is a radar device 1
Command signal 25 transmitted from the communication antenna 10
The signal is amplified and demodulated by the receiver 12, converted into a control signal in the flying object coordinates by the signal processing unit 13, and sent to the autopilot 15. The autopilot 15 creates and sends a steering angle command signal based on the attitude information of the guided flying object itself and the control signal, and the steering device 16 performs steering according to the steering angle command signal. When the relative distance between a target (not shown) and the guided flying object reaches a predetermined distance, the guided flying object 23 operates the transmitter 11 to emit radio waves from the main antenna 9. The radiated radio wave is emitted to a target (not shown), then received by the main antenna 9 as a reflected signal, amplified and demodulated by the receiver 12 and sent to the signal processing unit 13 to start autonomous guidance. . The attitude, position, and speed information 24 of the guided flying object is sent to the radar device 1 via the communication antenna 10. Fuze / warhead 1
7 detects that the target and the guided flying object have come close to each other, ignites a warhead, and destroys the target. On the other hand, under the radio wave interference, the interfering radio wave mixed with the reflected signal enters from the main antenna 9, passes through the receiver 12, and is sent to the signal processing unit 13 and the ECCM circuit 14. In the ECCM circuit 14,
A determination is made as to the presence or absence of interference, and if an interference radio wave exists within the frequency band that can be received by the receiver 12, a switching signal for tracking processing is sent to the signal processing unit 13 and the signal processing unit 13
Then, the process shifts from target tracking to tracking processing for jamming radio waves.

In the conventional system, the guided flying object 23
After the start of the autonomous guidance, the processing was performed only by the ECCM circuit 14 inside the guidance flying vehicle even if the radio wave was obstructed.
The ECCM circuit 14 determines whether the received signal is a signal transmitted by the guided flying object itself, whether the received signal has a magnitude corresponding to a relative distance to the target, and the like, and the processing of the signal processing unit 13 is saturated. When the input of the level to be received is received, the receiver 12 is stopped for a certain period of time to guide the guided flying object, or the transmission of the transmitter 11 is stopped, and the tracking is switched to the jamming radio source to guide the flying. The purpose of defeating the target with a predetermined probability for guiding the body 23 could not be achieved. In addition, since the ground device 8 and the guided flying object 23 do not cooperate with each other, the guided flying object 23 and the ground device 8 independently process each other. There is no means for determining that the body 23 is under obstruction, and the guided flying body 23
Guidance control, transmitter 11, receiver 12, signal processing unit 13
Could not support control such as switching of jamming processing.

[0007]

A conventional guided vehicle usually has a main antenna 9 for tracking and a receiver 12 using one wave in the X band to the Ku band with respect to a target including a jammer. , The interfering radio waves mixed in from the main antenna 9 also include similar frequency components, and the ECCM circuit 1
4 was also limited to a range of processing functions within the frequency bandwidth of the transmitter 11. After switching from the target to the interfering radio wave source due to strong radio interference, if the signal input from the main antenna 9 is interrupted, the tracking cannot be continued. On the other hand, since the ground device 8 has no means for determining whether or not the guided flying object 23 is obstructed, it is determined whether or not the guided flying object 23 is tracking the target or to the source of the jamming radio wave. I wasn't ready to launch the next round because I didn't know if it was.

[0008] Under radio wave interference, noise is usually contained in a signal processed inside the guidance flying object 23, and when the steering is performed using the signal, the flying motion is accompanied by the fluctuation of the noise. Becomes unstable. If this unstable flying motion continues, it will cause a large guidance error at the expected meeting point with the target. When the ground device 8 predicts a guidance error from the attitude, position, and velocity information of the guided flying object transmitted from the guided flying object 23 and the target information being tracked by the radar device 1, and is larger than a preset value. It is necessary to stop the autonomous guidance of the guidance flying object 23 and switch to guidance by control from the ground device. Guided flying object 23
Due to the physical limitations of the mounting space and mass of the ECCM circuit 14, the range of the interference processing function in the ECCM circuit 14 was also limited, and it was not possible to cope with various types of interference such as barrage jam. Therefore, the ground device 8 obtains and analyzes the interference information received by the guided flying object 23, selects the interference processing according to the frequency and the power level, and transmits the interference 11, the transmitter 11, the receiver 12, and the It is necessary to control the operation of the signal processing unit 13.

SUMMARY OF THE INVENTION The present invention has been made to solve such a problem, and the instantaneous interference is improved by the improvement of the interference processing capability of the guided flying vehicle itself and the cooperative operation of the guided flying vehicle and the ground equipment. Analyze the information to determine the type and intensity of the disturbance,
The purpose is to achieve a predetermined destruction effect or an ineffective effect of an enemy attack by performing a process having flexibility according to a situation such as a time factor.

[0010]

SUMMARY OF THE INVENTION The guided flying object system according to the first aspect of the present invention separates from a conventional main antenna and a receiver in order to cope with a wide band and power disturbance such as a barrage jam or a power jam. A wideband receiving antenna and a wideband receiver are provided to enable reception processing in the UHF to millimeter wave band, the reception level is equal to or higher than a predetermined value, and the signal level of a radio wave input from the main antenna is small, and an induction signal is not generated. If it is determined that the signal is stable, the tracking is switched by a signal from the broadband receiver, and an effect can be obtained by guiding the signal to the source of the jamming radio wave. On the other hand, the ground apparatus predicts and evaluates the guidance error and the defeat effect at the predicted meeting point, so that the predetermined target as the system can be achieved by firing the next round.

The guided flying object system according to the second aspect of the present invention minimizes the influence of jamming waves entering from the main antenna of the guided flying object and being mixed in the processing of the receiver and the signal processing unit. Furthermore, by improving the analysis accuracy of jamming radio waves, measuring frequency and power, and discriminating jamming modes, gain control of the receiver, frequency response control and signal processing mode control according to the type of jamming are performed, and narrow band Cope with obstacles caused by spot jams and fraud and continue autonomous guidance.

Further, the guidance vehicle system according to the third aspect of the invention uses a signal processing result sent from the guidance vehicle to calculate a guidance error at an expected meeting point on a ground apparatus, and to calculate the error. As a result of the evaluation, if the guidance error becomes large even if the autonomous guidance is continued as it is and it is determined that it is difficult to cope with the disturbance processing, the control of the guided flying object is switched to a command from the ground.

Further, the guided flying object system according to the fourth aspect of the present invention includes an interference frequency transmitted from the guided flying object,
Interference information such as the interference power level is analyzed in time series, and the frequency of the transmitter is switched so as to be asynchronous with the period of the jamming radio waves such as sweep jam and repeater jam. At the same time, the demodulation frequency of the receiver is also switched.

The guided flying object system according to the fifth aspect of the present invention calculates the target based on the ever-changing target, the relative positional relationship with the jammer and the guided flying object, and the interference processing information of the guided flying object. A HOJ (Home On Jam) mode signal is sent from the analysis result of the magnitude of the guidance error and the disturbance information, and the signal processing mode of the guidance vehicle is switched from the target to the jammer.

[0015]

BEST MODE FOR CARRYING OUT THE INVENTION

Embodiment 1 FIG. FIG. 1 is a block diagram of a guided flying vehicle system according to a first embodiment of the present invention. In the figure, 1, 2, 6 to 18 and 23 to 25 correspond to those in FIG.
Correspond to those shown in FIG. The ECCM circuit 14 compares the level of the target signal received and processed by the main antenna 9 with the level of the interfering signal.
Send a signal to The wideband antenna 19 constantly receives radio waves in the UHF to millimeter wave band, attenuates or amplifies and demodulates the signal with the wideband receiver 20, and the signal processing control circuit 21 checks whether the reception level is equal to or higher than a preset value. It is determined whether or not the tracking is switched from the target to the jammer based on the signal from the ECCM circuit 14 and the tracking process of the signal processing unit 13 is switched to the received signal of the wideband receiver 20. On the other hand, the evaluation judging circuit 3 of the shooting control device 6 calculates the flying motion state of the guided flying object 23 after the launch by the guided flying object 2.
3 based on the information sent from the position, the speed, the attitude signal is determined whether the change of the signal amount of any of the attitude signal is in a predetermined range, whether the need for guidance calculation evaluation, If the set value is exceeded, the guidance calculation evaluation circuit 4 calculates the defeat probability at the predicted meeting point. Normally, the destruction probability P is obtained by Equation 1 using the destruction probability Pr by the warhead, the guidance probability PG to the target, and the mission reliability PM of the ground equipment and the guided flying.

[0016]

(Equation 1)

FIG. 9 is a plane view showing the relationship between the relative position of the target and the guided flying object and the guidance error, and shows the destruction probability Pr.
Is a function of the effective radius r of the warhead, the guiding probability PG is a function of the guiding error R, and the mission reliability PM not shown is
It is the probability that the ground equipment and the guided vehicle can operate normally for the mission time from the launch of the guided vehicle to the meeting with the target.

As a result of the calculation, when it is determined that the predetermined destruction probability cannot be obtained, it is possible to prepare the launch of the next round in advance, thereby shortening the reaction time of the system. FIG. 2 shows the relationship between the target signal and the interfering signal, and shows a state in which the signal received from the main antenna 9 and the wideband antenna 19 includes the signal from the target and the interfering signal. If the interference signal level is higher than the set value, the signal processing control circuit 21 determines to switch the tracking from the target to the interference device, and also switches the signal to be used to the signal from the broadband antenna 19. FIG. 3 shows an example of a jamming signal received after changing the tracking to the jammer. In the case where the jamming signal does not exist in the frequency band that can be received by the main antenna 9 and the broadband antenna 19 receives the jamming signal. is there. If the disturbance that has been applied while the jammer is being tracked by the main antenna 9 is stopped, the tracking becomes impossible. However, if the broadband antenna 19 and the broadband receiver 20 can receive the signal, the tracking to the jammer is not performed. Continuation becomes possible, and the guided flying object can be guided to the jammer.

Embodiment 2 FIG. 4 is a block diagram of a guided flying vehicle system according to a second embodiment of the present invention. In the figure, 1, 2, 6 to 18 and 23 to 25
Corresponds to the one shown in FIG. Frequency judgment circuit 2
In step 6, the reception signal from the broadband receiver 20 is received, the interference frequency is identified, and in the case of a plurality of frequencies, the power and time for each frequency are measured by the power measurement circuit 27. The interference mode discrimination circuit 28 identifies an interference mode based on the interference frequency, the power level, and the time, selects an operation mode that can cope with the interference mode, and instructs the signal processing control circuit 21. The signal processing control circuit 21 switches to an operation selected from a plurality of interference processing modes provided in the signal processing unit 13 in advance. The jamming modes include broadband jamming, narrowband jamming, and fraudulent jamming. FIG. 5 shows an example of a received broadband jamming signal and a narrowband jamming signal. The target signal is buried in the jamming signal. ing. The received signal is FF
The frequency component is identified by T or the like, and the power level and the duration of the detected frequency are measured by an amplitude detector, a counter, or the like. Based on the relationship between the measured frequency band, power level, and duration, the interference mode is identified with a preset interference mode pattern. For example, if the frequency band is narrow, the power level is high, and the duration is relatively short, it is identified as a narrow band jammer. Also, the frequency band is wide, the power level is relatively small,
If the duration is long, it is identified as a broadband jammer. After the interference mode is specified, an effective interference processing mode for the interference is selected. In the case of narrow band interference, reception and signal processing by a narrow band filter are selected. FIG. 6 shows an example of a signal obtained through frequency determination, power measurement, and interference mode identification processing. In the broadband interference signal shown in FIG. 5, a power component is integrated on the frequency axis, and the integration amount is represented as The phase is inverted and added to the interfering signal to eliminate the phase. Further, the narrow band interference signal can be removed by passing through a narrow band filter.

Embodiment 3 FIG. 7 is a block diagram of a guided flying vehicle system according to a third embodiment of the present invention. In the figure, 1, 2, 6 to 18 and 23 to 25
Corresponds to the one shown in FIG. The flying object guidance determination circuit 29 determines whether the guidance control of the flying object is to be performed from the ground device side based on the prediction result of the defeat probability by the guidance calculation evaluation circuit 4, and sends a guidance control signal to the radar device 1. I do. The guidance control signal sent from the radar device 1 is received and processed by the link processing circuit 30 via the communication antenna 10 of the guidance flying object, sent to the guidance signal processing circuit 31, and sent from the signal processing unit 13 to the autopilot 15. The output control signal is switched to the guidance control signal. The feature of this embodiment is that the effect of the system is improved by prohibiting the autonomous guidance of the guidance flying object and guiding by the control from the ground device side. FIG. 8 shows a processing flow of the guidance calculation evaluation and the flying object guidance determination, and performs a target motion prediction calculation for predicting future motion data based on target information sent from the radar device 1. At the same time, a guided flying object prediction calculation is performed from the guided flying object information (posture, position, speed, and interference information) 24. The prediction calculation uses Equation 2.

[0021]

(Equation 2)

The relative position and velocity of both the target and the guided flying object 23 are calculated using the following equation (3).

[0023]

(Equation 3)

From the calculated relative position and speed, guidance calculation such as lateral acceleration, attitude angle, steering amount, etc. of the guided flying object is performed. Equation 4 is used to calculate the lateral acceleration.

[0025]

(Equation 4)

A guidance error is calculated from a predicted position between the target and the guidance vehicle 23 at a predicted meeting point with the target,
The destruction probability is calculated from the result. Based on the calculated destruction probability and a preset expected value, a flying object guidance determination is performed to determine whether guidance control by the ground equipment is necessary. If the guidance value is smaller than the expected value, a guidance control signal (time, lateral acceleration ) To the guidance vehicle via the radar device.

Embodiment 4 FIG. 10 is a block diagram of a guided flying object system according to a fourth embodiment of the present invention. In the figure, 1, 2, 6 to 18 and 23 to 2
5 corresponds to that shown in FIG. The transmitter 11
The receiver 12 has a function of switching between a plurality of frequencies and a function of selecting a transmission cycle, and the receiver 12 has a demodulation function corresponding to the frequency generated by the transmitter 11. The disturbance information characteristic analyzer 32 analyzes the relationship between the frequency component and the power component in a time series based on the disturbance radio wave information (frequency, power, signal processing mode) 24 sent from the guidance flying object 23, and performs guidance. An interference processing control signal 25 for controlling the interference processing of the flying object 23 is created and sent to the guidance flying object 23 via the radar device 1. In the guidance vehicle 23, the link processing circuit 30 receives and demodulates the interference processing control signal 25, and sends a control signal to the transceiver control circuit 33. The transceiver control circuit 33 controls the frequencies of the transmitter 11 and the receiver 12 based on the control signal. FIG. 11 shows an example of the operation of the jammer information analyzer 32 with respect to the repeater jam.
A repeater jam is determined based on the same period of the received signal from the target and the repeater jam signal from the jammer. The relationship between the transmission signal of the guided flying object 23 and the reception signal from the target after controlling the transmitter 11 to transmit a frequency having a different cycle from the repeater jam after the determination of the interference mode is shown. After the transmitter 11 is controlled, the repeater jam signal and the received signal do not overlap, so that tracking of the target can be continued. FIG. 12 shows an example of the operation of the disturbance information characteristic analyzer 32 for the sweep jam. The disturbance signal applied to the guided flying object and the disturbance information analyzer 3 are shown in FIG.
2 shows the relationship between time and power level and the relationship between time and frequency as a result of the analysis performed in step 2. As a result of the analysis, the frequency received by the main antenna 9 increases with the passage of time, and there is interference power over the entire receivable frequency band. In this case, the power level decreases with the passage of time. Judging from this feature as a sweep jam, as a jamming process,
The transmitter 11, the receiver 12, and the signal processing unit 13 are controlled so as to switch to a frequency having a lower interference power level and transmit the signal, or to use the signal received only during the time when the interference power is excessive, and to perform the current tracking state. I do.

Embodiment 5 FIG. 13 is a block diagram of a guided flying object system according to Embodiment 5 of the present invention. In the figure, 1, 2, 6 to 18 and 23 to 2
5 corresponds to that shown in FIG. The HOJ mode determination circuit 34 tracks the signal processing mode of the signal processing unit 13 of the guidance flying vehicle 23 to a specific jammer based on the analysis result of the interference information characteristic analyzer 32 and the prediction guidance error of the guidance calculation evaluation circuit 4. It determines whether or not to switch to the processing mode (HOJ mode) for performing, and sends a mode control signal for switching to the guidance vehicle 23 via the radar device.
In the guided flying object 23, the reception is performed by the link processing circuit 30,
It performs demodulation processing and sends a control signal to the HOJ mode control circuit 35. The HOJ mode control circuit 35 receives the mode control signal and switches to the HOJ mode provided in the signal processing unit 13 as a processing mode in advance, and issues a HOJ switching command to the transceiver control circuit 33. The transceiver control circuit 33 issues a command to stop generation of a transmission signal of the transmitter 11 and generation of a demodulation frequency of the receiver 12. FIG.
It shows an example of the operation of the HOJ mode determination circuit 34, and shows the results of an analysis performed by the HOJ mode determination circuit with the disturbance applied to the guidance flying object 23. As shown in the figure, the target signal is buried in the interference signal, and it is determined that the interference signal is large. Further, if the interference duration is greater than a preset ratio based on the power level and the ratio of the reception duration of the interference to a certain reference period, it is determined that tracking to the interference source can be maintained. In addition to the above conditions, as a result of the guidance calculation evaluation shown in FIG. 8, when the defeat probability is equal to or less than the expected value, a mode control signal for switching to the HOJ mode is transmitted to the guidance flying object 23 via the radar device 1.

[0029]

According to the first aspect of the present invention, an interfering radio wave which cannot be received from the main antenna of the guided flying object is received by the wideband receiving antenna and the wideband receiver, and the intensity of the interference is detected. Enables tracking and guidance to jammers and destroys them.

According to the second aspect of the present invention, the characteristics of the jamming radio waves coming from the wideband receiving antenna and the wideband receiver are analyzed with higher accuracy, and the guidance is appropriately performed based on the frequency characteristics and the power level. By controlling the signal processing mode of the flying object, it is possible to maintain the guidance probability to the target and reliably destroy the flying object.

According to the third aspect of the present invention, when the guided flying object tracking and guiding the target is in a state where autonomous guidance is impossible due to radio wave interference, the guided flying object is transmitted from the ground equipment to the guided flying object. By performing the guidance control, a predetermined defeat probability can be obtained for the target in the obstruction environment.

According to the fourth aspect of the present invention, the radar apparatus receives the interference situation received by the guided flying object, analyzes it with high accuracy by the shooting control device, and transmits the guided flying object to the transmitter and receiver. By controlling the operation of the robot in accordance with the nature of the obstruction, tracking and guidance for the target in the obstructive environment can be maintained, and an effective defeat effect can be expected.

According to the fifth aspect of the present invention, as a result of guidance calculation evaluation and disturbance analysis performed by the shooting control device performed on the guided flying vehicle during the autonomous guidance flight in the disturbance environment, the defeat probability for the target is obtained. Is unable to reach the predetermined value, and when it is possible to make a transition to the jammer, the guided aircraft is tracked and guided in the HOJ mode, thereby destroying the jammer or avoiding the attack and rendering it ineffective. As well as eliminating the effects on other flying guided vehicles.

[Brief description of the drawings]

FIG. 1 is a block diagram showing Embodiment 1 of a guided flying object system according to the present invention.

FIG. 2 is a diagram showing a relationship between a target signal and a disturbance signal in the first embodiment of the guided flying object system according to the present invention.

FIG. 3 is a diagram showing an example of a jamming signal applied after tracking to the jammer of the first embodiment of the guided flying object system according to the present invention;

FIG. 4 is a block diagram showing Embodiment 2 of the guided flying object system according to the present invention.

FIG. 5 is a diagram showing an example of a wideband interference signal and a narrowband interference signal of Embodiment 2 of the guided flying object system according to the present invention.

FIG. 6 is a diagram illustrating an example of a signal obtained through frequency determination, power measurement, and interference mode identification processing in Embodiment 2 of the guided flying object system according to the present invention.

FIG. 7 is a block diagram showing Embodiment 3 of the guided flying object system according to the present invention.

FIG. 8 is a diagram showing a processing flow of guidance calculation evaluation and flying object guidance determination of Embodiment 3 of the guided flying object system according to the present invention.

FIG. 9 is a diagram showing a relationship between a relative position between a target and a guided flying object and a guidance error in the third embodiment of the guided flying object system according to the present invention.

FIG. 10 is a block diagram showing Embodiment 4 of the guided flying object system according to the present invention.

FIG. 11 is a diagram illustrating an operation example 1 of the disturbance information characteristic analyzer according to the fourth embodiment of the guided flying object system according to the present invention;

FIG. 12 is a diagram showing an operation example 2 of the disturbance information characteristic analyzer of Embodiment 4 of the guided flying object system according to the present invention.

FIG. 13 is a block diagram showing Embodiment 5 of the guided flying object system according to the present invention.

FIG. 14 is a diagram showing an operation example of the HOJ mode determination circuit of Embodiment 5 of the guided flying object system according to the present invention.

FIG. 15 is a state diagram of a guided flying object, a ground device, a target, and a jammer when radio interference is applied.

FIG. 16 is a block diagram of a guided flying vehicle system configured by a conventional technique.

[Explanation of symbols]

Reference Signs List 1 radar device, 2 shooting / guidance calculation unit, 3 evaluation judgment circuit, 4 guidance calculation evaluation circuit, 5 special control calculation unit, 6
Shooting control device, 7 launchers, 8 ground equipment, 9 main antenna, 10 communication antenna, 11 transmitter, 12
Receiver, 13 signal processing unit, 14 ECCM circuit, 15
Autopilot, 16 Steering device, 17 Fuze / warhead, 18 Propulsion device, 19 Broadband receiving antenna, 20
Broadband receiver, 21 signal processing control circuit, 22 special signal processing unit, 23 guidance flying object, 24 guidance flying object information, 25 guidance command signal, 26 frequency judgment circuit, 27 power measurement circuit, 28 interference mode discrimination circuit,
29 Flying object guidance determination circuit, 30 link processing circuit, 31 guidance signal switching circuit, 32 disturbance information characteristic analyzer, 33 transceiver control circuit, 34 HOJ mode determination circuit, 35 HOJ mode control circuit, 50 target, 51
Jammer A, 52 Jammer B, 53-55 Jamming zone,
56 Antenna beam for guided flying vehicles, 57 Antenna beam for radar equipment.

──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. ⁶ Identification code FI G05D 1/12 G05D 1/12 C

Claims (5)

[Claims] 1. A target for detecting and tracking a target, performing a shooting / guidance calculation based on the tracked target information, issuing a launch command, and capturing a target in a flying object and a ground device for launching a flying object. In a guided flying vehicle system consisting of a guided flying vehicle that tracks and autonomously guides and destroys a target, a radar that detects and tracks the target, and tracks the guided flying vehicle and communicates with the guided flying vehicle A shooting / guidance calculation unit that calculates shooting parameters and guidance command signals by performing shooting calculations and guidance calculations using tracking information from the device and the radar device, and the position and speed of the guidance vehicles. An evaluation judgment circuit that determines the necessity of guide calculation evaluation after projectile launch from the attitude signal, and a guide calculation evaluation that calculates and evaluates the probability of defeat during flight from the relative distance and relative speed between the target and the guide vehicle. Consists of circuits A ground device equipped with a fire control device and a launcher that fires a guided flying object, a main antenna that emits and receives radio waves, receives a guidance command signal from the radar device, and guides the radar device. A communication antenna for transmitting flying object and target information, a receiver for generating a transmission signal, a receiver for amplifying and demodulating signals received from the main antenna and the communication antenna, and a signal processing for detecting and processing a target signal , ECCM (Electric Counter C) that processes the jamming signal at the time of target tracking
counter measurement circuit, an autopilot that creates a flight control signal from the target signal at the time of target tracking and attitude information of the guided flying object itself, a broadband reception antenna that receives jamming radio waves, and a reception signal from the broadband reception antenna. Attenuated, amplified, demodulated, and configured with a wideband receiver and a signal processing control circuit that switches the following processing of the signal processing unit from a target to a jammer when the signal level from the wideband receiver is equal to or greater than a preset value. And a guided flying object system. 2. A frequency judging circuit for receiving an incoming signal from a broadband receiver and identifying and judging an interference frequency, a power measurement circuit for measuring the power of the interference frequency, a power measurement circuit for measuring the power of the interference frequency, 2. The guided jumper according to claim 1, further comprising: a disturbance mode discriminating circuit for discriminating the disturbance mode from the measurement result, selecting a signal processing mode for coping with the disturbance mode, and instructing the signal processing control circuit. Sho body system. 3. In a state in which the guided flying object is flying while tracking the target, it is determined whether or not the guidance control of the flying object is to be performed from the ground equipment based on the result of the guidance calculation evaluation of the shooting control device. A flying object guidance determination circuit that sends a guidance control signal to the radar device when a predetermined defeat probability cannot be achieved, a link processing circuit that performs reception processing of the guidance control signal, and reception and demodulation from the link processing circuit 3. The guided flying object according to claim 2, further comprising: a guided signal switching circuit that switches a control signal from a signal processing unit to a flying control signal of an auto pilot based on the signal and a switching signal for switching the guidance control signal. Guided flying object system. 4. An interference processing control signal for controlling the interference processing of the guided flying object by performing a power level and frequency characteristic analysis as a function of time based on the interference radio wave information sent from the guided flying object. A disturbance information characteristic analyzer to be transmitted to the radar device is provided in the ground device; a link processing circuit for receiving the disturbance processing control signal transmitted from the radar device; and a transmission based on a demodulated signal from the link processing circuit. 4. The guided flying object system according to claim 3, further comprising a transceiver control circuit for issuing a command for controlling a frequency and a transmission cycle of the receiver and the receiver. 5. A specific jammer based on the power level, frequency and time analysis results of a ground information interference analyzer and a prediction guidance error calculated by a guidance calculation evaluation circuit to determine the signal processing mode of the guidance vehicle. HOJ (Ho
A HOJ determination circuit that determines whether to switch to the “me OnJam” mode is provided in the ground equipment, and a link processing circuit that performs reception processing of the mode control signal transmitted from the radar apparatus and a demodulated signal from the link processing circuit 5. The guidance vehicle system according to claim 4, further comprising a HOJ mode control circuit for switching an operation mode of the signal processing unit to the tracking of the jammer based on the guidance vehicle.