JPH028669B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a proximity fuse device mounted on a guided flying vehicle to detect a nearby target aircraft.

Conventional proximity fuse devices use, for example, a microwave Doppler radar as their detection unit.
The antenna pattern is set to be perpendicular to the axis of the flying object 11, as shown by the dotted line A in FIG. The projectile warhead is then detonated after a certain period of time (detonation time) after the antenna pattern A detects the target. for example,
As shown in Fig. 2a, the flying object 11 approaches the target aircraft 12 from the front, detects the front end of the target, and detonates after a certain period of time, and as shown in Fig. 2b, the projectile 11 detonates.
effectively hits the target aircraft 12. However, the third
When the flying object 11 approaches the target aircraft 12 from behind as shown in Figure a, if it is detonated at a certain time after the target is detected, the relative approach speed of the flying object 11 to the target aircraft 12 will change as shown in Figure 2. As shown in FIG. 3b, the bullet 13 is slower than the target aircraft 12
They may be scattered behind the aircraft and fail to hit the target aircraft 12. In order to solve these drawbacks, the relative speed between the flying object and the target is measured in advance,
A method has been proposed in which the slope of the target detection pattern of the proximity fuze is changed depending on the relative speed of the two.

However, in the method of measuring the relative speed between the projectile and the target in advance, a signal for measuring the relative speed is emitted as it approaches the target, which means that the presence of the projectile is detected and the target makes an evasive movement. etc., the probability of hitting may decrease.

The present invention was made in view of the above circumstances, and
By changing the inclination of the antenna pattern of the proximity signal relative to the aircraft axis according to the turning acceleration of the flying object, which is proportional to the movement of the target, the target aircraft can be hit without the target aircraft detecting the presence of the flying object. The present invention provides a proximity fuze device that can increase the accuracy.

An embodiment of the present invention will be described in detail below with reference to the drawings. In FIG. 4a, 41 is a body of a guided flying object, and a motor 42 is fixed to the body 41 so as to be positioned, for example, on the axis of the aircraft. A fixed transmitter/receiver 44 is provided so as to be driven back and forth in the machine axis direction by the rotating shaft 43 of the motor 42. For example, the transmitter/receiver 44 has a structure in which the central shaft portion of the transmitter/receiver 44 and the rotating shaft 43 are screwed together. It's summery. A horn-shaped waveguide antenna 45 as shown in FIG. Together with the integrally modularized signal processor, it constitutes a part of the proximity fuse device. A window 46 made of synthetic resin, for example, is provided in a part of the fuselage 41.
The opening of the antenna 45 faces the inner surface of the antenna 6 . A rubber-like flange 47, for example, is attached to the periphery of the tip of the antenna 45, and the flange 47 is fixed to the body 41 by being fixed to, for example, a frame 48 inside the window 46. The antenna pattern A of the upper and lower antenna pairs and the left and right antenna pairs makes it possible to detect target aircraft around the aircraft. In the case where the upper and lower antenna pairs and the left and right antenna pairs are perpendicular to the aircraft axis, antenna pattern A is orthogonal to the aircraft axis of the flying object 11 as shown in Figure 5a, similar to Figures 1a and b described above. However, the motor rotation shaft 43
When the base end of the antenna moves forward or backward together with the transmitter/receiver 44 due to the rotation of Begins to lean backwards or forwards.

Furthermore, two accelerometers 4 are installed to detect the vertical and horizontal accelerations of the aircraft body 41, respectively.
9 are installed in the fuselage, and the output signals of these accelerometers are amplified by an amplifier 50 to drive the motor 42, and the polarity (+, -) and The direction and amount of rotation of the motor 42 are controlled according to the level.

When the flying object follows the target aircraft and approaches the point of impact on the target aircraft, the flying object turns due to the presence of miss distance. In this case, the turning acceleration of the flying object increases as the miss distance increases. If the miss distance is large, it takes longer for the warhead fragments to reach the target, so it must be detonated earlier. For this reason, as the turning acceleration increases, the amount of rearward movement of the transmitter/receiver 44 by driving the motor 42 in accordance with the output signal of the accelerometer increases, and the forward tilt of the antenna pattern A increases. To accelerate the detection of a target aircraft so that when it is detonated after a certain detonation time, the bullet fragments will effectively hit the target aircraft. In this way, by tilting antenna pattern A forward when the turning acceleration is large, antenna pattern A can detect the target aircraft at an early timing, and a hit effect can be obtained by detonating after a certain detonation time. .

As described above, according to the present invention, a mechanism is provided that detects the turning acceleration of the flying object and changes the inclination of the proximity fuze antenna pattern with respect to the flying object axis according to this detection output, so that the accuracy of the target aircraft can be improved. It is possible to provide a proximity fuze device that can increase the number of flying objects and prevent a target aircraft from detecting the presence of a flying object.

[Brief explanation of drawings]

Figures 1 to 3 are for explaining conventional proximity fuze devices, Figures 1a and b are antenna pattern diagrams, and Figures 2a and b are detonation diagrams when approaching a target aircraft from the front. Figures 3a and 3b are diagrams showing the detonation effect when approaching a target aircraft from behind, and Figure 4a is a diagram showing the schematic configuration of an embodiment of the proximity fuze device according to the present invention. 4B is a perspective view showing an example of the antenna shown in FIG. 4A, and FIGS. 5A to 5C are views showing different states of the antenna pattern in the proximity fuse device shown in FIG. 4A. 11... Flying object, 12... Target aircraft, 41... Airframe, 42... Motor, 43... Rotating shaft, 44...
Transmitter/receiver, 45... antenna, 49... accelerometer, A... antenna pattern.

Claims (1)

[Claims] 1. In a proximity fuze device mounted on a guided flying vehicle that detects a target aircraft using an antenna pattern that spreads in the peripheral direction of the flying vehicle and generates a detonation signal after a certain period of time, an accelerometer that detects the turning acceleration of the flying vehicle; , is driven according to the detection output of this accelerometer, and when the turning acceleration of the flying object is large,
1. A proximity fuze device comprising: a mechanism that changes the inclination of the antenna pattern with respect to the flying object's axis in the direction of movement of the flying object compared to when turning acceleration is small.