JP2020169792A - Missile - Google Patents

Abstract

To obtain a missile capable of enhancing heat resistance of a junction part of a radome body and a radome ring.SOLUTION: A missile 1 comprises a cylindrical airframe 2, a radome body 6 installed at a tip of the airframe 2, a radome ring 7 joined to an outer peripheral surface of the airframe 2 and the radome body 6 to couple the airframe 2 and the radome body 6, a junction part 11 having the radome body 6 and the radome ring 7 with brazing and a spacer 8 provided between the airframe 2 and the radome body 6. A board thickness of the radome ring 7 is thinner than a board thickness of the radome body 6 and a board thickness of the airframe 2 at a part coupled by the radome ring 7.SELECTED DRAWING: Figure 2

Description

The present invention relates to a flying object including a radome that protects the antenna.

The airframe to fly toward the target by radio wave guidance includes the airframe, an antenna mounted inside the airframe, and a radome installed at the tip of the airframe to protect the antenna. The radome includes a radome main body and a radome ring that connects the radome main body and the airframe.

The radome body needs to transmit radio waves transmitted and received by the antenna. Further, since the radome body is heated to about 1000 ° C. by aerodynamic heating during flight, heat resistance and heat impact resistance are required. Therefore, the material of the radome body is generally ceramic, which is a dielectric material having a low coefficient of thermal expansion. The coefficient of thermal expansion of ceramics is 0 to 5 × 10 ^-6 / ° C.

On the other hand, as the material of the airframe, it is common to use a highly rigid metal material such as iron or aluminum. The coefficient of thermal expansion of the metallic material ^ranges from 10 × 10 ^-6 / ° C to 30 × 10 ^-6 / ° C.

When the radome body and the airframe are directly joined, thermal stress is generated at the joint between the radome body and the airframe due to the difference in the coefficient of thermal expansion during flight, and the radome body using ceramic, which is a brittle material, is destroyed. May occur. Therefore, it is common practice to connect the radome body and the airframe with a radome ring having high rigidity and a relatively low coefficient of thermal expansion to relieve the thermal stress acting on the radome body.

It is common to use a low thermal expansion metal such as Fiber-Reinforced Plastic (FRP) or Invar for the radome ring. The coefficient of thermal expansion of fiber reinforced plastics ^ranges from 4 × 10 ^-6 / ° C to 10 × 10 ^-6 / ° C. The coefficient of thermal expansion of low thermal expansion metals ^ranges from 1 × 10 ^-6 / ° C to 5 × 10 ^-6 / ° C.

Conventionally, as a method of fixing the radome body and the radome ring, an adhesive is used as described in Patent Document 1. Epoxy-based adhesives are generally used as the adhesives. The heat resistant temperature of the epoxy adhesive is about 350 ° C. However, in an environment where an aerodynamic load is generated during flight, the temperature at which the adhesive strength of the epoxy adhesive can be maintained is about 200 ° C.

Square root extraction No. 5-71699

The higher the surface temperature of the flying object by aerodynamic heating, the higher the temperature of the adhesive that fixes the radome body and the radome ring. Since the surface temperature of the flying object is heated to a maximum of 1000 ° C. or higher, the adhesive strength of the adhesive exceeds the temperature at which it can be maintained, and the fixing strength between the radome body and the radome ring decreases. Therefore, when using an adhesive, it is necessary to reduce the total amount of aerodynamic heating by lowering the flying speed or shortening the flying time. As a result, there is a problem that the improvement of the performance of the flying object is hindered.

The present invention has been made in view of the above, and an object of the present invention is to obtain a flying object capable of increasing the heat resistance of the joint portion between the radome body and the radome ring.

In order to solve the above-mentioned problems and achieve the object, the flying object according to the present invention includes a cylindrical airframe, a radome body installed at the tip of the airframe, an outer peripheral surface of the airframe and an outer peripheral surface of the radome body. It is provided with a radome ring that is joined to and connects the airframe and the radome main body, and a joint portion in which the radome main body and the radome ring are brazed.

According to the present invention, there is an effect that a flying object capable of increasing the heat resistance of the joint portion between the radome body and the radome ring can be obtained.

Sectional drawing which shows the flying object which concerns on Embodiment 1 of this invention Enlarged sectional view of part X shown in FIG. Explanatory drawing for explaining various dimensions of the flying object according to Embodiment 1. Explanatory drawing for explaining various dimensions of the flying object according to Embodiment 1. A graph showing the relationship between the flying time of the flying body and the temperature of the joint according to the first embodiment. A block diagram showing a flying object according to the second embodiment of the present invention. Enlarged view of part Y shown in FIG. Explanatory drawing of the flying object according to the second embodiment as viewed along the axial direction. Enlarged view of part Z shown in FIG. It is explanatory drawing which shows the flying object which concerns on Embodiment 3 of this invention, and is the block diagram which shows the radome ring and its periphery. It is explanatory drawing which shows the flying body which concerns on the modification 1 of Embodiment 3, and is the block diagram which shows the radome ring and its periphery. Sectional drawing along line XII-XII shown in FIG. It is explanatory drawing which shows the flying body which concerns on the modification 2 of Embodiment 3, and is the block diagram which shows the radome ring and its periphery.

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

Embodiment 1.
FIG. 1 is a cross-sectional view showing a flying object 1 according to the first embodiment of the present invention. The flying object 1 flies toward the target by radio wave guidance. The airframe 1 includes an airframe 2, an antenna 3, a radome 4 for the airframe, and a heat insulating material 5. In the following description, the flying radome 4 will be simply referred to as the radome 4. FIG. 1 shows the aerodynamic heating A generated when the flying object 1 flies, the aerodynamic load B along the flying direction, and the aerodynamic load C in the direction perpendicular to the flying direction.

The machine body 2 is a metal member having a higher coefficient of thermal expansion than the radome body 6 described later. The machine body 2 is formed in a cylindrical shape. Hereinafter, the direction along the central axis O of the airframe 2 is simply referred to as an axial direction, and the radial direction of the airframe 2 is simply referred to as a radial direction. As the material of the machine body 2, iron, aluminum, or the like having a coefficient of thermal expansion of 10 × 10 ^-6 / ° C to 30 × 10 ^-6 / ° C is used in the present embodiment. The tip of the machine body 2 is open.

The antenna 3 is a device provided inside the machine body 2 to detect a target. The heat resistant temperature of the antenna 3 is, for example, 150 ° C.

The radome 4 is a member that closes the opening at the tip of the airframe 2 and protects the antenna 3. FIG. 2 is an enlarged cross-sectional view of part X shown in FIG. The radome 4 includes a radome body 6, a radome ring 7, and a spacer 8.

The radome body 6 is a hollow member installed at the tip of the airframe 2 and forming an outer shell at the tip of the flying object 1. The outer shape of the radome body 6 is formed into a streamlined shape that tapers toward the distance from the machine body 2. The end of the radome body 6 is open toward the machine body 2. In the present embodiment, the material of the radome body 6 is a ceramic having a low dielectric constant and capable of transmitting radio waves. Ceramic has a coefficient of thermal expansion of 0 to 5 × 10 ^-6 / ° C or less, and is excellent in heat resistance and thermal shock resistance. The radome body 6 is fixed to the machine body 2 via the radome ring 7 and the spacer 8.

The radome ring 7 is a member that is joined to the outer peripheral surface of the machine body 2 and the outer peripheral surface of the radome main body 6 to connect the machine body 2 and the radome main body 6. The method of fixing the radome ring 7 to the machine body 2 is not particularly limited, but in the present embodiment, the radome ring 7 is fixed to the body body 2 with screws 9. Hereinafter, the portion where the radome ring 7 and the machine body 2 are fixed by the screw 9 is referred to as a fastening portion 10. The radome ring 7 is brazed to the outer peripheral surface of the radome body 6. Hereinafter, the portion where the radome body 6 and the radome ring 7 are brazed is referred to as a joint portion 11. As the material of the radome ring 7, a low thermal expansion metal having a coefficient of thermal expansion of 1 × 10 ^-6 / ° C to 5 × 10 ^-6 / ° C is used in the present embodiment. The low thermal expansion metal is, for example, Invar. The radial dimension of the radome ring 7 is smaller than the radial dimension of the radome body 6 and the body 2 at the portion connected by the radome ring 7. That is, in this embodiment, a thin plate radome ring 7 is used. As the material of the radome ring 7, FRP having high rigidity and a coefficient of thermal expansion of 4 × 10 ^-6 / ° C to 10 × 10 ^-6 / ° C may be used.

The spacer 8 is a member installed so as to be sandwiched between the machine body 2 and the radome main body 6. The spacer 8 is arranged radially inside the radome ring 7. The spacer 8 is made of a material having a lower thermal conductivity than that of the airframe 2. A resin or alloy is used as the material of the spacer 8. The resin used as the material of the spacer 8 is, for example, acrylic having a melting point of about 100 ° C. and polycarbonate having a melting point of about 150 ° C. The alloy used as the material of the spacer 8 is, for example, a tin alloy having a melting point of about 250 ° C. among tin alloys and a zinc alloy having a melting point of 200 ° C. to 300 ° C. among zinc alloys.

At the tip of the machine body 2, a machine body side butt surface 21 that is inclined with respect to a surface perpendicular to the axial direction is formed. At the end of the radome body 6, a body-side butt surface 41 that is inclined with respect to a surface perpendicular to the axial direction is formed. The spacer 8 is formed with a first contact surface 81 in contact with the machine body side butt surface 21 and a second contact surface 82 in contact with the main body side butt surface 41. The first contact surface 81 and the second contact surface 82 are inclined with respect to a surface perpendicular to the axial direction. The first contact surface 81, the second contact surface 82, the machine body side butt surface 21, and the main body side butt surface 41 are parallel to each other.

The heat insulating material 5 is a member that covers the outer peripheral surface of the radome ring 7 and the outer peripheral surface of the machine body 2 to suppress the temperature rise of the flying body 1. The heat insulating material 5 may be appropriately selected from known heat insulating materials. The heat insulating material 5 is fixed to the outer peripheral surface of the radome ring 7 and the outer peripheral surface of the machine body 2 with an adhesive or the like.

Here, various dimensions of the flying object 1 will be described with reference to FIGS. 3 and 4. 3 and 4 are explanatory views for explaining various dimensions of the flying object 1 according to the first embodiment. The radius of the radome body 6 is R, the dimension along the axial direction of the spacer 8 is M, the dimension along the axial direction from the center of the screw 9 to the tip of the machine body 2 is L, and the inclination angle of the spacer 8, that is, the radial direction. Let θ be the angle formed by the straight line 12 and the spacer 8 along the line. The inclination angle θ of the spacer 8 is an inclination angle with respect to a surface perpendicular to the axial direction of the first contact surface 81, the second contact surface 82, the machine body side butt surface 21, and the main body side butt surface 41. Further, the amount of thermal expansion in the radial direction of the radome body 6 is ΔRc, the amount of thermal expansion in the radial direction of the machine body 2 is ΔRm, the amount of thermal expansion in the axial direction of the redome ring 7 is ΔLr, and the amount of thermal expansion in the axial direction of the machine body 2 is set. Let ΔLm and the amount of thermal expansion of the spacer 8 in the axial direction be ΔLt. Further, the coefficient of thermal expansion of the radome body 6 is αc, the coefficient of thermal expansion of the machine body 2 is αm, the coefficient of thermal expansion of the spacer 8 is αt, the coefficient of thermal expansion of the radome ring 7 is αr, and the temperature change from room temperature is ΔT. The amount of thermal expansion ΔRc in the radial direction of the radome body 6 is calculated by the following equation (1).
ΔRc = R ・ αc ・ ΔT ・ ・ ・ (1)

The amount of thermal expansion ΔRm in the radial direction of the airframe 2 is calculated by the following equation (2).
ΔRm = R ・ αm ・ Δt ・ ・ ・ (2)

The amount of thermal expansion ΔLr in the axial direction of the radome ring 7 is calculated by the following equation (3).
ΔLr = (L + t) ・ αt ・ ΔT ・ ・ ・ (3)

The amount of thermal expansion ΔLm in the axial direction of the airframe 2 is calculated by the following equation (4).
ΔLm = L ・ αm ・ ΔT ・ ・ ・ (4)

The amount of thermal expansion ΔLt in the axial direction of the spacer 8 is calculated by the following equation (5).
ΔLt = t ・ αt ・ ΔT ・ ・ ・ (5)

When the following equation (6) is satisfied, the thermal expansion of each member due to the temperature change ΔT from room temperature is canceled out. That is, there is no warpage or gap between the members.
tan θ = (ΔLm + ΔLt-ΔLr) / (ΔRm-ΔRc) ... (6)

In the above formula (6), the dimension t along the axial direction of the spacer 8 and the axis of the spacer 8 are set to the optimum values obtained from the axial thermal expansion amount ΔLm of the machine body 2 and the axial thermal expansion amount ΔLr of the redome ring 7. By setting the amount of thermal expansion ΔLt in the direction, the spacer 8 is less likely to float or warp due to the difference in the coefficient of thermal expansion between the redome ring 7 and the machine body 2.

In the above equation (6), the inclination angle θ of the spacer 8 can be freely set by adjusting the dimension t along the axial direction of the spacer 8 and the thermal expansion amount ΔLt of the spacer 8 in the axial direction. For example, by inclining the spacer 8 at an angle corresponding to the coefficient of thermal expansion of the radome ring 7, the spacer 8 and the airframe 2, the spacer 8 floats and warps due to the difference in the coefficient of thermal expansion between the radome ring 7 and the airframe 2. It becomes difficult. Further, when the aerodynamic load C in the direction perpendicular to the flight direction is large among the aerodynamic loads B and C, or when it is desired to align the central axes of the machine body 2 and the radome body 6, the inclination angle θ of the spacer 8 is increased. By doing so, it is possible to increase the load bearing capacity of the flying object 1 and reduce the misalignment.

When the aerodynamic load C in the direction perpendicular to the flight direction is small among the aerodynamic loads B and C, a flat plate spacer 8 that does not incline in the direction perpendicular to the flight direction can be used. That is, when θ = 0 ° in which the spacer 8 becomes a flat plate in the above equation (6), the following equation (7) may be satisfied.
ΔLm + ΔLt−ΔLr = 0 ... (7)

Next, the action and effect of the flying object 1 according to the first embodiment will be described.

FIG. 5 is a graph showing the relationship between the flying time of the flying body 1 and the temperature of the joint portion 11 according to the first embodiment. The temperature T ₀ is the initial temperature of the flying object 1. The temperature T ₁ is the heat resistant temperature of the adhesive. The temperature T ₂ is the heat resistant temperature of silver wax. In FIG. 5, the case where the heat insulating material 5 has a low heat insulating effect is shown by line 13, and the case where the heat insulating material 5 has a high heat insulating effect is shown by line 14. In FIG. 5, for ease of explanation, lines 13 and 14 are schematically shown by straight lines. Actually, it is a curve because conditions such as flight speed and flight altitude change over time.

As shown in FIG. 1, in the flying object 1, heat is transferred from the radome main body 6 and the heat insulating material 5 to the joint portion 11 by the aerodynamic heating A at the time of flying. As shown by lines 13 and 14 in FIG. 5, the temperature of the joint 11 continues to rise as the flight time increases.

When the radome body 6 and the radome ring 7 are joined with an adhesive, the flying time is set to time t ₁ or less when the heat insulating effect of the heat insulating material 5 is low, and the flying time when the heat insulating effect of the heat insulating material 5 is high. Must be less than or equal to the time t ₂ . On the other hand, in the present embodiment, by joining the radome body 6 and the radome ring 7 by brazing, the heat resistant temperature of the silver brazing is higher than the heat resistant temperature of the adhesive, so that the flying time is t. Can be extended to ₃ or more. That is, as compared with the case of using an adhesive, the heat resistance of the joint portion 11 between the radome body 6 and the radome ring 7 can be increased, and the flying speed and the flying time can be improved. The brazing may be other than silver brazing.

As shown in FIG. 1, when the flying object 1 flies, aerodynamic loads B and C are applied to the radome body 6. At this time, in the present embodiment, since the radome main body 6 is fixed to the machine body 2 via the radome ring 7 and the spacer 8, the aerodynamic loads B and C applied to the radome main body 6 are the radome ring 7 and the spacer 8. After being dispersed and transmitted to the aircraft 2, it is transmitted to the aircraft 2. That is, in the present embodiment, two routes, a route via the radome ring 7 and a route via the spacer 8, are provided as the load transmission path from the radome main body 6 to the machine body 2. As a result, the load bearing capacity of the flying object 1 can be increased. When the load bearing capacity of the flying object 1 can be increased by using the spacer 8, the radome body 6 and the radome ring 7 may be joined with an adhesive.

Further, the aerodynamic loads B and C applied to the radome main body 6 are distributed and transmitted to the radome ring 7 and the spacer 8, so that the aerodynamic loads B and C applied to the radome ring 7 from the radome main body 6 are reduced. Can be done. Therefore, the radome ring 7 can be made into a thin plate. By making the radome ring 7 a thin plate, the thermal stress around the joint portion 11 due to the difference in the coefficient of thermal expansion between the radome body 6 and the radome ring 7 can be relaxed, and the radome body 6 and the body 2 The thermal stress due to the difference in the coefficient of thermal expansion can be relaxed.

The radome main body 6, the radome ring 7, the spacer 8 and the machine body 2 are not limited to the positional relationship shown in FIG. 1, and may be appropriately changed as long as the effects of the present application can be obtained.

Embodiment 2.
The flying object 1 according to the second embodiment will be described. FIG. 6 is a configuration diagram showing a flying object 1 according to a second embodiment of the present invention. FIG. 7 is an enlarged view of the Y portion shown in FIG. In the second embodiment, the same reference numerals are given to the parts that overlap with the first embodiment, and the description thereof will be omitted.

The radome ring 7 of the flying object 1 according to the present embodiment has a first fixing portion 71 fixed to the outer peripheral surface of the radome body 6 by brazing and a second fixing portion 71 fixed to the outer peripheral surface of the machine body 2 with screws 9. It has a fixed portion 72. The joint portion 11 and the fastening portion 10 are arranged so as to be staggered along the circumferential direction of the flying object 1. The shape of the first fixing portion 71 is not particularly limited, but in the present embodiment, it is formed in a trapezoidal shape protruding toward the tip of the radome main body 6. The shape of the second fixing portion 72 is not particularly limited, but in the present embodiment, it is formed in a trapezoidal shape protruding in the direction opposite to that of the first fixing portion 71.

The radome ring 7 has a first fixing portion 71 fixed to the radome body 6 having a coefficient of thermal expansion lower than that of the body 2 and a second fixing portion 72 fixed to the body 2 having a coefficient of thermal expansion higher than that of the radome body 6. A flexure structure is formed by. Due to this flexure structure, the first fixing portion 71 and the second fixing portion 72 can be relatively displaced in the radial direction of the flying body 1 when aerodynamic heating A is applied to the flying body 1. The flexure structure is formed over the entire circumference of the radome ring 7.

FIG. 8 is an explanatory view of the flying object 1 according to the second embodiment as viewed along the axial direction. FIG. 9 is an enlarged view of the Z portion shown in FIG. When aerodynamic heating A is applied to the flying object 1, the radome body 6 and the airframe 2 thermally expand in the radial direction. At this time, since the coefficient of thermal expansion of the radome body 6 is smaller than the coefficient of thermal expansion of the machine body 2, the first fixed portion 71 is displaced in the arrow D direction relative to the second fixed portion 72. In the present embodiment, since the radome ring 7 is a thin plate, the rigidity in the radial direction is low, and the rigidity in the circumferential direction is higher than that in the radial direction. Further, the flexure structure of the radome ring 7 is arranged over the entire circumference. Therefore, the radome body 6 is supported by the radome ring 7 with low rigidity in the radial direction. As a result, while connecting the radome body 6 and the machine body 2 with high rigidity, the thermal stress around the radome body 6 and the joint portion 11 due to the difference in the coefficient of thermal expansion in the radial direction between the radome body 6 and the body 2 is relaxed. Can be done. The shape of the radome ring 7 shown in FIG. 6 is formed in a wavy shape in the present embodiment, but is not particularly limited as long as it has a flexure structure.

Embodiment 3.
The flying object 1 according to the third embodiment will be described. FIG. 10 is an explanatory diagram showing the flying object 1 according to the third embodiment of the present invention, and is a configuration diagram showing the radome ring 7 and its surroundings. In the third embodiment, the same reference numerals are given to the parts that overlap with the first embodiment, and the description thereof will be omitted.

The radome ring 7 of the flying object 1 according to the present embodiment has a first fixing portion 71 fixed to the outer peripheral surface of the radome body 6 by brazing and a second fixing portion 71 fixed to the outer peripheral surface of the machine body 2 with screws 9. It has a fixed portion 72. A plurality of slits 73 extending along the axial direction are formed in the first fixing portion 71. The plurality of slits 73 are arranged so as to be spaced apart from each other along the radial direction. The shape of the slit 73 is rectangular in the present embodiment, but may be oval or elliptical.

In the present embodiment, in order to reduce the thermal stress around the joint portion 11 due to the difference in the coefficient of thermal expansion between the radome ring 7 and the radome body 6, a low thermal expansion metal having a low coefficient of thermal expansion is used as the material of the radome ring 7. , The thickness of the radome ring 7 is reduced. However, when the flying object 1 is particularly exposed to a high temperature, the radome ring 7 must be made extremely thin so that the thermal stress cannot be within the allowable range. Such a design may cause the radome ring 7 to fall below the manufacturing limit or may not meet the rigidity required for the radome ring 7. In this regard, in the present embodiment, since the slit 73 is formed in the first fixing portion 71 of the radome ring 7, the radome body 6 and the radome ring 7 are connected to each other while ensuring a sufficient plate thickness of the radome ring 7. The thermal stress around the joint portion 11 due to the difference in the coefficient of thermal expansion can be relaxed.

The joint portion 11 may be formed in the wavy shape shown in FIGS. 11 and 12. FIG. 11 is an explanatory diagram showing the flying object 1 according to the modified example 1 of the third embodiment, and is a configuration diagram showing the radome ring 7 and its periphery. FIG. 12 is a cross-sectional view taken along the line XII-XII shown in FIG. The first fixing portion 71 of the radome ring 7 shown in FIG. 12 is formed in a wavy shape. That is, the first fixing portion 71 has a plurality of contact portions 74 that abut on the outer peripheral surface of the radome main body 6, and a plurality of separating portions 75 that are separated from the outer peripheral surface of the radome main body 6. The flying body 1 is formed with a joint portion 11 in which the radome body 6 and the abutting portion 74 of the radome ring 7 are brazed. Also in this modification, the thermal stress around the joint portion 11 due to the difference in the coefficient of thermal expansion between the radome body 6 and the radome ring 7 can be relaxed while ensuring a sufficient plate thickness of the radome ring 7.

Further, instead of the slit 73, the joint portion 11 may be arranged in a striped shape shown in FIG. FIG. 13 is an explanatory diagram showing the flying object 1 according to the second modification of the third embodiment, and is a configuration diagram showing the radome ring 7 and its surroundings. The joints 11 shown in FIG. 13 are arranged in a striped pattern. Each joint 11 extends linearly along the axial direction. The plurality of joints 11 are arranged so as to be spaced apart from each other along the radial direction. The plurality of joints 11 may be arranged in a grid pattern, a point cloud pattern, or the like. Also in this modification, the thermal stress around the joint portion 11 due to the difference in the coefficient of thermal expansion between the radome body 6 and the radome ring 7 can be relaxed while ensuring a sufficient plate thickness of the radome ring 7.

The configuration shown in the above-described embodiment shows an example of the content of the present invention, can be combined with another known technique, and is one of the configurations without departing from the gist of the present invention. It is also possible to omit or change the part.

1 Radome, 2 Airframe, 3 Antenna, 4 Radome, 5 Insulation, 6 Radome Body, 7 Radome Ring, 8 Spacer, 9 Screws, 10 Fasteners, 11 Joints, 12 Straight Lines, 13, 14 Lines, 21 Airframes Side butt surface, 41 Main body side butt surface, 71 1st fixed part, 72 2nd fixed part, 73 slit, 74 contact part, 75 separation part, 81 1st contact surface, 82 2nd contact surface, A aerodynamic heating, B, C aerodynamic load, O central axis.

Claims (10)

Cylindrical body and
The radome body installed at the tip of the aircraft and
A radome ring that is joined to the outer peripheral surface of the machine body and the outer peripheral surface of the radome body to connect the machine body and the radome body.
A flying body provided with a joint portion to which the radome body and the radome ring are brazed. The flying object according to claim 1, wherein the plate thickness of the radome ring is thinner than the plate thickness of the radome body and the plate thickness of the airframe at a portion connected by the radome ring. The flying object according to claim 1 or 2, further comprising a spacer provided between the airframe and the radome body. The thermal expansion amount of the spacer along the axial direction of the flying body is ΔLt, the thermal expansion amount of the redome ring along the axial direction is ΔLr, and the thermal expansion amount of the airframe along the axial direction is ΔLm. When the amount of thermal expansion of the airframe along the radial direction of the flying body is ΔRm, the amount of thermal expansion of the radome body along the radial direction is ΔRc, and the inclination angle of the spacer with respect to the axial direction is θ. , Tan θ = (ΔLm + ΔLt−ΔLr) / (ΔRm−ΔRc) The flying object according to claim 3, wherein the equation holds. The fourth aspect of the present invention, wherein the first contact surface in contact with the airframe and the second contact surface in contact with the radome body of the spacer are inclined with respect to the surface perpendicular to the axial direction. Flying body. Further provided with a fastening portion for fastening the airframe and the radome ring,
The flying object according to any one of claims 1 to 5, wherein the joint portion and the fastening portion are arranged so as to be staggered along the circumferential direction of the flying object. The flyer according to any one of claims 1 to 6, wherein a slit is provided in a portion of the radome ring corresponding to the joint portion. The flyer according to any one of claims 1 to 6, wherein a portion of the radome ring corresponding to the joint portion is formed in a wavy shape. The flying object according to any one of claims 1 to 6, wherein the joints are arranged in a striped pattern, a grid pattern, or a point cloud pattern. Cylindrical body and
The radome body installed at the tip of the aircraft and
A radome ring that connects the machine body and the radome body and is fixed to the outer peripheral surface of the machine body and the outer peripheral surface of the radome body.
A flying body characterized by being arranged radially inside the radome ring and provided with a spacer provided between the airframe and the radome body.

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