JP3442624B2 - Guided flying object equipped with proximity target detection device - Google Patents

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION The present invention, Fei Shokarada body mounted adjacent target detection equipment for detecting that close to the target in the tracking activates the fuze by a detection signal of the target adjacent For example, It relates to the improvement of the guided flight that explodes the mounted warhead.

[0002]

2. Description of the Related Art In general, a conventional guided vehicle system such as a missile is composed of a projectile body 2 which flies toward a target 1 as shown in FIG.

The flying body 2 has a propulsion unit 2a for flying the flying body 1 toward a target 1, a transmitting / receiving antenna 2b for transmitting / receiving pulse radar waves, and the transmitting / receiving antenna 2
a guide portion 2c having a steering device and connected to b, and a target 1
The proximity fuze 2d that captures the approach of the above and generates an initiation signal, the warhead 2e activated by the initiation signal, and the like are mounted.

Therefore, the transmitting / receiving antenna 2 of the flying body 2
b transmits the radio wave transmitted from the guiding unit 2c to the target 1 and receives the reflected radio wave from the target 1, and the received signal is supplied to the guiding unit 2c.

After the flying body 2 starts to fly toward the target 1 by the thrust of the propulsion unit 2a, the guiding unit 2c introduces the received signal at the transmitting / receiving antenna 2b, and the target 1 is received based on the received signal. It is configured to detect a position, generate a guidance signal to fly toward a meeting point with the target 1 while tracking the target 1, and control the supply to the steering device of the guidance unit 2c.

When the projectile body 2 approaches the target 1 by the thrust of the propulsion unit 2a and the operation of the steering device of the guiding unit 2c, an initiation signal is generated from the detection signal of the target 1 by the beam formed by the close fuze 2d. Generate and signal the detonation 2
It was configured to feed e and explode the warhead 2e.

A light wave or a radio wave is used to form the target detection beam in the proximity fuze 2d.
d detects the reflected Doppler signal from the approaching target 1 by the light wave beam or the radio wave beam and generates the detonation signal, but from the discrimination of the detection level, the optimum timing for the effective explosion is sought.

[0008]

As described above, in the conventional guided vehicle system such as a missile, the flying body has a transmission / reception system in the guiding section for tracking the target, and in addition to this, the proximity target detection. Since the two transmission / reception systems for the close fuze and the transmission / reception system are separately provided, the configuration becomes large, which is a factor that hinders reduction in size and weight.

In particular, in recent years, there has been a demand for simplification of the configuration in order to further reduce the size and weight in order to improve the tracking function and to operate the system and improve the efficiency of equipment.

[0010] Therefore the present invention has been made in view of the above circumstances, aims with a simple structure, yet provide an induction projectile equipped with a proximity target detection equipment capable of realizing a more compact lightweight And

[0011]

A guided vehicle equipped with a proximity target detection device according to the present invention is mounted on a body of a flying object and emits a pulse radar wave transmitted from a transmitter to a space.
As well as a receiving antenna for receiving a reflected wave from the target, whether the target received by the transmitting and receiving antenna
Based on the reflected radio waves from
It is received by the guiding means for tracking and the transmitting / receiving antenna.
Based on the reflected radio waves from the target, it detects that the flying body is approaching the target and
Based on the transmitting / receiving antenna, a conical antenna pattern
Radiating pulse radar waves into the space
Proximity to generate and receive detonation signal based on reflected signal from target
The target detection means and the origin generated by this proximity target detection means
And a warhead that explodes based on an explosion signal.

[0012]

[0013]

As described above, in the guided flying object of the present invention, the flying object main body is provided with the transmission / reception antenna, and the target is tracked based on the target reflected radio wave received by the transmission / reception antenna and is also supplied to the warhead. Since it also generates signals, most of the transmission / reception signal processing system connected to it and the transmission / reception antenna peculiar to the proximity fuze, which was required in the past, can be used in common, simplifying the system configuration and downsizing the guided projectile. It became feasible.

[0015]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, an embodiment of the induction flying object provided with a proximity target detection equipment according to the present invention with reference to FIGS. 1 to 4 will be described in detail. The same components as those of the conventional guided vehicle shown in FIG. 5 are designated by the same reference numerals, and detailed description thereof will be omitted.

That is, FIG. 1 is a block diagram showing an embodiment of a guided projectile equipped with the proximity target detection device according to the present invention. As in the conventional case, the projectile body 2 is driven by the thrust of the propulsion unit 2a in the target direction. When the flight toward the
The radio wave transmitted by the pulse radar wave from is emitted toward the target 1 via the transmission / reception antenna 22.

FIG. 2 shows the guiding portion 21 and the transmitting / receiving antenna 2
2 shows the detailed circuit of FIG.
11, signal processor 212 for transmission and reception, exciter 2 for transmission
13 and the steering device 214 and the like, and the guide unit 21 has a transmission / reception function.

On the other hand, the transmitting / receiving antenna 22 comprises an antenna element group 221, an active circuit 222 and a distributor / comparator 223. The antenna element group 221 is composed of a plurality of antenna elements arranged in a plane array and the active circuit. 222
Is composed of a plurality of transmission / reception modules each of which is connected to each antenna element and has a built-in phase shifter, and the active circuit 222 includes a distributor / comparator 223 and an induction unit 2
1 is connected to the receiver 211 and the exciter 213.

Therefore, the transmission / reception antenna 22 is an active phased array antenna capable of electronic scanning by forming an arbitrary antenna pattern by controlling the phase shifter of the transmission / reception module and transmission / reception control, and the transmission signal from the exciter 213 is shown in FIG. As shown in FIG. 1, while transmitting toward the target 1 and receiving the reflected radio wave from the target 1, the receiver 2
Supply to 11.

Therefore, the receiver 211 of the guiding unit 21 receives the reflected reception signal from the target 1 and receives the first switching unit 2
It is configured to be supplied to the signal processor 212 via 15 and switched to the induction signal processing circuit 212a of the signal processor 212 when tracking the target 1 and to the proximity fuze circuit 212b when the proximity fuze is activated. .

Therefore, when the flying body 2 catches the target and performs tracking by the thrust of the propulsion unit 2a, the guidance signal processing circuit 212a generates a guidance mode excitation control signal and a guidance mode transmission / reception / phase control signal. The induction mode excitation control signal is supplied to the exciter 213 via the second switch 216. Upon receiving this, the excitation unit 213 generates a transmission pulse radar signal with a constant repetition period for target search and tracking, and supplies it to the distribution / comparator 223 of the transmission / reception antenna 22.

The distribution / comparator 223 is a transmission / reception antenna 22.
In the opening of the above, the transmission power is distributed so as to form a single beam pattern for target search and tracking as shown in FIG. 3, and is supplied to each corresponding transmission / reception module of the active circuit 222.

The induction mode transmission / reception / phase control signal generated by the induction signal processing circuit 212a is supplied to the third switching unit 2.
17 is supplied to the active circuit 222 of the transmission / reception antenna 22 to control the transmission / reception switcher and the phase shifter in each transmission / reception module, and to search and form the antenna element group 221.
A single beam for tracking scans the space containing Target 1 and captures Target 1 position.

Therefore, when the target 1 is tracked, the transmission repeating pulse signal reflected by the target 1 is amplified and frequency-converted by the receiver 211 of the signal processor 21 via the transmission / reception antenna 22, and then the first switching device. It is supplied to the induction signal processing circuit 212a via 215. Here, similarly to the conventional case, a guidance signal is generated from the information such as the azimuth and distance of the target 1 obtained from the target reflection signal and is supplied to the steering device 214.
The flying body 2 is guided and fly toward a meeting point with the target 1.

In tracking the target 1 by the transmitting / receiving antenna 22, a so-called amplitude monopulse system for detecting an angular error using two partially overlapping antenna patterns is used to obtain target 1 direction and distance information. Is also good.

On the other hand, when the proximity fuze is activated, the proximity fuze circuit 212b generates a proximity mode excitation control signal and a proximity mode transmission / reception / phase control signal, and the proximity mode excitation control signal is passed through the second switching circuit 216 to the exciter. 213
The exciter 213, which is supplied to the receiver, generates a proximity mode transmission pulse radar signal and supplies it to the distribution / comparator 223 of the transmission / reception antenna 22. In addition, the proximity fuze circuit 2
The proximity mode transmission / reception / phase control signal generated in 12b is supplied to the active circuit 222 of the transmission / reception antenna 22 via the third switch 217, and is configured to control transmission / reception.

At this time, the proximity mode transmission / reception / phase control signal controls the phase shifter of the active element 222 and, as shown in FIG. 4, causes the pencil beam antenna pattern 22a to move in the machine axis Z direction of the projectile body. The scanning is performed so that the rotation axis is conical. Although the tilt angle with respect to the machine axis Z direction is shown to be approximately 45 degrees in FIG. 4, it can be variably controlled to any angle so as to be optimum.

Therefore, the transmission pulse radar signal from the exciter 213 during the proximity fuze operation is subjected to transmission / reception control and transmission beam control by the proximity mode transmission / reception / phase control signal from the proximity fuze circuit 212b, and the pattern shown in FIG. The reflected pulse radar signal radiated toward the target 1 and approaching the target 1 passes through the receiver 211 and the first switch 215 similarly to the target reflected signal by the target detection beam in the conventional proximity fuze. , Is supplied to the proximity fuze circuit 212b, where an initiation signal is generated and supplied to the warhead 2e.

Therefore, in this embodiment, the transmitting / receiving antenna 22 at the time of transmission, the signal processor 212 for generating the induction / proximity mode excitation control signal and the induction / excitation mode transmission phase control signal, and the exciter 213 form a transmitter. A transmission / reception antenna 22, a receiver 211, and a signal processor 2 configured to receive a reception signal from the receiver 211.
A receiver is constituted by 12.

Regarding the operation of switching from the guidance mode to the proximity mode, generally, in order to scan the space 1 by the pulse radar and capture the distant target 1, the transmission pulse power corresponding to the detection distance to the target is required. Therefore, a considerable pulse time width and peak voltage are required.
While the transmission pulse is being output due to the transmission / reception switching, the reception circuits after the active circuit 222 are cut off. However, when the flying body 2 gradually approaches the target 1 and the distance to the target 1 becomes short, the target 1 becomes short. The reflected pulse signal of is within the time width of the transmission pulse, and the reflected signal from the target cannot be obtained.

Therefore, the receiver 211 detects that the target reflected pulse signal from the transmission / reception antenna 22 is no longer input, generates a switching signal, and operates the first to third switching devices 215 to 217. To switch from the induction mode to the proximity mode and replace the induction signal processing circuit 212a with the output signal from the proximity fuze circuit 212b, that is, the proximity mode excitation control signal, to the exciter 213, and the proximity mode transmission / reception / phase. Control signals are provided to active circuit 222. It should be noted that the switching signal of the receiver 211 is output by deciding that the reception of the repeated radar pulse signal of the target reflection signal is interrupted, and is output, for example, a combination circuit of a pulse shaping circuit and a CR time constant circuit Can be realized by

In this way, the switching operation from the guidance mode to the proximity mode is performed, and the exciter 213 spatially transmits the pulse radar signal from the exciter 213 under the conical beam scanning as described above. Radiate to.

Further, instead of scanning the pulse radar signal into a conical beam, a conical beam may be formed and radiated into space.

Further, in the control of the active circuit 222 of the proximity mode transmission / reception / phase control signal, the antenna element group 221 arranged in a plane array is divided into a central portion and an outer peripheral portion thereof, and a plurality of antennas in the central portion are divided. The elements may be switched and controlled so that the CW radar signal is transmitted and a plurality of antenna elements arranged in a donut shape outside thereof are used for reception. In that case, the transmitting antenna in the central portion forms a wide beam to continuously transmit the pulse radar signal toward the target 1 direction, and the receiving antenna on the outer side is a single beam (pencil as shown in FIG. 4). (Beam pattern) 22a may be formed so as to perform high-speed conical scanning within the spatial region formed by a wide beam for transmission.

That is, in the proximity target detection, a sharp beam is formed and scanned by a plurality of antenna elements arranged on the outside of the antenna element group 221 in a plane array, and a pulse is generated by the plurality of antenna elements in the central portion. , CW or F
The reflected radio wave from the target 1 of the M-CW transmission radio wave may be received at the repeated scanning timing.

In the proximity fuze, the timing of the detonation signal supplied to the warhead 2e is important, but in this embodiment, the scanning direction of the antenna pattern is variably controlled with respect to the machine axis direction to perform the proximity processing. it can. Therefore, based on the relative distance and relative velocity to the target 1 observed by the guidance signal processing circuit 212a, the axial direction antenna pattern scanning direction that can obtain the optimum warhead detonation timing is calculated in advance to form the antenna pattern. When the reflected signal from the target is received, a detonation signal that triggers is generated and output to the warhead 2e, so that the warhead 2e can effectively explode the warhead in response to the detonation signal.

The transmission beam by the transmission pulse radar wave or the like corresponds to the beam for the conventional close fuze and only catches the target 1 which is already close and has a short distance. The transmission power may be relatively small.

As described above, in this embodiment, the transmitting / receiving antenna 22 mounted on the flying body 2 for transmitting and receiving the radio wave for following the target 1, and the radio wave is supplied to the transmit / receive antenna 22. , A guide signal is generated based on the target reflected radio wave received by the transmission / reception antenna 22 to cause the flying body 2 to follow the target 4, and the flying body 2 targets the target 1 based on the target reflected radio received by the transmitting / receiving antenna 22. And a switching unit 215 to 21 in the guiding unit 21.
According to the configuration of FIG. 6, since the transmitting / receiving antenna 22 and the guiding portion 21 are used both for guiding and for operating the proximity fuze, the number of components can be reduced and the manufacturing including design can be simplified.

Further, according to the above structure, the transmitting and receiving antennas are used both for guiding and for operating the close fuze, so that the structure can be simplified, and a small and lightweight guided flying object can be realized. It is possible to realize a guided flight object that has been controlled.

[0040]

As described above, according to the present invention, induction projectile equipped with a proximity target detection equipment according to the invention, induce projectile itself and a proximity fuse function and target tracking flight, and receiving antenna and induction Since the main structure of the department was shared,
We were able to realize the simplification of the configuration and the reduction in size and weight.

[Brief description of drawings]

FIG. 1 is a configuration diagram showing an embodiment of a guided vehicle according to the present invention.

FIG. 2 is a circuit diagram showing a detailed configuration of a transmission / reception antenna and a guiding unit of the guided vehicle shown in FIG.

FIG. 3 is an antenna pattern diagram of the guided flying object shown in FIG. 1 during target tracking.

FIG. 4 is an antenna pattern diagram when the proximity target of the guided flying object shown in FIG. 1 is detected.

FIG. 5 is a system configuration diagram showing a configuration of a conventional guided vehicle.

[Explanation of symbols]

1 goal 2 Flying body 21 Guidance 211 receiver 212 signal processor 212a Induction signal processing circuit 212b Proximity signal processing circuit 213 Exciter 214 Steering device 215, 216, 217 Switching device 22 Transmit / receive antenna 221 Antenna element group 222 Active circuit 223 Distribution / Comparator 2e bullet head

Continuation of the front page (56) Reference JP-A-7-79116 (JP, A) JP-A-4-62399 (JP, A) JP-A-3-221799 (JP, A) JP-A-4-340100 (JP , A) JP-A-2-166398 (JP, A) JP-A-2-103400 (JP, A) (58) Fields investigated (Int.Cl. ⁷ , DB name) G01S ⁷ /00-7/42 G01S 13/00-13/95 F24C 13/04 H01Q 3/26

Claims (3)

(57) [Claims] 1. A transmission mounted on a main body of a flying body and transmitted from a transmitting unit.
While emitting a pulse radar waves in the space, a transmitting and receiving antenna for receiving a reflected wave from the <br/> target, the reflected wave from the target received by the transmitting and receiving antenna
Based on the guidance, the main body of the flying object is tracked toward the target.
Means and detecting that the flying body main body approaches the target based on the reflected radio waves from the target received by the transmitting and receiving antennas.
In addition, based on this detection signal,
Switch the conical antenna pattern on the antenna
Radial radar waves are radiated into space, and the reflected signal from the target is used as the basis.
A proximity target detector for generating receiving a detonation signal, based on the detonation signal generated by the proximity target detection means
A guided projectile equipped with a proximity target detection device , characterized in that it has an explosive warhead . 2. A guided air vehicle equipped with the proximity target detecting device according to claim 1 , wherein the transmitting / receiving antenna is a phased array antenna. Wherein the transmitting and receiving antennas, proximity according to the scanning direction of the antenna pattern to be scanned in the conical, with respect to axis direction of the flying body, to claim 1 or claim 2, characterized in that variably controlled Equipped with a target detection device
Guided flight .