JPS58204382A - Guided air frame system - Google Patents

Abstract

PURPOSE:To increase equivalently the gain a phased array antenna, by correcting a launching forecasting angle by a target speed in case when a launching forecasting angle calculated in accordance with target information which is caught is larger than an angle decided in advance. CONSTITUTION:A radar 2 radiates radio waves 3 to a target, receives a reflecting signal 4, and extracts targer information. A future position of the target, a forecasting hit point and a launching forecasting angle are calculated by a control computer 5 from said target information. In case when a forecasting angle is large than a value set in advance, a forecasting angle correcting circuit 12 subtracts the forecasting angle by some angle being proportional to a target speed, and gives a command to a launching machine 6 as to the correcting forecasting angle.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a guided missile system using radio wave guidance, and when the expected launch angle calculated to point to the expected hit point of a target is larger than a preset angle, In other words, if the gain of the phased array antenna mounted on a guided flying vehicle becomes smaller than a certain value, the angle of view of launch will be reduced to equivalently increase the gain of the phased array antenna to detect the target early. It is characterized by the fact that

Figure 1 shows a conventional guided spacecraft system9.
In the figure, (1) is the target, (2) is the radar that emits radio waves (3) to target +11, receives the reflected signal of (4), and extracts the target information, and (5) is the radar that detects the target from the target information. A control computer that calculates the future position, predicted hit point, and firing angle (
6) is the launcher, and (7) is the guiding force body.

Figure 2 shows the internal configuration of a guidance device for a guided spacecraft equipped with a phased array antenna, which is currently being developed around the world. In Figure 1, (8) is the phased array antenna, and (9) is the transmitter. machine, O(l is the reception signal processing unit, aD is the beam control computer. Figure 3 is a state diagram when the guided flying vehicle is launched, (&) is the body axis of the guided flying vehicle, ( θ1) is the reference angle between the target and the guided projectile.

(b) is the predicted hit point, and R) is the expected angle.

In this conventional steering system, a phased array antenna is mounted and fixed at right angles to the body axis of the guided vehicle in order to electronically scan the antenna beam. On the other hand, the gain of a phased array antenna decreases in proportion to 1 (XIS'7), where the deviation angle from the front direction is V It decreases by (the square of cDsψ-).

FIG. 4 shows an embodiment of this invention, (1) to (7).
) is the same as in Figure 1. 03 is a line-of-sight angle correction circuit, and when the line-of-sight angle is larger than a preset value, it subtracts the line-of-sight angle by a certain angle proportional to the target speed, and commands the corrected line-of-sight angle to the launcher (6). It is something. In other words, when the beam angle of the phased array antenna mounted on the guided flying object is larger than a preset value, that is, when the gain of the phased array antenna is lower than the required value, the line-of-sight angle is corrected. By doing so, the target detection ability is maintained or increased in an equivalent manner, and early detection of the target is made possible. Therefore, by the guided projectile detecting the target early and starting tracking.

The guidance time is increased, the miss distance is reduced, and the $4 capability of the system is increased.

As described above, according to the present invention, even if the line of sight becomes large, it can be corrected by the target speed, thereby minimizing the gain reduction of the phased array antenna, optimizing the detection ability of the entire guidance device, and Early growth is possible.

[Brief explanation of drawings]

Figure 1 is a configuration diagram showing a conventional guided flying vehicle system, Figure 2 is a schematic internal configuration diagram of a guided flying vehicle equipped with a phased array antenna, and Figure 8 is a diagram of the state of the guided flying vehicle during launch. , FIG. 4 is a diagram showing an embodiment of the guided flying object system according to the present invention, in which (1) is a target, (
2) is the radar, (3) is the wave wave, +401 reflected signal, (5
) is the control computer, (6) is the launcher, (7) is the guided aircraft, (8) is the phased array antenna, (9) is the transmitter, al) is the reception signal processing unit, C11l is the beam control computer, Q'3 is a prospect angle correction circuit. In the drawings, the same or corresponding parts are designated by the same reference numerals. Figure 2

Claims (1)

[Claims] In a guided spacecraft system consisting of a guided spacecraft equipped with a phased array antenna, a radar that obtains target information, a spacecraft launcher, and a control computer, control is performed based on target information captured by the radar. If the expected launch angle calculated by the computer is larger than a predetermined angle, the expected angle correction circuit commands the launcher to subtract an angle proportional to the target speed from the expected launch angle, and the guided missile 1. A guided flying object system configured to equivalently increase the gain of a faceted array antenna by emitting .