JPS62297772A - Radar device - Google Patents

Abstract

PURPOSE:To intercept a target which is small in effective reflection area, and plural targets by operating a switching device right before a guided airframe is launched and guiding the airframe by a semiactive homing system when the radar effective reflection area of the target is smaller than a prescribed value. CONSTITUTION:A ground radar 1 detects the radar effective reflection area of the target and when the area is larger than the prescribed size, the switching device 15 is operated on the ground before the guided airframe is launched so as to guide the guided airframe by the semiactive homing system. Consequently, a front receiver 17 and a rear receiver 19 are connected and transmitter 14, a receiver 17, and a front antenna 16 are disconnected. The radar 1 while sending a radio wave to the target transmits a rear signal 8 to the guided airframe. The receiver 19 which receives the signal 8 through a rear antenna 18 amplifies this signal and sends it to the receiver 17 through the device 15. The receiver 17 detects information on the target from the signal from the receiver 19 and the signal from the antenna 16 which is obtained by receiving a reflected wave 9 from the target 6.

Description

[Detailed Description of the Invention] 3. Detailed Description of the Invention [Field of Industrial Application] This invention relates to a guidance device for a guided flying object. More specifically, the present invention relates to a radar system for a flying object that uses a guidance method that combines a command command method, an active homing method, and a semi-active homing method as a guidance method for a guided flying object.

[Conventional technology]

Conventional guidance methods using radio waves mainly include an active homing method, a semi-active homing method, and a command guidance method.

The active homing method is a method that attempts to obtain information about the target by active means, by installing a small radar on the guided flying object, emitting radio waves to the target and receiving the reflected radio waves. This method obtains information about the target and tracks the target.

The semi-active homing method is a method in which only the radar transmitter is placed outside the body being guided.

The radar is placed on the mother plane for air-to-air guidance vehicles, and on the ground for ground-to-air guidance vehicles.

The command guidance method detects information about the target and the guided flying object using a radar located outside the guided flying object.

This method uses a computer to find the meeting point and then commands the radar to steer the flying object.

Conventional guidance devices use an active homing method.

The semi-active homing method and command guidance method were used alone, or the command guidance method and active homing method were used in combination.

[Problems to be solved by the invention] The active homing method can track the target using its own radar, so even if multiple targets attack at the same time, multiple guided flights can be launched simultaneously. , has the feature of being able to intercept multiple targets simultaneously, but since the radar transmitting and receiving device must be mounted on a guided flying object with limited volume and weight, the radar detection distance is limited, and active homing Radar equipment using this method had the disadvantage that it could only guide targets over short distances. Because of this drawback, active homing methods are usually not used alone.

Command guidance is used until the active homing type radar device reaches a distance at which it can track the target.

Note that the command guidance described above is used during the early and middle stages of the flight of the guided flying object, so the guidance accuracy may be approximately, and there is no need to continuously irradiate the target with radar radio waves. In this case, one radar can guide multiple guided missiles, so the ability to simultaneously respond to multiple targets is not impaired.

However, for targets with an extremely small radar effective reflection area, such as stealthized cruising missiles, which are assumed to be a future threat, a guidance system using the actu-homing method has an even shorter detection range. Because the minimum detection distance necessary to intercept the
Even if the command guidance and active homing methods were combined, there was a drawback that the target could not be intercepted.

The command guidance method has the disadvantage of poor guidance accuracy and is not suitable for terminal guidance.

On the other hand, the semi-active homing method places the radar on the base aircraft or on the ground and irradiates the target with high-output, narrow-beam radio waves, making it possible to extend the detection distance and track targets with extremely small effective radar reflection areas. However, the radar has the disadvantage that it is necessary to continuously emit radio waves to the target, and the ability to simultaneously deal with targets is limited by the number of radars.

[Means for solving problems]

This invention was made in order to solve the problems of the above-mentioned combination of active homing method and command guidance method and semi-active homing method. By simultaneously possessing a semi-active homing guidance means and a stealthized cruising missile, it is possible to intercept targets with an extremely small radar effective reflection area, such as stealthized cruising missiles, and also to intercept multiple targets at the same time. The purpose of this project is to obtain a body-based radar device.

[Effect]

In this invention, when the radar effective reflection area of the target is less than a predetermined value, the wrinkle active homing method and the semi-active homing method are switched by a signal from the ground radar immediately before the guided flying object is launched. Activate the switching device to guide the flying object using the semi-active homing method.

〔Example〕

FIG. 1 is a diagram showing an example of the operation of a guided flying object using a radar device according to the present invention. Tl) is a ground radar that transmits a command signal (3) for commanding and guiding the guided flying object (2) during the initial and middle stages of flight of the guided flying object (2). The guided flying object (2) is guided by the command signal (3) until guidance using the active homing method becomes possible. The target (4) is a target with a large radar effective reflection area compared to a target with an extremely small radar effective reflection area such as a stealthized cruising missile. Induced corneal body (
2) emits radio waves to the target (4) and receives reflected waves (5) from the target. The guiding body (2) and the target (4) approach each other.

When the power of the reflected wave from the target (4) increases, the guiding gonioglial body (2) can receive the reflected wave (5) from the target (4) and track the target. At this point, the guided flying object (2) is switched from command guidance to active homing guidance. On the other hand, if the target is a cruising missile that has an extremely small effective radar reflection area and cannot be guided by the active homing method, it is guided by the semi-active homing method.

The radar (11) detects the effective reflection area of the target, and if it is less than a predetermined value, that is, a value that makes it impossible to guide the active homing method, the radar (11) uses a semi-active homing method to guide the gonioplasty. Radio waves are irradiated to the target (6) and the guiding angle body (7). (6
) is a target with an extremely small effective radar reflection area, such as a cruising missile! +7) is target (6) 1
It is a guided angle body that tracks.

The guiding body (7) receives the rear signal (8) emitted from the radar (11) and the reflected wave (9) from the target (6).

It is guided by a semi-active homing method.

FIG. 2 is a configuration diagram showing an embodiment of the guidance device according to the present invention. First, an example of the operation when guiding a guided flying object in accordance with a command from the ground will be explained. (1) is a ground radar, which transmits a command signal (3) for performing early and intermediate guidance of the guiding goniocele. Command signal (3) transmitted from the command antenna (ground radar port)
is received and sent to the command receiver aυ. The command receiver Uυ amplifies the signal sent from the command antenna Ql. The signal amplified by the command receiver Qυ is sent to the signal processing device α. The signal processing device α detects a guidance control signal 2, such as a velocity spectral signal, necessary for guiding the guiding body, and sends its output to the control device αJ.

The command guidance control signal from the ground radar is based on the earth-fixed coordinates, and the control device flQ1 converts the guidance control signal sent from the signal processing device tJ7J from the earth-fixed coordinates to the aircraft coordinates of the guidance angle body. Converted.

The guiding goniometric body is controlled based on the guiding control signal obtained by coordinate transformation.

Next, an example of the operation when guiding the guiding corneal body using the active homing method will be shown.

I is a transmitter, which is connected to a switching device Q9 to be described later. (II is a front antenna that receives the output of the transmitter α4 via the switching device α9, irradiates the target (4) with radio waves, and at the same time receives the reflected wave (5) from the target. The received signal is sent to the front receiver Q?+.The front receiver aη amplifies the signal sent from the front antenna tte, and at the same time uses a part of the output of the transmitter α Target information 1 For example, detect the pitch angle and yaw angle when looking at the target from the flying object.The front receiver also obtains target information using η. The information obtained by the front receiver aη is not particularly specified.

The signal is sent to signal processing device Q3. In signal processing device +13.

The target information obtained by the front receiver Qη is used to obtain a guidance signal necessary for guiding the flying object, such as the line-of-sight angular velocity between the guiding flying object and the target. The output of the signal processing device Q is sent to the control device I, and based on this signal, the control device (13 controls the flying object).

The target information obtained using the active homing method and semi-active homing method is as follows.

Since it is based on the aircraft coordinates, there is no need to convert from earth-fixed coordinates to aircraft coordinates.

Switching from commanded guidance to active homing type guidance is performed by the signal processing device 0.

It may be switched when the signal-to-noise ratio of the output of the front receiver Q7+ exceeds a predetermined value, or it may be switched depending on the magnitude of the output, and is not limited to 2%.

Next, an example of the operation when guiding the guiding corneal body using the semi-active homing method will be shown.

The ground radar (1) detects the target's V-da effective reflection area, and if it is less than a predetermined size, it guides the guided flying object using a semi-active homing method, so before launching the guided flying object, Activate the switching device on the ground.

In the case of a semi-active homing method, the switching device (IcJ is a front receiver aη and a rear receiver αl, which will be described later).
It operates to connect the transmitter I and the front receiver (Iη) and to disconnect the transmitter 0 and the front antenna 1Q.

In the semi-active method, a ground radar emits radio waves at the target and at the same time sends a rear radar to the guided flying vehicle.
Send signal (8). The rear antenna αe receives the rear signal (8) and sends it to the rear receiver α9. The rear receiver α1 amplifies the signal from the rear antenna a and sends it to the front receiver αη via the switching device aS. The front receiver αη receives the signal from the rear receiver a9 and the target (
The signal from the front antenna which received the reflected wave (9) from 6) is used to detect target information.

The difference between the semi-active homing method and the active homing method is whether the reference signal is created using the output of the rear receiver (I) or a part of the output of the transmitter (14). The legs and other movements are the same.

〔Effect of the invention〕

As described above, according to the present invention, the command command method, active homing method, and semi-active homing method are combined as the guidance method of the guided flying object, and when the radar effective reflection area of the target is less than a predetermined value, Since the guided missile is guided using a semi-active homing method, it is possible to intercept targets with extremely small effective radar reflection areas, such as stealthized cruising missiles, and it is also possible to intercept multiple targets at the same time. .

[Brief explanation of the drawing]

FIG. 1 is a diagram showing an example of the operation of a guided flying object using a guidance device according to the present invention, and FIG. 2 is a configuration diagram showing an embodiment of the guidance device according to the present invention. (1) is ground radar, (2) is guided flying object, (3)
is a command signal, (4) is a target, and (5) is a reflected wave from target (4). (6) is a target with a small radar effective reflection area, (7) is a guided flying object that tracks target (6), and (8) is a rear signal. (9) is the reflected wave from target (6), (11 is the command antenna, a force is the command receiver, 2 is the signal processing device, QI is the control device, 04 is the transmitter, a field is the switching device, ae is a front antenna, (Iη is a front receiver, (11 is a rear antenna, and (19 is a rear receiver.) In FIG. 1, the same or corresponding parts are denoted by the same reference numerals.

Claims (1)

[Claims] A command antenna that receives a command signal from the ground, a command receiver that amplifies the output of the command antenna, a rear antenna that receives a rear signal from the ground, and a rear antenna that amplifies the output of the rear antenna. A receiver, a front antenna that emits radio waves to a target and receives reflected waves from the target, a transmitter that supplies transmission power to the front antenna, and a transmitter that amplifies the output of the front antenna and transmits target information at the same time. A front receiver for detection, a signal processing device for detecting a guidance control signal from the output of the front receiver or the output of the command receiver, and a guided flying object based on the signal obtained by the signal processing device. Equipped with a control device to control the system and a switching device to switch from the active homing method to the semi-active homing method, it simultaneously has a command guidance function, an active homing function, and a semi-active homing function, and the target radar effective reflection area is predetermined. A radar system for an air vehicle that switches to a semi-active homing method based on a signal from a ground radar immediately before the guided object is launched.