JPS59145980A - Guided flying object - Google Patents

Abstract

PURPOSE:To execute a conical scan at the time of searching a target, and to execute a tracking by a monopulse after catching said target by driving to switch a phase shifter by a prescribed system. CONSTITUTION:When a flying object is launched, a sine wave signal having the same amplitude and a phase different by pi/2 are impressed to the four groups of phase shifters 9-12 through a transmitter, a duplexer 15 and a comparator 14, a conical scan is executed by corresponding left and right, and upper and lower antennas 5-8, and a target search is executed to obtain the high probability of geometrical lock-on and to catch the target in the center of an antenna beam. In this state, when the target is caught and a lock-on signal is outputted from a lock-on deciding circuit 27, the constant-voltage of the same phase is impressed to the phase shifters 9-12 through a controller 13 and the comparator 14, and it is possible to execute a quick switching to a target tracking with a good characteristic against a radio wave disturbance by the monopulse by the antennas 5-7, etc.

Description

[Detailed Description of the Invention] The present invention relates to a guided flying object equipped with a radar device,
In more detail, when searching for a target, a guided flying object is equipped with a radar device that performs conical scanning to increase the probability of geometric lock-on, and after target acquisition, switches to monopulse tracking to perform tracking with enhanced Fi CCM performance. This is what we are trying to propose.

Conventional monopulse radar equipment installed on guided flying vehicles launched from the ground or from aircraft uses an antenna that points its antenna in the direction of the target aircraft (hereinafter referred to as the target aircraft) immediately before the guided flying vehicle launches. It is set and fired, and after five shots it captures the target aircraft within the anti-nano beam, locks on to it, and moves on to tracking. However, if there is a large error in setting the antenna in the direction of the target aircraft, or if the target aircraft moves rapidly, there is a drawback that the target aircraft cannot be captured at the center of the antenna beam.

This invention was made to improve the above-mentioned drawbacks, and will be described in detail below.

Figure 1 shows the antenna pattern when the dimensions of the antenna are the same. If the point is 3.3 cLB lower than the peak, then in the case of the conical scan method, the capture range can be doubled.

If the conical scan method is used when searching for a target, the probability of geometric lock-on to the target can be improved.

Next, I will explain the situation of the guided flying object and the target aircraft.

In Figure 2, (1) is the guided flying object, (2) is the target aircraft, (3) is the rendezvous point, and (4) is the pay line. Equipped with a radar device that can switch between guided flying object +11&'i monopulse and conical scan methods.

The antenna is pointed in the direction of Aya's line of sight (4) just before launch. After launch, the radar device installed on the guided flying object (1) searches for the target aircraft (21) using a conical scan method, and when it captures the target aircraft (2) with its antenna beam, it locks onto it and locates the center of the antenna beam. The radar device then switches to the monopulse method to track the target aircraft (2) and guide the guided flying object f11 itself to the rendezvous point (31).

Next, a specific example for realizing the principle of this invention will be shown.

In FIG. 3, +51 to (8) are each antenna (A
), antenna (131, 7y antenna (C1, 7y antenna (D
), +91 to 12 are phase shifters (A) that control the amount of phase shift of the passing signal in response to a control signal from a controller to be described later.
, phase shifter (B), phase shifter (C), phase shifter (D+, +1
Reference numeral 3 is a controller that generates four types of control signals that have the same amplitude and a phase shift of 90°.When receiving a signal from a delay circuit, which will be described later, all control signals are set to constant voltage and voltage. C41 is the sum of the signals passing through four phase shifters (hereinafter referred to as sum signal) [output of phase shifter (Al), output of I91 + phase shifter (Bl (output of I)] and [output of phase shifter (C1 (Output of Ill + phase shifter (Di
oi+ output] (hereinafter referred to as EL double signal), and [
output of phase shifter (A) + 9+ + output of phase shifter (D) 1121] and [phase shifter CBl 01 ) output child B phase a (C1
u) output) (hereinafter referred to as AZ multiplied signal), and a51 is a tuplexer that separates the transmitted and received signals.

(16) is a transmitter that generates a transmission signal, (17+ is a local oscillator that generates a signal with a frequency that is 11 frequencies higher than the frequency of the signal generated by the transmitter, and am is the output power of the local oscillator surface by 3 etc. power divider (A).

(191, 12 mark, (21+ is comparator (I41
A mixer (7!, mixer (B)) mixes the sum signal outputted from the EL multiplied signal, the AZ multiplied signal, and the local oscillator (171) to convert the IP multiplied signal.

The mixer (C1, C121, n, +24) is an amplifier (A), an amplifier (B), an amplifier (C1,
(251 is a power divider (B) that divides the IP multiplied signal-converted sum signal into three equal parts) is a signal processing circuit that performs signal processing such as frequency conversion and removal of unnecessary signals. Outputs a modulated signal containing . (271 is a lock-on judgment circuit that detects that the signal level exceeds a predetermined value and outputs a lock-on signal. The delay circuits, f2e and Cl0I, phase-detect the modulation signal containing the angular error using the control signal and output the EL.
The phase detector (Al and phase detector (B), C'll+, (3H'; when tracking m monopulse, comparator 04) which takes out the angular error signal of A phase detector (C1) and a phase detector (Di, 1
331G is a servo device that changes the pointing direction of the antenna using an angle error signal, and when it receives a lock-on signal and does not receive a signal from a delay circuit, it uses a phase detector (AI).
It works with the angular error signal by conical scanning from C21 and phase detector (BH301), and after receiving the signal from the delay circuit (28) and combining it with J↓, the phase detector outputs the angular error from the sum, KL multiplied signal, and AZ multiplied signal. It works by the angular error signal from the detector (C11311) and the phase detector (D) (33).

, Note that before lock-on, the angle error signal does not work.

The servo device (331) also serves to spatially stabilize the antenna against mechanical vibrations of the guided flying object fi+.

With this configuration, a phase shifter (As1n2π to Al +9+
ft, phase shifter (BIQ [# to As1n (zxft-ding), phase shifter (C) un to Aein (2πft --)
+ Phase shifter (DJ +121 to Aein (2πft3
When a control signal of π m=) is given, the antenna (Al +5+
, antenna (Bl (61, antenna (C1 + 71 and antenna (D) + 81 have a rotation frequency fHz around the antenna axis)
The angle of inclination of the antenna beam with respect to the antenna axis is determined by the amplitude A of the control signal.

Furthermore, if the control signal applied to each phase shifter is set to a predetermined constant voltage (for example, OV), the phase shift delay amount of each phase shifter becomes constant, and the comparator (14) outputs a monopulse sum signal, A KL multiplied signal and an AZ multiplied signal are obtained.

Now, when the guided flying object (1) is launched with this configuration,
The signal passes through the transmitter 0 and the eduplexer 09, is divided into four by a comparator (141), and enters each phase shifter.

Since each phase shifter is applied with a sinusoidal control signal generated by the φ1j controller 131 with the same amplitude and a different phase, the phase shifter of each path has a shift corresponding to the control signal. The phase-delayed signal is guided to the antenna by pattern synthesis of antenna (A) +5+, antenna (Bl +61), antenna (C) ry+, and antenna (DJ +81).

It becomes an antenna beam that performs conical scanning and is radiated into space. When the target aircraft (2) enters the antenna beam, the radiated signal is reflected by the target aircraft (21) and returns.The reflected signal follows the opposite path and is output as a sum signal of comparator 04. Output. This sum signal is subjected to amplitude modulation of the rotation speed f of the conical scan. The amplitude modulated sum signal passes through a duplexer f+51 and is guided to a mixer (Shiho).

Here, the signal is mixed with the local oscillator oTI signal divided into three equal parts by the power divider (A) 0 seconds to form an IF multiplied signal.

Next, it is amplified by the engineering F amplifier (Al +221 and enters the signal processing circuit c! mark. Here, it undergoes signal processing such as frequency conversion and enters the lock-on judgment (271). Also, the signal processing circuit cle removes unnecessary signals, etc. The modulated signal containing the angular error is output to the phase detector (A1 t29!) and the phase detector (Bl (30), where the phase is detected by the control signal and the angular error signal of KL and AZ is output. becomes.

When the lock-on determination circuit (2'71) exceeds a predetermined value, the lock-on signal is output to the servo device M1 +331 and the delay circuit ■.When the servo device +33 receives the lock-on signal, the phase detector (Al (2) The EL and AZ angle error signals from the phase detector (B) t3ω change the pointing direction of the antenna and reduce the angle error.

on the other hand.

After a predetermined time delay, the lock-on signal that has entered the delay circuit is sent to the controller (131) and the servo equipment (33+).

Upon receiving this signal, the controller O) changes the control signal to a constant voltage and makes the phase shift delay amount of the phase shift constant for all four paths. As a result, the output of comparator (14) is:
A sum signal, PL multiplied signal and AZ multiplied signal are obtained. Note that the sum signal is not subjected to amplitude modulation at frequency f. sum signal, EL
The double signal and the AZ double signal are converted into IF double signals by mixers on their respective paths, and then amplified. The amplified EL multiplied signal and AZ multiplied signal are each phase-detected by a phase detector (C) (311) and a phase detector (DJ (3Z) using a sum signal divided into three equal parts by a power divider. It becomes an angle error signal and enters the servo device.On the other hand, the signal output by the delay circuit example is also input to the servo device, and when this signal is received, the 9 phase detector (C1 (3++ and phase detector (The antenna is driven by the angle error signals of FjL and AZ output by Di +321, works so that the angle error signals become zero, and continuously tracks the target aircraft (2).

As explained above, by using the conical scan method when searching for a target, it is possible to capture the target aircraft even if the angle setting error of the antenna before one firing is large and even if the target aircraft makes a rapid turn. This makes it possible to improve the lock-on probability to the target aircraft.

[Brief explanation of the drawing]

Fig. 1 is a diagram explaining the antenna pattern, Fig. 2 is a diagram showing the situation of engagement, and Fig. 3 is a configuration diagram of a radar device that realizes the principle of the present invention. 21
is the target aircraft, (3) is the meeting point, and (4) is the line of sight. (5) to (81 are antennas, (9) to (121 are phase shifters, +131 is a controller. (141 is a comparator, +151 is a duplexer, 061 is a transmitter, 071 is a local oscillator, (lI + industrial power divider , f+9)~Q1) is a mixer, (221~
(24) is a power amplifier, and +251 is a power divider. 0 mark is a signal processing circuit, C171 is a lock-on determination circuit, ■ is a delay circuit, Zheng~C121 is a phase detection circuit, and east is a servo device. Note that the same or corresponding parts in FIG. 9 are designated by the same reference numerals. Agent Shin Kuzuno −

Claims (1)

[Claims] Four antenna elements, four phase shifters connected to each antenna element, the sum of signals passed through the four phase shifters,
An antenna consisting of a comparator that calculates the difference between the two sets of upper and lower signals and the difference between the two sets of left and right signals, and a generator that generates a signal that controls the amount of phase shift delay of the phase shifter; a transmitter and a receiver that transmit and receive signals;
A signal processing circuit that processes the received signal and extracts the error signal. A circuit that performs lock-on judgment, one set of phase shift detectors that extracts the angle error from the error signal, another set of phase detectors that creates the angle error from the antenna sum and difference signals, and drives the antenna using the angle error. In a guided flying vehicle equipped with a radar device consisting of a servo device, when searching for a target, a conical scan of the antenna beam is performed by adding sine wave signals of equal amplitude to each of the four phase shifters or with a different phase. After acquisition, the signal applied to the phase shifter is a DC voltage of a predetermined value, and the angular error is switched to a monopulse method in which the target is tracked using the sum and difference signals from the comparator. A guided flying object equipped with a distinctive radar device.