JPH063098A - Guided flight - Google Patents

Abstract

(57) [Abstract] [Purpose] In a guided vehicle with two types of target tracking means, light waves and radio waves, the air resistance is reduced and the destruction of the optical window part due to aerodynamic heating is prevented, resulting in high guidance accuracy. To have. [Structure] A retractable light wave seeker box including a light wave seeker 4 and an optical window 2 is attached to the inside of the machine body. When guiding by the radio wave seeker 3, the optical window section 2 is stored inside the machine body, and when the distance where the light wave seeker can be used is reached, the light wave seeker box is taken out of the machine body in accordance with a signal from the guiding device and the optical window section 2 is used. To appear and activate the light wave seeker.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to extension of the range of a guided flying object, improvement of guiding accuracy, prevention of performance deterioration of an optical sensor due to heat generated during flight, and prevention of deformation and destruction of an optical window due to thermal stress. It is about.

[0002]

2. Description of the Related Art FIG. 7 is a cross-sectional view of a conventional guiding device for a guided flying object, wherein 1 is a radio dome, 2 is an optical window, 3 is a radio wave seeker, and 4 is a light wave seeker. A conventional guided vehicle having two tracking means for radio waves and light waves as shown in FIG. 7 uses the radio wave seeker 3 to track a target at a long distance, and a light wave when it is at a short distance. Track with the Seeker 4. Since the electric wave seeker generally has a longer detection distance than the optical wave seeker, a long-range guided vehicle can be obtained.
On the other hand, the light wave seeker detects and tracks infrared rays emitted from the target, so that a guided flying object that is difficult to be detected by the target can be obtained. By utilizing such characteristics of both the radio wave seeker and the light wave seeker, it is possible to realize a guided flying object that has a long range and is difficult to be detected by a target.

In the conventional guided vehicle, the radio wave dome 1 and the optical window 2 are shown in FIG.
It must be spherical as shown in (a) or pyramidal as shown in FIG. 7 (b). When a spherical dome is used as shown in FIG. 7 (a), the light wave seeker 4 needs to be arranged at the center of the axis of the body of the guided flight body so that there is no optical path difference of the light wave with respect to the light wave seeker 4. Radio Seeker 3
Since the antenna cannot be placed in the central part, the detection performance deteriorates. In addition, since the spherical dome has high air resistance, the velocity of the guided flying body is rapidly lost and the range is shortened, and at the same time, the turning performance during guided flying is deteriorated.

Further, the spherical dome is also disadvantageous to the aerodynamic heating generated when flying at high speed. When an object with a blunt tip such as a hemisphere flies at a high speed exceeding the speed of sound, a strong shock wave is generated in front of the flying object, and the kinetic energy of the fluid is converted into thermal energy by friction and compression. This energy flows into a thin layer of air around the guided vehicle, the boundary layer, which raises the temperature of the air in the boundary layer. This is so-called aerodynamic heating. The amount of heat flowing from the boundary layer into the guided vehicle increases in proportion to the heat transfer coefficient on the surface of the guided vehicle and the temperature difference between the boundary layer and the surface of the guided vehicle. At this time, if the optical window is heated and its temperature rises, the optical window itself emits infrared rays, and the optical sensor cannot correctly track the target.

Further, since the guided aircraft usually accelerates rapidly, the temperature rise due to aerodynamic heating is also rapid, and there is a problem that the thermal stress due to thermal expansion becomes excessive and the optical window is destroyed.

On the other hand, as shown in FIG. 7 (b), when a pyramidal dome is used, the light wave seeker 4 can be arranged so as to be offset from the center of the axis of the body of the guided vehicle, so that the radio wave seeker 3 is at the center. The antenna can be placed in the part, and the detection performance does not deteriorate. However, in order to increase the incident angle of light on the optical window 2 and ensure the optical performance, it is necessary to increase the angle θ of the pyramid. As a result, the air resistance of the dome becomes large, the range becomes short as in the case of the spherical dome, and at the same time, problems such as deterioration of the turning performance and the performance of the optical sensor during guided flight and destruction of the optical window occur.

[0007]

[Problems to be Solved by the Invention] As described above,
In conventional guided air vehicles, the temperature of the optical dome rises due to aerodynamic heating when flying at high speed. As a result, the performance of the optical sensor is deteriorated, so that there is a problem that the guiding accuracy is deteriorated. There is also a problem that it is necessary to limit the operation speed to a low value and it is not possible to cope with a target that makes a sharp turn at high speed. Further, since the guided flying body normally accelerates rapidly, the temperature rise due to aerodynamic heating is also rapid, and there is a problem that the thermal stress due to thermal expansion becomes a problem and the optical dome is destroyed.

The present invention has been made in order to solve such a problem, and the light wave seeker portion is stored in the body,
It was made to project outside the fuselage when necessary. This allows
The body shape suitable for the radio wave seeker and the light wave seeker can be selected according to the distance to the target.

In addition to the above, gas or liquid is blown into the boundary layer of the optical window, heat of vaporization when the liquid vaporizes, and latent heat accompanying the phase change when the solid liquefies-vaporizes or sublimates, etc. This method is intended to suppress the temperature rise of the optical window portion due to aerodynamic heating when the optical window is exposed.

[0010]

According to the present invention, when the target is at a long distance without using the light wave seeker, the optical window and the light wave seeker should not be exposed to the outside, and the flight should be performed in the optimum shape for flight. The air resistance is reduced to increase the range and at the same time prevent the flight speed from decreasing. If the target is within a short distance to use the light wave seeker, remove the retractable light wave seeker box stored inside the aircraft so that the optical window appears, and activate the light wave seeker. Improves tracking performance for movement.

Further, as a method of projecting the lightwave seeker box to the outside, the lightwave seeker box is held by a hinge and a clasp, and the clasp is released by a signal sent from the guiding device, and the lightwave seeker box and the body are intervened. The optical window is exposed to the outside of the machine by the pushing force of the spring.

Further, as a method of projecting the lightwave seeker box to the outside, the lightwave seeker box is held by a hinge, and when a signal is sent from the guiding device to the actuator, the optical window portion in which the actuator is activated appears outside the machine body. It was done like this.

As another method of projecting the lightwave seeker box to the outside of the dome, a part of the outer surface of the fuselage is removed according to a signal sent from the guiding device, and the lightwave seeker box is projected to the outside of the fuselage from the back. It is the one.

In addition, the guide vehicle according to another embodiment of the present invention has the effect of injecting a gas or a liquid into the gas flow outside the optical window protruding to the outside of the body to thicken the boundary layer and the like. The amount of heat transfer to the surface is reduced.

In addition, a guiding flying body according to another embodiment of the present invention is provided with a small hole around the optical window, through which the liquid is vaporized and discharged to absorb the heat generated in the boundary layer. Is.

In addition, in another embodiment of the present invention, a guided flying object is a solid having a high liquefaction-vaporization or sublimation property, which covers the periphery of the optical window, and the optical window portion protruding to the outside of the machine body is heated by vaporization heat. It is designed to be cooled.

[0017]

In the guided vehicle according to the present invention, a light wave seeker box containing a light wave seeker is attached inside a predetermined position in the circumferential direction of the machine body. By storing the light wave seeker box during the first mid-range flight, the air resistance of the guided vehicle is reduced and the flight distance is extended. At the end of flight, the light wave seeker box is brought out of the airframe so that the optical window appears, and the light wave seeker is activated to improve the tracking performance for the target.

[0018]

【Example】

Example 1. FIG. 1 is an explanatory view showing an embodiment of the present invention, in which 5 is a hinge, 6 is a stopper plate, and 7 is a spring. Figure 1
FIG. 1 (a) shows a state in which the guided vehicle according to the present invention is at a long distance from the target, and FIG. 1 (b) shows that the guided vehicle according to the present invention is at a short distance from the target. The state in some cases is shown.

In the guided vehicle according to the present invention, a lightwave seeker box including a lightwave seeker 4 and an optical window 2 is mounted inside a predetermined position in the circumferential direction of the body. This light wave seeker box has a surface having the same shape as the outer shape of the machine body and an optical window surface.

When the guided vehicle is at a long distance from the target, the light wave seeker box portion is housed inside the body as shown in FIG. 1 (a). The light wave seeker box and the inside of the machine body are connected via a hinge 5 and a spring 7, and the spring 7 is contracted when stored. At this time,
The guided flying body is guided to the target by the radio wave seeker 3. The shape of the radio wave dome 1 is optimally designed in consideration of the radio wave characteristics and the aerodynamic characteristics, so that good radio wave characteristics, that is, long detection distance and low air resistance can be realized.

When the guide vehicle according to the present invention approaches the target and comes close enough to use the light wave seeker 4, the command from the radio wave seeker 3 is transmitted to the stopper plate 6 and disengages. The seeker box rotates around the hinge 5 by the force stored in the spring 7 and comes out of the body. As a result, as shown in FIG. 1B, the optical window 2 appears outside the flying body, and the light wave seeker 4 operates. As a result, the target tracking performance of the flying object is improved, and ultimately high guidance accuracy is obtained. The influence of the increase in the air resistance due to the change in the external shape of the machine body is not a problem because the time for guiding using the light wave seeker 4 is usually limited to the short time during the final guidance.

Example 2. In the first embodiment, the light wave seeker box is projected to the outside of the machine by the spring 7,
An actuator is used in the second embodiment shown in FIG. Figure 2
2A shows a state where the flying object is at a long distance from the target, and FIG. 2B shows a state where the flying object is at a short distance to the target. When the flying object becomes close enough to use the light wave seeker 4, the command from the radio wave seeker 3 is transmitted to the actuator 8 by the signal cable, and the light wave seeker box rotates by the actuator 8 about the hinge 5. The same operation as 1 can be expected.

Example 3. In the first and second embodiments, the light wave seeker box rotates about the hinge, and as a result, the optical window is exposed to the outside of the machine body. On the other hand, in the third embodiment shown in FIG. 3, a command from the radio wave seeker is transmitted to the stopper plate 6 through the signal cable 9, and when the stopper plate 6 is released, the cover 10 forming a part of the machine body is removed. The light wave seeker box that has been removed and hung on the rail 11 is pushed out by the force of the spring 7 and protrudes outside the fuselage.

Example 4. FIG. 4 is an explanatory view showing another embodiment of the present invention, FIG. 4 (a) is a sectional view, and FIG. 4 (b).
3A and 3B are perspective views, each showing a state in which the guide vehicle is in a short distance from the target. In the figure, 12 is a high-pressure gas container for cooling, 13 is a flexible tube, and 14
Is a gas discharge hole. The guided air vehicle according to the present invention has a high-pressure gas container for cooling inside the airframe, and a gas such as nitrogen stored therein is provided by a flexible tube 13 on the tip side of the airframe around the optical window 2. It is led to the discharge hole 14 and discharged to the outside air. The released gas forms a flow layer between the outside air and the flying object as shown by the broken line in Fig. 4 (a), and the thickness of the boundary layer increases. The velocity gradient with the body surface becomes gentle, and the heat inflow decreases. In addition, the gas reduces the velocity in the boundary layer and reduces the heat transfer coefficient, which reduces the inflow of heat into the guided vehicle. From the above effects,
The inflow of heat from the outside air heated by aerodynamic heating can be significantly reduced. Since the gas discharge hole 14 receives the dynamic pressure of the flow of the outside air, the pressure of the gas needs to be high in order to overcome this and discharge the gas.

It is also conceivable to use a cooling liquid such as water instead of the high pressure gas. However, if the liquid stored in the liquid container 15 is placed inside the airframe,
Emission hole 1 provided on the optical window 2 by the tube 13
A high-pressure pump is required in order to lead to No. 4 and further to discharge to the outside air from the discharge hole 14.

Example 5. FIG. 5 is an explanatory view showing another embodiment of the present invention, FIG. 5 (a) is a sectional view, and FIG. 5 (b).
3A and 3B are perspective views, each showing a state in which the guide vehicle is in a short distance from the target. In this embodiment, after pumping the liquid to the optical window with a high pressure pump 16,
It is leached to the outside through the small holes of the perforated plate 17 adhered to the body tip side outside the optical window, vaporized and discharged into the boundary layer. At this time, in addition to the effect of Example 4, the temperature in the boundary layer can be lowered by the endothermic reaction accompanying the phase change of the coolant.

Example 6. FIG. 6 is an explanatory view showing another embodiment of the present invention, FIG. 6 (a) is a sectional view, and FIG. 6 (b).
3A and 3B are perspective views, each showing a state in which the guide vehicle is in a short distance from the target. In this example,
The periphery of the optical window 2 of the guide vehicle is covered with a solid 18 for cooling. This cooling solid may be sublimable or liquefied.
A highly vaporizable one such as phenol resin is used. When the guided flying object approaches the target, the light wave seeker box appears outside the body, and the optical window 2 is exposed to the outside air and becomes high temperature, the solid is liquefied-vaporized or sublimated. At this time, since the heat in the heated boundary layer around the induction flying object is absorbed as latent heat, the temperature of the boundary layer decreases.
The present invention has the advantage that the resistance is not increased because it does not have unnecessary protrusions on the outside, and at the same time the structure is simple because it does not require a piping system inside.

[0028]

Since the present invention is constructed as described above, it has the following effects.

Attach a lightwave seeker box containing a lightwave seeker at a predetermined position in the circumferential direction of the guided flight,
By storing the light wave seeker box inside the aircraft during the first mid-range flight, the air resistance of the guided flight can be reduced and the flight distance can be extended. Also, at the time of terminal flight, since the optical window with high transmittance of light waves emitted by the target is projected outside the aircraft to follow the target using the light wave seeker, it is difficult for the guided flight object to be found from the target. can get. In this way, by selectively using the radio wave seeker and the light wave seeker according to the distance from the target, it is possible to improve the tracking performance for the motion of the target.

Further, another embodiment of the present invention is (1)
A means for guiding the cooling high-pressure gas or liquid to the tip of the airframe around the outside of the optical window is provided, and is discharged to the boundary layer outside the optical window. (2) A small hole is provided around the outside of the optical window, and the liquid is stained through this (3) Liquefaction around the optical window-covering it with a highly vaporizable or sublimable solid so that the optical window undergoes a phase change when exposed to the outside air,
By preventing the heat generated when flying at high speed from flowing into the optical window, the temperature rise of the optical window is suppressed, and the deterioration of the performance of the optical sensor due to radiation from the optical window and thermal stress Deformation and destruction can be prevented.

[Brief description of drawings]

FIG. 1 is a diagram showing a guidance control device according to a first embodiment of the present invention.

FIG. 2 is a diagram showing a guidance control device according to a second embodiment of the present invention.

FIG. 3 is a diagram showing a guidance control device according to a third embodiment of the present invention.

FIG. 4 is a diagram showing a guidance control device according to a fourth embodiment of the present invention.

FIG. 5 is a diagram showing a guidance control device according to a fifth embodiment of the present invention.

FIG. 6 is a diagram showing a guidance control device according to a sixth embodiment of the present invention.

FIG. 7 is a diagram showing a conventional guidance control device.

[Explanation of symbols]

 1 Radio Dome 2 Optical Window 3 Radio Wave Seeker 4 Light Wave Seeker 5 Hinge 6 Clasp 7 Spring 8 Actuator 9 Signal Cable 10 Cover 11 Rail 12 High Pressure Gas Container for Cooling 13 Flexible Tube 14 Ejection Hole 15 Cooling Liquid Container 16 Pump 17 Yes Perforated plate 18 Highly vaporizable solid for cooling

─────────────────────────────────────────────────── ─── Continuation of the front page (51) Int.Cl. ⁵ Identification code Office reference number FI Technical display location H01Q 1/42 7037-5J H05K 7/20 Q 8727-4E

Claims (3)

[Claims] 1. A guide vehicle having two types of target tracking means for light waves and radio waves, and having a radio dome on the tip side thereof, at a predetermined position in the circumferential direction of the machine, protruding from the outer surface of the machine during use. A guided air vehicle characterized by being provided with a light wave seeker box having an optical window for 2. The guide flying vehicle according to claim 1, wherein the boundary layer outside the optical window is provided with a mechanism for discharging a gas or a liquid. 3. The guided flying vehicle according to claim 1, wherein the periphery of the optical window is covered with a solid for cooling the optical window by liquefaction-vaporization or sublimation.