JP2003130590A - Ground apparatus, guided airframe and guided airframe body system - Google Patents

Abstract

PROBLEM TO BE SOLVED: To solve the problem wherein in order to achieve a designated defeating effect even in the electronic jamming, it is necessary to perform fuzing processing in linkage of a guided airframe and a ground apparatus and control the generation of a detonating signal in response to a command from the ground apparatus according to the status. SOLUTION: In the ground apparatus, a guidance error is calculated to create a detonating enable signal (distance information) as the condition of generating a detonating signal and a detonation adjust signal from the characteristic information on a target, and a command for the detonation control for the guided airframe can be given.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a ground device for detecting and tracking a target, destroying an enemy's aerial target under radio interference, and performing shooting / guidance calculation to launch a guided vehicle. is there. The present invention also relates to a guided flying vehicle that is launched from the above ground device and that tracks a target and autonomously guides it. Further, the present invention relates to a guide aircraft system including the above ground device and a guide aircraft.

[0002]

2. Description of the Related Art An ECCM (Electric Counte) built into a guided vehicle when the guided vehicle is obstructed.
Since there is a limit to high power interference and complicated deceptive interference in the interference processing by the (r Counter Measurement) circuit and the distance determination processing in the signal processing unit, accurate distance determination processing cannot be performed, so the target will eventually reach the target with a certain probability. Could not achieve the purpose of destroying.

In a state in which the guided vehicle is tracking the target and autonomously guiding the target, the guided vehicle itself is effective for distance detection processing and detonation adjustment even if the guided vehicle is obstructed. Since there was no means for judging whether or not processing was performed, there was no fuze processing measure for the entire guided flight system including ground equipment.

First, FIG. 6 shows a state diagram of a guide vehicle, a ground device, a target, and a jammer when radio waves are disturbed while the guide vehicle is launched and autonomously guiding. The target 50 tracked by the guided vehicle 24 is located in the area assisted by the jamming of the jammer 51, and the guided vehicle is jammed by both the target 50 itself and the jammer 51. The ground device 10 has no means for determining whether or not the guided vehicle 24 is being disturbed. Therefore,
The guided flying object 24 needs to carry out signal processing of interference radio waves and distance detection processing within the processing capacity of the built-in ECCM circuit and signal processing unit, and adjusts the detonation with inaccurate distance information including noise. This caused the premature detonation or non-detonation. In the figure, reference numerals 53 and 54 denote interference areas from the target and the jammer, and 56 and 57 denote antenna beams of the guided vehicle and the radar device.

FIG. 17 shows a block diagram of a conventional guided vehicle system including a guided vehicle and a ground device. The ground device 10 includes a radar device 1, a shooting control device 8 and a launcher 9. Target information obtained from the radar device 1 that detects and tracks a target (not shown)
Based on (position, distance, speed), the shooting of the shooting control device 8
The guidance calculation unit 2 calculates launch specifications, sends them to the launcher 9, and presets information in the guidance vehicle 24. Also, shooting
The guidance calculator 2 calculates the optimum launch time and issues a launch instruction to the launcher 9. When the launch instruction is issued, the propulsion device 22 of the guided flying body 24 is ignited and the flight is started.

The shooting / guidance calculation unit 2 calculates a guidance command signal in flight using the target information that changes from moment to moment and sends it to the radar device 1. The guidance flying body 24 receives the guidance command signal 26 transmitted from the radar device 1 by the communication antenna 12, amplifies and demodulates by the receiver 14, and converts it into a control signal in the flying body coordinates by the signal processing unit 15. , The relative speed signal and the distance signal are detected and sent to the proximity fuze 20. Auto pilot 17
Then, a steering angle command signal is created and transmitted based on the attitude information of the guided flying object itself and the control signal, and the steering device 18 steers according to the steering angle command signal.

The guided flying object 24 causes the transmitter 13 to generate a transmission signal for a target (not shown), and radiates a radio wave from the main antenna 11. The radiated radio wave is applied to a target (not shown) and then as a reflected signal, the main antenna 1
1 is received, amplified and demodulated by the receiver 14 and sent to the signal processing unit 15 to start guiding autonomously. Further, the attitude, position, and velocity information 25 of the guided flying object is sent to the radar device 1 via the communication antenna 12. The fuze antenna 19 receives a reflected signal from the target when the target and the guided vehicle 24 (not shown) are present in the vicinity.
The proximity fuze 20 detects that the target and the guided vehicle 24 approach each other from the distance signal from the signal processing unit 15 and the received signal from the fuze antenna 19, and the detonation signal is generated after the delay time corresponding to the relative speed elapses. Is generated, the explosive charge of the warhead 21 is ignited to destroy the target.

On the other hand, under radio interference, interfering radio waves mixed with the reflected signal enter from the main antenna 11 and the receiver 14
And is sent to the signal processing unit 15 and the ECCM circuit 16. EC
The CM circuit 16 determines whether or not there is interference, and if there is an interfering radio wave within the frequency band of the guided vehicle 24,
A distance signal switching signal is sent to the signal processing unit 15, and the signal processing unit 15 receives the distance signal from the ECCM circuit 16 and sends it to the proximity fuze 20.

In the conventional system, the guided air vehicle 24
After starting the autonomous guidance, the signal processing unit 15 inside the guidance vehicle carried out distance detection processing and used the detected distance signal as one of the detonation conditions. In the electromagnetic interference, the ECCM circuit 16 determines whether or not the signal processing unit 15 inside the guided vehicle 24 can detect the distance based on the received signal, and if possible, the signal processing unit 15 detects the distance. The determined distance signal is sent to the proximity fuze 20, but if it is determined to be impossible, a preset distance signal is sent to the signal processing unit 15.
In the proximity fuze 20, the distance signal sent from the signal processing unit 15 and the reception of the target reflection signal from the fuze antenna 19 are used as conditions for generating the detonation signal, and further the target and the guided aircraft 2
Since the detonation generation time is adjusted by the relative speed with respect to 4, if the distance signal is inaccurate, the purpose of destroying the target with a predetermined destruction probability could not be achieved.

In addition, the ground device 10 and the guidance aircraft 24
Since the fuze processing in cooperation with the ground device 10 is not performed, the ground device 10 does not have a means for determining that the guide vehicle 24 is in the middle of interference, and the ground device 10 guides the flight 2
4. Distance detection processing of the signal processing unit 15 in the inside, proximity fuze 20
We could not support the control such as the detonation time.

[0011]

When there is no radio wave interference, the conventional guided vehicle also includes a distance signal detected by the signal processing unit 15, a relative velocity signal and a target reflection signal from the fuze antenna 19. In addition, the initiation time was adjusted by the proximity fuze 20 and the initiation signal was generated.

On the other hand, when the ECCM circuit 16 determines that the signal processing unit 15 cannot detect the distance due to interference, the preset distance signal is used as one of the detonation conditions. It was uncertain whether or not the detonation signal was generated at the optimum position close to the flying object 25.

Under radio interference, the signal processed inside the guided flying object 24 usually contains noise, and when steering is performed using the signal, the flying object is controlled along with the fluctuation of the noise. Becomes unstable. If this unstable spacecraft control continues, it will cause a large guidance error at the expected meeting point with the target. In such a state, even if the detonation signal is generated using the preset distance signal, the predetermined defeating effect cannot be obtained.

In the ground device 10, the guide aircraft 2
Predict the guidance error from the attitude, position, and velocity information of the guide vehicle transmitted from 4 and the target information being tracked by the radar device 1, and accurately detect the relative distance between the target and the guide vehicle 24. It is necessary to switch to the generation of the detonation signal under the control of the ground device 10.

For a wide range of targets whose approach speeds range from low speed to high speed, it is not always possible to detonate at the optimum relative position between the guide vehicle 24 and the target that maximizes the warhead effect, so high destruction is achieved. The effect was not obtained.

Furthermore, a fighter bomber, TBM (Tactical Ball)
The physical size of the target and the approach speed differ depending on the type of target such as istic missile), helicopter, etc. Need to be adjusted.

The present invention has been made in order to solve such a problem, and by the fuze processing operation in cooperation with the guide vehicle and the ground device, the target characteristic can be obtained regardless of the interference environment or the presence or absence of interference. It is possible to achieve a predetermined destruction effect or a nullification of the enemy's attack by performing processing with a certain flexibility.

[0018]

The ground device of the first invention uses a radar device that tracks a target and a guided vehicle and communicates with the guided vehicle, and tracking information from this radar device. Shooting / guidance calculator that calculates the launch parameters and guidance command signals of the guided vehicle, the position, velocity, and attitude signals of the above-mentioned guided vehicle, the probability of destruction after launch, and the distance between the guided vehicle and the target. And a shooting control device having an arm determination circuit for generating a detonation permission signal for a guided vehicle.

In the ground device of the second invention, the target is TBM (Tactic) by using the information from the radar device to the shooting control device.
TBM sent as a detonation adjustment signal to a guided vehicle via a radar device.
It is equipped with a determination circuit.

The ground device of the third invention uses the information from the radar device in the shooting control device of the second invention to determine that the target is a helicopter, and detonates the guided vehicle via the radar device. It is equipped with a helicopter determination circuit for sending as an adjustment signal.

The ground device of the fourth invention uses the information from the radar device as the target for the shooting control device of the third invention.
It is equipped with an ASM judgment circuit that judges M (Air To Surface Missile) and sends it as a detonation adjustment signal to a guided vehicle via a radar device.

The ground device of the fifth aspect of the invention uses the information from the radar device in the shooting control device of the fourth aspect of the invention to select a target to be destroyed when there are a plurality of targets, and to guide the target via the radar device. It is equipped with a target selection circuit that sends it as a detonation adjustment signal to the flying object.

The guide aircraft according to the sixth invention is defined by claim 1.
[5] A guide vehicle launched from the ground device according to any one of [1] to [5], which receives a main antenna that radiates and receives radio waves, and a guide command signal and a detonation permission signal from the radar device, and the radar. A communication antenna that transmits information on the guided vehicle to the device, a transmitter that generates a transmission signal, a receiver that amplifies and demodulates the received signals from the main antenna and communication antenna, and detects the target signal. Create a flight control signal from the signal processing unit that processes it, the ECCM (Electric Counter Counter Measurement) circuit that processes the radio interference signal at the time of target tracking, and the above target signal at the time of target tracking and the attitude information of the guided flying object itself. The auto pilot, the fuze antenna that receives the reflected signal when the target is near the guided aircraft, and the received signal from the fuze antenna A proximity fuse for detecting that passes near the body, in which a detonator control circuit for adjusting the initiation time using a detection signal from the detonation permission signal and proximity fuse from the radar device.

The guide flying system of the seventh invention is
The ground equipment of the first to fifth inventions and the guide vehicle of the sixth invention are provided.

[0025]

BEST MODE FOR CARRYING OUT THE INVENTION Embodiment 1. First Embodiment FIG. 1 is a block diagram of a guided vehicle system showing a first embodiment of the present invention. In the figure, 1, 2, 8-22, 24
26 to 26 correspond to those shown in FIG. ECCM circuit 1
6 is the same as the frequency band generated by the transmitter 13, and when it is determined that the interference signal is large, the communication antenna 12
The initiation request signal is sent to the radar apparatus 1 via the route and the signal processing unit 15 is prohibited from sending the distance detection signal to the proximity fuze 20. The arm determination circuit 3 receives the position, velocity, attitude signal, and detonation permission request signal 25 sent from the guide vehicle 24, and calculates the destruction probability at the expected meeting point between the target and the guide vehicle.

FIG. 7 shows a processing flow of preprocessing in the arm determination circuit 3, and in addition to the received information such as the above-mentioned position and speed, future motions based on target information sent from the radar device. The target motion prediction calculation for predicting the original is performed, and the motion prediction calculation of the guide vehicle 24 is performed. The above calculation uses Equation 1.

[0027]

[Equation 1]

The relative distance and the relative velocity between the target and the guide vehicle 24 are calculated from Equation 2 using the motion data of the target and the flying vehicle 24.

[0029]

[Equation 2]

The destruction probability is calculated from the calculated guidance error at the predicted meeting point. The mission reliability of the ground equipment and the guided aircraft is usually calculated by using Equation 3 as a constant.

[0031]

[Equation 3]

FIG. 8 shows the relationship between the relative position of the target and the guide vehicle and the guide error on a plane. The destruction probability Pr is a function of the effective radius r of the warhead, and the guide probability PG is the guide error.
The function of R, or mission reliability PM, is the probability that the ground device and the guided vehicle can operate normally with respect to the mission time from the launch of the guided vehicle to the meeting with the target.

The arm determination circuit 3 creates and sends out the detonation permission signal by using the guidance error calculated in the pre-processing which can take a high probability of destruction. FIG. 9 shows the contents of the process of creating the detonation permission signal. Distance information is created by multiplying the guidance error calculated when the destruction probability exceeds a predetermined probability by a predetermined in-range correction coefficient, and the distance information is generated. Is sent to the guided air vehicle as a detonation permission signal.

The detonation permission signal (distance information) is sent to the detonation control circuit 23 via the radar device 1 and the communication antenna 12. FIG. 10 shows conditions for generating a detonation signal by the detonation control circuit 23. The target and the guided vehicle are within a predetermined distance, there is a detection signal from the proximity fuze 20, and delay due to relative speed. A detonation signal is generated on condition that time has elapsed.

As described above, when there is an interfering signal and the distance signal cannot be detected by the signal processing unit 15 of the guide vehicle 24, the detonation permission signal sent from the ground device 10 is used to set the target. It is possible to generate a detonation signal at an optimum position between the and the guide vehicle.

Embodiment 2. FIG. 2 is a block diagram of a guided vehicle system showing a second embodiment of the present invention. In the figure, 1, 2, 8-22, 24-26
Corresponds to that shown in FIG. TBM judgment circuit 4
Determines TBM from the intrusion angle, altitude, and speed information, which are target information of the radar device 1. The determined result is sent to the initiation control circuit 23 via the radar device 1 and the communication antenna 12 as an initiation adjustment signal, and is used for timing adjustment of the initiation signal generation.

FIG. 11 shows the processing contents of the TBM determination circuit 4. The target intrusion angle, altitude and speed information detected and processed by the radar device 1 are collated with a preset TBM basic characteristic pattern, Determine if it is a TBM.

The TBM has a flight characteristic of flying in a ballistic trajectory from a high altitude to a super high speed. However, when the target penetration angle, altitude, and velocity information detected by the radar device 1 satisfy all of the following conditions: , TBM. (1) Invasion angle (flying invasion angle): 45 degrees or more (2) Altitude: 15 km or more (3) Speed: 3 Mach or more In addition, the criteria of these conditions are an example, and the performance of the target threat is improved. If there is a change, it is necessary to change the condition criteria accordingly.

FIG. 12 shows conditions for generating a detonation signal by the detonation control circuit 23. The target and the guided vehicle are within a predetermined distance, there is a detection signal from the close fuze 20, and the relative A detonation signal is generated on condition that the delay time set by the speed and TBM target has elapsed.

FIG. 13 shows the correction of the delay time by the detonation adjustment signal. The detonation timing is corrected according to the delay time amount corresponding to the relative speed with reference to the expected meeting time. Usually, the directional characteristics of the near-fuze antenna 19 for receiving a close target, the scattering distribution of the warhead 21, the scattering speed of the bullet pieces, and the like are known amounts, and therefore the relationship between the relative speed and the delay time is known in advance. Also, because the target is determined to be TBM,
Since the physical size of the target is added to the delay time correction, the detonation signal is generated at the relative position where the destruction effect is high.

Embodiment 3. FIG. 3 is a block diagram of a guided vehicle system showing a third embodiment of the present invention. In the figure, 1, 2, 8-22, 24-26
Corresponds to that shown in FIG. The helicopter determination circuit 5 determines the helicopter from the altitude and speed information that is the target information of the radar device 1. The determined result is sent to the initiation control circuit 23 via the radar device 1 and the communication antenna 12 as an initiation adjustment signal, and is used for timing adjustment of the initiation signal generation.

FIG. 14 shows the processing contents of the helicopter determination circuit 5. The target altitude and speed information detected and processed by the radar device 1 is collated with a preset helicopter basic characteristic pattern to form a helicopter. Or not.

Operationally, the helicopter normally penetrates the attack point at an extremely low altitude along the terrain. Although the flight characteristics of the helicopter are low altitude and low speed, if the target altitude and speed information detected by the radar device 1 satisfy all of the following conditions, it is determined to be a helicopter. (1) Altitude: 1 Km or less (2) Speed: 1.5 Mach or less Note that the criteria of these conditions are examples, and if the performance of the target threat improves or changes, it is necessary to change the criteria of the conditions accordingly. is there.

The conditions for generation of detonation and the setting of the delay time correction amount by the detonation control circuit 23 are the same as those described in the second embodiment, and are as shown in FIGS. 12 and 13.

Fourth Embodiment Fourth Embodiment FIG. 4 is a block diagram of a guided vehicle system showing a fourth embodiment of the present invention. In the figure, 1, 2, 8-22, 24-26
Corresponds to that shown in FIG. ASM judgment circuit 6
Is the received power and altitude, which is the target information of the radar device 1,
ASM is judged from speed information. The determined result is sent to the initiation control circuit 23 via the radar device 1 and the communication antenna 12 as an initiation adjustment signal, and is used for timing adjustment of the initiation signal generation.

FIG. 15 shows the processing contents of the ASM determination circuit 6, and the target size is estimated from the received power detected and processed by the radar device 1 using the equation (4). Since the performance of the components such as the antenna and the transmitter that make up the radar device is a known amount, the target size σ is determined by the distance R between the target detected by the radar device 1 and the radar device and the received power Pr.
Is estimated. Estimated target size and target altitude,
The speed information is collated with the preset ASM basic characteristic pattern, and the AS
It is determined whether or not it is M.

ASM is fired from the mother aircraft of an aircraft from a medium altitude to an attack point. However, the ASM ejected at a middle altitude once rises, enters the dive, and has an intrusion angle (typical intrusion angle) in the range of 45 degrees to 55 degrees. As for the flight characteristics of ASM, since the speed of the mother machine is added to the speed of the ejected ASM, it flies at high speed and high penetration angle. But TB
The difference from M is that ASM is a small target and the speed is smaller than TBM, so the size of the target detected by radar device 1
If the altitude and speed information satisfy all of the following conditions, AS
Judge as M. (1) Target size (radar cross section): 0.
1m ² or less (2) Altitude: 10Km or more (3) Speed: 2Mach or more Note that the criteria of these conditions are examples, and if the performance of the target threat improves or changes, it is necessary to change the criteria of the conditions accordingly. There is.

[0048]

[Equation 4]

The conditions for generation of detonation and the setting of the delay time correction amount by the detonation control circuit 23 are the same as those described in the second embodiment, and are as shown in FIGS. 12 and 13.

Embodiment 5. FIG. 5 is a block diagram of a guided vehicle system showing a fifth embodiment of the present invention. In the figure, 1, 2, 8-22, 24-26
Corresponds to that shown in FIG. Target selection circuit 7
Uses the destruction probability for each target calculated in the preprocessing based on the plurality of target information of the radar device 1 to compare and collate the destruction probability for each target with respect to the guided flying object in flight, and the probability is high. Select a goal. The result is sent to the detonation control circuit 23 via the radar device 1 and the communication antenna 12 as the unique information of the target and used for timing adjustment of the detonation signal generation.

FIG. 16 shows the processing contents of the target selection circuit 7, which uses the information of the target and the guided vehicle received by the radar device 1 as a reference for a specific guided vehicle in flight. It is determined whether or not there are a plurality of targets having close expected meeting points, and if there are, targets are compared and compared based on the destruction probability calculated in the preprocessing of the arm determination circuit 3, and a target having a high destruction probability is obtained. select.

[0052]

EFFECTS OF THE INVENTION According to the present invention, in the case where the guide vehicle that is tracking and guiding the target becomes incapable of detecting the target due to radio interference, By sending the detonation permission signal to the target, it is possible to obtain a predetermined probability of destroying the target in the disturbing environment.

Further, according to the present invention, the TBM target flying at an extremely high speed and associated with the guided vehicle is discriminated and judged at an early stage, and information is sent to the guided vehicle, whereby the target speed and size can be increased. It is possible to detonate at an optimal position in consideration of, and to obtain a high defeating effect.

According to the present invention, a helicopter target that comes in at an extremely low altitude and associates with a guided vehicle is identified and sent at an early stage, and information is sent to the guided vehicle so that the target altitude and speed are taken into consideration. It is possible to detonate at the optimum position and obtain a high destruction effect.

Further, according to the present invention, a small target such as ASM which flies at high speed and associates with the guided vehicle is discriminated and judged at an early stage, and information is sent to the guided vehicle so that the altitude of the target can be determined. It is possible to detonate at an optimal position considering speed, and obtain a high defeating effect.

According to the present invention, from multiple targets such as a fighter bomber that invade with a large number of aircraft and meet with a guided aircraft,
By selecting a specific target at an early stage and sending information to the guide vehicle, it is possible to detonate at an optimum position in consideration of the guide error and obtain a high defeat effect.

[Brief description of drawings]

FIG. 1 is a block diagram showing a first embodiment of a guided vehicle system according to the present invention.

FIG. 2 is a block diagram showing a second embodiment of the guided vehicle system according to the present invention.

FIG. 3 is a block diagram showing a third embodiment of the guided vehicle system according to the present invention.

FIG. 4 is a block diagram showing a fourth embodiment of the guided vehicle system according to the present invention.

FIG. 5 is a block diagram showing a fifth embodiment of the guided vehicle system according to the present invention.

FIG. 6 is a state diagram of a guide vehicle, a ground device, a target, and a jammer when radio interference is applied.

FIG. 7 is a block diagram showing a processing flow of preprocessing of the arm determination circuit according to the first embodiment of the guided vehicle system according to the present invention.

FIG. 8 is a diagram showing the relationship between the relative position of the target and the guide vehicle and the guide error of the first embodiment of the guide vehicle system according to the present invention.

FIG. 9 is a diagram showing an example of detonation permission signal creation processing according to the first embodiment of the guided vehicle system according to the present invention.

FIG. 10 is a logic diagram showing conditions for generating a detonation signal in the first embodiment of the guided vehicle system according to the present invention.

FIG. 11 is a diagram showing an example of TBM determination processing of the second embodiment of the guided flying object system according to the present invention.

FIG. 12 is a logic diagram showing conditions for generating a detonation signal according to Embodiments 2 to 5 of the guided vehicle system according to the present invention.

FIG. 13 is a diagram showing correction of the detonation delay time of Embodiments 2 to 5 of the guided vehicle system according to the present invention.

FIG. 14 is a diagram showing an example of helicopter determination processing according to the third embodiment of the guided flying object system according to the present invention.

FIG. 15 is a diagram showing an example of ASM determination processing of a fourth embodiment of the guided flying object system according to the present invention.

FIG. 16 is a diagram showing an example of target selection processing of a fifth embodiment of the guided flying object system according to the present invention.

FIG. 17 is a block diagram of a guided vehicle system constructed by conventional technology.

[Explanation of symbols]

1 radar device, 2 shooting / guidance calculation unit, 3 arm determination circuit, 4 TBM determination circuit, 5 helicopter determination circuit,
6 ASM judgment circuit, 7 target selection circuit, 8 shooting control device,
9 launchers, 10 ground equipment, 11 main antennas,
12 communication antennas, 13 transmitters, 14 receivers, 1
5 signal processor, 16 ECCM circuit, 17 autopilot, 18 steering device, 19 fuze antenna, 20 proximity fuze, 21 warhead, 22 propulsion device, 23 detonation control circuit,
24 guidance aircraft, 25 position, velocity, attitude, detonation permission request information, 26 guidance command / detonation permission signal / detonation adjustment signal, 50 target, 51 jammer, 53-54 jamming area, 56 guidance antenna Beam, 5
7 Antenna beam of radar equipment.

Claims (7)

[Claims] 1. A ground device for detecting and tracking a target, and for launching a guided vehicle based on the tracked target information,
A radar device that tracks the target and the guided vehicle and communicates with the guided vehicle, and shooting information that calculates the launch parameters of the guided vehicle and the guidance command signal using the tracking information from this radar device. Guidance calculator, position of the above guidance aircraft,
A shooting control device having an arm determination circuit that determines the probability of destruction after launch from the velocity and attitude signals and the distance between the guided vehicle and the target, and generates an initiation permission signal for the guided vehicle. Characteristic ground equipment. 2. The target of the shooting control device is TBM (Tactical Ballistic Missile) using information from a radar device.
2. The ground apparatus according to claim 1, further comprising a TBM determination circuit which determines that it is a signal and sends it as a detonation adjustment signal to a guided vehicle via a radar device. 3. The shooting control device comprises a helicopter determination circuit that determines that the target is a helicopter using information from the radar device and sends it as a detonation adjustment signal to the guided vehicle via the radar device. The ground device according to claim 2, wherein 4. The shooting control device uses the information from the radar device to determine that the target is an ASM (Air To Surface Missile), and sends it as a detonation adjustment signal to the guide vehicle via the radar device. The ground apparatus according to claim 3, further comprising a determination circuit. 5. The shooting control device selects a target to be destroyed when there are a plurality of targets using the information from the radar device, and selects the target to be sent as a detonation adjustment signal to the guide vehicle via the radar device. The ground device according to claim 4, further comprising a circuit. 6. In a guided vehicle launched from the ground device according to claim 1, a main antenna for radiating and receiving radio waves, a guidance command signal and a detonation permission signal from the radar device. And a communication antenna for receiving the information on the guided vehicle to the radar device, a transmitter for generating a transmission signal, and a receiver for amplifying and demodulating the reception signals from the main antenna and the communication antenna. , A signal processing unit that detects and processes a target signal, and an ECCM (Electric Counter Co) that processes a jamming signal during target tracking.
(unter Measurement) circuit, an autopilot that creates a flight control signal from the target signal above when tracking a target and the attitude information of the guided vehicle itself, and a reflection signal when the target is in the vicinity of the guided vehicle The fuze antenna and the proximity fuze that receives the received signals from the fuze antenna and detects that the target passes near the guided vehicle, the detonation permission signal from the radar device and the detection signal from the proximity fuze An induction vehicle characterized by being provided with a detonation control circuit for adjusting the detonation time by using the detonation control circuit. 7. A guided flying object system comprising a ground device for detecting and tracking a target, and launching a flying object based on the tracked target information, and a guided flying object for flying to a target. A guide aircraft system comprising the ground device according to any one of claims 1 to 5 and the guide aircraft according to claim 6.