JPH09257396A - Antenna of guided missile - Google Patents

Abstract

PROBLEM TO BE SOLVED: To obtain an antenna of a guided missile that can be harder to find by the target of the guided missile without the operation of a gimbal during the first and the second stage of guidance. SOLUTION: A guided missile is provided with a second grid 12 that is provided with a mechanism that rotates a metal grid between an angle in parallel to the plane of polarization of electromagnetic wave from a radiator and the angle of 90 degrees that is in square to it in front of the radiator 3 that emits electromagnetic wave and the metal grid of the second grid 12 is rotated to be in parallel to the plane of polarization of searching wave so that searching wave by a radar from the target of the guided missile is reflected during the initial and middle stage guidance in which the antenna is not used.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an antenna of a guided vehicle which is not detected by a target radar equipped with a radar.

[0002]

2. Description of the Related Art FIG. 5 (a) is a schematic view of an example of an antenna of a conventional guided vehicle, 1 is a body of the flying vehicle, 2 is a radome, 3 is a radiator installed in the radome 2. 4 is a gimbal that moves the radiator 3, and 5 is an axis of the flying body. FIG. 5B is a view seen from the front of the axle 5 of the flying vehicle, and in this figure, the radiator 3 faces the front. Fig. 5 (c) is an operational diagram of the antenna of the guided vehicle, 6 is the deflection angle of the radiator 3 with respect to the axis 5 of the vehicle, 7 is the target of the guided vehicle, 8 is equipped with the target 7 mentioned above. Radar, 9 is a search wave from the radar 8, and 10 is a reflected wave of the search wave reflected by the radiator 3.

The antenna of a conventional guided vehicle is constructed as described above, and when the radiator 3 faces the front of the vehicle axis 5 of the vehicle, the search wave of the radar 8 of the target 7 is directed in the target direction. Since the guided vehicle is detected from the target 8 by being reflected on the target 8, in the first mid-term guidance without using the antenna, the radiator 3 is deflected with respect to the axis 5 of the vehicle and the search for the radar 8 of the target 7 is performed. The wave 9 is reflected in a direction other than the target so that the guided flying object is not easily detected from the target 8.

[0004]

In the antenna of the conventional guided vehicle as described above, the radiator 3 is deflected with respect to the axis 5 of the vehicle even during the first mid-term guidance without using the antenna. Since the gimbal 4 is operated, it is necessary to provide a power source and a control command for the first mid-term induction, and the motor heats up due to the long-term operation of the gimbal 4 and the temperature rises, so the torque is reduced and the control performance is reduced. There was a problem of deterioration.

The present invention has been made to solve the above-mentioned problems, and it is possible to make it difficult to be detected from the target of the guide vehicle without operating the gimbal during the first mid-term guide. Aim to get the antenna of the body.

[0006]

In the antenna of a guided vehicle according to the first invention, a first grid having a metal grid orthogonal to the plane of polarization of a radiator is arranged in front of an opening of a radiator that radiates radio waves. The second grid is provided adjacent to the first grid and having a mechanism in which the angle of the metal grid rotates 90 degrees from parallel to orthogonal to the polarization plane of the radiator.

The antenna of the guide vehicle according to the second invention is such that the first grid and the second grid are arranged at a deflection angle with respect to the plane perpendicular to the aircraft axis of the flight vehicle. is there.

The antenna of the guide vehicle according to the third aspect of the present invention comprises the first grid and the second grid arranged on a curved surface.

Further, the antenna of the guide vehicle according to the fourth aspect of the invention is such that the main reflector of a paraboloidal curved surface having a metal grid parallel to the plane of polarization of the primary radiation is directly opposed to the primary radiator that radiates radio waves. The polarization plane of the radio wave reflected by the main reflector
A grid having a mechanism for rotating the angle of the metal grid by 90 degrees from parallel to orthogonal to the polarization plane of the reflected wave of the reflection plate is provided on the back surface of the main reflection mirror of the inverse Cassegrain antenna having a reflection plate that rotates 0 degree. It is a thing.

[0010]

BEST MODE FOR CARRYING OUT THE INVENTION

Embodiment 1. 1 is a view showing a first embodiment of the present invention, and FIG. 1 (a) is a schematic view seen from the side of a guided vehicle, in which 1 is a body of the flying vehicle, 2 is a radome, and 3 is a radome. Is a radiator that radiates vertically polarized radio waves, 5 is an axis of a flying object, and 11 is a first grid arranged in front of the opening of the radiator 3 having a metal grid orthogonal to the plane of polarization of the radio waves radiated by the radiator 3. , 12 is the first
The angle of the metal grid adjacent to the grid of the radiator 3
The second grid rotates 90 degrees by the bearing 13 from parallel to orthogonal to the plane of polarization of the radio wave radiated by the, and 14 is a motor with a roller 15 for rotating the second grid 12. FIG. 1B is a view as seen from the front of the aircraft axis. In this figure, the metal grid of the second grid 12 is parallel to the plane of polarization of the radiator 3.
Figure 1 (c) is a view of the aircraft from the front of the axle,
This figure shows a state in which the metal grid of the second grid 12 is orthogonal to the polarization plane of the radio wave radiated by the radiator 3.

The antenna of the guide vehicle constructed as described above is used in the first mid-term guidance without using the antenna.
By making the metal grid of the second grid 12 parallel to the plane of polarization of the radiator 3, the search wave reflected by the second grid 12 is reflected when the search wave by the radar of the target of the vehicle is vertical polarization. In the case of horizontal polarization, the search wave passes through the second grid 12 but is reflected and scattered by the first grid 11, so that it is difficult to find a guided flying object from the target of the flying object. Further, when the antenna of the guidance aircraft is used for the terminal guidance, the motor 14 is rotated to make the metal grid of the second grid 12 orthogonal to the plane of polarization of the radiator 3 so that the radiation of the radiator 3 is emitted. The wave passes through the second grid 12.

Embodiment 2. FIG. 2 is a diagram showing a second embodiment of the present invention, in which 16 is a deflection angle taken by the first grid 11 and the second grid 12 with respect to the plane perpendicular to the aircraft axis 5 of the flying vehicle. is there. In this embodiment, the first grid 11 and the second grid 11 are arranged so that the directions in which the search waves of the radar of the target of the flying object are reflected and scattered in directions other than the target in the first mid-term guidance without using the antenna are used.
The grid 12 has a deflection angle with respect to the vertical plane of the aircraft axis 5.

Embodiment 3 FIG. 3 is a diagram showing a third embodiment of the present invention, in which the first grid 11 and the second grid 12 are arranged on a curved surface. In this embodiment, in the first mid-term guidance that does not use the antenna, the search wave by the radar of the target of the flying object has different reflection angles depending on the positions of the curved surfaces of the first grid 11 and the second grid 12, so the scattering direction is different. Spread.

Embodiment 4 FIG. 4 is a diagram showing a fourth embodiment of the present invention. FIG. 4 (a) is a schematic view seen from the side of a guided vehicle, in which 1 is a body of the flying vehicle, 2 is a radome, and 5 is a radome. Is the axis of the flying object, 17 is the primary radiator that radiates horizontally polarized radio waves, and 18 is the primary radiator 1.
7, a parabolic curved main reflecting mirror having a metal grid parallel to the plane of polarization of the primary radiation that faces 7; 19 is a reflector for rotating the plane of polarization of the radio wave reflected by the main reflecting mirror 18 by 90 degrees;
Is a gimbal for moving the reflection plate 19, 21 is a bearing 2 from the plane parallel to the polarization plane of the radio wave reflected by the reflection plate 19
2 is a grid having a mechanism for rotating 90 degrees by 2, and 23 is a motor with a roller 24 for rotating the grid 21. FIG. 4B is a view as seen from the front of the aircraft axis. In this figure, the metal grid of the grid 21 is parallel to the polarization plane of the radio wave reflected by the reflector 19. FIG. 4 (c) is a view as seen from the front of the aircraft axis. In this figure, the metal grid of the grid 21 is the reflector 1.
9 shows a state orthogonal to the polarization plane of the radio wave reflected by 9.

The antenna of the guide vehicle constructed as described above is used in the first mid-term guidance without using the antenna.
By making the metal grid of the grid 21 parallel to the plane of polarization of the radio wave reflected by the reflector 19, if the search wave by the target radar of the spacecraft is vertically polarized, the search wave is reflected by the grid 21. In the case of horizontally polarized waves, the search wave passes through the grid 21 but is reflected and scattered by the main reflecting mirror 18, so that it is difficult to find the guided flying object from the target of the flying object. Further, when using the antenna of the guidance aircraft for the terminal guidance, the motor 23 is rotated to make the metal grid of the grid 21 orthogonal to the polarization plane of the radio wave reflected by the reflection plate 19, The radio wave reflected by the plate 19 passes through the grid 21.

[0016]

According to the present invention, by providing a mechanism for rotating the grid by 90 degrees when starting the terminal guidance using the antenna of the guided vehicle, during the first mid-term guidance not using the antenna, Guidance from the target of the flying object Since it is not necessary to operate the gimbal to deflect the radiator or the reflector with respect to the axis of the flying object so that it is hard to find the flying object, the power and control commands are guided in the first mid-term Since it is not equipped for use, and because the gimbal motor does not operate for a long time, there is no deterioration in control performance due to heat generation.

[Brief description of drawings]

FIG. 1 is a diagram showing Embodiment 1 of an antenna of a guided vehicle according to the present invention.

FIG. 2 is a diagram showing a second embodiment of an antenna of a guided vehicle according to the present invention.

FIG. 3 is a diagram showing a third embodiment of an antenna of a guided vehicle according to the present invention.

FIG. 4 is a diagram showing a fourth embodiment of an antenna of a guided vehicle according to the present invention.

FIG. 5 is a diagram showing an antenna of a conventional guide vehicle.

[Explanation of symbols]

1 body, 2 radomes, 3 radiators, 4 gimbals, 5 aircraft axes, 6 deflection angles, 7 targets,
8 radar, 9 search wave, 10 search wave reflection wave, 11
1st grid, 12 2nd grid, 13 bearings, 4 motors, 15 rollers, 16 deflection angles,
17 Primary radiator, 18 Main reflector, 19 Reflector, 2
0 gimbal, 21 grid, 22 bearings, 2
3 motors, 24 rollers.

Claims (4)

[Claims] 1. A first grid having a metal grid disposed in front of an opening of a radiator for radiating radio waves and having a plane orthogonal to the plane of polarization of the radiator, and a metal grid adjacent to the first grid having an angle of the radiator of the radiator. An antenna for a guided aircraft, comprising a second grid having a mechanism for rotating 90 degrees from parallel to orthogonal to the wavefront. 2. The guide vehicle according to claim 1, wherein the first grid and the second grid are arranged at a deflection angle with respect to a plane perpendicular to the aircraft axis. Aerial line. 3. The antenna of a guide vehicle according to claim 1, wherein the first grid and the second grid are arranged on a curved surface. 4. A primary reflector that radiates radio waves, a main reflecting mirror having a parabolic curved surface having a metal grid parallel to the plane of polarization of the primary radiation that is directly facing the primary radiator, and a main reflector for the radio waves reflected by the main reflecting mirror. A reflection plate for rotating the plane of polarization by 90 degrees; and a grid having a mechanism for rotating the angle of the metal grid on the back surface of the main reflector by 90 degrees from parallel to orthogonal to the plane of polarization of the reflected wave of the reflection plate. An aerial line of a guided flight characterized by.