JPS6334400B2 - - Google Patents

Description

[Detailed description of the invention]

The present invention provides a radar capable of searching and tracking a target by driving a ventil beam using an electronic scanning antenna of the target search and tracking radar.
Binary modulated transmission waves using a specified pseudo-random code are used as transmission radio waves to search and track the target, and on the other hand, when intercepting a target at a long distance with a missile, the fired missile is transmitted using the electronic scanning antenna mentioned above. Tracking is performed and intermediate guidance specifications are sent out. In this case, the transmission frequency band is the same as when tracking the target, but a binary modulated transmission wave is used using a different designated code, and the missile is included in the designated code. This method inserts the intermediate guidance specifications of the missile that is about to fly, and the missile that is about to fly receives the missile tracking transmission wave based on the transmission frequency and missile designation code that are synchronized before launch, and uses the corresponding designation code. Decipher the target to obtain intermediate guidance specifications and fly in the direction of the updated intercept point. Modify the route and continue approaching, and when the missile approaches the target and is within a certain distance, the missile will send another radio wave. This missile fire control system intercepts a target by transmitting signals from itself and performing active homing, and is characterized by the above system in that it is not necessary to have a missile guidance illuminator for each interception target. Conventionally, the method of searching and tracking a target with radar and intercepting it with a missile is the passive method as a missile.
There are semi-active and active methods, and one of these methods has been adopted. In recent years, with the advancement of radar and missile technology, there is a tendency for the above-mentioned single method to be combined. For example, if the launched missile is far from the target, the predicted intercept point will change while the missile is about to fly, so in this case intermediate guidance is required to fly the missile to a new intercept point every moment. Such communication means are employed between the missile and the radar device. When the missile approaches the target, it changes to semi-active or active mode, and intercepts the target using radio wave guidance for a short period of time. Interception of targets with missiles under such complex radio wave environments has been considered. In the above case, the command link method as a means of intermediate guidance of the missile requires communication using radio waves in a different frequency band from that for target tracking, which requires a separate microwave system and requires hardware. There will be more. In addition, in the case of a missile control system that uses a semi-active system for final guidance, as many illuminators as the number of targets to be intercepted are required, and a radar transmitter for the illuminators is required. In this invention, the radio waves used for intermediate guidance use the same frequency range as the radio waves used for target tracking, but by code-modulating the transmitted radio waves, the code for target tracking and the code for missile tracking and intermediate guidance By using different codes, target tracking and missile intermediate guidance can be performed by the same microwave electronic scanning antenna/radar. In addition, the Let's Fly missile detects that it is close to the target and intercepts the target by emitting radio waves and active homing. The above device allows multi-target operation without the need for illuminator radar or command link, and without the need for large amounts of hardware due to the configuration of electronic scanning antenna radar equipment and terminal McTive missile. Interception is possible. The details of this invention will be explained using FIGS. 1 to 3. Figures 1a and 1b are diagrams showing the concept of the present invention, and the transmitted radio waves of the electronic scanning antenna A in Figure 1a form a Bensil beam B, but when tracking the target C, the transmitted radio waves are As shown in Figure b, when tracking the missile E launched from the missile launcher D, which is binary modulated with a pseudo-random code, the transmitted radio wave of the pencil beam F is converted into a different designated code containing intermediate guidance information as shown in Figure 1B. Indicates binary modulation. Furthermore, even if the pencil beams for target tracking and missile tracking overlap, code identification processing is performed based on the characteristics of the pseudo-random code, so neither the target search and tracking radar nor the missile itself will make false detections. . FIG. 2 is an example in which the transmitted radio waves are pulses, and conceptually shows the coding for target tracking and missile tracking. A in FIG. 2 is an example of a transmission pulse train during target tracking. Each transmission pulse consists of seven divided sections, and the seven sections are (1,
The transmitting RF frequency is binary modulated according to a pseudo-random code (1 is 0°, -1 is
180° phase inversion). The relationship between the transmission pulse train A in Figure 2 is that the pseudorandom code is 1 for the first pulse A1 and the next transmission pulse A2.
It has a code shifted by one cycle, and the next transmitted pulse A3 also has a code shifted by one cycle. With this code arrangement, the target reflected wave due to pulse A1 and the target reflected wave due to pulse A2 are not mistakenly detected in the radar receiver due to the nature of the autocorrelation function of the pseudorandom code, and the target distance can be detected. give the means. As an example, in Figure 2, pseudorandom code A
Correlation function between 1 and A2 <A1, A1>=7, A1
It is shown that the correlation function between and A2 is <A1, A2>=-1. In the radar receiver, by performing the above correlation process, the transmitted pulse A1
The target reflected wave for the target can be extracted. B in Figure 2 is an example of a transmission pulse train during missile tracking.The transmission pulse B1 consists of 7 sections, and in the 7 sections, the transmission RF frequency is binary according to the code indicated by (1, -1 code). Modulation (1 is 0°, -
1 indicates that the phase is inverted by 180°. The first three sections of the seven code sections of the transmission pulse train B1, B2, B3, ... all have the same code, indicating that they are transmission pulses for missile tracking, and the information is transmitted by the code contents of the three sections. The last four sections indicate the data content. For example, the first three sections of B1, B2, and B3 are

If [Formula] indicates that it is the angle change information of the predicted intercept point, then the remaining 4 sections of the code 7 section of the transmission pulse B1 are

A rule is made in advance such that the following formula indicates the start of data, the next four sections of the transmission pulse B2 indicate the azimuth error angle, and the four sections of the next transmission pulse B3 indicate the elevation error angle. Therefore, in missile tracking, the missile about to fly receives the above-mentioned transmitted radio waves, decomposes and identifies the RF modulation code of the received pulse, and then
If the code of the section is the same during reception over a certain period of time, it will be taken in as missile intermediate guidance data, and if it is not the same, it will be rejected. Before a missile is launched, it is tuned by being given a transmission RF frequency used for missile tracking by a radar control system inside the missile launcher. Figure 3 is a block diagram of the missile fire control system (hereinafter referred to as this system). 1 in FIG. 3 is an overall block diagram of the radar control system, which includes an operator console section 2, a radar data processor (hereinafter abbreviated as RDP) 3, a weapon control processor (hereinafter abbreviated as WCP) 4, and a code controller. Generator exciter section (hereinafter abbreviated as CDE) 5, transmitter section 6, beam control section (hereinafter abbreviated as BSC) 7,
It is composed of a phased array antenna section 8, a receiver section 9, a radar signal processing section 10, and an external interface section 11. 12 consists of missiles and missile launchers. The operator console section 2 in Fig. 3 is a device that performs man-machine interface between this device and the device/operator.
4, as well as displaying radar search/tracking status and determining missile interception. After starting and controlling the entire system based on the command from the operator console section 2, the RDP 3 transmits the radar control signal 21 to the CDE 5, the transmitter section 6, the BSC 7, the receiver section 9, and the radar signal processing section 1.
Send to 0. The signals 21 commonly include a radar mode designation, a PRF designation, a device timing signal, a tracking target command, a missile tracking command, and a device BIT command. In addition, after RDP3 performs radar control, BSC
The target predicted coordinate signal 22 is sent to 7, but
The signal 22 becomes a missile predicted coordinate signal during missile tracking. The BSC 7 receives the signal 22, quickly calculates a phase-amplitude signal 23 for forming an electronic scanning beam pattern, and sends it to the phased array antenna section 8. Phased array antenna section 8 forms an electronic scanning beam pattern according to signal 23. RDP3 also provides local oscillator selection signal 25 to CDE5 according to the radar mode.
It outputs a code designation signal 26 for transmission radio waves and intermediate guidance data 27 for missile tracking. The CDE 5 selects the local oscillator frequency, which is the basis of the transmission frequency, based on the above signal 25, and multiplies it to the transmission RF.
The code designation signal 26 forms a pseudo-random code during target tracking, and the RF signal is binary-modulated for each transmission pulse to form a coded transmitter drive signal 31 and sent to the transmitter unit 6.
sent to. When tracking a missile, the code becomes a code containing missile intermediate guidance data and the RF signal is binary modulated. Further, in this device, it is possible to change the frequency over a wide band using the local oscillator selection signal 25 described above. The CDE 5 also receives a coded first LO signal 32, an uncoded second LO signal 33, and a basic master oscillator signal 34 for reception processing.
The signal is sent to the receiver section 9. The transmitter unit 6 RF amplifies the encoded transmitter drive signal 31 according to the device timing signal from the RDP 3, sends the transmitted RF signal 35 to the phased array antenna unit 8, and transmits the electronic scanning beam pattern. Transmit into space according to. It is also used for missile tracking from the transmitter section 6.
A portion of the RF signal is sent to the missile launcher to frequency tune the missile. The transmitted radio wave is reflected from the target or the missile about to fly, is received again by the phased array antenna section 8, and is sent to the receiver section 9 as a signal 36 which is combined into sum and difference components by the comparator section. The receiver section 9 converts the signal 36 into a distance RF signal,
The elevation error RF signal and the azimuth error RF signal are inputted, mixed with the coded first LO signal 32 from the CDE 5, code conversion processing is performed, and code correlation is taken. As a result of code correlation, only received waves having the same code have a large output. This output is further mixed with a second LO signal 33 and finally mixed with a basic master oscillator signal 34 to form a distance video signal 41, an elevation error video signal 42, and an azimuth error video signal 43, respectively.
The signal is sent to the radar signal processing section 10 as a signal. The receiver section 9 also performs AGC processing and ECCM processing. The radar signal processing unit 10 processes the above-mentioned signals 41 and 4.
After inputting 2,43 and A/D conversion, the receiver 9's
Level detection processing for AGC processing is performed and AGC
A control signal 44 is formed and sent to the receiver section 9;
Furthermore, if clutter removal filter processing, Doppler discrimination filter processing, code correlation processing, video integration, average value calculation processing, and target detection processing are target tracking,
In the case of tracking a missile about to fly, it is carried out in any case. The output of the radar signal processing unit 10 includes target detection distance number m45 and elevation error angle 4.
6. Azimuth error angle 47 is sent to RDP3. RDP3 is then the pulse repetition frequency (hereinafter
By repeating the above tracking process, a target detection distance number n45 for the PRF is obtained, and a combination of target detection distance numbers (m, m,
n, . . .), target distance data is finally obtained. Furthermore, an elevation error angle and an azimuth error angle are obtained as the average of the angular error data when the PRF is changed. RDP3 performs optimal metric filter processing on the target distance data, elevation error angle, and azimuth error angle in both target tracking and missile tracking.
Target tracking data 51 or missile tracking data 5
2 is obtained and sent to the WCP 4 and operator console section 2. Furthermore, the RDP 3 calculates the predicted target position or the predicted missile flight position as the output of the above-mentioned measurement filter, and sends it to the BSC 7 as a predicted target coordinate signal 22 that drives an electronic scanning pencil beam for moment-by-moment tracking. WCP4 performs missile interception performance and missile firing calculations based on target tracking data 51 from RDP3, calculates predicted intercept points, and uses control data 53 of missiles and missile launchers to
It is sent to the missile launcher 12 via the external interface 11. After the missile launch, WCP
4 uses the target tracking data 51 and missile tracking data 52 from the RDP 3 to perform correction calculations on the predicted intercept point, and sends it to the RDP 3 as missile intermediate guidance data 54. As mentioned above, when tracking a missile, the RDP 3 converts the data 54 from the WCP 4 and outputs it to the CDE 5 in the form of the signal 27, which is then sent as coded data of a transmission pulse. The above control data 53 and missile intermediate guidance data 54 for missiles and missile launchers calculated by the WCP 4 are also sent to the operator console unit 2 and displayed. As described above, according to the present invention, in a radar having an electronic scanning antenna, transmission radio waves in the same frequency range are used when searching and tracking a target and when tracking a launched missile that is about to fly. Pseudo-random coding of the transmitted radio waves makes it possible to track the target and the missile without interfering with each other, and it is possible to send intermediate guidance information to the missile about to fly, thus making it possible to track the target. Since there is no need for irradiation with radio waves for missile guidance, it is possible to obtain a missile fire control system that enables missile control guidance to a large number of targets without an illuminator.

[Brief explanation of drawings]

Fig. 1 is a diagram showing the concept of missile control according to the present invention, Fig. 2 is a diagram showing an example of coding of transmitted radio waves in the case of target tracking and in the case of tracking an in-flight missile. The figure is a block diagram of the missile fire control system. 1...Radar control device, 2...Operator console section, 3...Radar data processor (RDP), 4...Weapons control processor (WCP),
5... Code generator exciter section (CDE), 6... Transmitter section, 7... Beam drive control section, 8... Phased array antenna section,
9... Receiver section, 10... Radar signal processing section, 1
1...External interface section, 12...Missile and missile launcher.

Claims (1)

[Claims] 1 A means for searching and tracking a target using a pencil beam of an electronic scanning antenna as a target search and tracking radar, a means for transmitting radio waves by phase modulating them using a pseudo-random code, and a means for transmitting a missile to intercept the tracked target. means for controlling the launch of the launcher;
Radio waves in the same frequency range as target tracking are used as a means of predicting and tracking the trajectory of a launched missile using the pencil beam of an electronic scanning antenna, and as a means of intermediate guidance of the missile after launch, but are different from target tracking. means for transmitting intermediate guidance specifications to the missile using coded radio waves, and means for synchronizing the transmitted radio waves between the target search and tracking radar and the missile to match the usage codes before launching the missile, On the other hand, when attempting to fly as a missile, there is a missile fire control system comprising means for receiving and decoding intermediate guidance specifications and correcting the flight direction based on the specifications, and means for active homing to final guidance.