JPH046399A - Guided missile - Google Patents

Abstract

PURPOSE:To concentrate the fragments of a warhead to an objective body correctly with the optimum timing without inviting any malfunction even during low-altitude flight by a method wherein igniting operation is commanded based on an information on a decided existing quadrant and another information on a relative speed between the obtactive body, which is outputted from a target guiding device, while a steering device is controlled based on the other information with respect to a distance between the surface of a terrain. CONSTITUTION:The existing quadrant of an objective body is decided by the retaining condition of a binnary signal output. An initiating timing generator 14 controls an existing quadrant signal from a quadrant deciding device 13 so that the fragments of a warhead are collided against the objective body surely based on a trigger pulse signal SL at a moment, whereat the target is rendezvoused with projecting beams from a target detecting device 11 employing a relative speed signal SV from a target guiding device 20. Whereby the igniting timing signal of an objective body existing direction is transmitted to a warhead. Reflected waves from the surfaces of sea and terrain are suppressed by clatter suppressing signal CS based on the clatter gate signal CLG of a radiowave target detector 11 whereby the objective body at a low altitude can be detected.

Description

[Detailed Description of the Invention] [Field of Industrial Application] The present invention relates to a guided flying object, and more particularly, a proximity fuze device that commands the ignition operation of a warhead ammunition when approaching a target object, and a The present invention relates to a guided flying object equipped with a target guidance device that controls capturing and tracking of an object, and a steering device that controls flight.

[Prior art and problems to be solved by the invention]

Conventionally, this type of proximity fuze device for flying objects uses a receiver to receive reflected waves from a target object that has entered a radio wave projection beam, demodulates and detects the reflected wave signal, and calculates the relative velocity difference with the target object. The ignition signal is sent by detecting the corresponding Doppler frequency component. An example of this technology is
For example, it is disclosed in Japanese Utility Model Publication No. 62-3741.

In this method, since the transmission output is a single frequency, it is easy to detect that the other party is emitting radio waves, and it is also susceptible to interference waves. The drawback is that it cannot be detected accurately.

Additionally, when flying at low altitudes, the target object cannot be accurately identified due to reflected waves from the ground surface (sea surface or ground surface), which may cause malfunctions or cause the receiving system to reach a "saturated" state. There is also the problem.

In view of these circumstances, a technique has been proposed in which a radio altimeter is provided to reduce the influence of reflected waves from the ground surface, thereby improving the accuracy of target object identification. However, this technique has the disadvantage that the device is relatively complex in construction and large in shape and size. An example of this technology is, for example, Japanese Patent Application Laid-Open No. 59-1502
It is disclosed in Publication No. 99.

Another known technique is to pulse-modulate the transmitted output to multiple frequencies, while limiting the received signal using a bandpass filter and gate circuit, and detecting only the received signal of the reflected wave from a nearby distance. and the ground surface at a distance farther than that (
There is a method in which reflected waves from the sea surface or ground surface are removed on the time axis and frequency axis. An example of this technique is disclosed in, for example, Japanese Unexamined Patent Publication No. 63-247600.

However, according to this method, the circuit constants are limited and fixed by the bandpass filter and gate circuit, so when a reflected wave from the ground surface is received within a set distance, each of the bandpass filter and gate circuit It is difficult to identify the target object because the circuit constant cannot be changed depending on the distance, and it also depends on the effective detection distance of the proximity fuze device.
The disadvantage is that the range in which the influence of reflected waves from the sea surface or ground surface can be removed is limited.

The present invention was created in view of the problems in the prior art, and is capable of accurately detecting the direction of the target object without causing malfunctions even when flying at low altitudes, and in turn, allows the warhead to strike the target object at the optimal timing. It is an object of the present invention to provide a guided flying object that can accurately concentrate the particles and improve the function of low-altitude guidance.

[Means for Solving the Problems] In order to solve the above problems, the present invention provides a proximity fuze device that commands the ignition operation of the ammunition of a warhead when approaching a target object, and a proximity fuze device that commands the operation of igniting the ammunition of a warhead when approaching a target object, and In a guided flying object equipped with a target guidance device to control and a steering device to control flight, the proximity fuze device is arranged in each quadrant of at least four quadrants divided in a circumferential direction around an axis of the flying object. A radio wave beam is projected in a cone shape at a predetermined set angle in the forward direction of the flying object, and a reflected wave from the target object with respect to the projected beam is detected to generate a detection signal in each quadrant according to the signal strength. a radio wave target detector that outputs; a circuit that compares the output detection signals with respective adjacent quadrant signal levels to determine the quadrant in which the target object exists;
a circuit that outputs information regarding the distance to the ground surface using control information based on reflected waves from the ground surface and information regarding the attitude angle of the flying object output from the target guidance device; The ignition operation is commanded based on information on the existence quadrant of the target object and information on the relative speed of the target object outputted from the target guidance device, and the steering device is controlled based on information on the distance between the target object and the ground surface. There is provided a guided flying object characterized by the following.

[Operation] According to the above-described configuration, the reflected wave from the target object is detected with respect to the projected beam from the radio wave target detector, the presence quadrant is determined, and the information regarding the relative speed with the target object outputted from the target guidance device. Based on this, a detection signal indicating the entry quadrant of a target object passing near the flying object is output. Therefore, even when flying at low altitude, the direction of the target object can be accurately detected without causing malfunction, and in turn, it is possible to accurately concentrate the fragments of the warhead on the target object at the optimal timing.

Additionally, when flying at low altitude, the steering system is controlled based on information regarding the distance to the ground surface.
It is possible to fly at low altitudes depending on the ground surface conditions. this is,
This contributes to improving the functionality of low-altitude guidance.

Note that other structural features and details of the operation of the present invention will be explained using the embodiments described below with reference to the accompanying drawings.

〔Example〕

FIG. 1 shows the configuration of a proximity fuze device mounted on a guided flying object as an embodiment of the present invention.

The proximity fuse device 10 in this embodiment is mounted on a flying object equipped with a warhead, together with a target guidance device (for example, a homing device) 20 that controls capture and tracking of a target object and a steering device 30 that controls flight. Proximity fuze device 10
The system is equipped with a radio wave target detector 11, an altitude signal converter 16, and a crane controller 15 as its main components, and uses a relative velocity signal SV from a target guidance device 20 to detect an incoming target object. On the other hand, it has the function of accurately concentrating and solidifying the bullet fragments of the warhead at the optimal timing.

In addition, the proximity fuse device 10 suppresses reflected waves from the ground surface (sea surface or ground surface), and the attitude of the flying object output from the target guidance device 20 when flying at a low altitude as shown in FIG. It has a function of outputting information regarding the distance to the ground surface (altitude signal SH and ground surface state signal SS) to the steering device 30 using angle information (attitude angle signal SA).

Note that the radio wave target detector 11 used here detects the direction of existence of a target object intruding into one of at least four quadrants divided in the circumferential direction around the axis of the flying object. It is possible. Here, an example of a device divided into four quadrants will be explained. In addition, the reference symbols ASI and AS shown in relation to the radio target detector 11 are
2, ARI, and AR2 indicate a transmitting antenna and a receiving antenna, respectively.

The radio target detector 11 detects a reflected beam from a target object that has entered the projected beam, compares the level of a detection signal corresponding to the detected beam with a predetermined threshold level, and performs quadrant detection based on the comparison. The beam signals (radio wave detection signals E1 to E4) are sent to the signal comparator 12 as voltage values. Further, the target detector 11 sends a momentary detection signal when the target object is detected to the quadrant determiner 13 and the detonation timing generator 14 as a trigger pulse SL. Regarding this technology, for example, the patent application filed by the applicant in 1983-
It is disclosed in the specification of No. 176484.

The signal comparator 12, as shown by way of example in FIG. 3, is constituted by a commonly used comparator circuit and compares the output signal levels of adjacent quadrant detection beams.

For example, when comparing the signal levels of beam 1 and beam 4, if the DC voltage of beam 4 (or beam 1) is higher, the output of comparator 2 is “0” (
or “1”) is sent to the quadrant determiner 13. Similarly, beams 2 and 3 are compared by comparator 1, beams 4 and 3 by comparator 3, and beams 1 and 2 by comparator 4, and each binary signal output is sent to quadrant determiner 13. Sent.

The quadrant determiner 13 receives the output trigger pulse of the target object reflection signal from the correlation filter module (not shown) in the radio wave target detector 11 as a latch signal SL.

This latch signal is generated as a trigger pulse by the detection signal at the moment when a target object is detected by any of the quadrant detection beams E1 to ε4, and is input to the quadrant determiner 13 and output to the signal comparator 12. It is used to hold the binary signal output from each comparator.

As shown in FIG. 4, the quadrant in which the target object exists is determined based on the state in which the binary signal output is held. For example, if the target object exists in quadrant ■, the outputs of comparators 1 and 2 will be “0”.
”, the outputs of comparators 3 and 4 become “1”, and this state is determined to be in the existence quadrant ■, and the detonation timing generator 14
Send to.

FIG. 5 shows the relationship between the comparator output and the existence quadrant for each quadrant.

The detonation timing generator 14 uses the relative velocity signal SV from the target guidance device 20 based on the trigger pulse signal SL at the moment of meeting the projection beam from the target detector 11, and determines the presence quadrant from the quadrant determiner 13. The signal is controlled to ensure that the bullet fragments of the warhead hit the target object, and an ignition timing signal in the direction of the target object is sent to the warhead.

The configuration of the clutter controller 15 includes, for example, a correlation filter in the radio wave target detector 11, as shown in FIG.
The clutter gate signal CLG from the module 21 is compared in a comparator circuit 22 of the clutter controller 15 with a threshold level vth, and if it is higher than the threshold level, the signal is sent to an integrator circuit 23;
It is integrated. The output of this integrating circuit 23 is sent to the altitude signal converter 1 as a clutter suppression signal voltage CS corresponding to the altitude.
6 and is sent to the voltage controlled oscillator 24 in the radio wave target detector 11.

The voltage controlled oscillator 24 of the radio target detector 11 controls the clock speed of a pseudo-random code generator (not shown) to change the detection distance corresponding to the altitude of the flying object from the sea surface or the ground surface at low altitude. Also, the altitude signal converter 16 calculates the distance (altitude) between the flying object and the sea surface or the ground surface.

The crack gate signal CLG from the above-mentioned correlation filter module 21 is designed so that a correlation output can be obtained at the farthest distance from the flying object. In other words, the flying object is flying at a low altitude and the reflected wave from the ground surface (sea surface or ground surface) is within the effective detection range (i.e., the voltage controlled oscillator 2
The above-mentioned correlation output is generated when the correlation output is obtained within the round trip distance of radio waves corresponding to the control range of 4).

The voltage controlled oscillator 24 in the radio wave target detector 11 controls the oscillation frequency fL with respect to the input voltage according to the relationship shown in FIG. 7, for example.

When the projectile is flying at a sufficiently high altitude, the output voltage of the correlation filter module 21 is small and the integrator circuit 23
Since the output of is 0■, the voltage controlled oscillator generates a signal at a frequency fL corresponding to the output.

However, when a flying object flies at a low altitude and an output is generated in the correlation filter module 21, and the output level exceeds the threshold level vth of the comparator circuit 22, the difference voltage between the two is output from the comparator circuit. Become so. After this output voltage is integrated by the integrating circuit 23,
The signal is input to the voltage controlled oscillator 24 in the radio wave target detector 11. At this time, the output oscillation frequency fL of the voltage controlled oscillator 24
, gradually increases (decreases) as the input voltage increases (decreases), as shown in FIG.

Since the pseudo-random code generator (not shown) is driven by the voltage-controlled oscillator 24, as the frequency fL increases, the clock speed of the pseudo-random code generator increases, and the period of one bit shortens. The round trip distance of the radio waves will also be shorter. Therefore, voltage controlled oscillator 2
4. The pseudo-random code generator, the correlation filter module 21, and the clutter controller 15 create a loop that tracks reflected waves from the sea surface or the ground surface, and the tracking distance is automatically adjusted according to the flight altitude of the projectile. It will change to In other words, the output signal of the clutter controller 15 (
The clutter suppression signal CS) will include information regarding distance. This tracking loop uses a downward projection beam to track the flying object.

Note that the clutter suppression signal C5 used here is generated by the clutter controller 15, but this is a method that can separate the reflected waves from the ground surface (sea surface or ground surface) and the reflected waves from the target object. If there is a target detector that can change the detection effective distance, its output signal may be used instead.

The altitude signal converter 16 calculates the altitude to the sea surface or the ground surface based on the clutter suppression signal CS from the clutter controller 15 and the attitude angle signal SA of the flying object output from the target guidance device 20.

As shown in FIG. 8, the clutter suppression signal CS from the clutter controller 15 is a received signal projected in front of the flying object and reflected from the sea surface or the ground surface, and as described above, the clutter suppression signal CS is a reflection of the projected beam. Indicates the distance to a point. Therefore, the distance signal C3 (corresponding to distance R in Fig. 8)
and the attitude angle signal SA (corresponding to angles φ and θ in the figure) of the flying object and the ground surface (sea surface or ground surface).
The distance (altitude) can be determined and sent to the steering device 30 as an altitude signal SH. In the illustrated example, the altitude H is expressed by the following formula.

In addition, the altitude signal converter 16 calculates the condition of the ground surface (for example, the wave height of the sea surface) based on the deviation of the calculated altitude signal SH, and calculates the condition of the ground surface at the time of flight (in this case, It can also be sent to the steering device 30 as a signal SS indicating the state of sea surface).

According to the guided flying object of this embodiment configured as described above, the following advantages can be obtained.

(1) Detection of the intrusion quadrant of a target object passing near the flying object based on information regarding the relative speed between the projection beam of the radio wave target detector 11 and the target object output from the target guidance device 20 (relative speed signal SV) The signal is sent accurately and the detonation timing signal is adjusted and sent to the warhead so that the bullet fragments of the warhead are concentrated and solidified on the target object at the optimal timing. Therefore, there is an improvement effect of maximizing the power of the warhead and improving the shooting down ability.

(2) The radio wave target detector 11 performs direct spread coding modulation on the transmission wave, and the transmission power density per unit frequency band is suppressed to a low level. Therefore, it is difficult to be detected by the other party, and even if there is interference, the correlation is taken inside the target detector, so it will not be affected by interference from the other party who does not know this modulation code (pseudo-random code). There is an advantage.

In addition, by using a millimeter wave target detector, it is possible to utilize the propagation loss characteristics due to resonance absorption inherent in millimeter waves, and it is also possible to make it less susceptible to detection or interference from the other side. .

(3) The target detection effective range of the radio wave target detector 11, that is, the round trip distance of the radio waves, can be set by the oscillation frequency of the transmission modulation code, and the detection range of the target object can be matched with the effective range of the warhead. Furthermore, it becomes possible to accurately determine in which direction the target object exists when viewed from the flying object (quadrant determination).

(4) The clutter suppression signal CS based on the clutter gate signal CLG of the II-wave target detector 11 suppresses reflected waves from the sea surface and the ground surface, making it possible to detect a target object at a low altitude.

(5) By sending altitude information (altitude signal 5) l) during low-altitude flight to the steering device 30 based on the clutter suppression signal CS and information regarding the attitude angle of the flying object (attitude angle signal SA), This makes it possible to fly at extremely low altitudes depending on the ground surface conditions (in this example, the sea surface conditions), without the need for other equipment such as a radio altimeter, making it difficult to be detected by the other side. There are advantages.

This advantage is extremely useful, especially considering that in recent years there has been a strong demand for devices that can fly as low as possible in order to avoid detection by anti-ship missiles and the like.

Furthermore, if the radio altimeter is no longer required, the carrying capacity of the flying object will be reduced by that amount, so that the thrust of the flying object can be increased isometrically.

〔Effect of the invention〕

As explained above, according to the present invention, the intrusion quadrant of the target object is determined based on the action of the radio wave target detector and the relative speed information from the target guidance device, so even when flying at low altitude, the target object can be detected without causing malfunction. It is possible to accurately detect the direction of existence of an object, and in turn, it is possible to accurately concentrate the bullet fragments of the warhead on the target object at the optimal timing.

Furthermore, since the steering device is controlled based on the altitude information of the flying object during low-altitude flight, it is possible to fly at a low altitude according to the ground surface condition, thereby improving the function of low-altitude guidance.

[Brief explanation of drawings]

Figure 1 is a block diagram showing the configuration of a proximity fuze device mounted on a guided flying object as an embodiment of the present invention, Figure 2 is a diagram showing the state during low altitude flight, and Figure 3 is the same as Figure 1. 4 is an output signal waveform diagram of the signal comparator in FIG. 3; FIG. 5 is a diagram showing the relationship between the quadrant in which the target object exists and each comparator output; Figure 6 is a circuit diagram showing an example of the configuration of the clutter controller in Figure 1, Figure 7 is a graph explaining some of the functions of the radio target detector, and Figure 8 is the action of the altitude signal converter. This is a diagram for explaining. (Explanation of symbols) 10... Proximity fuze device, 11... Radio target detector,
12... Signal comparator, 13... Quadrant determiner, 14.
... Detonation timing generator, 15 ... Clutter controller, 16 ... Altitude signal converter, 20 ... Target guidance device, 30 ... Steering device, E1 to E4 ... Radio wave detection signal, SA ...Attitude angle signal, SV..., relative velocity signal, S
H...Altitude signal, SS...Ground surface condition signal, CS/
...Clutter suppression signal, CLG...Clutter gate signal, SL...Latch signal. - Yoooo \ \ \ \ \ Diagram showing the situation during low altitude flight Figure EB Radio wave projection beam Figure 3 Output signal waveform diagram of the signal comparator Figure 4 Relationship between the target object's existence quadrant and each comparator output Figure 5 is a circuit diagram showing an example of the configuration of the signal comparator in Figure 1.
Figure 8 Diagram for explaining the action of the altitude signal converter

Claims (1)

[Claims] 1. A proximity fuze device (10) that commands the ignition operation of the ammunition of a warhead when approaching a target object, a target guidance device (20) that controls capture and tracking of the target object, and a flight In a guided flying vehicle equipped with a steering device (30) that controls the flying object, the proximity fuze device is arranged in front of the flying object in each of at least four quadrants divided in the circumferential direction around the aircraft axis. A radio wave beam is projected in a cone shape toward the direction at a predetermined set angle, and a reflected wave from the target object with respect to the projected beam is detected, and a detection signal (E1 to E4) corresponding to the signal strength is generated for each quadrant.
a radio wave target detector (11) that outputs a signal, and a circuit that compares the output detection signal with the signal level of each adjacent quadrant to determine the quadrant in which the target object exists (
12, 13), and information about the distance to the ground surface using control information (CS) based on reflected waves from the ground surface and information (SA) about the attitude angle of the flying object output from the target guidance device. (S
a circuit (16) that outputs a signal (H, SS), and performs the ignition operation based on information on the determined existence quadrant and information (SV) on the relative speed of the target object output from the target guidance device. A guided flying object, characterized in that the steering device is controlled based on information regarding the distance between the guided flying object and the ground surface. 2. Using a clutter gate signal (CLG) output from the radio target detector, set a detection quadrant range to the radio target detector so as to cancel the influence caused by reflected waves from the ground surface caused by the radio beam. The guided flight according to claim 1, further comprising a clutter controller (15) for controlling the guided flight, wherein the control information (CS) based on the reflected waves from the ground surface is supplied from the clutter controller. body.