JP2000088499A - Guided projectile - Google Patents

Abstract

PROBLEM TO BE SOLVED: To avoid tracking of an interceptor missile under tracking by providing a collapsible/developable reflector on the side of a seaker for guided projectile and reflecting a radio wave outputted from a radio wave source such that a required reflection strength can be attained. SOLUTION: A collapsed reflector 16 is developed when a wire is wound around a motor 15 and reflects radio wave 8 from a radio wave source 7 thus increasing the intensity of radio wave being reflected from a projectile 1 when viewed from the front side. Receiving gain of an opponent tracking radar and an interceptor missile is varied in correspondence with increased current strength. Subsequently, a control circuit 14 reverse the motor 15 to rewind the wire thus collapsing the reflector 16. Strength of radio wave being reflected on the projectile 1 decreases and the receiving circuit in an opponent tracking radar and an interceptor missile misses the projectile 1 temporarily. Consequently, the projectile 1 can avoid attack from the interceptor missile.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention detects radio waves emitted from a radio wave source such as a surface-to-air missile tracking radar, which does not emit radio waves by itself, and flies toward this radio wave source. Regarding the guided flying object, more specifically, the radio wave output from the above radio wave source is reflected by the reflector provided by itself so as to have a required reflection intensity, and functions to avoid an attack from the radio wave source. It is characterized by the following.

[0002]

2. Description of the Related Art FIG. 7 is an overall view showing the relationship between a conventional guided flying object and a target. In FIG.
Is a fuselage of the flying object 1, 3 is a seeker provided inside the fuselage 2, 4 is a receiving circuit for receiving an electric signal from the seeker 3, 5 is a rear wing arranged in a circumferential direction and rearward of the fuselage 2, 6
Is a steering wing arranged on the rear wing 5 to guide the fuselage 2 in a predetermined direction, 7 is a target radio wave source, and 8 is a radio wave radiated from the radio wave source 7. Fig. 8 shows a conventional guided flying vehicle Seeker 3
8A is a view of the seeker as viewed from the front, FIG. 8B is a view of the seeker as viewed from the back, FIG. 8C is a cross-sectional view of a dotted line portion of the seeker, and 3 is the seeker. , 9a-9
d is an antenna, 10 is an insulator for directing the antenna only in the front direction, 11 is a substrate for feeding the antenna, and 12 is a hybrid for transmitting radio waves.

Next, the operation will be described. The seeker 3 receives the radio wave 8 from the radio wave source 7 with four antennas 9 a to 9 d and transmits the hybrid 12 to the substrate 11.
The substrate 11 transmits the signal to the Σ channel, ΔAZ channel, Δ
The signal is divided into three channels of the EL channel, and is sent to the receiving circuit 4 of each channel as an electric signal. The receiving circuit 4 lowers the frequency of the electric signal sent from the seeker 3 by the variable frequency oscillator and measures the receiving frequency of the sum channel. When the reception frequency is measured, the frequency of the variable frequency oscillator is fixed, thereby lowering the frequency of the electric signal sent from the seeker 3, and comparing the signal intensities of the Σ and ΔAZ channels and the Σ and ΔEL channels. . The compared intensities are sent from the receiving circuit 4 to the signal processing circuit, where the angle error between the direction of the radio wave source 7 and the body 2 is calculated. A wing control signal is obtained from the calculated angle error and sent to a servo controlling the steering wing 6, which operates and directs the fuselage 2 toward the radio wave source 7. At the same time, the fixed seeker 3 is also directed toward the radio wave source 7. In this way, the flying object 1 always flies toward the radio wave source 7 and finally reaches the radio wave source 7.

[0004]

As described above, the conventional radio equipment does not radiate radio waves, but detects radio waves radiated by a radio wave source such as a ground-to-air missile tracking radar, and detects the radio waves. There are the following problems in the guided flying object flying in the direction. 461 to 4 of "Missile Engineering Dictionary" published by Hara Shobo in 1990
As described on page 62, if the shooting range of the guided vehicle is 25 km and the speed is 700 m / sec, it takes 35 seconds for the guided vehicle to reach the target. On the other hand, the radio wave reflection area of the guided flying object is 0.03 m ² , the noise figure of the target tracking radar is 10 dB, the S / N required for tracking is 10 dB, and the bandwidth of the tracking radar receiver is 1 Mhz. Then, the tracking distance is 24 km.
In other words, if it is within 24 km, it may be found by the target tracking radar and fired an interceptor missile, and the interceptable time is as long as 35 seconds or less, so once it is tracked and fired with the interceptor missile, it can not take an evasion movement Guided flying vehicles are often intercepted.

SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems, and a radio wave output from a radio wave source is reflected by a reflector provided on a guided flying object to obtain a required reflection intensity. It is reflected so as to avoid tracking of the intercepting missile during tracking.

[0006]

According to a first aspect of the present invention, a seeker for a guided flying object is provided with a foldable and deployable reflector on a side surface of a conventional seeker for a guided flying object.

[0007] The seeker of the guided flying object according to the second invention is one in which a reflector that rotates periodically is provided on a side surface of the conventional seeker of the guided flying object.

[0010] The seeker of the guided flying object according to the third invention is such that the conventional seeker of the guided flying object is connected to the gimbal to be movable.

A guided flying object according to a fourth aspect of the present invention is obtained by providing a foldable and deployable reflector on the body of a conventional guided flying object.

A guided flying object according to a fifth aspect of the present invention is a conventional guided flying object in which a fuselage including a movable reflector is provided on the fuselage.

[0011]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiment 1 FIG. 1 is an overall view showing Embodiment 1 of the present invention. FIG. 1 is a diagram showing the entire first embodiment of the present invention. In FIG. 1, 1 is a flying object, 2 is a fuselage, 3 is a seeker, 4 is a receiving circuit, 5
Is a rear wing, 6 is a steering wing, 7 is a radio wave source, 8 is a radio wave, 13 is a gain detection circuit for detecting a change in gain of a received signal, 14 is a control circuit, 15 is a motor, and 16 is a reflector. FIGS. 2A and 2B show a seeker portion according to the first embodiment of the present invention. FIG. 2A is a view of the seeker viewed from the front, FIG. 2B is a view of the seeker viewed from the back, and FIG. Sectional view of (d)
Is a view of the seeker from an oblique side, 3 is a seeker, 9 is
a to 9d are antennas, 10 is an insulator for directing the antennas 9a to 9d only in the front direction, 11 is a board for feeding the antennas 9a to 9d, 12 is a hybrid for transmitting radio waves, 15a to 15d. 15d is a motor, 1
6a to 16d are reflectors for reflecting radio waves, 17 is reflector 1
An outer frame for protecting 6a to 16d, 18 is a reflector 16
It is a wire for folding and unfolding a to 16d.

Next, the operation will be described. Antenna 9a
The radio waves received at ９ 9 d pass through the hybrid 12, pass through the substrate 11, and are sent to the receiving circuit 4 as electric signals.
A gain electric signal is sent from the receiving circuit 4 to the gain detecting circuit 13, and the gain detecting circuit 13 measures a change in gain. Normally, the flying object 1 senses the side lobe of the radio wave 8 of the other party's radio source 7 and flies toward it, but the other party's radio source 7 is a tracking radar, and the flying body 1 is found by the tracking radar. Then, the main lobe of the radio wave 8 faces the flying object 1. Since the gain difference between the main lobe and the side lobe is usually close to 20 dB, the gain detection
When it changes by about dB, it is determined that the flying object 1 has been found and the interceptor missile has been fired, and a signal is sent from the gain detection circuit 13 to the control circuit 14. The control circuit 14 operates the motors 15 a to 15 d (the number is not limited to four for convenience), and winds the wire 18. Folded reflector 16a connected to wire 18
16d (here, four for convenience, but any number) is opened by winding the wire 18 around the motors 15a to 15d (here, four for convenience but any number), and from the radio wave source 7 And the intensity of the radio wave reflected by the flying object 1 as viewed from the front increases. FIG. 2D shows an example of the reflector 16d being developed. At this time, the receiving circuits of the opponent tracking radar and the interceptor missile change to a reception gain corresponding to the increased radio field intensity. Next, the control circuit 14 reverses the motors 15a to 15d, rewinds the wire 18, and folds the reflectors 16a to 16d. At this time, the intensity of the radio wave reflected by the flying object 1 decreases, and the receiving circuit of the opponent tracking radar and the interceptor missile loses the flying object 1 for a moment. When the interceptor misses the flying object 1 as a target, it usually terminates the self-destruction or the flight for safety, so that the flying object 1 can avoid an attack from the intercepting missile.

Embodiment 2 FIG. FIG. 3 is a diagram showing a seeker portion according to Embodiment 2 of the present invention. In FIG. 3, (a)
Is a view of the seeker from the front, (b) is a view of the seeker from the back, and (c) is a sectional view of the seeker.
d, 10, 11, 12, and 17 are the same as in FIG.
15d is a motor for rotating the reflectors 16a to 16d, respectively, and 19a to 19d are reflectors 16a to 16d, respectively.
It is a rotation axis for rotating 16d. FIG. 1 is a diagram showing the entirety of a second embodiment of the present invention.

Next, the operation will be described. Antenna 9a
The radio waves received at ９ 9 d pass through the hybrid 12, pass through the substrate 11, and are sent to the receiving circuit 4 as electric signals.
A gain electric signal is sent from the receiving circuit 4 to the gain detecting circuit 13, and the gain detecting circuit 13 measures a change in gain. Normally, the flying object 1 senses the side lobe of the radio wave 8 of the other party's radio source 7 and flies toward it, but the other party's radio source 7 is a tracking radar, and the flying body 1 is found by the tracking radar. Then, the main lobe of the radio wave 8 faces the flying object 1. Since the gain difference between the main lobe and the side lobe is usually close to 20 dB, the gain detection
When it changes by about dB, it is determined that the flying object 1 has been found and the interceptor missile has been fired, and a signal is sent from the gain detection circuit 13 to the control circuit 14. The control circuit 14 operates the motors 15a to 15d (here, for convenience, the number is not limited to four), and sets the initial positions around the rotating shafts 19a to 19d (here, four for convenience but the number is not limited). Reflector 1 is horizontal to the traveling direction
6a to 16d (here, four for convenience, but the number is not limited) is rotated. The reflectors 16a to 16d reflect the radio waves from the radio wave source 7, and periodically change the intensity of the radio waves reflected by the flying object 1. At this time, the receiver circuit of the opponent tracking radar and the interceptor missile changes to the reception gain corresponding to the instantaneously increased radio field intensity, but immediately the flying object 1
The intensity of the reflected radio wave decreases, and the receiving circuit of the opponent tracking radar and the interceptor missile loses sight of the flying object 1 for a moment. When the interceptor misses the flying object 1 as a target, it usually terminates the self-destruction or the flight for safety, so that the flying object 1 can avoid an attack from the intercepting missile.

Embodiment 3 FIG. 4 is a diagram showing a seeker portion according to Embodiment 3 of the present invention. In FIG. 4, (a)
Is a view of the seeker from the front, (b) is a view of the seeker from the back, and (c) is a sectional view of the seeker.
d, 10, 11, and 12 are the same as in FIG.
, A support shaft 21 for supporting the gimbal 20, and a pedestal 21 to which the support shaft 21 is connected.

Next, the operation will be described. Antenna 9a
The radio waves received at ９ 9 d pass through the hybrid 12, pass through the substrate 11, and are sent to the receiving circuit 4 as electric signals.
A gain electric signal is sent from the receiving circuit 4 to the gain detecting circuit 13, and the gain detecting circuit 13 measures a change in gain. Normally, the flying object 1 senses the side lobe of the radio wave 8 of the other party's radio source 7 and flies toward it, but the other party's radio source 7 is a tracking radar, and the flying body 1 is found by the tracking radar. Then, the main lobe of the radio wave 8 faces the flying object 1. Since the gain difference between the main lobe and the side lobe is usually close to 20 dB, the gain detection
When it changes by about dB, it is determined that the flying object 1 has been found and the interceptor missile has been fired, and a signal is sent from the gain detection circuit 13 to the control circuit 14. The control circuit 14 operates the gimbal 20 and tilts the seeker 3. When viewed from the front, the strength of the radio wave reflected by the flying object 1 is mostly the strength of the radio wave reflected by the seeker 3, so that the
If you tilt, the strength of the radio wave decreases. At this time, the receiving circuit of the opponent tracking radar and the interceptor missile loses sight of the flying object 1 for a moment. When the interceptor misses the flying object 1 as a target, it usually terminates the self-destruction or the flight for safety, so that the flying object 1 can avoid an attack from the intercepting missile.

Embodiment 4 FIG. 5 is a diagram showing a fourth embodiment of the present invention. In FIG. 5, (a) shows a state where the reflector is folded, (b) shows a state where the reflector is expanded, and 1
Is a flying body, 2 is a fuselage, 3 is a seeker provided inside the fuselage 2, 4 is a receiving circuit provided inside the fuselage 2, 5 is a rear wing arranged circumferentially and rearward of the fuselage 6, Is a steering wing disposed on the rear wing 5 for guiding the fuselage 2 in a predetermined direction; 13 is a gain detection circuit provided inside the fuselage 2;
Is a control circuit provided inside the body 2, 16 is a reflector arranged in the circumferential direction of the body 2, and 23 is a support rod for operating the reflector 16.

Next, the operation will be described. The electric wave received by the seeker 3 is sent to the receiving circuit 4 as an electric signal.
A gain electric signal is sent from the receiving circuit 4 to the gain detecting circuit 13, and the gain detecting circuit 13 measures a change in gain. Normally, the flying object 1 senses the side lobe of the radio wave of the other radio source and flies toward it. However, when the other radio source is a tracking radar and the flying object 1 is found by the tracking radar, the radio wave 1 Of the main lobe is suitable for the flying object 1. Gain difference between main lobe and side lobe is usually 20d
When the gain is changed by about 20 dB in the gain detection circuit 13, it is determined that the flying object 1 has been found and the interceptor missile has been fired, and a signal is sent from the gain detection circuit 13 to the control circuit 14. The control circuit 14 operates the support rod 23 by the motor 15 to deploy the reflector 16, and the reflector 16 reflects the radio wave from the radio wave source and increases the intensity of the radio wave reflected by the flying object 1 as viewed from the front. Let it. At this time, the receiving circuits of the opponent tracking radar and the interceptor missile change to a reception gain corresponding to the increased radio wave intensity. Next, the control circuit 14 folds the reflector 16 by the motor 15 via the support rod 23. At this time, the intensity of the radio wave reflected by the flying object 1 decreases, and the receiving circuit of the opponent tracking radar and the interceptor missile loses the flying object 1 for a moment. When the interceptor misses the flying object 1 as a target, it usually terminates the self-destruction or the flight for safety, so that the flying object 1 can avoid an attack from the intercepting missile.

Embodiment 5 FIG. 6 is a view showing a fifth embodiment of the present invention. In FIG. 6, (a) is a state in which the slave unit is connected, (b) is a state in which the slave unit is disconnected, 1 is a flying unit, 2 is a fuselage, and 3 is an inside of the fuselage 2. , A receiving circuit provided in the fuselage 2, a rear wing 5 disposed in the circumferential direction and rearward of the fuselage 2, and a rear wing 6 disposed in the rear wing 5 and moving the fuselage 2 in a predetermined direction. 13 is a gain detection circuit provided inside the fuselage 2, 14 is a control circuit provided inside the fuselage 2, 15 is a motor provided inside the fuselage 2, 16 is a reflector, and 24 is a fuselage. 2 Slave unit connected to lower part 2
Reference numeral 5 denotes a connecting portion for connecting the fuselage 2 and the handset flying object 24.

Next, the operation will be described. The electric wave received by the seeker 3 is sent to the receiving circuit 4 as an electric signal.
A gain electric signal is sent from the receiving circuit 4 to the gain detecting circuit 13, and the gain detecting circuit 13 measures a change in gain. Normally, the flying object 1 senses the side lobe of the radio wave of the other radio source and flies toward it. However, when the other radio source is a tracking radar and the flying object 1 is found by the tracking radar, the radio wave 1 Of the main lobe is suitable for the flying object 1. Gain difference between main lobe and side lobe is usually 20d
When the gain is changed by about 20 dB in the gain detection circuit 13, it is determined that the flying object 1 is found and the interceptor missile is fired, and a signal is sent from the gain detection circuit 13 to the control circuit 14. The control circuit 14 operates the motor 15 to orient the reflector 16 perpendicularly to the direction of the radio wave source 7,
The reflector 16 reflects the radio wave from the radio wave source and increases the intensity of the radio wave reflected by the flying object 1 as viewed from the front. Next, the control circuit 14 disconnects the slave unit 24 from the connection unit 25. At this time, the receiving circuit of the opponent tracking radar and the interceptor missile changes to a reception gain corresponding to the increased radio field intensity, and tracks the handset flying object 24. Since the interceptor missile tracks not the flying object 1 but the slave airplane 24 having a large reflected radio wave intensity, the flying object 1 can avoid an attack from the intercepting missile.

[0021]

As described above, the present invention effectively removes the tracking of the self-intercepting missile and the self-propelled vehicle from the opponent's tracking radar as compared with the conventional guided flying vehicle, and prevents the attack from the intercepting missile. Can be avoided.

[Brief description of the drawings]

FIG. 1 is an overall view showing Embodiment 1 of a guided flying object according to the present invention.

FIG. 2 is a seeker diagram showing Embodiment 1 of the guided flying object according to the present invention.

FIG. 3 is a seeker diagram showing Embodiment 2 of a guided flying object according to the present invention.

FIG. 4 is a seeker diagram showing a third embodiment of the guided flying object according to the present invention.

FIG. 5 is a view showing a fourth embodiment of the guided flying object according to the present invention;

FIG. 6 is a view showing a fifth embodiment of the guided flying object according to the present invention;

FIG. 7 is an overall view of a conventional guided flying object.

FIG. 8 is a seeker diagram of a conventional guided flying object.

[Explanation of symbols]

1 projectile, 2 fuselage, 3 seeker, 4 receiving circuit, 5 rear wing, 6 steering wing, 7 radio source, 8 radio wave, 9
Antenna, 10 insulator, 11 substrate, 12 hybrid, 13 gain detection circuit, 14 control circuit, 15 motor, 16 reflector, 17 outer frame, 18 wires, 19
Rotating shaft, 20 gimbals, 21 support shafts, 22 pedestals,
23 props, 24 flying aircraft, 25 connections.

──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. ⁷ Identification symbol FI Theme coat ゛ (Reference) G05D 1/12 G05D 1/12 F // G01S 13/88 G01S 13/88 M

Claims (5)

[Claims] 1. A flying object which does not emit radio waves but flies in the direction of a target radio wave source,
A seeker for receiving radio waves inside the flying object body, a foldable and deployable reflector for reflecting radio waves on the side of the seeker, a wire for folding and deploying the reflector, and a control for the wires And a gain detection circuit that measures the intensity of radio waves received by the seeker,
A control circuit for controlling the motor based on the radio wave intensity measured by the circuit is provided, the radio wave from the direction of the radio wave source is reflected by a reflector, and the intensity of the radio wave reflected by the target and reflected by itself is changed. A flying object characterized by being made to fly. 2. A flying object that does not emit radio waves but flies toward a target radio wave source.
A seeker that receives a radio wave inside the flying object body, a rotatable reflector that reflects the radio wave on the side of the seeker, a motor for rotating the reflector, and the intensity of the radio wave received by the seeker are measured. A gain detection circuit and a control circuit for controlling the motor based on the radio wave intensity measured by the circuit are provided, the radio wave from the direction of the radio wave source is reflected by a reflector, and the target itself receives and reflects. A flying object characterized by changing the intensity of radio waves. 3. A flying object which does not emit radio waves but flies in the direction of a target radio wave source.
A seeker for receiving a radio wave inside the flying object body, a gimbal for moving the seeker three-dimensionally, a gain detection circuit for measuring the intensity of the radio wave received by the seeker, and a radio wave intensity measured by the circuit A control circuit for controlling the gimbal, and reflecting the radio waves from the direction of the radio wave source by the seeker, thereby changing the intensity of the radio waves reflected by the target and reflected by the target itself. . 4. A flying object which does not emit radio waves but flies toward a target radio wave source,
A seeker that receives radio waves inside the flying object body, a foldable and deployable reflector that reflects radio waves provided on the side of the flying body, and a support rod for folding and deploying the reflector, A motor for controlling the support rod, a gain detection circuit for measuring the intensity of the radio wave received by the seeker, and a control circuit for controlling the motor based on the radio wave intensity measured by the circuit; A flying object characterized in that a radio wave from a direction is reflected by the reflector, and the intensity of the radio wave reflected by the target received by the target is changed. 5. A flying object which does not emit radio waves but flies in the direction of a target radio wave source,
A seeker that receives radio waves inside the flying body, a slave flying body connected to the side of the flying fuselage, a connection part that separates the slave flying body from the fuselage, A gain detector for measuring the intensity of radio waves received by the seeker inside the flying object body, provided with a folded expandable reflector that reflects radio waves provided inside, and a motor for expanding the reflector. Provide a circuit and a control circuit for controlling the motor and the connection unit by the radio wave intensity measured by the circuit, to reflect a radio wave from the direction of the radio wave source in the reflector inside the handset flying object, A flying object characterized by changing the intensity of the radio wave reflected by the slave flying object received by the target.