JP6727151B2 - Radome for flying objects - Google Patents

Description

TECHNICAL FIELD The present invention relates to a radome for a flying object that protects electronic devices mounted on the flying object.

An electronic device such as an antenna that measures the distance and azimuth to the target is installed in the flying object that flies toward the target.To protect the electronic device from aerodynamics when flying, A radome is installed at the tip.

Many flying objects reach supersonic or hypersonic speed within a short time of a few seconds from the start of flying, and during flight, they are rapidly heated by friction with air, and the aircraft is exposed to high temperatures. Heating by friction with air during flight is called aerodynamic heating. In particular, the radome installed at the tip of the flying body is one of the parts of the flying body where the thermal environment is severe, and it receives a large aerodynamic load, large aerodynamic heating, thermal shock, and aerodynamic heating. Is heated to about 1000°C. Therefore, the radome body is required to have high strength and heat resistance and thermal shock resistance, and therefore, it is common to use ceramics, which is a dielectric material having a heat resistance temperature of 1000° C. or higher.

Furthermore, it is necessary for the flying object to transmit and receive radio waves via the radome body and measure the distance and direction to the target when flying. Therefore, the radome body is also required to have radio wave transparency. In order to satisfy the above required performance, fine ceramics having a low coefficient of thermal expansion are generally used as the material of the radome body. Generally, the coefficient of thermal expansion of fine ceramics is 5×10 ⁻⁶ /° C. or less.

On the other hand, the aircraft body of the flying body generally uses a high-rigidity material such as iron or aluminum. The coefficient of thermal expansion of materials such as iron or aluminum is usually in the range of 10×10 ⁻⁶ /° C. to 30×10 ⁻⁶ /° C.

There is a large difference in the coefficient of thermal expansion between the radome body and the aircraft body.Therefore, if the two are directly joined, a large amount of thermal stress will be generated at the joint due to aerodynamic heating during flight, and the radome body Cracks or cracks will occur. Therefore, the radome body is fixed to the machine via a radome ring made of fiber-reinforced plastic (FRP), which has high rigidity and a relatively low coefficient of thermal expansion, and the radome body and the radome ring are bonded together. It is common to fix with an agent. An epoxy-based or silicon-based adhesive is often used to fix the ceramic radome body and the radome ring.

JP-A-63-263197 JP-A-11-37699

As the radome body becomes hotter due to aerodynamic heating, the adhesive for fixing the radome body and the radome ring also gets hotter. Therefore, if the flight speed becomes high or the flight time becomes long and the total amount of aerodynamic heating increases, the adhesive will exceed the heat resistant temperature and the fixing strength between the radome body and the radome ring will decrease. There is a possibility that it will end up.

The present invention has been made in view of the above, and an object of the present invention is to obtain a radome for a flying object that can maintain the combination of the radome body and the radome ring even at high temperatures.

In order to solve the above-mentioned problems and to achieve the object, a radome for a flying vehicle according to the present invention is a radome ring fixed to a flying vehicle flying by radio wave induction toward a target, and a And a radome body installed at the tip. A radome for a flying vehicle according to the present invention includes a coupling member that couples a radome body and a radome ring with a frictional force due to surface pressure.

According to the present invention, there is an effect that it is possible to obtain a radome for a flying object that can maintain the connection between the radome body and the radome ring even under high temperature.

Sectional drawing which shows the structure of the radome for flying bodies which concerns on Embodiment 1 of this invention. 1 is a perspective view of a radome ring of a flying radome according to a first embodiment. Sectional drawing which shows the state before connecting the radome body and radome ring of the radome for flying bodies which concerns on Embodiment 1. Sectional drawing which shows the state after connecting the radome body and radome ring of the radome for flying bodies which concerns on Embodiment 1. Sectional drawing which shows the structure of the radome for flying bodies which concerns on Embodiment 2 of this invention. Sectional drawing which shows the state before connecting the radome body and radome ring of the radome for flying bodies which concerns on Embodiment 3 of this invention. Sectional drawing which shows the state after connecting the radome body and radome ring of the radome for flying bodies which concerns on Embodiment 3. FIG. Sectional drawing which shows the state before connecting the radome body and radome ring of the radome for flying bodies which concerns on Embodiment 4 of this invention. Sectional drawing which shows the state after connecting the radome body and radome ring of the radome for flying bodies which concerns on Embodiment 4.

Hereinafter, a radome for a flying object according to an embodiment of the present invention will be described in detail with reference to the drawings. The present invention is not limited to the embodiments.

Embodiment 1.
1 is a sectional view showing the structure of a radome for a flying object according to Embodiment 1 of the present invention. The flying body 20 measures the distance and azimuth to the target by radio waves transmitted and received by the electronic device 10, and flies toward the target by radio wave induction. The radome 50 for flying bodies connects the radome ring 3 fixed to the machine body 4, the radome body 1 installed at the tip of the machine body 4, and the radome body 1 and the radome ring 3 by frictional force due to surface pressure. And a coupling member 2. The radome ring 3 can be fixed to the machine body 4 by fastening with screws, but may be fixed by other methods.

The radome body 1 is attached to the machine body 4 mounting the electronic device 10 via the radome ring 3. The radome body 1 and the radome ring 3 are joined by a joining member 2.

The radome body 1 has a streamlined shape in which the tip of the outer shell is sharp, the outer diameter of the outer shell spreads smoothly from the tip to the rear end, and the rear end is open and hollow. A male screw 2a is formed on the entire outer wall of the coupling member 2.

Ceramics can be applied to the material of the radome body 1, but the material is not limited to this. FRP can be applied to the material of the radome ring 3, but the material is not limited to this. The material of the radome ring 3 may be selected according to the characteristics of the material used for the radome body 1, and aluminum alloy, titanium alloy, invariant steel, or Kovar can be applied.

FIG. 2 is a perspective view of the radome ring of the flying radome according to the first embodiment. The radome ring 3 is formed with a plurality of slits 5 extending from the tip side in the cylinder central axis direction. A female screw 6 is provided on the inner wall of the radome ring 3 in the region between the slits 5. FIG. 3 is a cross-sectional view showing a state before the radome body and the radome ring of the flying radome according to the first embodiment are joined together. FIG. 4 is a cross-sectional view showing a state after the radome body and the radome ring of the flying radome according to Embodiment 1 are coupled. As shown in FIG. 3, the outer diameter of the region between the slits 5 of the radome ring 3 is smaller than the inner diameter of the radome body 1 in a state before the radome body 1 and the radome ring 3 are coupled to each other. The ring 3 can be inserted inside the radome body 1. As shown in FIG. 4, by tightening the male screw 2a of the coupling member 2 to the female screw 6 of the radome ring 3, the region between the slits 5 of the radome ring 3 is expanded in the radial direction of the cylinder and the diameter is increased. .. When the outer wall 3a in the region between the slits 5 of the radome ring 3 that has been pushed out and the inner wall 1a of the radome body 1 come into contact with each other, a frictional force due to surface pressure is generated between the radome body 1 and the radome ring 3, The radome body 1 and the radome ring 3 are coupled by a frictional force. Since the bonding is performed by frictional force, the bonding force between the radome body 1 and the radome ring 3 is maintained even at a high temperature higher than the heat resistant temperature of the adhesive.

Further, by providing the inner wall 1a with a taper so that the inner diameter decreases toward the rear end portion 1b side of the radome body 1, when the radome body 1 receives a load in the distal direction, a gap between the radome body 1 and the radome ring 3 is formed. It is possible to prevent the radome body 1 from falling off the radome ring 3 by increasing the frictional force.

Further, the female screw 6 of the radome ring 3 is tapered so that the inner diameter decreases toward the tip side, so that the region between the slits 5 of the radome ring 3 widens in the radial direction of the cylinder when the coupling member 2 is screwed. The effect is increased, and the radome body 1 and the radome ring 3 can be more firmly coupled.

When flying, a temperature distribution occurs in which the temperature is high on the outer side and low on the inner side from the outer wall 1c of the radome body 1 to the inner wall 2b of the coupling member 2, so that the coupling member 2 on the inner side from the outer radome body 1 is generated. There may be a difference in thermal expansion due to temperature rise over time. When the coefficient of thermal expansion of the joining member 2 is smaller than that of the radome body 1, the deformation amount due to the temperature rise during flight is larger in the radome body 1 than in the joining member 2, so that the radome body 1 and the radome ring 3 are May reduce the binding force of. If the materials of the radome ring 3 and the connecting member 2 are selected so that the coefficient of thermal expansion increases in the order of the radome body 1, the radome ring 3, and the connecting member 2 in accordance with the above temperature distribution, the difference in the deformation amount due to the temperature distribution will be reduced. It can be made small, and the binding force can be maintained even at high temperatures.

In the radome 50 for a flying object according to the first embodiment, since the radome body 1 and the radome ring 3 are bonded by the frictional force due to the surface pressure, the bonding force is maintained even at a high temperature higher than the heat resistant temperature of the adhesive. It is possible to

Embodiment 2.
FIG. 5 is a sectional view showing a structure of a radome for a flying object according to Embodiment 2 of the present invention. In the radome 51 for a flying object according to the second embodiment, the connecting member 2 and the body 4 of the flying object 20 are integrated. By integrating the connecting member 2 and the machine body 4, the number of parts can be reduced, and the radome body 1 and the radome ring 3 and the radome ring 3 and the machine body 4 can be simultaneously connected. ..

Embodiment 3.
FIG. 6 is a cross-sectional view showing a state before the radome body and the radome ring of the flying object radome according to the third embodiment of the present invention are coupled. FIG. 7 is a cross-sectional view showing a state after the radome body and the radome ring of the flying radome according to the third embodiment are coupled. The radome body 1 of the flying radome 52 according to the third embodiment has an inner wall 1a provided with a taper whose inner diameter decreases toward the rear end 1b side. The radome ring 3 has a plurality of screw fastening holes 3b formed on its circumference. The coupling member 2 includes a fastening portion 2d having a female screw 2c that is screw-fastened to the radome ring 3 and a contact portion 2f having an outer wall 2e that is tapered so that the thickness thereof increases in the distal direction. The same number of coupling members 2 as the holes 3b for screw fastening of the radome ring are used. The taper provided on the inner wall 1a of the radome body 1 and the taper provided on the outer wall 2e of the coupling member 2 have the same inclination. That is, the inner wall 1a of the radome and the outer wall 2e of the connecting member 2 are parallel to each other.

By fastening the radome ring 3 and the joining member 2 with the screw 7 which is a fastening member, the inner wall 1a of the radome body 1 and the outer wall 2e of the joining member 2 come into surface contact, and the radome body 1 and the radome ring 3 are It is coupled via the coupling member 2. In the radome 52 for a flying object according to the third embodiment, the inner wall 1a of the radome body 1 and the outer wall 2e of the joining member 2 are in surface contact with each other and are joined by a frictional force, so that the temperature is higher than the heat resistant temperature of the adhesive. Also in the above, it is possible to maintain the coupling force between the radome body 1 and the radome ring 3.

Since the inner wall 1a of the radome body 1 has a tapered shape in which the inner diameter becomes smaller toward the rear end portion 1b side, the radome body 1 and the radome ring 3 are more firmly coupled to each other as compared to the case where the radome body is not tapered. Further, since the coupling member 2 can be downsized as compared with the first and second embodiments, the manufacturing cost can be suppressed.

Fourth Embodiment
FIG. 8 is a cross-sectional view showing a state before the radome body and the radome ring of the flying object radome according to Embodiment 4 of the present invention are coupled. FIG. 9 is a cross-sectional view showing a state after the radome body and the radome ring of the flying radome according to the fourth embodiment are coupled. In the radome 53 for a flying vehicle according to the fourth embodiment, the radome ring 3 is composed of an outer peripheral portion 3c and an inner peripheral portion 3d. The outer peripheral portion 3c is provided with a hole 3b for screw fastening. An annular recess 3f is formed at the front end 3e of the inner peripheral portion 3d. The other points are similar to those of the third embodiment. Since the annular recess 3f is formed at the front end 3e of the inner peripheral portion 3d of the radome ring 3, it is possible to prevent the coupling member 2 from rotating when the screw 7 is fastened.

The configurations described in the above embodiments are examples of the content of the present invention, and can be combined with other known techniques, and the configurations of the configurations are not departing from the scope of the present invention. It is also possible to omit or change parts.

1 radome body, 1a, 2b inner wall, 1b rear end part, 1c, 2e, 3a outer wall, 2 coupling member, 2a male screw, 2c, 6 female screw, 2d fastening part, 2f contact part, 3 radome ring, 3b screw fastening Hole, 3c outer peripheral part, 3d inner peripheral part, 3e front end, 3f concave part, 4 body, 5 slits, 7 screws, 10 electronic devices, 20 flying bodies, 50, 51, 52, 53 flying radomes.

Claims (7)

A radome ring fixed to the airframe of the flying body flying by radio wave induction toward the target,
A radome body installed at the tip of the machine body,
A connecting member that connects the radome body and the radome ring with a frictional force due to surface pressure ;
The radome body is provided with a taper on the inner wall of which the inner diameter decreases toward the rear end side,
The radome ring has a plurality of slits formed in the central axis direction of the cylinder,
The coupling member, flight-body where said slit of said radome ring push the portion which is formed in a cylindrical radially, characterized Rukoto contacting an outer wall of an inner wall and said radome ring of said radome main body Radome. The radome ring has a female thread having a taper on the inner cylindrical surface so that the inner diameter decreases toward the tip side,
The coupling member has a ring shape with an external thread formed on the outer wall,
Flight-body radome of claim 1, wherein said coupling member is an outer wall of the radome ring which is spread is screwed, characterized in that in contact with the inner wall of the radome body. The radome for a flying object according to claim 1 or 2 , wherein the radome body, the radome ring, and the coupling member have a large thermal expansion coefficient in this order. The radome for a flying vehicle according to any one of claims 1 to 3, wherein the connecting member and the machine body are integrated. A radome ring fixed to the airframe of the flying body flying by radio wave induction toward the target,
A radome body installed at the tip of the machine body,
A connecting member for connecting the radome body and the radome ring,
A radome for a flying object, wherein the radome body and the coupling member are coupled by a frictional force due to surface pressure, and the coupling member and the radome ring are coupled by a fastening member. The radome body is provided with a taper on the inner wall of which the inner diameter decreases toward the rear end side,
The radome ring has a plurality of screw fastening holes formed on the circumference,
The coupling member includes a fastening portion formed with an internal thread for screw-fastening the radome ring, and an abutting portion having an outer wall provided with a taper whose thickness increases in the distal direction.
The radome ring and the radome ring the said coupling member the same number of holes is screwed in, claim an inner wall and an outer wall of the fastening portion of said radome main body, characterized in that in surface contact 5 Radome for flying object described in. The radome for a flying object according to claim 6 , wherein the radome ring has an annular recess at the front end of the inner peripheral portion.

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