JPH0413098A - Guided airframe - Google Patents

Abstract

PURPOSE:To reduce the affection of clutter and improve the capacity of rendezvous with a target by a method wherein the timing of receiving reflected wave from ground, in which the reflection strength of the reflected wave becomes highest, is made to coincide with the timing of transmission of transmitting wave to the target to increase the loss of receiving power of the clutter from ground as much as possible. CONSTITUTION:A distance between clutters operating unit 19 operates a distance between a guided missile and ground in a direction, in which the reflection strength of reflected wave becomes highest among the directions of a main rope. A third pulse width PRF control unit 21 selects a pulse width PRF satisfying both of pulse width PRFs selected by a pulse width PRF control unit 121 and a second pulse width PRF control unit 21. In a guided missile M constituted in such a manner, the loss of the receiving power of a reflected wave from a target can be reduced and the loss of the receiving power of reflected wave from ground in the direction of the main rope can be increased whereby clutter suppressing characteristics are improved and the capacity of rendezvous with a low-altitude target or guidance accuracy is improved.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a guided flying vehicle that captures and tracks a target.

[Conventional technology]

First, a conventional control device of this type will be briefly explained.

In Figure 3, 1M is the guided missile, (1) is the target that the guided flying vehicle captures and tracks, (2) is the transmitted wave irradiated to the target (1), and (3) is the wave from the target (1). Reflected wave, (
4) is a transmission source section that generates a transmission signal of the transmission wave (2) to be irradiated to the target (Il); (5) is a transmission source section that supplies the transmission signal generated in the transmission source section (4) to an antenna to be described later; Sum receiver: The signal received by the preamplifier (
The circulator (6) supplies the transmission signal to the target fil as a transmission wave (2), receives the reflected wave (3) from the target (1), and receives the sum reception signal and Day 7 (difference).
The antenna that outputs the received signal, (7) is the antenna (6)
(8) is the first preamplifier that amplifies the weak sum reception signal received by antenna (6) with low noise, (91 is the weak differential reception signal received by antenna (6)) a second preamplifier that amplifies the signal with low noise;
00) is a one-to-one divider that divides the sum reception signal into two and outputs it to the relative speed detector and relative distance detector. 011 is the one that extracts the target signal from the sum reception signal and extracts the target (j) from the target signal.
A relative speed detector extracts the amount of transfer of the number of transmitted orbits e generated between the guided flying objects M and outputs a relative speed signal. A relative distance detector that extracts the distance error that occurs between M and outputs a relative distance signal (from the relative distance signal, the timing of receiving the reflected wave from the target and the timing of irradiating the transmitted signal to the target as a transmitted wave) The pulse width/PRF controller 2 ports 3) calculates the pulse width and PRF of the transmitted signal and outputs a sinus signal to generate the width and PRF in the transmission source section. An angle detection m that detects the angular direction of the target (11) with respect to the machine axis of M and outputs a beam pointing angle control signal and a target direction angle signal.

(141) is a beam pointing angle control unit that controls the beam pointing direction of the antenna (6) in the target (1) direction using a beam pointing angle control signal output from the angle detector 031; W (flight altitude, etc.), an inertial device unit that detects the attitude angle, Q51 is a relative speed signal output from relative speed detector 011, a relative distance signal output from two relative distance detection assistants, and an output of angle detection N031. Outputs a steering command signal for steering the guided flying object M in the direction of the meeting point with the target (1) based on the target direction angle signal of the target (1).
・11511.1 Autopilot [A steering device that steers the guided spacecraft M in the direction of the meeting point with the target (1) using the steering command signal output from 151. +171 is the power required for the components of the guided spacecraft M. It is a propulsion device that provides thrust to the guided flying vehicle M.

[Problem to be solved by the invention]

The timing of the reception of the reflected wave (3) from the target (1) of the conventional guided missile M (configured as described above).

By shifting the timing of the transmission of the transmission wave (2) to the target (1), we were able to reduce power loss as much as possible, improve the S/N, and guide it toward the meeting point with the target fll. .

However, since it did not take into account the reflected waves (clutter) from the ground, low-altitude targets were more affected by the rack, which could impede the ability to engage with target (1).

This invention is based on the timing of receiving the reflected wave that has the highest reflection intensity among the reflected waves from the ground included within the beam width in the main beam direction of the antenna, and the transmission wave (2) to the target (1). ) by adjusting the timing of the transmission and increasing the received power loss of reflected waves (clutter) from the ground as much as possible, thereby reducing the influence of clutter and improving the ability to meet the target (1). The purpose is to get a body.

[Means to solve the problem]

The guided spacecraft according to this invention calculates the distance between the guided spacecraft and the ground included within the beam width in the main lobe direction from the position and attitude angle information of the guided spacecraft and the target direction angle signal, and The means for outputting the clutter distance signal, the timing of receiving the reflected wave that has the highest reflection intensity among the reflected waves from the ground than the clutter distance a signal, and the timing of irradiating the transmitted signal to the target as the transmitted wave match. a second pulse width/PRF control unit that calculates the pulse width and PRF of the transmission signal and outputs a control signal for generating the pulse width and PRF in the transmission source unit;
A third pulse intensity PRF control section that outputs a control signal for generating PRF with a pulse width that satisfies both the output of the control section and the output of the second pulse intensity PRF control section to the transmission source section. It is something.

[For production]

This invention shifts the timing of receiving the reflected wave from the target and the timing of transmitting the transmitted wave, and at the same time aligns the timing of receiving the reflected wave from the ground in the main lobe direction with the timing of transmitting the transmitted wave. Therefore, it is possible to increase the loss of the received power of the reflected wave from the ground in the main lobe direction while reducing the loss of the received power of the target, resulting in better anti-clutter suppression characteristics and better performance against low-altitude targets. It is possible to improve the meeting ability, that is, the guidance accuracy.

〔Example〕

FIG. 1 is a diagram showing an embodiment of the present invention (1) to
(g), (1211, and (141)) are the same as in FIG. 3, and (191 to 口) are new devices added to FIG. 2.

(191 is the inertial device unit (141) output position and attitude angle information and the angle detector f131 output target direction angle signal to estimate the distance between the guided spacecraft and the ground in the main lobe direction, and calculate the clutter distance H and the signal. The clutter-to-clutter distance calculation unit to output calculates the clutter reflected power from the crank distance la (M number and antenna gain) from the clutter-to-clutter distance calculation unit () 9), and calculates the maximum clutter distance signal that maximizes the clutter reflected power. The output clutter maximum reflection intensity calculation unit (Q]) uses the output of the clutter maximum reflection intensity calculation unit (28) to irradiate the target with the timing of receiving the reflected wave from the ground and the transmission signal as a transmission wave based on the large clutter distance signal. Calculate the path/L path width and PRF of the transmission signal whose timing matches the
In 4), the second pulse width/PRF control part which outputs the control signal for generating the pulse width and PRF outputs the output of the first pulse width PRF control section (+21) and the second pulse width. The transmission source section (4) transmits a control signal for generating PRF and a pulse width that satisfies both the output of the PRF control section (21).
This is the third pulse width/PRF control part to be output to.

In addition, the Kura-tsuta distance calculation unit G11) calculates the distance between the guided flying object and the ground in the direction in which the reflected wave is received, which has the highest reflection intensity among the main lobe directions, using the following equation.

cos (--θm+θa-θ'b) RC: Distance between the guided projectile and the ground Hm + Guided body altitude θm: m: Guided body attitude angle Also, clutter maximum reflection intensity calculation factor) is θ゛b is R
Calculate c maχ.

G2(θ'bl Re'G(θ''b) - Antenna gain in the θ'b direction within the beam width Also. In the third pulse width PRF control section, the pulse width/PR
F nursery school section (121) and second pulse width/pRFli1
The pulse width selected in each section).

A pulse width that satisfies both of the PRF and a pulse width that satisfies both of the quadratic equations.

Select PRF.

L, N Positive number Rt Target amount relative distance τ Pulse width PRF Pulse repetition frequency A diagram of the relative relationship between the guided flying object M and the target (1) is shown in FIG. 2 for reference.

In the guided flying object M configured as described above, it is possible to reduce the loss of the received power of the reflected wave from the target and increase the loss of the received power of the ground reflected wave from the main lobe direction. The clutter suppression characteristics are improved, and the ability to meet low-altitude targets, that is, the guidance accuracy is improved.

[Effect of idea]

This invention has the configuration as explained above, and the timing of receiving the reflected wave from the target and sending it (the timing of sending the two liquids,
At the same time, the PRF and pulse width of the transmitted wave should be such that the reflected wave with the highest reflected strength among the reflected waves from the ground is received within the beam width in the main lobe direction. By making it possible to transmit clutter, it is expected that the anti-clutter suppression performance will be improved, and the ability to meet low-altitude targets, that is, the guidance accuracy, will be improved.

[Brief explanation of drawings]

FIG. 1 is a block diagram showing an embodiment of the present invention, FIG. 2 is a diagram showing the relative relationship between a guided missile and a target, and FIG. 3 is a block diagram showing a conventional guided flying vehicle. In the figure, (1) is the target, (2) is the transmitted wave, (3) is the reflected wave, (4) is the transmission source, (5) is the circulator,
(6) is the antenna, (7) is the dome, (8) is the first preamplifier, (9) is the second preamplifier, 00) is the one-to-one
Separation arrangement 1. (Ill is a relative velocity detector, 021 is a relative distance detector, (1211 is a first pulse width/PRF control unit, (131 is an angle detector, 041 is a beam direction angle control unit, (1411 is an inertial device unit, (time is the autopilot, (pickup is the steering device, G711. is the power source, decoy is the propulsion device, (191 is the inter-clutter distance calculation section, +21 is the clutter maximum reflection intensity calculation section, (211 is the second pulse width PRF The control unit (Ken) is the third pulse width/PRF control unit. In Figure 2, the same or equivalent parts are designated by the same symbols as 1.

Claims (1)

[Claims] a transmission source section that generates a transmission signal of a transmission wave to be irradiated to a target, a circulator that supplies the transmission signal to an antenna and a reception signal to a preamplifier section, and irradiates the target with the transmission signal as a transmission wave; An antenna that receives reflected waves from a target, a dome that protects the antenna from the outside world, a first preamplifier that amplifies a weak sum reception signal received by the antenna with low noise, and the antenna. The second one receives the signal and amplifies the weak differential reception signal with low noise.
a preamplifier, a 1:1 distributor that divides the sum reception signal into two channels, a speed channel and a distance channel, and a target signal extracted from the sum reception signal distributed by the 1:1 distributor. A relative speed detector extracts a relative speed signal from the signal, a relative distance detector extracts a relative distance signal from the sum reception signal distributed by the one-to-one distributor, and a reflected wave from the target from the relative distance signal. The timing of reception of the transmission signal and the timing of irradiation of the transmission signal to the target as a transmission wave are shifted.The first system calculates the pulse width and PRF of the transmission signal and outputs a control signal for generating the pulse width and PRF at the transmission source section. a pulse width/PRF control section; an angle detector that extracts a beam directivity angle control signal and an angle signal from the differential reception signal; and a beam directivity angle control that controls the beam of the antenna in a target direction using the beam directivity angle control signal. , an inertial device section that detects the position (flight altitude, etc.) and attitude angle of the guided spacecraft, information on the position and attitude angle of the guided spacecraft, a relative speed signal, a relative distance signal, and a target direction angle signal. an autopilot that generates a steering command signal to steer the guided flying vehicle in the direction of the meeting point with the target;
In a guided spacecraft equipped with a steering device that steers the guided spacecraft in the direction of the meeting point with the target based on a steering command signal, the main lobe direction is determined based on the position and attitude angle information of the guided spacecraft and the target direction angle signal. a clutter-to-clutter distance calculation unit that calculates the distance between the guided missile and the ground and outputs a clutter distance signal, and calculates clutter reflected power from the clutter distance signal and the beam direction gain of the antenna, so that the clutter reflected power is maximized. A clutter maximum reflection intensity calculation unit that outputs a maximum clutter distance signal, and a pulse width of the transmission signal that matches the timing of the reflected wave from the ground and the timing of irradiating the transmission signal to the target from the maximum clutter distance signal. A second circuit that calculates the PRF and outputs the pulse width and a control signal for generating the PRF at the transmission source section.
and the first pulse width PR.
a third pulse width/control unit that outputs a control signal for generating a pulse width and PRF that satisfy both the output of the F control unit and the output of the second pulse width PRF control unit to the transmission source unit; A guided flying object characterized by the following: