JP2002357400A - Radio wave source tracking airframe and system and method for controlling airframe - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide an airframe, such as the missile, etc., that can perform complicated signal processing without being restricted by the scale or price of a device. SOLUTION: The airframe is provided with an antenna which receives radio waves from a radio wave source, a tuning receiving means which measures data by tuning to received waves of a prescribed frequency, and a transmitting means which transmits the measured data by radio. The airframe is also provided with a receiving means which receives control data found on the basis of the measured data by radio.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a radio source tracking flying object, a flying object control system, and a flying object control method, and more particularly, to guidance control of a flying object such as a missile that tracks a radio source based on a received radio wave. Regarding system improvement.

[0002]

2. Description of the Related Art FIG. 10 is a block diagram showing a configuration example of a conventional radio wave source tracking missile, and shows a guidance system control system. The radio source tracking missile includes an angle tracking antenna 11, a tuning receiving unit 12, a signal processing unit 16, and a flight control unit 15.

[0003] The angle tracking antenna 11 is means for receiving a radio wave from a radio wave source. The tuning receiving means 12
Before launch, frequency data to be tuned is transmitted from a base unit (not shown), and based on the frequency data, radio wave specification data is tuned to the received radio wave to measure radio wave specification data, and a target direction is determined based on the measured data.

[0004] The signal processing means 16 calculates the target azimuth and the flight information of the missile itself (for example, position, flight speed,
Based on the flight direction), flight control of the missile is performed, and reception control for the radio wave source is performed so that the target azimuth is not mistaken due to disturbance radio waves. That is, the signal processing means 1
The tuning receiver 12 and the flight control means 15 operate on the basis of the reception control signal and the flight control signal output by the control unit 2.

[0005]

The conventional radio source tracking missile is provided with a signal processing means 16, and this signal processing means 16 needs to perform complicated calculations. However, such missiles require (1) a small device scale and (2) low cost because they are disposable, so that there is a limit to the improvement of the processing capability of the signal processing means 16. There was a problem that there is.

In particular, when the radio wave source stops using (emission) the radio wave or takes countermeasures such as generating disturbance due to another radio wave source, there is a problem that the flight control of the radio wave tracking missile becomes uncertain. Was. Further, since the same is required for the size of the angle tracking antenna 1 and the size of the tuning receiver 2, there is a problem that the receiving sensitivity tends to be insufficient.

SUMMARY OF THE INVENTION The present invention has been made to solve the above-described problems, and provides a missile or other flying object capable of performing complicated signal processing without being limited by the size and cost of the apparatus. The purpose is to: Another object of the present invention is to improve the reliability of flight control of a flying object.

[0008]

According to the first aspect of the present invention, there is provided a radio source tracking flying object which tunes to an antenna for receiving a radio wave from a radio source and performs data measurement in synchronization with a received radio wave of a predetermined frequency. It comprises a receiving means, a transmitting means for wirelessly transmitting the measured data, and a receiving means for wirelessly receiving the control data obtained based on the measured data.

The tuning receiving means tunes to a predetermined frequency of the radio wave received by the antenna and measures radio wave specification data. The measurement data is wirelessly transmitted by the transmission means. The transmitted measurement data is received by the flying object controller provided with the signal processing means. The signal processing means obtains control data of the flying object based on the received data and wirelessly transmits the control data to the flying object. This transmission data is received by the receiving means of the flying object, and is used for controlling the radio source tracking flying object. For this reason, the control of the flying object based on the received radio wave at the radio source tracking flying object can be performed using the signal processing means outside the radio source tracking flying object.

In the radio source tracking flying object according to the present invention, the transmitting means transmits flight information of the flying object together with the measurement data, and the control data is obtained based on the measurement data and the flight information. Flight control means for performing flight control based on a reception signal of the reception means.

The transmitting means of the radio source tracking flying object wirelessly transmits flight information of the flying object together with the measurement data. Thereby, the signal processing means of the flying object controller can obtain the flight control data of the flying object based on the received measurement data and the flying information. When the flying object controller transmits control data including the flight control data thus obtained to the flying object, the flight control means of the flying object performs flight control based on the received flight control data. Therefore, the flight control of the flying object based on the received radio wave at the radio source tracking flying object can be performed using the signal processing means outside the radio source tracking flying object.

According to a third aspect of the present invention, there is provided a radio source tracking flying object according to the present invention, wherein the control data includes control data of a tuning frequency, and the tuning receiving means controls the tuning frequency based on a signal received by the receiving means. Be composed. The control data of the tuning frequency may be frequency data for designating a frequency or data for instructing a search.
The control data may include the flight control data together with the reception control data.

[0013] The signal processing means of the flying object controller determines the tuning frequency of the flying object or the search thereof based on the received measurement data. When the flying object controller transmits control data including the tuning frequency control data to the flying object, the tuning receiving means of the flying object operates based on the received control data. For this reason, control of the tuning reception operation of the flying object based on the received radio wave at the radio source tracking flying object can be performed using the signal processing means outside the radio source tracking flying object.

According to a fourth aspect of the present invention, a flying object control system according to the present invention comprises a radio source tracking flying object and a flying object controller. The radio source tracking projectile includes an antenna for receiving a radio wave from the radio source, a tuned receiving unit for performing data measurement in synchronization with a received radio wave of a predetermined frequency, and a transmission for wirelessly transmitting the measured data to the projectile controller. And a receiving means for wirelessly receiving control data from the flying object controller.
On the other hand, the flying object controller is provided with signal processing means for obtaining control data based on measurement data received from the radio source tracking flying object. The radio source tracking flying object is a missile or the like, and the flying object control device may be an aircraft, a ship,
Vehicles and fixed facilities on the ground may be used.

A flying object control system according to a fifth aspect of the present invention includes a radio source tracking flying object and a flying object controller. The radio source tracking flying object is an antenna that receives a radio wave from a radio source, a tuned reception unit that tunes to a received radio wave of a predetermined frequency to perform data measurement, and the measured data together with the flight information of the flying object. The transmission device includes a transmission unit that wirelessly transmits the control data to the controller, a reception unit that wirelessly receives the control data from the flying object controller, and a flight control unit that performs flight control based on the received control data. On the other hand, the flying object controller is provided with signal processing means for obtaining control data of the flying object based on measurement data received from the radio source tracking flying object and flight information of the flying object.

According to a sixth aspect of the present invention, there is provided a flying object control system, wherein the flying object controller controls an antenna for receiving a radio wave from a radio wave source, and tunes reception by performing data measurement in synchronization with a received radio wave of a predetermined frequency. Means. The signal processing means of the flying object controller generates control data based on the measurement data of the flying object controller and the measurement data of the radio wave source tracking flying object. Therefore, for example, the position of the radio wave source can be obtained using the principle of triangulation, and the flight control of the flying object can be performed based on this position.

According to a seventh aspect of the present invention, a flying object control system according to the present invention comprises a radio source tracking flying object, a flying object controller, and a radio wave receiver. The radio receiver has an antenna for receiving a radio wave from a radio source, and a tuning reception unit for performing data measurement in synchronization with a reception radio wave of a predetermined frequency, and wirelessly transmits the measured data to the flying object controller. . The signal processing means of the flying object controller generates control data based on the measurement data of the radio wave receiver and the measurement data of the radio wave source tracking flying object. Therefore, for example, the position of the radio wave source can be obtained using the principle of triangulation, and the flight control of the flying object can be performed based on this position.

In the flying object control system according to the present invention, the radio wave receiver is configured as another radio source tracking flying object different from the above radio source tracking flying object.

According to a ninth aspect of the present invention, there is provided a flying object control system including a radio source tracking flying object and a flying object controller. The radio source tracking flying object is an antenna that receives a radio wave from a radio source, a tuned reception unit that tunes to a received radio wave of a predetermined frequency to perform data measurement, and the measured data together with the flight information of the flying object. The transmission device includes a transmission unit that wirelessly transmits the control data to the controller, a reception unit that wirelessly receives the control data from the flying object controller, and a flight control unit that performs flight control based on the received control data.

Also, the flying object controller includes an antenna for receiving a radio wave from a radio wave source, a tuned receiving means for performing data measurement in synchronization with a received radio wave of a predetermined frequency, and measurement data or a radio wave source for the flying object controller. Signal processing means for generating control data based on any of the measurement data received from the tracking flying object. Therefore, when the reception sensitivity of one (for example, the flying object) is low, the control data can be generated based on the other measurement data. That is, the signal processing unit can be operated by switching the measurement data.

According to a tenth aspect of the present invention, in the flying object control system according to the present invention, the signal processing means operates on the basis of the measurement data in the flying object controller immediately after the emission of the radio source tracking flying object. It is configured to switch to an operation based on measurement data in the tracking flying object. This switching timing is, for example, the receiving sensitivity of the flying object,
It can be determined based on the elapsed time after launch, the distance from the flying object to the radio wave source, and the like.

According to an eleventh aspect of the present invention, in the flying object control system according to the present invention, the control data includes control data of a tuning frequency, and the tuning receiving means controls the tuning frequency based on a signal received by the receiving means. Is done.

According to a twelfth aspect of the present invention, there is provided a flying object control system, wherein the flying object controller controls an antenna for receiving a radio wave from a radio wave source and tunes reception of data by tuning to a received radio wave of a predetermined frequency. Means. Further, the signal processing unit predicts the appearance of another unknown radio wave source based on the measurement data obtained by the tuning reception unit of the flying object controller, and generates control data for tuning to the radio wave from the other radio wave source. It is configured to generate.

The signal processing means of the flying object controller uses the radio wave source identification means to predict the appearance of the next radio wave source that has not been transmitted yet, based on the radio wave transmitted from one radio wave source. The signal processing means generates control data for tuning to a radio wave from the other radio source, and the control data is transmitted from the flying object controller to the radio source tracking flying object. For this reason, it is possible to use a radio source identifying means outside the radio source tracking flying object to control the tuning receiving means of the flying object in advance so as to tune to the frequency of the radio source expected to appear.

According to a thirteenth aspect of the present invention, there is provided a flying object control method according to the present invention, wherein a first tuning reception step of performing data measurement in synchronization with a predetermined frequency of a radio wave received by a radio source tracking flying object is performed. A first communication step of wirelessly transmitting data from the radio source tracking flying object to the flying object controller, a signal processing step of obtaining control data in the flying object controller based on the measurement data received from the radio source tracking flying object, A second communication step of wirelessly transmitting the obtained control data from the flying object controller to the radio source tracking flying object.

The flying object control method according to the present invention includes a second tuning receiving step of performing data measurement in synchronization with a predetermined frequency of a radio wave received by the flying object controller, wherein the signal processing is performed. The step is configured to generate control data based on the measurement data at the flying object controller and the measurement data at the radio source tracking flying object.

According to a fifteenth aspect of the present invention, there is provided a flying object control method according to the third aspect, wherein a third tuning receiving step of performing data measurement in synchronization with a predetermined frequency of a radio wave received by the radio wave receiver is performed. A third communication step of wirelessly transmitting from the radio receiver to the flying object controller, wherein the signal processing step generates control data based on the measurement data at the radio receiver and the measurement data at the radio source tracking flying object. It is configured as follows.

[0028]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiment 1 FIG. 1 is a block diagram showing an example of the configuration of a missile system according to Embodiment 1 of the present invention, and shows a guidance system of a radio wave source tracking missile provided with signal processing means outside the missile. In the figure, 1 is a radio source tracking missile as a flying object, 2 is a base unit as a flying object controller, 11 is an angle tracking antenna, 12
Is a tuning receiving means, 13 is a data transmitting means, 14 is a data receiving means, 15 is a flight control means, 23 is a signal processing means,
Reference numeral 24 denotes a radio wave specification database.

The radio source tracking missile 1 includes a radio source tracking antenna 11, a tuning reception unit 12, a data transmission unit 13,
It comprises data receiving means 14 and flight control means 15. The base machine 2 is an aircraft on which the missile 1 is mounted and fired, and includes signal processing means 23 and a database 24 for missile flight control after firing.
The measurement data in the missile 1 is transmitted to the base unit 2 and subjected to signal processing in the base unit 2 to generate control data.
The control data is transmitted to the missile 1, and the missile 1 operates based on the control data. By such a method, the reception control and the flight control of the missile 1 can be performed.

That is, the tuning receiving means 12 measures the specification data of the radio wave received by the antenna 11, and the data transmission means 13 wirelessly transmits the specification data together with the flight data of the missile 1 to the base unit 2. Signal processing means 23
Determines the flight direction of the missile 1 based on the specification data and the flight data, generates flight control data, and generates reception control data of the tuning reception means 12.
At that time, the database 24 is used.

The generated flight control data and reception control data are wirelessly transmitted from the base unit 2 to the missile 1 and received by the data receiving unit 14. Data receiving means 14
Outputs the reception control data to the tuning reception means 12 and outputs the flight control data to the flight control means 15.
The tuning receiving means 12 performs target detection and measurement of radio wave specifications based on the reception control data. Flight control means 15
Performs flight control of the missile 1 based on the flight control data.

Next, the operation of each block will be described in more detail. The angle tracking antenna 11 receives a radio wave emitted from a radio wave source and outputs a reception signal to the tuning reception unit 12. Here, the angle tracking antenna 11 is formed of a spiral antenna having four beams, and a sum signal and a difference signal in the azimuth direction with respect to the missile machine axis direction of the missile 1 and the monopulse angle measurement method, and
The sum signal and the difference signal in the elevation direction are obtained.

FIG. 2 is an explanatory diagram for explaining an angle measuring method in the angle tracking antenna 11. P1 and P2 in the figure are the antenna pattern of the antenna 11, B1
Is a sum beam and B2 is a difference beam. The angle tracking antenna 11 has two antenna patterns in the azimuth direction and the elevation direction, respectively, and both function according to the same principle. The sum signal (sum beam B1) is obtained by adding the output of the antenna pattern P1 and the output of the antenna pattern P2, and the difference signal (difference beam) is obtained by subtracting the output of the antenna pattern P2 from the output of the antenna pattern P1. It is. Since the difference pattern has a monotonically increasing region, the input direction can be obtained from the level.

The tuning receiving means 12 tunes to a predetermined frequency band, measures target radio wave data, obtains a target azimuth, and outputs these data to the data transmitting means 13. The frequency band to be tuned is usually transmitted as frequency data from the base unit 2 to the missile 1 before the missile 1 is launched. Upon detecting the target radio wave in the tuning frequency band, the tuning receiving means 12 measures the data of the radio wave (for example, azimuth, frequency, pulse repetition period, pulse width, power). Here, the target azimuth is calculated based on the sum signal and the difference signal from the antenna system 11 as an angle between the missile machine axis and the target direction, and is obtained for each of the azimuth direction and the elevator direction. The radio wave specifications obtained in this manner are transmitted to the data transmitting means 13.
Output to

The data transmitting means 13 is the tuning receiving means 12
Is transmitted to the base unit 2 together with the flight data of the missile 1 (for example, position, flight speed, and flight direction). The flight information of the missile 1 is obtained by using GPS or inertial navigation means (not shown). Mother machine 2
Receives transmission data from the missile 1, the signal processing means 23 determines the direction in which the missile 1 should fly based on the received data, and generates flight control data.

The radio wave specification database 24 is a database created in advance based on known radio wave specifications relating to various targets, and includes characteristic data of radio wave specifications. When the radio wave specification is measured for an unknown target, the type of the target can be determined by comparing the radio wave specification with the radio wave specification database 24.

The signal processing unit 23 checks the radio wave data measured by the missile 1 against the database 24, discriminates the radio wave emitted from the target from the disturbance radio wave, and determines the target direction. When radio waves of similar specifications are received from other directions, discrimination is made based on the change rate of the target direction. When the target direction is determined in this way, the direction in which the missile 1 should fly is calculated so that the target direction maintains a predetermined value.

The predetermined value for maintaining the target direction is, for example, 0 ° when the target moves at a low speed,
When moving at high speed, the accrual angle for performing the proportional navigation can be set. That is, for a low-speed target, the flight direction in which the missile 1 flies straight to the measured target position is determined. On the other hand, for a high-speed target, a flight direction in which the target position is added to the accrual angle is calculated. The accrual angle is determined based on, for example, the distance to the target, the moving speed, and the like.

When the target performs the avoidance action by changing the frequency, the tuning frequency of the tuning receiving means 12 is changed to search for the target radio wave, and the tuning receiving means 12 is set to receive the radio wave from the same target again. Control. That is, the reception control data generated by the signal processing unit 23 is transmitted from the base unit 2 to the missile 1. The transmission data is received by the data receiving means 14, and the synchronous receiving means 12 operates based on the received data.

When the target stops transmitting radio waves, the flight direction is determined by predicting a future position from data detected earlier. That is, the target position can be estimated based on the position and the flight direction of the missile 1 itself and the target direction and the distance to the target obtained by the signal processing unit 23 by the above method. The distance to the target is calculated from the received power. The signal processing unit 23 can also calculate the flying direction of the missile 1 by calculating the estimated rate of change of the target position to predict the future position.

When the flight direction of the missile 1 is determined, the signal processing means 23 generates flight control data of the missile 1,
The transmission from the base unit 2 to the missile 1 is performed. This transmission data
The data is received by the data receiving unit 14. The flight control means 15 controls the wings and the like of the missile 1 based on the received data, so that the flight control of the missile 1 is performed so as to head in the flight direction determined by the signal processing means 23.

In this missile system, since the signal processing means 23 is mounted on the base unit 2, a signal processor with higher performance can be used as compared with the conventional missile system mounted on the missile 1. That is, by mounting on the base unit 2, restrictions due to weight, size, cost, and the like are greatly reduced, and advanced flight control can be realized. Further, the ability to predict the future position of the target when the target stops radio wave transmission, the ability to discriminate the target from disturbance radio waves, and the like can be improved.

Embodiment 2 In the first embodiment, an example of a missile system that measures data of a radio source obtained by the missile 1 has been described. In the present embodiment, a missile system that also measures data of a radio source in the base unit 2 will be described. .

FIG. 3 is a block diagram showing an example of the configuration of a missile system according to Embodiment 2 of the present invention. A signal processing means is provided in a base unit, and the position of a radio wave source is determined based on the missile and the received radio waves in the base unit. The guidance system of the radio source tracking missile for estimating is shown. In the figure, 1 is a radio source tracking missile, 2 is a base unit, 11 and 21 are angle tracking antennas, 12 and 22 are tuning receiving means, 13 is data transmitting means, 14 is data receiving means, 15 is flight control means,
23 is a signal processing means, and 24 is a radio wave specification database. The difference from the system of FIG. 1 is that the base unit 2 includes an angle tracking antenna 21 and a tuning reception unit 22.

The missile 1 is similar to the missile 1 in FIG. The antenna 21 and the tuning receiving means 22 of the base unit 2 are the same as the antenna 11 and the tuning receiving means 12 of the missile 1, respectively, and seek data of the same radio source at different positions. That is, each of the missile 1 and the base unit 2 receives radio waves from the same target and obtains radio wave specification data. Then, the obtained specification data are both input to the signal processing means 23.

Therefore, the signal processing means 23 obtains the respective positions of the missile 1 and the base unit 2 and the direction of the radio source viewed from each. That is, the position of the missile and the azimuth of the radio wave source viewed from the missile are determined by the tuning receiving means 1
2 and transmitted from the data transmission means 13. Further, the position of the base unit 2 is obtained using a known method, for example, a GPS or inertial navigation unit (not shown), and the direction of the radio wave source viewed from the base unit 2 is obtained by the tuning reception unit 22. The signal processing unit 23 can accurately determine the position of the radio wave source based on the principle of triangulation based on these data.

In addition, even if either the missile 1 or the base unit 2 receives a disturbance from the same direction as the radio wave source and it is difficult to discriminate the radio wave from the target from the disturbance,
On the other hand, there is a possibility that the influence of disturbance can be excluded from the difference in position. That is, in the first embodiment, if the missile receives a disturbance of the same specification data as the target, and the azimuth change rate is small, the missile may be directed to the disturbance. In the embodiment, the measurement accuracy of the target position can be improved, and the possibility of eliminating the influence of disturbance increases.

According to the present embodiment, with respect to the radio waves from the same target, both the missile 1 and the base unit 2 determine the specification data, and the signal processing means 23 determines the target direction based on the specification data. By doing so, the performance of eliminating the influence of disturbance can be improved.

Embodiment 3 In the second embodiment, the example of the missile system that performs the triangulation between the missile and the base unit has been described. However, the position of the radio wave source may be estimated by the triangulation between the two missiles in the same manner. Also in this case, the influence of disturbance can be eliminated.

FIG. 4 is a block diagram showing an example of the configuration of a missile system according to Embodiment 3 of the present invention. A signal processing means is provided in a base unit, and a radio wave source is determined based on radio waves received by two different missiles. The guidance system of the radio source tracking missile for estimating the position is shown. 1A, 1B in the figure
Is a radio source tracking missile, 2 is a base unit, 11 is an angle tracking antenna, 12 is a tune receiving unit, 13 is a data transmitting unit,
14 is a data receiving means, 16 is a flight control means, 23 is a signal processing means, and 24 is a radio wave specification database. The base unit 2 is an aircraft on which the missiles 1A and 1B are mounted and fired, and includes a signal processing unit 23 and a database 24 for controlling flight of each of the missiles 1A and 1B after firing.

The missiles 1A and 1B correspond to the missile 1 shown in FIG.
Is the same as In each of the missiles 1A and 1B, the angle tracking antenna 11 receives a radio wave from the same radio wave source, and the tuning reception unit 12 measures radio wave specification data. The measured radio wave specification data is transmitted from the respective data transmission means 13 to the same base unit 2 together with the missile flight information. The signal processing means 23 of the base unit 2 estimates the position of the radio source by triangulation based on these data. Based on the position of this radio source, each missile 1A,
1B is determined, and respective flight control data is generated. The flight control data of the missiles 1A and 1B are transmitted to the corresponding missiles and received by the data receiving means 14 of each missile. In this case, the influence of disturbance can be eliminated.

Embodiment 4 FIG. In the first and third embodiments, an example of a missile system in which the base unit includes a missile and a signal processing unit will be described. In the second embodiment, the base unit further includes a data measurement unit (antenna and tuning reception unit) of a radio source. An example of a system to do this has been described. On the other hand, in the present embodiment, a missile system in which these elements are distributed and mounted on a plurality of aircraft capable of data link will be described.

FIG. 5 is a block diagram showing an example of the configuration of a missile system according to the fourth embodiment of the present invention. The missile system in which the mounting of the missile, the radio wave reception processing, and the signal processing are shared by different units, respectively. It is shown. In the figure, reference numeral 1 denotes a missile, 2A denotes a base machine on which a missile is mounted and launched, 2B denotes a base machine that receives radio waves from a radio wave source and measures specification data, and 2C performs signal processing and transmits control data to the missile 1. It is a mother machine. The mother machines 2A, 2B, 2C
The two can communicate with each other and control the missile 1 in cooperation with each other.

The missile 1 is configured similarly to the missile 1 in FIG. The base unit 2B includes an antenna 11, a tuning reception unit 12, and a data transmission unit 13. The base unit 2C measures radio wave specification data in the same manner as the missile 1.
Wirelessly. When the missile 1 is fired from the base unit 2A, data measurement of the same radio wave source is started by the missile 1 and the base unit 2B.

The missile 1 and the base unit 2B measure the specification data for the same radio wave source, and the obtained measurement data is transmitted to the base unit 2C together with the flight data of the missile 1 and the base unit 2B. The base unit 2C is the same as the base unit 2 in FIG. 4, and the signal processing unit 23 estimates the position of the radio source by triangulation based on data from the missile 1 and the base unit 2B.
Then, the flight direction of the missile 1 is obtained from the position of the radio wave source, and transmitted to the missile 1 as flight control data.

According to the present embodiment, a missile system can be configured by using a mother machine equipped with missile launch, a mother machine measuring radio wave data, and a mother machine performing signal processing as separate aircraft.

In each of the above embodiments, an example was described in which the missile launching device and the base machine serving as the missile control device were an aircraft, but the missile control device to which the present invention is applied is not limited to an aircraft. However, missiles are not limited to those launched from aircraft. Similarly, the mother machine that measures the radio wave specification data is not limited to an aircraft.
These mother machines may be, for example, ships, vehicles, ground fixed facilities, and the like.

Embodiment 5 FIG. In the first to fourth embodiments,
Immediately after the launch of the missile, the case where the radio wave source is received by the angle tracking antenna 1 of the missile and flight control is performed is shown.
In the present embodiment, a description will be given of a case where flight control is performed based on radio wave source data received by an antenna of a base unit in a stage from launch to intermediate guidance.

FIGS. 6 and 7 are explanatory diagrams showing an example of the operation of the missile system according to the fifth embodiment of the present invention. The missile 1 and the base unit 2 are both provided with angle tracking antennas 11 and 21 and tuning receivers 12 and 22. On the other hand, the signal processing means 23 is provided only in the mother device 2. The signal processing unit 23 generates flight control data of the missile 1 based on the radio wave data measured by the missile 1 or the base unit 2.

That is, the signal processing means 23 transmits the missile 1
If the reception sensitivity of either one of the base unit 2 and the base unit 2 is insufficient, the flight control data of the missile 1 can be generated based on the radio wave specification data measured on the other side. FIG. 6 is a diagram illustrating a case where data measurement of a radio source is performed by the base unit 2, and FIG. 7 is a diagram illustrating a case where data measurement of a radio source is performed by the missile 1.

In FIG. 6, the antenna 21 of the base unit 2 receives a radio wave from a radio wave source, and the tuning receiving means 22 measures the specification data of the received radio wave. The signal processing unit 23 generates flight control data of the missile 1 using the database 24 based on the measurement data. At this time, missile 1
The flight information of the missile 1 transmitted from is used. The generated flight control data is transmitted to the missile 1, received by the data receiving unit 14, and the flight control unit 15 controls the flight.

In FIG. 7, the antenna 11 of the missile 1 receives a radio wave from a radio wave source, and the tuning reception means 22 measures the specification data of the received radio wave. The signal processing unit 23 generates flight control data of the missile 1 using the database 24 based on the measurement data and the flight information received from the data transmission unit 13. The generated flight control data is transmitted to the missile 1, received by the data receiving unit 14, and the flight control unit 15 controls the flight.

Immediately after the missile 1 is launched, the angle tracking antenna 11 and the tuning receiving means 12 mounted on the missile 1
Is insufficient, but the base unit 2 may be able to receive signals sufficiently. This tendency is particularly strong in the case of a tracking radar device in which the radio wave source is tracking the base unit 2. However, even in such a case, the sensitivity of the missile 1 is improved in the terminal guidance in which the missile 1 approaches the target.

That is, in the intermediate guidance after the missile launch, the antenna 21 of the base unit 2
It is preferable that the flight control is performed based on the specification data measured by the antenna, and in the terminal guidance, the flight control is performed based on the specification data received by the antenna 11 of the missile 1 and measured by the tuning reception unit 12.

For this reason, the measurement data used by the signal processing means 23 is switched from the reception signal of the base unit 2 to the reception signal of the missile 1 during the missile flight. The switching timing is determined based on, for example, the receiving sensitivity obtained from the received power of the missile 1, the elapse of a predetermined time after launch, the distance from the missile to the target, and the like.

According to the present embodiment, the signal processing means used for normal flight control using a missile antenna or the like and the signal processing means used for intermediate guidance using the base station antenna are combined by one signal processor. It can be shared.

Embodiment 6 FIG. By using a radio source identification device, based on radio waves transmitted from a certain radio source,
It may be possible to predict the appearance of the next radio source that has not yet been transmitted. When the base unit 2 is equipped with such a radio source identification device, the signal processing unit 23 uses the radio source identification device to set the missile tuning reception unit 12 in advance to the frequency of the radio source that is expected to appear. Can be controlled to be synchronized with

FIGS. 8 and 9 are explanatory diagrams showing an example of the operation of the missile system according to the sixth embodiment of the present invention. The signal processing means 23 in the figure is configured to include a radio wave source identification device (not shown).

In FIG. 8, the antenna 21 of the base unit 2 receives a radio wave from the radio wave source 1, and the tuning receiving means 22 measures the data of the received radio wave. The signal processing means obtains the frequency of the radio wave source 2 that has not yet emitted a radio wave but is expected to emit a radio wave based on the specification data, and generates reception control data. The generated reception control data is transmitted to the missile 1. The data is received by the data receiving unit 14. The tuning receiving means 12 controls the tuning frequency based on the reception control data.

FIG. 9 shows a state in which the radio wave source 2 starts emitting radio waves, the antenna 1 of the missile 1 receives the radio waves, and the tuning receiving means 12 tunes. At this time, base unit 2 receives the radio wave from radio wave source 1 and the radio wave from radio wave source 2.

This embodiment is particularly effective when the frequency of the radio wave first received by the base unit is in a region where the missile cannot be received. Further, when the next radio wave source appears while the missile is flying, the missile can track the angle of the radio wave source at a short distance, so that there is an effect that the radio wave source side has less room to take countermeasures. The timing at which the base unit 2 predicts the appearance of a new radio wave and tunes the missile 1 to that frequency may be during flight of the missile or during preparation for flight.

[0072]

According to the present invention, the radio source tracking flying object is
Data measurement is performed in synchronization with the received radio wave from the radio wave source, and the measured data is wirelessly transmitted and the control data is wirelessly received. Therefore, the flying object can be controlled using the signal processing means outside the radio wave tracking flying object. Therefore,
The missile guide can be made small and inexpensive. In addition, advanced flight control becomes possible, and it is possible to stop transmission on the radio wave source side and cope with countermeasures such as disturbance radio waves.

[Brief description of the drawings]

FIG. 1 is a block diagram showing an example of the configuration of a missile system according to a first embodiment of the present invention, which shows a guidance system for a radio wave source tracking missile provided with signal processing means outside the missile.

FIG. 2 is an explanatory diagram for explaining an angle measurement method in the angle tracking antenna 11.

FIG. 3 is a block diagram showing an example of a configuration of a missile system according to a second embodiment of the present invention, in which a signal processing unit is provided in a base unit and a position of a radio source is estimated based on radio waves received by the missile and the base unit. The guidance system of the radio source tracking missile is shown.

FIG. 4 is a block diagram showing an example of a configuration of a missile system according to a third embodiment of the present invention, in which a signal processing unit is provided in a mother machine, and a position of a radio wave source is estimated based on radio waves received by two different missiles. A guidance system for a radio source tracking missile that is moving is shown.

FIG. 5 is a block diagram showing a configuration example of a missile system according to a fourth embodiment of the present invention, which shows a missile system in which mounting of a missile, radio wave reception processing, and signal processing are shared by different airframes. ing.

FIG. 6 is an explanatory diagram showing an example of the operation of the missile system according to the fifth embodiment of the present invention, and is a diagram showing a state before switching in which data of a radio source is measured by the base unit.

FIG. 7 is an explanatory diagram showing an example of the operation of the missile system according to Embodiment 5 of the present invention, and is a diagram showing a state after switching in which data of a radio source is measured by the missile.

FIG. 8 is an explanatory diagram showing an example of the operation of the missile system according to the sixth embodiment of the present invention, and shows how a new radio wave is predicted to appear based on a received radio wave.

FIG. 9 is an explanatory diagram showing an example of the operation of the missile system according to Embodiment 6 of the present invention, and shows a state in which the missile receives a newly appearing radio wave and is tuned.

FIG. 10 is a block diagram showing a configuration example of a conventional radio wave source tracking missile, showing a guidance system control system.

[Explanation of symbols]

1,1A, 1B Radio source tracking missile (flying object), 11
Angle tracking antenna, 12 tuning reception means, 13 data transmission means, 14 data reception means, 15 drive control means, 2, 2C base unit (flying object control unit), 2A base unit (flying object mounted unit), 2B base unit (radio wave reception) ), 20 angle tracking antenna, 12 tuned receiving means, 23 signal processing means, 24 radio wave specification database.

Claims (15)

[Claims] An antenna for receiving a radio wave from a radio wave source, a tuned reception unit for performing data measurement in synchronization with a reception radio wave of a predetermined frequency, a transmission unit for wirelessly transmitting measured data, And a receiving means for wirelessly receiving the control data obtained by the radio wave source tracking flying object. 2. The transmitting means transmits flight information of the flying object together with the measurement data. The control data includes flight control data obtained based on the measurement data and the flight information. 2. The apparatus according to claim 1, further comprising: flight control means for performing flight control based on the signal.
Radio source tracking flying object described in. 3. The control data according to claim 1, wherein the control data includes control data of a tuning frequency, and the tuning receiving means controls the tuning frequency based on a signal received by the receiving means. Radio source tracking flying object described. 4. A flying object control system comprising a radio source tracking flying object and a flying object controller, wherein the radio source tracking flying object is tuned to an antenna for receiving a radio wave from a radio source and a reception radio wave of a predetermined frequency. Tune receiving means for performing data measurement, transmitting means for wirelessly transmitting the measured data to the flying object controller, and receiving means for wirelessly receiving control data from the flying object controller, wherein the flying object controller A flying object control system comprising signal processing means for obtaining control data based on measurement data received from a source tracking flying object. 5. A flying object control system comprising a radio source tracking flying object and a flying object controller, wherein the radio source tracking flying object is tuned to an antenna for receiving a radio wave from a radio source and a reception radio wave of a predetermined frequency. Tuning receiving means for performing data measurement, transmitting means for wirelessly transmitting the measured data together with the flight information of the flying object to the flying object controller, receiving means for wirelessly receiving control data from the flying object controller, Flight control means for performing flight control based on control data, the flying object control device includes signal processing means for obtaining control data based on measurement data received from the radio source tracking flying object and flight information of the flying object. A flying object control system, characterized in that: 6. The flying object control device includes an antenna for receiving a radio wave from a radio wave source, and a tuned reception unit for performing data measurement in synchronization with a reception radio wave of a predetermined frequency. The flying object control system according to claim 5, wherein the control data is generated based on the measurement data of the body controller and the measurement data of the radio source tracking flying object. 7. An antenna for receiving a radio wave from a radio wave source, and a tuning receiving means for performing data measurement in synchronization with a received radio wave of a predetermined frequency, and wirelessly transmits the measured data to the flying object controller. The flying object control system according to claim 5, further comprising a radio wave receiver, wherein the signal processing means generates control data based on measurement data in the radio wave receiver and measurement data in the radio source tracking flying object. . 8. The flying object control system according to claim 7, wherein the radio wave receiver is another radio source tracking flying object different from the radio source tracking flying object. 9. A flying object control system comprising a radio source tracking flying object and a flying object controller, wherein the radio source tracking flying object is tuned to an antenna for receiving a radio wave from the radio source and a reception radio wave of a predetermined frequency. Tuning receiving means for performing data measurement; transmitting means for wirelessly transmitting the measured data together with the flight information of the flying object to the flying object controller; receiving means for wirelessly receiving control data from the flying object controller; Flight control means for performing flight control based on control data, wherein the flying object controller receives an antenna from a radio wave source, And a signal processing means for generating control data based on either the measurement data in the flying object controller or the measurement data received from the radio source tracking flying object. Shokarada control system. 10. The method according to claim 1, wherein the signal processing means operates based on the measurement data in the flying object controller immediately after the launch of the radio source tracking flying object, and thereafter switches to an operation based on the measurement data in the radio source tracking flying object. The flying object control system according to claim 9, wherein: 11. The apparatus according to claim 4, wherein said control data includes control data of a tuning frequency, and said tuning receiving means controls a tuning frequency based on a signal received by said receiving means. The flying object control system according to any one of the above. 12. A flying object controller, comprising: an antenna for receiving a radio wave from a radio wave source; and a tuned reception unit for performing data measurement in synchronization with a reception radio wave of a predetermined frequency. 12. The flying device according to claim 11, wherein an appearance of another unknown radio wave source is predicted based on measurement data in the controller, and control data for tuning to a radio wave from the other radio wave source is generated. Body control system. 13. A first tuning receiving step of performing data measurement in synchronization with a predetermined frequency of a radio wave received by a radio source tracking flying object, and transmitting the measured data from the radio source tracking flying object to a flying object controller. A first communication step of wirelessly transmitting, a signal processing step of obtaining control data in the flying object controller based on the measurement data received from the radio source tracking flying object, and transmitting the obtained control data from the flying object controller to the radio source. A second communication step of wirelessly transmitting to the tracking flying object. 14. A second tuning receiving step for performing data measurement in synchronization with a predetermined frequency of a radio wave received by the flying object controller, wherein the signal processing step includes a step of measuring data and a radio wave source in the flying object controller. 14. The flying object control method according to claim 13, wherein control data is generated based on measurement data of the tracking flying object. 15. A third tuning receiving step of performing data measurement by tuning to a predetermined frequency of a radio wave received by a radio wave receiver, and a third step of wirelessly transmitting the measured data from the radio wave receiver to the flying object controller. 14. The flying object according to claim 13, further comprising a communication step, wherein the signal processing step generates control data based on measurement data in the radio wave receiver and measurement data in the radio source tracking flying object. Control method.