JPH07190692A - Guided missile - Google Patents

Abstract

PURPOSE:To improve a guiding capacity from an initial stage of guiding to a terminating stage. CONSTITUTION:The guided missile comprises an S/N detector 23 for calculating an S/N, an S/N deciding unit 24 for outputting a high-level signal and a low- level signal before and after exceeding a predetermined S/N, an offset signal generator 25 for outputting an angle offset signal according to the output of the unit 24, and a first corrector 26 and a second corrector 27 for combining the output of the generator 25 and an output of an angle detector 15 and outputting an offset beam directing angle control signal and an offset target direction angle signal to a beam directing angle controller 16 and an auto-pilot 17 in a conventional guided missile M.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a guided vehicle which detects infrared rays or reflected waves generated from a target and captures and tracks the target.

[0002]

2. Description of the Related Art First, a conventional guided vehicle M of this type will be described. In FIG. 7, M is a guided aircraft, 1
Is a target wave that the guide vehicle captures and tracks, 2 is a transmitted wave that irradiates the target 1, 3 is a reflected wave from the target 1, and 4 is a transmitted signal that irradiates the target 1 as a transmitted wave 2 from the target 1. An antenna that receives the reflected wave 3 and outputs a sum received signal and a diff received signal, 5 is a transmission source unit that generates a transmission signal of a transmission wave 2 that irradiates a target 1, and 6 is a transmission signal that is generated by the transmission source unit 5. Is supplied to the antenna 4, and the circulator that supplies the sum received signal received by the antenna 4 to the first preamplifier described later, 7 is a dome that protects the antenna 4 from the outside, and 8 is received by the antenna 4. A first preamplifier for amplifying a weak sum received signal with low noise, 9 is a second preamplifier for amplifying a weak diff received signal received by the antenna 4 with low noise, and 10 is a first preamplifier. A sum received signal (P) output from the preamplifier 8, Locking and on signal output of the target signal detection circuit 12 for predicates, than the target signal received power signal of the output target signal detected during reception power detector 13 to be described later (P _MIN), induced spacecraft M is the target 1 Until it is turned on, the sum reception signal (P) is output as it is to the relative speed detector 11, which will be described later, and after locking on to the target 1, the sum reception signal (P) is output to P _MIN + 1 + K and P- (P _MIN / 1+
K), and the relative speed detectors 11 to be described later are provided for each.
And a variable distributor 11 to be supplied to the relative distance detector 14, and 11 extracts a target signal from the sum received signal, and then extracts a Doppler shift amount of the transmission wave frequency generated between the target 1 and the guide vehicle M from the target signal. Then, the relative speed detector that outputs the relative speed signal, 12 confirms that the target 1 is captured from the target signal of the relative speed detector 11, and after confirming, the target signal detection circuit that outputs the lock-on signal, Reference numeral 13 indicates that the guide vehicle M is the target 1 based on the sum reception signal output from the first preamplifier 8 and the lock-on signal output from the target signal detection circuit 12.
Target signal received power signal when locked on (p _MIN )
A target signal detection received power detector that outputs a signal, 14 is a relative distance detector that extracts a distance error that occurs between the target 1 and the guided vehicle M from the sum received signal, and outputs a relative distance signal, and 15 is a diff reception An angle detector that detects the angle direction of the target 1 with respect to the axis of the guided flying object M from the signal and outputs a beam directivity angle control signal and a target direction angle signal. 16 is a beam directivity angle control signal output from the angle detector 15. A beam directivity angle controller for controlling the beam directing direction of the antenna 4 to the direction of the target 1 by means of a relative speed signal output from the relative speed detector 11, a relative distance signal output from the relative distance detector 14, and an angle. An autopilot that outputs a steering command signal for steering the guided vehicle M in the direction of the meeting point with the target 1 based on the target direction angle signal output from the detector 15.
Reference numeral 8 denotes a steering device that steers the guided vehicle M toward the meeting point with the target 1 by a steering command signal output from the autopilot 17, and 19 generates a proximity detonation pulse when passing near the target 1 A fuze that generates an initiation detonation pulse when it hits directly, and generates an initiation signal that detonates a warhead 20 described later by the proximity detonation pulse or the initiation detonation pulse, 2.
0 will explode due to the detonation signal when meeting with Goal 1 and Goal 1
The reference numeral 21 denotes a warhead that causes damage to the guide vehicle, 21 is a power source that supplies electric power required for the components of the guided vehicle M, and 22 is a propulsion device that applies thrust to the guided vehicle M. However, the value of K is set at K = 10 ^{(S / N) / 10} -1 (S / N is a decibel value) depending on the degree of S / N that is improved before and after the target signal extraction of the relative speed detector. To do.

A process until the conventional guided aircraft M damages the target 1 will be described. The transmission signal generated by the transmission source unit 5 is transmitted as a transmission wave 2 from the antenna 4 to the target 1 via the circulator 6. Goal 1
The reflected wave 3 is received through the antenna 4. Since the sum received signal extracted from the received reflected wave 3 is weak, it is amplified by the first preamplifier 8 and input to the relative speed detector 11 via the variable distributor 10. Relative speed detector 1
Reference numeral 1 extracts a target signal from the sum received signal and sends it to the target signal detection circuit 12 and also extracts the Doppler shift amount between the target 1 and the guided vehicle M from the target signal and sends it to the autopilot 17 as a relative velocity signal. The relative distance detector 14 receives the sum received signal amplified by the first preamplifier 8 via the variable distributor 10, extracts the distance between the target 1 and the guided flying object M, and outputs the relative distance signal. To the auto pilot 17. The angle detector 15 is the second preamplifier 9
The angle signal in the target 1 direction is extracted from the diff received signal amplified in step 1 and sent to the autopilot 17, and at the same time, the beam directivity angle control signal for controlling the beam of the antenna 4 in the target 1 direction is generated and the beam directivity angle control unit 16 Send to. The autopilot 17 produces a steering command signal for steering the guided vehicle M in the direction of the meeting point with the target 1 from the relative velocity signal, the relative distance signal, and the target direction angle signal, and then the steering device 18
Send to. The steering device 18 causes the guided flying object M to fly toward the meeting point with the target 1 in response to the steering command signal.
Ultimately, the guided flying object M directly hits the target 1 or a detonation signal is generated from the fuze 19 when the target 1 passes in the vicinity of the target 1 to explode the warhead 20 to cause great damage to the target 1.

[0004]

The conventional guided vehicle M is constructed as described above, and if the S / N is low or the S / N varies even if the target signal can be extracted from the sum received signal. In this case, the center point of the S-shaped characteristic of the angle detector is affected by noise as shown in FIG. Therefore, the target direction angle signal and the beam pointing angle control signal become unstable and the ability to guide to the target 1 is reduced, or the beam width of the antenna 4 is limited by the diameter of the guide projectile M (antenna 4 diameter), The error (angle resolution) is improved by S / N,
Since it was not improved significantly, the angular resolution was insufficient for a small target (small effective reflection cross-sectional area), and there was a problem with the meeting ability.

The present invention has been made to solve the above-mentioned problems, and the first embodiment is a predetermined S / N.
Until the following is obtained, the target direction angle signal and the beam pointing angle control signal become unstable by offsetting the center point of the S-shaped characteristic of the angle detector to a point not affected by noise (Δθ in FIG. 9). The purpose is to improve the ability to guide to goal 1.

In the second embodiment, the center point is offset as in the first embodiment, but the offset amount is varied in proportion to the S / N to make the target direction angle signal and the beam pointing angle control signal unstable. The purpose is to improve the ability to guide to goal 1 by preventing

The third embodiment is similar to the second embodiment, but when the target 1 interferes with it, it switches to the HOJ mode and jumps. Even if it is received, the object is to improve the ability to guide to the target 1 by controlling the target direction angle signal and the beam directivity angle control signal so as not to become unstable.

The fourth embodiment does not use the angle output having the S-shaped characteristic which is affected by noise until a predetermined S / N is obtained, and narrows the antenna beam after the predetermined S / N is obtained. The purpose is to improve the angular resolution by banding and improve the guiding ability to the target 1.

The fifth embodiment narrows the band of the antenna beam similarly to the fourth embodiment, but the beam width is not fixed and S
The purpose is to change the beam in proportion to / N, improve the angular resolution, and improve the ability to guide the target 1.

The sixth embodiment is similar to the fifth embodiment, but when the obstacle is received from the target 1, it switches to the HOJ mode and flies. Therefore, even if the obstacle is received, the target direction angle is changed. The purpose is to control the signal so that it does not become unstable and to improve the ability to guide to the target 1.

[0011]

The guided vehicle M according to the first embodiment calculates and outputs S / N from the output of the target signal detection circuit 12 and the output of the target detection reception power detector 13. Means and a predetermined S from the S / N of the output of the means.
High level signal is output until the number exceeds / N
Means for outputting a low level signal after exceeding N, means for outputting a predetermined angle offset signal when the output of the means is a high level signal, and means for outputting an angle offset zero signal in the case of a low level signal, A means for synthesizing the output of the angle detector 15 and the angle offset signal of the means, and outputting an offset beam directivity angle control signal to the beam directivity angle control unit 16, and a means for synthesizing the output of the angle detector 15 and the angle offset signal, And means for outputting the offset target direction angle signal to the autopilot 17.

Guided flying vehicle M according to the second embodiment
Is a means for calculating and outputting S / N from the output of the target signal detection circuit 12 and the output of the target detection received power detector 13, and a variable offset amount control signal proportional to the S / N of the output of the means. For outputting the angle offset signal proportional to the variable offset amount control signal of the output of the means, the output of the angle detector 15 and the angle offset signal of the means are combined, and the offset beam directivity angle control is performed. It is provided with means for outputting a signal to the beam directivity angle control unit 16 and means for combining the output of the angle detector 15 and the angle offset signal and outputting the offset target direction angle signal to the autopilot 17.

Guided flying vehicle M according to the third embodiment
Outputs a high level signal from the output of the first preamplifier 8 and the output of the target signal detection circuit 12 in the second embodiment when the target 1 is not detected and is disturbed, When the output of the means is a high level signal, the output of the angle detector 15 as it is,
In the case of the low level signal, a means for outputting an offset beam directivity angle control signal obtained by combining the output of the angle detector 15 and the angle offset signal to the beam directivity angle control unit 16, and in the case of the high level signal, the angle detector 15 In the case of a low level signal without changing the output of, the means for outputting the offset target direction angle signal obtained by combining the output of the angle detector 15 and the angle offset signal to the autopilot 17 is added.

Guided flying vehicle M according to the fourth embodiment
Is a means for calculating and outputting S / N from the output of the target signal detection circuit 12 and the output of the target detection received power detector 13, and the S / N of the output of the means exceeds a predetermined S / N. Means for outputting a high level signal up to a predetermined S / N, and a means for outputting a low level signal after exceeding a predetermined S / N, and when the output of the means is a low level signal, a predetermined beam narrowing signal is output, A means for outputting a beam narrowing zero signal in the case of a high level signal, and the output to control the effective dither range of the output of the angle detector 15, and output the controlled signal to the beam directivity angle control unit 16. Means for outputting the target direction angle signal to the autopilot 17 in synchronization with the effective dither of the output of the angle detector 15 by the beam narrowing signal, and sum reception in synchronization with the beam narrowing signal. Signal side first Means for subtracting the output of the second preamplifier 9 on the side of the differential reception signal from the output of the preamplifier 8 and outputting it to the target signal detection reception power detector 13 and the variable distributor 10. It was done.

Guided flying vehicle M according to the fifth embodiment
Is a means for calculating and outputting S / N from the output of the target signal detection circuit 12 and the output of the target detection received power detector 13, and a variable narrowing control proportional to the S / N of the output of the means. Means for outputting a signal, means for outputting a beam narrowing signal proportional to the variable narrowing control signal of the output of the means,
A means for controlling the effective dither range of the output of the angle detector 15 by the output, and outputting the controlled signal to the beam directivity angle control unit 16, and a means for outputting the output of the angle detector 15 by the beam narrowing signal. Means for outputting the target direction angle signal to the autopilot 17 in synchronization with the effective dither,
Similarly, in synchronization with the beam narrowing signal, the output of the second preamplifier 9 on the differential reception signal side is subtracted from the output of the first preamplifier 8 on the sum reception signal side to detect the target signal. And a means for outputting to the time reception power detector 13 and the variable distributor 10.

Guided flying vehicle M according to the sixth embodiment
In the fifth embodiment, a high-level signal is output from the output of the first preamplifier 8 and the output of the target signal detection circuit 12 when the target 1 is not detected and interference is generated, and otherwise When the output of the means is a high level signal, the output of the angle detector 15 is kept unchanged, and when the output of the means is a low level signal, the angle detector 15 is output by a beam narrowing signal. Control the effective dither range of the output of
The means for outputting the controlled signal to the beam directivity angle control unit 16 and the output of the angle detector 15 in the case of the high level signal as it is, and the beam narrowing signal in the case of the low level signal to detect the angle. The target direction angle signal in synchronization with the effective dither of the output of the instrument 15
And the output of the first preamplifier 8 in the case of the high level signal and the output of the band narrowing signal generator 34 in the case of the low level signal when the target signal is detected. And means for outputting to the variable distributor 10.

[0017]

The first embodiment of the present invention acts to stably guide the guide vehicle M even when the S / N is low.

In addition, the second embodiment functions to stably guide the guided flying object M even when the S / N is low or the S / N is unstable.

In the third embodiment, the target 1 is disturbed, the S / N is low even if the target 1 is not disturbed, and the S / N ratio is low.
Even when / N is unstable, it acts so as to stably guide the guide vehicle M.

In the fourth embodiment, when a predetermined S / N is obtained, the antenna beam is narrowed to improve the angular resolution and thus the guiding performance of the guiding flying object M is improved. .

Further, in the fifth embodiment, when a predetermined S / N is obtained, the antenna beam is narrowed in proportion to the S / N to improve the angular resolution. Act to improve.

The sixth embodiment operates in the same manner as the fifth embodiment, and also operates so as to stably guide the guided flying body M even when the target 1 interferes with it.

[0023]

【Example】

Example 1 FIG. 1 is a diagram showing a first example, and 1 to 22 are the same as FIG. 7. 23 to 27 are devices newly added to FIG. 7. Reference numeral 23 is an S / N detector that calculates and outputs S / N from the output of the target signal detection circuit 12 and the output of the received power detector 13 at the time of detecting the target signal, and 24 is the S / N output of the S / N detector 23. An S / N determination unit that outputs a high-level signal until it exceeds a predetermined S / N from N, and outputs a low-level signal after it exceeds a predetermined S / N, and 25 indicates an output of the S / N determination unit 24. Is an output of an angle offset signal when it is a high level signal, and an output of an angle offset of zero signal when it is a low level signal, and 26 synthesizes the output of the angle detector 15 and the output of the offset signal generation unit 25, The beam pointing angle control unit 16 outputs the offset beam pointing angle control signal.
The second correction unit 27 outputs the offset target direction angle signal to the auto-pilot 17 by synthesizing the output of the angle detector 15 and the output of the offset signal generation unit 25.

When the guide vehicle M detects the target signal and locks on the target 1, and the S / N is high, the S-characteristic of the angle system shows a clean straight line even in the central portion as shown in FIG. However, when the S / N is low, the output becomes unstable under the influence of noise as shown in FIG. In the guided flying object M configured as in the first embodiment, the S / N detection unit 2
Until the S / N calculated in 3 exceeds a predetermined level, the offset signal generator 25 outputs the angle offset signal corresponding to the straight line portion Δθ in which the influence of noise in FIG. 9 is avoided. First
Of the angle detector 1 to the beam directivity angle control unit 16.
The output of FIG. 5 and the angle offset signal are combined to output the offset beam directivity angle control signal, and the second correction unit similarly outputs the offset target direction angle signal to the autopilot 17. With these outputs, the steering device 18 and the antenna 4 are stably controlled even when the S / N is low, and the guiding ability of the guided vehicle M to the target 1 can be improved.

FIG. 2 is a diagram showing a second embodiment, in which 1-2
3, 26 and 27 are the same as those in FIG. 2, and 28 and 29 are shown in FIG.
It is a device that is newly added in place of 24 and 25. 28
Is an S / N-compatible offset amount control signal generator that outputs a variable offset amount control signal proportional to the S / N of the output of the S / N detector 23, and 29 is an output of the S / N-compatible offset amount control signal generator 28. Is a variable offset signal generator that outputs an angle offset signal in proportion to the variable offset amount control signal.

In the guide vehicle M constructed as in the second embodiment, the angle offset value Δθ is reduced when the S / N value is high, and the S / N value is low. Is controlled by the S / N corresponding offset amount control signal generator 28 and the variable offset signal generator 29 so as to increase the value of Δθ so as to avoid the influence of noise. Therefore, when the S / N is low or unstable. However, the steering device 18 and the antenna 4 are stably controlled, and the guiding ability of the guided flying object M to the target 1 can be improved.

FIG. 3 is a diagram showing a third embodiment, in which 1-2
3, 26 to 29 are the same as in FIG. 2, and 30 to 32 are in FIG.
This is a newly added device. Reference numeral 30 denotes a high level signal when the output of the first preamplifier 8 and the output of the target detection circuit 12 does not detect the target 1 and is interfered with, and otherwise outputs a low level signal. HOJ that outputs
When the output of the HOJ determination circuit 30 is a high level signal, the output of the angle detector 15 is unchanged, and when the output of the HOJ determination circuit 30 is a low level signal, the output of the first correction unit 26 is passed to the beam directivity angle control unit and output. When the output of the HOJ determination circuit 30 is a high level signal, the first SW, 32 keeps the output of the angle detector 15 as it is, and when it is a low level signal, the second correction unit 2
It is a second SW that outputs the output of 7 to the autopilot 17 and outputs it.

In the guide vehicle M constructed as in the third embodiment, when the obstacle is not disturbed by the target 1, it operates in the same manner as in the second embodiment and is disturbed by the target 1. Even in the case of the above, the HOJ determination circuit 30 switches the mode to the HOJ mode, and the angle detector 15 produces a beam directivity angle control signal and a target direction angle signal for guiding in the target 1 direction which is an interference source. The beam is output to the beam directivity angle control unit 16 and the autopilot 17 by the second SW 32. By these outputs, the steering device 18 and the antenna 4 are stably controlled even in the disturbing environment, and the guiding ability of the guided flying object M to the target 1 can be improved.

FIG. 4 is a diagram showing a fourth embodiment of the present invention.
Is the same as in FIG. 23, 24, 33 to 36 are devices newly added to FIG. 7. Reference numeral 23 is an S / N detector that calculates and outputs S / N from the outputs of the target signal detection received power detector 13 and the target signal detection circuit 12, and 24 is the S / N output of the S / N detector 23. A high-level signal is output until it exceeds a predetermined S / N, and a low-level signal is output after the predetermined S / N is exceeded. 33 is an output of the S / N determination unit 24. In the case of a low level signal, a predetermined beam narrowing signal is output, and in the case of a high level signal,
A beam narrowing signal generation unit for outputting a beam narrowing zero signal, 34 synchronizes with the beam narrowing signal, and outputs from the sum received signal output of the first preamplifying unit 8 to the second preamplifying unit 9 Of the beam narrowing signal output of the beam narrowing signal generator 33 by subtracting the diff received signal output of the above, and outputting to the reception power detector 13 and the variable distributor 10 at the time of detecting the target signal. A third correction unit 36 which controls the effective dither range of the output of the angle detector 15 by the digitization signal and outputs the controlled signal to the beam directivity angle control unit 16, and 36 is the output of the beam narrowing signal generation unit 33. Accordingly, the correction unit 4 outputs the target direction angle signal to the autopilot 17 in synchronization with the effective dither of the output of the angle detector 15.

In the guide vehicle M constructed as in the fourth embodiment, the unstable angular characteristic affected by noise is not used for guidance until a predetermined S / N is obtained, and After the S / N is obtained, the output of the beam narrowing signal generator 34 is changed to the output of the beam narrowing signal generator 34 shown in FIG.
0 from the sum received signal of the first preamplifier 8 shown in FIG.
12 is created by subtracting the differential reception signal of the second preamplifier 9 shown in FIG. Since this narrow band signal is a steep beam and the angular resolution can be improved as compared with the conventional one, the angle detector 15 moves the beam directivity angle control unit 1.
6 and the output to the autopilot 17 is the third correction unit 35.
As a result, the ability of the guide vehicle M to guide the target 1 can be improved by being improved by the fourth correction unit 36.

FIG. 5 is a diagram showing a fifth embodiment, in which 1-2
3, 34 to 36 are the same as those in FIG. 37 and 38 are shown in FIG.
This is a newly added device in place of the above 24 and 33. 37
Is an S / N-compliant narrowing amount control signal generator that outputs a variable narrowing control signal that is proportional to the S / N of the output of the S / N detector 23, and 38 is an S / N-compliant narrowing amount control signal It is a variable beam narrowing signal generator that outputs a beam narrowing signal that is proportional to the variable narrowing control signal output from the generator 37.

In the guide vehicle M constructed as in the fifth embodiment, when the S / N value is high, the range of the beam to be narrowed (Δα in FIGS. 10, 11 and 12). ) Is narrowed, and when the S / N value is low, the range of the beam to be narrowed is widened. The S / N-compliant narrowing amount control signal generator 37 and the variable beam narrowing signal generator 38 are provided. Since the control is performed by, the angular resolution can be controlled in accordance with the change of S / N, and the guide ability of the guide vehicle M to the target 1 can be improved.

FIG. 6 is a diagram showing a sixth embodiment, in which 1-2
3, 34 to 38 are the same as those in FIG.
Is a device newly added to FIG. 30 is the first
From the output of the preamplifier 8 and the output of the target signal detection circuit 12, the HOJ outputs a high level signal when the target 1 is not detected and is disturbed, and otherwise outputs a low level signal. Judgment circuit, 39, when the output of the HOJ judgment circuit is a high level signal, the output of the angle detector 15 is unchanged,
When the signal is a low bell signal, the third SW, 40 for passing the output of the third correction section 35 to the beam directivity angle control section 16 and outputting it is H
When the output of the OJ determination circuit 30 is a high level signal, the output of the angle detector 15 remains unchanged, and when it is a low level signal, the fourth
When the output of the HOJ determination circuit 30 is a high level signal, the fourth SW 41 passing the output of the correction unit 36 of the above to the autopilot 17 and outputting it is a low level without changing the output of the first preamplification unit 8. In the case of a signal, the output of the narrow band signal generator 34 is used as the target signal detection reception power detector 13 and the variable distributor 1.
It is a fifth SW that passes and outputs to 0.

In the guide vehicle M constructed as in the sixth embodiment, when the obstacle is not disturbed by the target 1, the same action as in the fifth embodiment is exerted and the obstacle is disturbed by the target 1. Even in this case, the HOJ determination circuit 30 switches to the HOJ mode, and the angle detector 15 produces a beam directivity angle control signal and a target direction angle signal for guiding in the target 1 direction which is an interference source. The signal is output to the beam directivity angle control unit 16 and the autopilot 17 by the fourth SW 40 and the fifth SW 41. With these outputs, the steering device 18 and the antenna 4 are stably controlled even in an obstructing environment, and the guiding ability of the guided vehicle M to the target 1 can be improved.

[0035]

All of the first to sixth embodiments have the effect of improving the ability to guide to the target 1 by the configuration as described above.

[Brief description of drawings]

FIG. 1 is a configuration block diagram showing a first embodiment of the present invention.

FIG. 2 is a configuration block diagram showing a second embodiment of the present invention.

FIG. 3 is a configuration block diagram showing a third embodiment of the present invention.

FIG. 4 is a configuration block diagram showing a fourth embodiment of the present invention.

FIG. 5 is a configuration block diagram showing a fifth embodiment of the present invention.

FIG. 6 is a configuration block diagram showing a sixth embodiment of the present invention.

FIG. 7 is a block diagram showing a configuration of a conventional guide vehicle M.

FIG. 8 is a diagram showing an S-shaped characteristic of the angle detector 15 when S / N is high.

FIG. 9 is a diagram showing an S-shaped characteristic of the angle detector 15 when the S / N is low.

10 is a diagram showing a sum reception signal pattern of the output of the first preamplifier 8. FIG.

11 is a diagram showing a differential reception signal pattern of the output of the second preamplifier 9. FIG.

FIG. 12 is a diagram showing a pattern obtained by subtracting a diff received signal pattern from a sum received signal pattern.

[Explanation of symbols]

 1 Target 2 Transmitted Wave 3 Reflected Wave 4 Antenna 5 Transmission Source Section 6 Circulator 7 Dome 8 First Preamplifier 9 Second Preamplifier 10 Variable Distributor 11 Relative Speed Detector 12 Target Signal Detection Circuit 13 Target Signal detection reception power detector 14 Relative distance detector 15 Angle detector 16 Beam directivity angle control unit 17 Autopilot 18 Steering device 19 Fuze 20 Warhead 21 Power supply 22 Propulsion device 23 S / N detection unit 24 S / N determination unit 25 Offset signal generation unit 26 First correction unit 27 Second correction unit 28 S / N compatible offset amount control signal generation unit 29 Variable offset signal generation unit 30 HOJ determination circuit 31 First SW 32 Second SW 33 Beam narrowing Banding signal generation unit 34 Narrowing signal generation unit 35 Third correction unit 36 Fourth correction unit 37 S / N compatible narrowing amount control signal Generator 38 Variable beam narrowing signal generator 39 Third SW 40 Fourth SW 41 Fifth SW

─────────────────────────────────────────────────── ─── Continuation of the front page (51) Int.Cl. ⁶ Identification code Internal reference number FI technical display location G05D 1/12 D

Claims (6)

[Claims] 1. A transmission source unit for generating a transmission signal of a transmission wave for irradiating a target, a circulator for supplying the transmission signal to an antenna and supplying a reception signal to a preamplifier, and a target for the transmission signal as a transmission wave. To receive the reflected wave from the target, the first preamplifier that amplifies the weak sum (sum) received signal received by the antenna with low noise, and the weak preamplifier received by the antenna. A second pre-amplifier for amplifying the diff (difference) received signal with low noise, a relative speed detector for extracting a target signal from the sum received signal and a relative speed signal from the target signal, and the sum A relative distance detector that extracts a relative distance signal from a received signal, a target signal from the target signal of the relative speed detector, confirms that the target signal has been captured, and a target signal detection circuit that outputs a lock-on signal after confirmation, Sam above Signal and lock-on signal,
Target signal detection power output target signal reception power signal when the guide flight locks on the target and the above thumb reception signal, lock-on signal and target signal reception power signal Until the target locks on, the sum reception signal is output to the relative speed detector as it is, and after the target is locked on, the sum reception signal is supplied to the relative speed detector and the relative distance detector, respectively. A distributor, an angle detector that outputs a beam directivity angle control signal and a target direction angle signal from the diff received signal,
From the beam directivity angle control unit that controls the beam of the antenna in the target direction by the beam directivity angle control signal, and the relative velocity signal, the relative distance signal, and the target direction angle signal, the guiding projectile is directed toward the meeting point with the target. An autopilot that generates a steering command signal to steer, a steering device that steers the guided vehicle toward the meeting point with the target by the steering command signal, a dome that protects the antenna from the outside world, and a proximity when passing near the target Generates a detonation pulse, and also generates a detonation detonation pulse when it hits the target directly, and generates a detonation signal for detonating the warhead by these detonation pulses. Guided vehicle equipped with a warhead that causes a large amount of damage to the guided vehicle, a power supply that supplies power to the components of the guided vehicle, and a propulsion device that applies thrust to the guided vehicle. The S / N detecting section for calculating and outputting S / N from the output of the target signal detecting circuit and the output of the received power detector at the time of detecting the target signal, and the S / N of the output of the S / N detecting section are predetermined. The high-level signal is output until the S / N of the S / N is exceeded, and the low-level signal is output after the predetermined S / N is exceeded. In the case of a low level signal, a predetermined angle offset signal is output, and in the case of a low level signal, an offset signal generator that outputs an angle offset zero signal is combined with the output of the angle detector and the output of the offset signal generator to generate an offset beam directivity control signal. A first correction unit for outputting to a beam directivity angle control unit;
A guided flying vehicle comprising a second correction unit for combining the output of the angle detector and the output of the offset signal generation unit and outputting the angle signal of the target offset direction to the autopilot. 2. The S / N determination section is configured to output S of the S / N detection section.
S / which outputs a variable offset control signal proportional to / N
The offset signal generator is replaced with an N corresponding offset amount control signal generator, and the offset signal generator is replaced with a variable offset signal generator that outputs an angle offset signal proportional to the variable offset control signal output from the S / N corresponding offset amount control signal generator. The guidance aircraft according to claim 1, wherein the guidance aircraft is provided by changing it. 3. A high level signal is output from the output of the first preamplifier and the output of the target signal detection circuit when a target is not detected and interference is occurring, and a low level signal is output otherwise. When the output of the HOJ determination circuit and the output of the HOJ determination circuit is a high level signal, the output of the angle detector is unchanged, and when the output of the HOJ determination circuit is a low level signal, the output of the first correction unit is passed to the beam directivity angle control unit and output. When the output of the first SW and the HOJ determination circuit is a high level signal, the output of the angle detector is unchanged, and when the output of the first level and the HOJ determination circuit is a low level signal, the output of the second correction unit is passed to the autopilot and output as a second SW. The guidance aircraft according to claim 2, further comprising: 4. A beam narrowing signal generation unit which outputs a predetermined beam narrowing signal when the output of the S / N determination unit is a low level signal and outputs a beam narrowing zero signal when the output is a high level signal. And a third correction unit for controlling the effective dither range of the output of the angle detector by the output of the beam narrowing signal generation unit and outputting the controlled signal to the beam pointing angle control unit, and the beam narrowing band. A fourth correction unit that outputs the target direction angle signal to the autopilot in synchronization with the effective dither of the output of the angle detector by the output of the beam narrowing signal generation unit and the beam narrowing band output of the beam narrowing signal generation unit Narrowing signal generation for subtracting the output of the second preamplifier from the output of the first preamplifier in synchronization with the signal And a section. Guided flying vehicle. 5. The S / N determination section is set to S of the output of the S / N detection section.
S / N-compliant narrowing amount control signal generator that outputs a variable narrowing control signal that is proportional to / N, and replaces the beam narrowing signal generator with the S / N-compliant narrowing amount control signal generator 5. The guided flying object according to claim 4, further comprising a variable beam narrowing signal generating section for outputting a beam narrowing signal proportional to the variable narrowing control signal of the output of FIG. 6. A high level signal is output from the output of the first preamplifier and the output of the target signal detection circuit when a target is not detected and is being interfered with, and otherwise a low level signal is output. When the output of the HOJ determination circuit and the output of the JOJ determination circuit are high level signals, the output of the angle detector is unchanged, and when it is a low level signal, the output of the third correction unit is passed to the beam directivity angle control unit and output. When the output of the third SW and the HOJ determination circuit is a high level signal, the output of the angle detector is unchanged, and when the output of the fourth level is a low level signal, the output of the fourth correction unit is passed to the autopilot and output. When the output of the HOJ determination circuit is high level, the output of the first preamplifier is used, and when the output of the HOJ determination circuit is low level, the output of the narrowing band signal generator is used as it is. Fifth S that is output to the vessel The guidance aircraft according to claim 5, further comprising W.