JP2002228399A - Rocket and its guiding controller - Google Patents

Abstract

PROBLEM TO BE SOLVED: To accurately fly a rocket flying toward a target while subjected to guidance control toward the target with a simple constitution. SOLUTION: A GPS receiver 415 is mounted at a rocket (guided missile) 4 to be launched to obtain accurate position measurement data of the rocket 4 itself flying toward the target 2. A guided flying control signal of the rocket 4 is obtained from position measurement data of own rocket and target position data from a ground radar system 1. Since the rocket 4 obtains accurate self- position measurement data on three-dimensional coordinate axes by the receiver 415, the rocket 4 can easily calculate a flying tracing course directed toward an optimum target 2 according to the same position data on the three- dimensional coordinate axes of the target 2 transmitted from the ground. Thus, constitution loads of not only the rocket 4 itself but also the radar system 1 or the like on the ground can be alleviated.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a rocket suitable for detecting a target such as an enemy missile with a radar device or the like, firing the target, and intercepting the target. The improvement of the guidance control device.

[0002]

2. Description of the Related Art When a rocket, such as a guided missile, is launched to intercept an enemy missile or the like that is entering, the rocket is usually equipped with a homing device, and a homing guide is provided. While flying toward the target.

[0003] However, the target capture distance in the homing device, that is, the lock-on distance, is naturally limited. Particularly, in the homing device mounted on a rocket, the lock-on distance is greatly restricted by the antenna opening diameter of a radio wave seeker or the like and the transmission power, so that a target flying from a distant place is quickly attacked at a point far away. If you try to do so, the rocket launched in the target direction will activate the homing device at a distant point,
It is necessary to guide the rocket separately until the target can be locked on.

FIG. 3 shows that a radar apparatus 1 on the ground searches for and captures an invading enemy missile (target) 2, and in order to intercept the captured target 2, a homing device is launched from a launch apparatus 3. FIG. 2 is a schematic configuration diagram illustrating a situation in which a rocket 4 such as a guided missile mounted on the vehicle is fired, and a target 2 is attacked.

[0005] That is, the radar device 1 that has captured the target 2 that has entered from a distance by searching continuously captures the position, and sequentially shoots data such as the current position, the flight direction, and the flight speed of the target 2. It is supplied to the command and control device 5.

[0006] The shooting command and control device 5 which has received data such as the current position, the flight direction, and the flight speed of the target 2 from the radar device 1 uses a high-speed calculation of a mounted computer to perform the calculation.
In addition to predicting the future flight course of the target 2, the position of the predicted hit position P at which the launched rocket 4 can pass directly after approaching or approaching the target 2 and the predicted hit position P
Is calculated until the rocket 4 fired toward the vehicle reaches the expected hit position P.

When the shooting command and control device 5 determines that the launched rocket 4 can encounter the target 2 at the expected hit position P, the shooting command and control device 5 sends the rocket 4 or the launch device 3 A command is sent to launch and launch the rocket 4 toward the predicted lock-on position L.

[0008] Even after the rocket 4 is launched and launched, the position of the target 2 is constantly changing.
Continuously captures and tracks the target 2, and sequentially supplies update data such as the current position, the flight direction, and the flight speed of the target 2 to the shooting command and control device 5.

The shooting command and control device 5 receiving the updated data
Calculates the predicted lock-on position L of the target 2 continuously by the computer, updates the data only when the predicted lock-on position L predicted earlier changes, and temporarily updates the updated data via the radar device 1. Successive uplink (u
(link) to the rocket 4. The rocket 4, which has always received the latest data of the predicted lock-on position L from the radar device 1, which is the transmitting means on the ground, corrects the flight course by calculation based on the received update data of the predicted lock-on position L. Since the steering wing is controlled, the target 2 can be approached and the target 2 can be captured at the predicted lock-on position L.

As described above, even after the launch of the rocket 4, the firing command and control device 5 continues to perform guidance control to an area where the rocket 4 can lock on the target 2 by itself, so that the mounted homing device locks the target 2. After turning on, the autonomous homing guidance makes it possible to collide with or pass the target 2 so that the fuze mounted thereon explodes the warhead to shoot down the target 2.

As described above, the rocket 4 such as a guided missile that flies toward the target 2 with the assistance of the radar device 1 and the shooting command and control device 5 is schematically configured as shown in FIG.

That is, the rocket 4 has a control unit 41 and a guiding unit 42, and both operate by receiving power supply from a power supply device 43 such as a thermal battery.

Until the radio seeker of the guiding unit 42 captures the target 2 and forms an autonomous homing device together with the control unit 41, the control unit 41 transmits from the shooting command and control device 5 via the radar device 1. Predicted lock-on position L
Control of the steering wings 44, 44 based on the data of
The flight toward the predicted lock-on position L is performed.

That is, the control unit 41 of the rocket 4 includes a data link receiving device 411, a gyro (gyroscope) 412, a guidance control circuit 413, and a steering device 414.
The data link receiving device 411 receives the predicted lock-on position L data transmitted from the radar device 1 on the uplink, and together with the attitude data of the own aircraft (rocket 4) obtained by the gyro 412, the guidance control circuit 413.

The guidance control circuit 413 has an INS (INS:
Inertial Navigation System
m) It has a processing operation circuit 413a and a guidance processing circuit 413b, and has a built-in computer.

The INS processing operation circuit 413a obtains inertial navigation data based on the predicted lock-on position L data obtained from the data link receiving device 411 and the flight attitude data of the own aircraft obtained from the gyro 412, and also obtains the predicted lock-on data. The flight control parameters for reaching the ON position L are calculated.

On the other hand, the guidance processing circuit 413b generates a steering signal to fly toward the predicted lock-on position L along the flight course based on the flight control data calculated by the INS processing operation circuit 413a, and controls the steering device 414. Steering wheel 4 through
4 and 44 are controlled.

On the other hand, the guiding unit 42 supplies an antenna 421 aperture-directed in the machine axis direction, supplies a radar wave to the antenna 421 and radiates the radar wave to the space, receives a radar reflected wave from the target 2, and And a frequency unit 422 for obtaining the azimuth angle data of
And an antenna control circuit 423 for driving the antenna 421 by obtaining the target azimuth angle data from the antenna.

As described above, the guiding section 42 is controlled by the control section 41.
When the radar wave radiated from the antenna 421 approaches the distance at which the lock-on is possible by the guidance control performed by the antenna 421 and captures the target 2 in the field of view, the antenna control circuit 423 uses the antenna 421 directional angle information to control the guidance of the control unit 41. The signal is supplied to the circuit 413.

That is, after the guidance unit 42 captures the target 2 in the guidance unit 42, the guidance control device 413 replaces the signal from the data link reception device 411 with the antenna control circuit 423.
From the azimuth angle signal of the target 2 from the
Since the steering signal to the target 4 is generated, an autonomous homing device based on the azimuth angle signal of the target 2 is configured.

As described above, the conventional rocket 4 such as a guided missile performs guided flying with the assistance of the ground-based radar device 1 and the shooting command and control device 5 in the initial first stage of launch. In the second stage after the target 2 has been captured by lock-on, the mounted guiding unit 42 and control unit 41
As a result, the rocket 4 approaches the target 2 so as to collide with or pass by the active autonomous homing guidance, and can explode and shoot down the mounted warhead by the operation of a fuse (not shown).

[0022]

As described above, according to a conventional rocket such as a guided missile and a guidance control device for the rocket, the rocket is guided in a target direction while being assisted by a radar device and a transmission device on the ground. From the first stage of launching and flying toward the target, in the middle of the flight after the launch, the target 2 is intercepted through the second stage of flying while locking on the target by the operation of the mounted homing device.

Therefore, in order to detect an invading target at an early stage and to shoot it down in a distant place, as described above, the radar device 1 and the shooting command and control device 5 on the ground require the rocket 4 to approach the target 2. It was necessary to guide the target 2 far enough to be able to catch within the lock-on distance.

Therefore, in the conventional rocket and the guidance control apparatus for the rocket, in the first stage, it is necessary to guide the guided missile 4 to a distant distance with high accuracy, and therefore, the burden on the ground side to support this is required. Had to construct and deploy a large search-following radar apparatus having a large aperture antenna capable of obtaining high output and high resolution.

Also, the rocket itself calculates advanced flight control parameters for reaching the predicted lock-on position L based on mere flight attitude data obtained from a gyro or the like and target position data from the ground. Therefore, the burden on the computer was greatly increased and improvement was demanded.

Therefore, the present invention provides a simple structure with a reduced burden on the ground equipment as well as the rocket itself.
It is an object of the present invention to provide a rocket capable of accurately guiding and flying toward a target and a guidance control device for the rocket.

[0027]

A first aspect of the present invention receives a transmitted target position data, generates a steering signal based on the received target position data, controls a steering wing, and flies toward a target. The rocket includes a GPS receiver, and is configured to generate the steering signal based on the own position data obtained from the GPS receiver and the target position data.

According to a second aspect of the present invention, there is provided a radar device for searching for and capturing an opponent's flying object and deriving position data of the opposing flying object, and a position data of the opposing flying object derived from the radar device. A rocket guidance control comprising: a transmitting means for transmitting; and a rocket that receives position data of the other flying object by the transmitting means, generates a steering signal based on the received position data, and flies toward the flying object. In the device, the rocket is equipped with a GPS receiver, and based on its own position data obtained from the GPS receiver and the received position data of the other flying object,
It is characterized in that it is configured to generate the steering signal.

As described above, the rocket has a GPS (Glob)
al Positioning System) A GPS receiver is installed to obtain high-precision self-position data from the GPS receiver. Therefore, it is possible to easily generate a high-accuracy steering signal for a target, and not only the rocket itself but also the ground , Etc., the load on the radar device and the like can be greatly reduced.

[0030]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of a rocket according to the present invention and a guidance control device for the rocket will be described below in detail with reference to FIGS. 3 and 4
The same reference numerals are given to the same components as those of the conventional configuration shown in FIG.

FIG. 1 shows that a radar device 1 on the ground searches for and captures an invading target (enemy missile) 2 and guides and launches a rocket 4 such as a guided missile from a launch device 3 to intercept the target. FIG. 2 is a schematic configuration diagram illustrating a situation in which the vehicle intercepts the vehicle.

That is, first, the radar device 1 continuously obtains the target position data on the three-dimensional coordinate axis of the target 2 captured by the search and obtains the wake of the target 2, and obtains the trajectory of the target 2 from the wake as in the conventional case. A flight direction, a flight speed, and the like are calculated by a computer, and the data is transmitted to the shooting command and control device 5 together with the current position data of the target 2.

When the rocket 4 is launched and fired based on the current position data of the target 2 from the radar device 1 and the flight direction and speed data from the radar device 1, the fired command and control device 5 moves the rocket 4 to the target. The vehicle 1 predicts an encounter position on a three-dimensional coordinate axis that can pass directly through or approach the vehicle 2 and predicts an expected hit position P and a predicted arrival time T until the launched rocket 4 can reach the expected hit position P.
Is calculated at a high speed by a computer, and the rocket 4 or the launching device 3 is controlled so that the rocket 4 is launched so that the predicted hit position P can be reached.

After the rocket 4 has been fired from the firing device 3, the shooting command and control device 5 first obtains the position data of the target 2 continuously captured by the radar device 1 based on the position data of the target 2.
The data of the current position of the target 2 and the data of the flight direction and the flight speed transmitted to the target 2 are sequentially updated. Therefore, the firing command and control device 5 receiving the updated data sequentially and tertiarily outputs the data through the radar device 1. The updated data of the predicted lock-on position L on the original coordinate axis is transmitted to the rocket 4 by the uplink.
Send to the side.

On the other hand, the rocket 4 fired by the command of the shooting command and control device 5 is configured as shown in FIG.

The rocket 4 has a control unit 41 as in the prior art.
And a guide unit 42, based on the current position data of the target 2 transmitted only when the predicted lock-on position L is changed from the radar device 1 while receiving power supply from the power supply device 43 such as a thermal battery. It flies toward the predicted lock-on position L on the updated three-dimensional coordinate axis, and flies in a guided manner so that the target 2 can be captured within the lock-on distance by the mounted homing device.

That is, the control unit 41 of the rocket 4 includes a data link receiving device 411, an inertial navigation device 412 including a gyro, a guidance control circuit 413, and a steering device 414.
And GPS (Global Positionin)
g System) GPS receiver 415 including antenna
Is configured.

As shown in FIG. 1, the GPS receiver 415 receives a signal from the GPS satellite 6 and can obtain highly accurate position measurement data on its own three-dimensional coordinate axis (rocket 4). . Although only one GPS satellite 6 is shown in FIG. 1, by receiving signals from at least four GPS satellites 6, it is possible to know the current position of the own aircraft on an accurate three-dimensional coordinate axis. it can.

Accordingly, the guidance control circuit 413 sets the predicted lock-on position L data on the updated three-dimensional coordinate axis of the target 2 sequentially transmitted from the ground radar device 1 via the data link receiving device 411, Gyro 41
Flight attitude data of own aircraft (rocket 4) obtained in 2
And the self-position measurement data on the high-precision three-dimensional coordinate axis obtained from the GPS receiver 415 is supplied.

The guidance control circuit 413 includes an INS processing operation circuit 413a and a guidance processing circuit 413b.
Since the guidance control circuit 413 can obtain the predicted lock-on position L data of the target 2 on the three-dimensional coordinate axis and the highly accurate self-position measurement data on the three-dimensional coordinate axis as well, the own flight attitude data should be added. Of the rocket 4 as well as the distance to the predicted lock-on position L
The azimuth angle of the predicted lock-on position L can be obtained with high accuracy by a simple calculation.

That is, the INS processing operation circuit 413a of the guidance control circuit 413 is different from the conventional one in that the INS processing (the predicted lock-on position L of the target 2) and the I (the current position of the rocket 4) on the same three-dimensional coordinate axis. Since the relative positional relationship can be obtained with high accuracy from the positional information of
13b, the optimum flight course that can encounter the target 2 can be calculated easily and with high accuracy, and a steering signal along the flight course can be supplied to the steering device 414.

On the other hand, similarly to the conventional rocket 4 shown in FIG. 4, the guiding section 42 has an antenna 421 whose directing direction is directed to the machine axis direction, supplies and radiates a radar wave to the antenna 421, Frequency unit 42 that receives the radar reflected wave from
The antenna control circuit 423 that has obtained the azimuth angle data obtained by the frequency unit 422 controls the antenna 421 so that the antenna 421 always points in two target directions, and the azimuth angle data is It is supplied to the guidance control circuit 413 of the guidance unit 41.

Therefore, when the antenna 421 has captured the target 2 and received the azimuth angle signal of the target 2 from the antenna control circuit 423, the guidance control circuit 413 replaces the signal of the data link receiver 411 with the target azimuth signal. Since the azimuth angle signal of 2 is introduced, a homing device is formed so as to lock on the target 2 on the basis of the flight attitude data of the own aircraft from the inertial navigation device 412 so that the homing device collides with or passes the target 2 with a high probability. When approaching, the fuze (not shown) can be activated to explode the warhead.

In the above description, the rocket 4 such as a guided missile in the present embodiment performs active homing, but the same function and effect can be obtained by applying passive homing or semi-active homing. be able to.

In the above description, the rocket 4 captures the incoming target 2 in the front direction and intercepts it. However, the rocket 4 may follow the target 2 obliquely from behind and shoot it down. For example, an infrared camera or the like is mounted as a seeker for the rocket 4 in place of the antenna 421, captures infrared rays radiated by the engine or the like of the target 2, and maintains the view direction of the captured camera at a constant angle with the machine axis direction. The passive infrared homing that tracks the target 2 may be configured to track and shoot down the target 2.

As described above, according to the rocket according to the present invention and the guidance control device for the rocket, the rocket is provided with a GP.
Since the S receiver 415 is mounted and its own high-precision current position data on the three-dimensional coordinate axis is obtained, after the launch of the rocket 4, guided flight with the assistance of the ground radar device 1 and the shooting command and control device 5 In doing so, even if the accuracy of the target position data from the ground is slightly reduced, it is possible to easily generate a high-accuracy steering signal, and reduce the burden on the radar device etc. on the ground as well as the rocket body. it can.

As described above, the rocket according to the present invention,
According to the guidance control device of the rocket, the GPS receiver mounted on the rocket obtains its own current position data on the three-dimensional coordinate axes with high accuracy, so that it is possible to easily generate a high-precision steering signal. Thus, the burden on the radar device on the ground or the like can be reduced, and a remarkable effect can be exhibited in practical use.

[Brief description of the drawings]

FIG. 1 is a schematic configuration diagram showing one embodiment of a guidance control device for a rocket according to the present invention.

FIG. 2 is a schematic configuration diagram of the rocket shown in FIG.

FIG. 3 is a schematic configuration diagram showing a conventional rocket guidance control device.

FIG. 4 is a schematic configuration diagram of the rocket shown in FIG.

[Explanation of symbols]

 Reference Signs List 1 radar device 2 target (enemy missile) 3 launch device 4 rocket (guide missile) 41 control unit 411 data link receiving device 412 gyro 413 guidance control circuit 414 steering device 415 GPS receiver 42 guidance unit 421 antenna 422 frequency unit 423 antenna control Circuit 5 Shooting command and control device (transmitting means) 6 GPS satellite

Claims (4)

[Claims] 1. A rocket that receives transmitted target position data, generates a steering signal based on the received target position data, controls a steering wing, and flies toward a target, includes a GPS receiver. A rocket configured to generate the steering signal based on own position data obtained from the GPS receiver and the target position data. 2. The rocket according to claim 1, wherein the target position data is position data on a three-dimensional coordinate axis predicted to collide with or pass a target. 3. A radar device for searching for and capturing an opponent's flying object and deriving position data of the opposing flying object, transmitting means for transmitting position data of the opposing flying object derived from the radar device, A rocket guidance control device comprising: a rocket that receives position data of the other flying object by the transmitting means, generates a steering signal based on the received position data, and flies toward the flying object. , A GPS receiver mounted thereon, and configured to generate the steering signal based on the own position data obtained from the GPS receiver and the received position data of the other flying object. Guidance control device for rocket. 4. The rocket guidance according to claim 3, wherein the position data of the other flying object is position data on a three-dimensional coordinate axis predicted to collide with or pass by the other flying object. Control device.