JPH0518700A - Guided missile - Google Patents

Abstract

PURPOSE:To prevent the deterioration of strength of a ring and the deformation as well as the collapse of a radome due to heat stress. CONSTITUTION:A guided missile, having a guidance controller for catching a target by a radio wave antenna 1, is provided with a radome 8, a high- pressure gas source 4 and a plurality of high-pressure pipelines 5 provided in the guidance controller while high-pressure gas releasing holes 6, connected to the tip end of the high-pressure pipeline 5, are formed on the rear end of the radome. A high-pressure gas source and a guiding means, guiding gas, accumulated in the high-pressure gas source, to the outer surface of a ring 2, are provided in the guidance device of the guided missile to prevent the inflow of heat, generated upon flying with a high speed, as well as the temperature rise of the ring by discharging the gas to the outer surface of the ring 2.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to improving the strength of a guide vehicle that captures a target by using a radio wave antenna and guides the target.

[0002]

2. Description of the Related Art FIG. 6 is a schematic view of a guide vehicle using a conventional radio wave antenna. In the figure, 1 is a radio antenna, 2
Is a ring, 3 is a shock wave, and 8 is a radome. When a conventional guided vehicle using the radio wave antenna 1 flies at a high speed beyond the speed of sound, a strong shock wave 3 is generated in the front,
The fluid is rapidly decelerated, the kinetic energy of the fluid is converted into heat energy, and the fluid is heated. This is called aerodynamic heating.

Aerodynamic heating is an important issue, especially for guided vehicles that fly at high speeds. Aerodynamic heating is a phenomenon that occurs when the kinetic energy of a fluid is converted into heat energy as described above, and is caused by friction when air flows along the surface of a guided flying body and compression of air near the stagnation point. To do. Friction and compression convert the kinetic energy of the air into heat energy, which flows into the thin air layer around the guided vehicle, the boundary layer, which raises the temperature of the air in the boundary layer. The temperature rise of air due to aerodynamic heating is given by the following equation.

[0004]

[Equation 1]

Here, γ is the specific heat ratio of air and is usually 1.
4 is used. M∞ is the flight speed of the guided flying object, T
∞ is the absolute temperature of air. For example, when the guided flying object flies in the air at a temperature of 20 ° C. at 5 times the speed of sound, that is, M∞ = 5, the temperature of the air becomes 1500 ° C. or more at the stagnation point of the guiding flying object. In this way, heat flows from the air heated to a very high temperature into the boundary layer formed around the guided vehicle, raises the temperature of the boundary layer, and further heat enters the surface of the guided vehicle. However, the temperature of the guided vehicle will rise. At this time, the amount of heat flowing into the boundary layer from the outside air is proportional to the heat transfer coefficient on the outer surface of the boundary layer and the temperature difference between the outside air and the outer surface of the boundary layer. The amount of heat flowing from the boundary layer into the guide vehicle is proportional to the heat transfer coefficient on the surface of the guide vehicle and the temperature difference between the boundary layer and the surface of the guide vehicle. This can be expressed as follows.

[0006]

[Equation 2]

Here, Q is the amount of heat flowing in, H is the heat transfer coefficient, and (T ₂ −T ₁ ) is the temperature difference between the outside air and the outer surface of the boundary layer or the temperature difference between the boundary layer and the surface of the guided vehicle. is there.

On the other hand, the radome 8 and the ring 2 decrease in material strength due to temperature rise due to aerodynamic heating, and
There is a difference in the coefficient of thermal expansion between both materials, so radome 8 and ring 2
There was a risk that the thermal stress generated in the mounting part would be excessive and the radome would be destroyed.

[0009]

As described above, in the conventional guided vehicle, the strength of the ring is lowered due to the temperature rise of the ring due to the aerodynamic heating when flying at high speed, and the radome and the ring are However, since there is a difference in the coefficient of thermal expansion, there has been a problem that the thermal stress due to the thermal expansion generated in the mounting portion of the radome and the ring becomes excessive and the radome is destroyed.

The present invention has been made to solve the above problems, and blows a gas onto the outer surface of a ring to cause a low-temperature gas flow between a heated air flow behind a shock wave and an object. Is formed to prevent heat from flowing in and suppress the temperature rise of the ring.

[0011]

A guided flying vehicle according to the present invention has a high-pressure gas source, and is provided with means for guiding and blowing the gas to the outer surface of the ring by a plurality of high-pressure pipes.

Further, a ring-shaped high-pressure pipe having a plurality of holes is used in order to widen the space in the induction control device.

Further, a plurality of high-pressure pipes are arranged outside the ring in order to eliminate the need to open a gas discharge hole in the radome.

Further, one ring-shaped high-pressure pipe having a plurality of holes is arranged outside the ring in order to reduce air resistance.

Further, a pressure vessel for enclosing a radio wave antenna is used in order to eliminate unnecessary protrusions on the outside, prevent an increase in air resistance, and simplify the structure.

[0016]

In the present invention, it is possible to prevent the inflow of heat from the outside air by blowing the gas onto the outer surface of the ring, suppress the rise in the temperature of the ring, and prevent the strength of the ring from being reduced and the radome from being broken due to thermal stress. At the same time, the flight speed range is expanded.

[0017]

【Example】

Example 1. 1A and 1B are explanatory views showing an embodiment of the present invention. FIG. 1A is a sectional view and FIG. 1B is a perspective view. In the figure, 4 is a high pressure gas source, 5 is a high pressure pipe, and 6 is a gas discharge hole. When the guided flying object according to the present invention flies at a high speed exceeding the speed of sound, a shock wave 3 is generated as shown in FIG. 1 (a), and behind the shock wave 3, the gas is rapidly decelerated and the kinetic energy becomes Heat is generated by being converted into energy and by friction on the surface of the guided vehicle.

The guide vehicle according to the present invention has a high-pressure gas source 4 inside the airframe, and the gas stored in the high-pressure gas source 4 is arranged inside the airframe as shown in FIG. 1 (a). The high-pressure pipe 5 guides the gas to the gas discharge hole 6 provided on the rear end of the radome 8 and discharges it to the outside air. The released gas forms a flow layer between the flow of the outside air and the ring 2 as shown by the broken line in FIG. At this time, the released gas itself absorbs the heat in the heated boundary layer around the guided vehicle, so that the temperature of the boundary layer decreases. Further, since the thickness of the boundary layer increases due to the released gas, the temperature gradient between the surface of the boundary layer and the surface of the guided vehicle becomes gentle, and the inflow of heat decreases. Further, the released gas reduces the velocity in the boundary layer and reduces the heat transfer coefficient, so that the heat inflow to the guide vehicle is reduced. With the above effects, the inflow from the outside air heated by the aerodynamic heating can be significantly reduced.

Example 2. 2A and 2B are explanatory views showing another embodiment of the present invention. FIG. 2A is a sectional view and FIG. 2B is a perspective view. In this embodiment, there is only one high-pressure pipe 5 in the induction controller, which is piped along the inner wall of the radome 8 in a ring shape, and a plurality of holes are formed at the positions connected to the emission holes 6 of the radome 8. ing.

In this case, since there is only one high-pressure pipe 5, a large space can be secured in the induction control device, which is advantageous for mounting electronic equipment.

Example 3. 3A and 3B are explanatory views showing another embodiment of the present invention. FIG. 3A is a sectional view and FIG. 3B is a perspective view. In this embodiment, a plurality of high-pressure pipes 5 are arranged outside at regular intervals in the circumferential direction, and gas is discharged from the discharge holes 6 at the tip of the high-pressure pipe 5.

Therefore, since it is not necessary to provide the radome 8 with a discharge hole for discharging a gas, the strength of the radome 8 is not lowered, which is advantageous when the aerodynamic load acting on the radome 8 is extremely severe. At the same time, a large space can be secured in the guidance control device, which is advantageous for mounting electronic devices.

Example 4. 4A and 4B are explanatory views showing another embodiment of the present invention. FIG. 4A is a sectional view and FIG. 4B is a perspective view. In this embodiment, the high pressure pipe 5 is connected to the radome 8
The pipe is formed in a ring shape along the outer wall of, and a plurality of gas discharge holes 6 are provided at circumferential positions.

Therefore, a large space can be secured in the guidance control device, which is advantageous for mounting electronic equipment and at the same time,
Since only one pipe is exposed to the outside, there is also an advantage that it does not cause an excessive increase in resistance.

Example 5. 5A and 5B are explanatory views showing another embodiment of the present invention. FIG. 5A is a sectional view and FIG. 5B is a perspective view. In this embodiment, the radio wave antenna 1 is housed in the pressure vessel 7, the gas from the high-pressure gas source 4 is sent to the pressure vessel 7 through the high-pressure pipe, and the outside air is emitted from a plurality of discharge holes 6 provided at the rear end of the radome 8 in the circumferential direction. To release.

Therefore, there is an advantage that the structure is simple because there is no unnecessary protrusion on the outside so that the resistance does not increase and a complicated piping system is not required.

[0027]

As described above, according to the present invention, the high-pressure gas source and the means for guiding the gas stored in the high-pressure gas source to the outer surface of the ring are provided in the guide device for the guide vehicle.
By releasing the heat to the outer surface of the ring, the heat generated when flying at high speed is prevented from flowing into the ring, the temperature rise of the ring is suppressed, the strength of the ring is reduced, and the deformation and deformation of the radome due to the thermal stress occur. You can prevent destruction.

[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 conventional guidance control device.

[Explanation of symbols]

1 radio antenna Two rings 3 shock wave 4 High pressure gas source 5 high pressure piping 6 emission holes 7 Pressure vessel 8 radome

Claims (4)

[Claims] 1. A high-pressure gas source and a gas from the high-pressure gas source at the rear end of the radome in a guidance aircraft having a guidance control device for capturing a target by a radio-wave antenna and a radome for protecting the radio-wave antenna. A guide aircraft which is provided with a gas discharge means for guiding and spraying it on the outer surface. 2. A guide flight according to claim 1, wherein a hole for discharging high pressure gas is formed at the rear end of the radome as the gas discharging means, and the hole is connected to the outlet of the high pressure pipe connected to the high pressure gas source. Shobo. 3. A high pressure gas discharge hole is formed as a gas discharge means at the outlet of the tip of the high pressure pipe connected to the high pressure gas source,
The guide vehicle according to claim 1, wherein the hole is arranged outside the radome. 4. A pressure vessel for enclosing a radio wave antenna as a gas discharging means, and a high pressure pipe for feeding the gas from a high pressure gas source to the pressure vessel are provided, and the gas from the pressure vessel is provided outside the rear end of the radome. The guide flying vehicle according to claim 1, wherein a hole for discharging high-pressure gas to be discharged to the surface is formed at the rear end of the radome.