JPH0455699A - guided flying body - Google Patents

Abstract

PURPOSE:To reduce the air resistance of a guided missile to extend the flying range of the same upon initial and intermediate period of flying and operate an optical wave seeker by employing an optical window and permit the improvement of tracking performance to the movement of a target upon final flying by a method wherein the optical wave seeker is operated in accordance with a distance between the terget by the opening and/or closing operation of an opening and closing window. CONSTITUTION:When a guided missile is at a long distance with respect to a target, an opening and closing window 5 is closed under a condition that the window 5 is along the configuration of the radio wave dome 1 and the guided missile is guided to the target by a radio wave seeker 3. The configuration of the radio wave dome 1 is designed so as to be the optimum considering the radio wave characteristics as well as the aerodynamic characteristics of the missile whereby a long detecting range and a low air resistance can be obtained. When the guided missile apporaches the target to a short distance capable of employing an optical wave seeker 4, a command from the radio wave seeker 3 is transmitted to the opening and closing window 5 whereby the opening and closing window 5 is opened into the direction of an arrow sign. As a result, an optical window 2, high in the transmitting coefficient of an optical wave or large in the angle of incidence of the optical wave, is employed to operate the optical seeker 4 whereby the target-tracking performance of the fuselage is improved.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to extending the range and improving the guidance accuracy of a guided flying object.

[Prior Art] Fig. 5 is a sectional view of a conventional guidance device for a guided flying object, in which (1) is a radio dome, (2) is an optical window, (3) is a radio seeker, and (4) is a radio wave seeker. It is a light wave seeker. Conventional guided flying objects that have two tracking means, radio waves and light waves, as shown in Figure 5, use a radio wave seeker (3) to track when the target is far away, and then If there is, tracking is performed using a light wave seeker (4). Radio wave seekers generally have a longer detection range than light wave seekers, so they can provide long-range guided missiles. On the other hand, a light wave seeker detects and tracks infrared rays etc. emitted from a target, making it possible for a guided projectile to be detected by the target.

By taking advantage of the characteristics of both the radio wave seeker and the light wave seeker, it is possible to realize a guided projectile that has a long range and is difficult to be detected by its target.

[Problems to be Solved by the Invention] In the conventional guided spacecraft, the radio dome (1) and the optical window (2) are spherical, as shown in Figure 5(a), due to the optical requirements of the light wave seeker. Or, as shown in FIG. 5(b), the radio dome fil and the optical window (2) must have a pyramidal shape. When using a one-spherical dome as shown in Fig. 5(a), the light wave seeker (4) is placed at the center of the gas axis of the guiding root mass so that there is no optical path difference between the light waves and the light wave seeker (4). It is necessary to use a radio seeker (
3) Since the antenna cannot be placed in the center, the detection performance deteriorates.

In addition, the five-spherical dome has a large air resistance, so the speed of the guiding root body is rapidly lost, the firing range is shortened, and at the same time, the turning performance during the guiding root body is also deteriorated. 5 more
Spherical domes are also disadvantageous against aerodynamic heating that occurs when flying at high speeds. On the other hand, as shown in FIG. 5(b), when using a pyramid-shaped dome, the light wave seeker (
4) can be placed offset from the center of the gas axis of the guiding root body, so the radio wave seeker (3) can place the antenna in the center, and the detection performance does not deteriorate, but the incidence of light on the optical window (2) In order to increase the angle and ensure optical performance, it is necessary to increase the angle θ of the pyramid. As a result, the problem arises that the air resistance of the dome is large (and the firing range is short like a spherical dome), and at the same time, the turning performance during guided rooting also deteriorates.This invention solves these problems. At long distances where a light wave seeker is not used, the opening/closing window is closed following the shape of the radio wave to reduce air resistance, extending the firing range, and at short distances where a light wave seeker can be used. In,
The purpose of the present invention is to obtain a guiding rhizoid that can improve target tracking performance by opening an opening window and operating a light wave seeker.

[Means for Solving the Problems] The guided rhizoid according to the present invention is capable of operating an optical seeker according to the distance to a target by opening and closing an opening/closing window.

In addition, the guided rhizoid according to another invention of the present invention further sprays a light wave seeker cooling gas onto the external front surface of the optical window, thereby making it possible to suppress the temperature rise of the optical window due to aerodynamic heating. .

[Function] In this invention, when the guiding rhizome is far away from the target, the opening/closing window is closed along the radio dome to reduce air resistance and extend the firing range while allowing the target to fly. Prevent speed reduction.

When the target is at a short distance, the opening/closing window is opened and the light wave seeker is activated to improve tracking characteristics for the target's movement. In addition to the above, in another aspect of the present invention, a light wave seeker cooling gas is further blown onto the external front surface of the optical window to suppress the temperature rise of the optical window due to aerodynamic heating and prevent performance deterioration of the light wave seeker. Improve tracking characteristics for target movement.

[Example] FIG. 1 is a diagram showing an example of the present invention, (5)
is an opening/closing window. Figure 1 fa) shows the situation when the guiding root body according to the present invention is located at a long distance from the target, and Figure 1 (b) shows the situation when the guiding root body according to the present invention is located at a long distance from the target.
It shows a cross section of the state when the object is close to the target. When the guiding root body according to the present invention is located at a long distance from the target, as shown in FIG.
5) is closed following the shape of the radio dome (1). At this time, the guided root body is guided to the target by the radio wave seeker (3). The shape of the radio dome (1) is
Since it is designed to suit radio wave characteristics and aerodynamic characteristics, it is possible to obtain good radio wave characteristics, that is, a long detection distance and low air resistance. The induced root mass according to this invention is
When the target is close enough to use the light wave seeker (4).

A command from the radio wave seeker (3) is transmitted to the opening/closing window (5), and the opening/closing window (5) is opened in the direction of the arrow as shown in FIG. 1 fb). As a result, an optical seeker (4) using an optical window (2) with a high transmittance of light waves, that is, a large incident angle of light waves.
) is activated. As a result, the target tracking performance of the seven aircraft will improve, ultimately resulting in high guidance accuracy. Optical window (2)
Air resistance increases due to the exposure of the light wave seeker (4), but this effect is not a problem because the time for guidance using the light wave seeker (4) is usually limited to a short time during final guidance. be.

FIG. 2 is an explanatory diagram showing the removal of the guided projectile according to the present invention, and FIG. 2 ta+ shows the state when the guided projectile according to the present invention is far away from the target.
FIG. 2(b) shows a state in which the guided flying object according to the present invention is at a short distance from the target.

FIG. 3 is a diagram showing another embodiment of the present invention, (5
) is an opening/closing window, (6) is a tube, and (7) is a nozzle.

FIG. 3(a) shows the state when the guided projectile according to the present invention is far away from the target, and FIG. 3(b)
The guided projectile according to this invention.

It shows a cross section of the state when the object is close to the target. When the guided missile according to the present invention is located at a long distance from the target, as shown in FIG.
5) is closed following the shape of the radio dome (1). At this time, the guided flying object is guided to the target by the radio wave seeker (3). The shape of the radio dome (1) is
Since it is optimally designed considering radio wave characteristics and aerodynamic characteristics, it is possible to obtain good radio wave characteristics, that is, long detection distance and low air resistance. When a guided missile according to another embodiment of the present invention approaches a target and is at a close enough distance that the light wave seeker (4) can be used, a command from the radio wave seeker (3) is sent to the opening/closing window (5). ), and the opening/closing window (5) is
It is opened in the direction of the arrow as shown in Figure (b). As a result, the light wave seeker (4) operates using the optical window (2) having a high light wave transmittance, that is, a large light wave incident angle. Furthermore, at this time, the cooling gas for the light wave seeker (4) is supplied to the tube (6).
the tube (
6), the optical window (2) is heated by aerodynamic heating, preventing the temperature from rising and preventing the optical window (2) from emitting infrared rays. It can be suppressed. Therefore, the light wave seeker (
4) Target tracking performance is improved, ultimately resulting in high guidance accuracy. Air resistance increases due to the exposure of the optical window (2), but the effect is9 Normally, the light wave seeker (2)
) is limited to a short time during the final induction, so it does not amount to 9 problems.

FIG. 4 is an explanatory diagram showing the appearance of a guided flying object according to another embodiment of the present invention, and FIG. On the other hand, FIG. 4(b) shows a state where a guided flying object according to another embodiment of the present invention is located at a short distance from the target.

[Effects of the Invention] As explained above, this invention reduces the air resistance of a guided projectile during early and mid-flight by operating a light wave seeker according to the distance to the target by opening and closing the opening/closing window. Make it smaller to extend the distance it can fly, and when it comes time to fly.

Since the light wave seeker can be operated using an optical window that has high transmittance for light waves emitted by the target, tracking performance for the movement of the target can be improved. Furthermore, another embodiment of the present invention uses the cooling gas of the light wave seeker to suppress the temperature rise due to aerodynamic heating of the optical window, thereby preventing performance deterioration of the light wave seeker, thereby improving the tracking performance.
The final effect is to increase accuracy.

[Brief explanation of the drawing]

FIG. 1 is a sectional view showing an embodiment of the present invention, and FIG. 2 is an external view of a guided flying object according to the present invention. FIG. 3 is a sectional view showing another embodiment of this invention, FIG. 4 is an external view of a guided flying object according to another embodiment of this invention,
FIG. 5 is an explanatory diagram showing a conventional guided flying object. In the figure, (1) is a radio dome, (2) is an optical window, and (3) is a radio dome.
) is a radio wave seeker, (4) is a light wave seeker, (5) is an opening/closing window, (6) is a tube, and (7) is a nozzle. Note that the same line numbers in Figure 9 indicate the same or corresponding parts.

Claims (1)

[Claims] (1) In a guided flying vehicle that has two types of target tracking means, light waves and radio waves, the dome of the guidance device of the guided flying object has an optical window, a light wave seeker, and a guidance device that initially closes along the dome. A guided flying vehicle characterized by being provided with an opening/closing window that opens according to a signal from the aircraft. (2) A patent claim characterized in that the dome of the guiding device is provided with a tube for guiding cooling gas, and a nozzle attached to the tip of the tube for spraying the cooling gas onto the entire external surface of the optical window. Range of guided flying objects described in paragraph (1).