Radome for projectiles and method for manufacturing a radome for projectiles

Abstract

To obtain a radome for a flying object that can suppress rattle in the direction perpendicular to the axis and improve rigidity against bending loads. [Solution] The radome 1 for a projectile comprises a radome body 10 having a base end 10a and a tip end 10b, a fixing member 11 for fixing the radome body 10 to the radome ring 3 or the aircraft body 2, and a load receiving portion 12 for receiving the load acting on the fixing member 11 in the direction of the aircraft axis. The fixing member 11 has a first fixing portion 11a including an elastic portion 11c that can be elastically deformed in the direction perpendicular to the aircraft axis, and a second fixing portion 11b that has higher rigidity in the direction perpendicular to the aircraft axis than the first fixing portion 11a. When the direction from the base end 10a to the tip end 10b of the radome body 10 along the aircraft axis is considered the front, and the direction from the tip end 10b to the base end 10a along the aircraft axis is considered the rear, a reducing portion 10d is formed on the inner circumferential surface 10c of the radome body 10 in which the inner circumferential dimension decreases as it approaches the rear.

Description

Technical Field

[0001] The present disclosure relates to a dome for a projectile disposed at the tip of the projectile and a method for manufacturing the dome for the projectile.

Background Art

[0002] When a projectile flies toward a set target, it is necessary to measure the position and orientation of the projectile and control the projectile. Electronic devices for measuring the position and orientation of the projectile are mounted at the tip of the projectile. To protect the electronic devices from the aerodynamic forces during flight, the electronic devices are covered by a dome-shaped dome.

[0003] A projectile flying at supersonic or hypersonic speeds is subjected to heating due to friction with air during flight and heating from air that has been rapidly compressed and become very hot. Due to such aerodynamic heating, the dome disposed at the tip of the projectile is heated to about 1000°C in just a few seconds after being launched. Therefore, the dome is required to have high heat resistance and high thermal shock resistance. Also, since the dome receives a large aerodynamic load during flight, the dome also requires high strength. Furthermore, since the projectile needs to measure the relative position between the projectile and the target during flight, it is necessary to transmit and receive radio waves by the electronic devices through the dome, and the dome is also required to have radio wave transmissivity that allows the radio waves emitted by the electronic devices to pass through. Therefore, as the material of the dome, ceramics, which are dielectric materials having high heat resistance with a heat resistance temperature of 1000°C or higher, high strength, and that transmit radio waves, are generally used.

[0004] For the ceramics of the dome, ceramics having a linear expansion coefficient of 5×10 -6 / K or less, such as alumina, cordierite, fused silica, silicon nitride, etc., are generally used. On the other hand, for the material of the airframe of the projectile, from the viewpoints of weight reduction and low cost, alloys with a linear expansion coefficient of 10×10 -6 / K to 30×10-6 It is common to use metals with the / K designation.

[0005] When a radome and the airframe are directly joined due to a large difference in their coefficients of thermal expansion, aerodynamic heating during flight can generate significant thermal stress at the joint, potentially causing the radome, which is made of brittle ceramic material, to break. Therefore, it is common practice to indirectly connect the radome and the airframe via a radome ring made of fiber-reinforced plastics (FRP) or a low-thermal-expansion metal, which have high rigidity and a relatively low coefficient of thermal expansion. This helps to mitigate the thermal stress acting on the radome.

[0006] Traditionally, radomes and radome rings are often fixed together with epoxy or silicone adhesives. When ceramic radomes and radome rings are fixed together with adhesive, if the adhesive is subjected to aerodynamic heating that exceeds its heat resistance temperature, the bond between the radome and radome ring cannot be maintained. One method that can maintain the bond between the radome and radome ring even at high temperatures is to use mechanical bonding. However, when mechanical bonding is used, the difference in the coefficient of thermal expansion between the radome and radome ring may lead to a loss of airtightness between the radome and radome ring, or cracking of the radome.

[0007] As a method for solving such problems, the technology disclosed in Patent Document 1 is known. Patent Document 1 discloses a technology for fixing the radome ring and the aircraft body by arranging the end face of the radome in the axial direction with at least a part of the end face of the aircraft body in the axial direction and providing an elastic member between the two end faces to prevent loosening of the radome ring and the aircraft body. Patent Document 1 also discloses a technology for fixing the radome and the radome ring by providing a recess in the radome at the joint with the radome ring and fixing the radome ring and the split ring placed in the recess with a screw to restrict the movement of the radome ring. [Prior art documents] [Patent Documents]

[0008] [Patent Document 1] Japanese Patent Publication No. 2019-090572 [Overview of the project] [Problems that the invention aims to solve]

[0009] However, the technology disclosed in Patent Document 1 has the problem that a gap inevitably occurs between the split ring and the bottom surface of the recess, causing rattling of the radome in the direction perpendicular to the machine axis.

[0010] Furthermore, in the technology disclosed in Patent Document 1, the recess provided in the radome reduces the second moment of area of ​​the radome, and stress concentration occurs at the corners of the recess. As a result, there is a problem that the rigidity against the bending load acting on the radome during flight is insufficient.

[0011] This disclosure has been made in view of the above, and aims to provide a radome for a projectile that can suppress rattling in the direction perpendicular to the machine axis and improve rigidity against bending loads. [Means for solving the problem]

[0012] To solve the above-mentioned problems and achieve the objective, the radome for a projectile according to this disclosure comprises a radome body, a fixing member, and a load-bearing portion. The hollow radome body has a base end located toward the aircraft body in the axial direction and a tip end located opposite the aircraft body in the axial direction. The fixing member is positioned on the inner circumference of the radome body and fixes the radome body to the radome ring or aircraft body. The load-bearing portion is integrated with the fixing member or provided separately from the fixing member and receives the axial load acting on the fixing member. The fixing member has a first fixing portion and a second fixing portion. The first fixing portion contacts the inner circumferential surface of the radome body and includes an elastic portion that is elastically deformable in the direction perpendicular to the axial direction. The second fixing portion is provided on the inner circumference of the first fixing portion and has higher rigidity in the direction perpendicular to the axial direction than the first fixing portion. When the direction from the base to the tip of the radome body along the axis of the machine is considered the front, and the direction from the tip to the base of the radome body along the axis of the machine is considered the rear, a tapering section is formed on the inner surface of the radome body in which the inner circumference decreases as it approaches the rear. [Effects of the Invention]

[0013] The radome for projectiles according to this disclosure has the effect of suppressing rattle in the direction perpendicular to the machine axis and improving rigidity against bending loads. [Brief explanation of the drawing]

[0014] [Figure 1] This is a cross-sectional view of the tip portion of a projectile equipped with a radome for a projectile according to Embodiment 1, cut along the axis of the machine, showing the state before the radome body and the fixing member are fixed together. [Figure 2] This is a cross-sectional view of the tip portion of a projectile equipped with a radome for a projectile according to a modified embodiment of Embodiment 1, cut along the axis of the machine, showing the state before the radome body and the fixing member are fixed together. [Figure 3]A cross-sectional view when the tip portion of the flying body equipped with the dome for the flying body according to Embodiment 1 is cut along the axial direction, showing the state where the dome body and the fixing member are fixed [Figure 4] A partially enlarged cross-sectional view showing the fixing member shown in FIG. 3 and its periphery [Figure 5] A cross-sectional view showing an example of a manufacturing method of the dome for the flying body according to Embodiment 1 [Figure 6] A cross-sectional view when the tip portion of the flying body equipped with the dome for the flying body according to Embodiment 2 is cut along the direction orthogonal to the axis [Figure 7] A perspective view showing the first fixing portion in Embodiment 2 [Figure 8] A cross-sectional view when the tip portion of the flying body equipped with the dome for the flying body according to Embodiment 3 is cut along the axial direction, showing the state where the dome body and the fixing member are fixed [Figure 9] A cross-sectional view when the tip portion of the flying body equipped with the dome for the flying body according to Embodiment 4 is cut along the axial direction, showing the state where the dome body and the fixing member are fixed [Figure 10] A cross-sectional view showing an example of a manufacturing method of the dome for the flying body according to Embodiment 4 [Figure 11] A cross-sectional view when the tip portion of the flying body equipped with the dome for the flying body according to Embodiment 5 is cut along the axial direction, showing the state where the dome body and the fixing member are fixed [Figure 12] A cross-sectional view when the tip portion of the flying body equipped with the dome for the flying body according to Embodiment 6 is cut along the axial direction, showing the state where the dome body and the fixing member are fixed [Figure 13] A cross-sectional view when the tip portion of the flying body equipped with the dome for the flying body according to Embodiment 7 is cut along the axial direction, showing the state where the dome body and the fixing member are fixed [Figure 14]Cross-sectional view when the tip portion of the flying object equipped with the radome for a flying object according to Embodiment 8 is cut along the axis direction, showing the state where the radome body and the fixing member are fixed [Figure 15] Cross-sectional view when the tip portion of the flying object equipped with the radome for a flying object according to Embodiment 9 is cut along the axis direction, showing the state where the radome body and the fixing member are fixed [Figure 16] Cross-sectional view when the tip portion of the flying object equipped with the radome for a flying object according to Embodiment 10 is cut along the axis direction, showing the state where the radome body and the fixing member are fixed [Figure 17] Cross-sectional view when the tip portion of the flying object equipped with the radome for a flying object according to Embodiment 11 is cut along the axis direction, showing the state before the radome body and the fixing member are fixed [Figure 18] Cross-sectional view when the tip portion of the flying object equipped with the radome for a flying object according to Embodiment 11 is cut along the axis direction, showing the state where the radome body and the fixing member are fixed [Figure 19] Cross-sectional view when the tip portion of the flying object equipped with the radome for a flying object according to Embodiment 12 is cut along the direction orthogonal to the axis [Figure 20] Cross-sectional view when the tip portion of the flying object equipped with the radome for a flying object according to Embodiment 13 is cut along the axis direction, showing the state where the radome body and the fixing member are fixed [Figure 21] Cross-sectional view when the tip portion of the flying object equipped with the radome for a flying object according to Embodiment 13 is cut along the direction orthogonal to the axis [Figure 22] Cross-sectional view when the tip portion of the flying object equipped with the radome for a flying object according to Embodiment 14 is cut along the axis direction, showing the state where the radome body and the fixing member are fixed [Figure 23] Cross-sectional view when the tip portion of the flying object equipped with the radome for a flying object according to Embodiment 15 is cut along the axis direction, showing the state where the radome body and the fixing member are fixed [Modes for carrying out the invention]

[0015] The following describes in detail, with reference to the drawings, a projectile radome according to an embodiment and a method for manufacturing the projectile radome.

[0016] Embodiment 1. Figure 1 is a cross-sectional view of the tip portion of a projectile 100 equipped with a projectile radome 1 according to Embodiment 1, cut along the axis of the machine gun, and shows the state before the radome body 10 and the fixing member 11 are fixed together. In Figure 1, only one half of the projectile 100 (the portion corresponding to the upper half when cut by a plane perpendicular to the plane of paper including the machine gun C) is shown (the portion corresponding to the lower half when cut by a plane perpendicular to the plane of paper including the machine gun C is not shown). Hereinafter, when describing the direction of each component of the projectile 100, the direction parallel to the machine gun C of the projectile 100 will be called the axis of the machine gun, the direction perpendicular to the machine gun C (axis of the machine gun) will be called the direction perpendicular to the machine gun, and the rotational direction around the machine gun C will be called the circumferential direction. In addition, in the direction perpendicular to the machine gun, the direction from the outside to the inside of the projectile 100 will be called the inner circumference, and the direction from the inside to the outside of the projectile 100 in the direction perpendicular to the machine gun will be called the outer circumference. The axis of the machine gun is the direction parallel to the direction in which the projectile 100 flies.

[0017] The projectile 100 shown in Figure 1 flies towards a set target using radio guidance. The projectile 100 comprises a fuselage 2, a radome ring 3, and a projectile radome 1. In Figure 1 and other diagrams, the fuselage 2 is schematically represented by a dashed line.

[0018] Aircraft 2 is the main body of the projectile 100. Aircraft 2 is formed in a cylindrical shape. A projectile radome 1 is attached to the tip of aircraft 2 in the axial direction via a radome ring 3. A rocket motor or rocket engine (not shown) is provided at the base end of aircraft 2 in the axial direction. The tip of aircraft 2 in the axial direction is open. The material used for aircraft 2 is a metal such as an iron-based alloy or an aluminum-based alloy.

[0019] The radome ring 3 is a component that connects the aircraft body 2 and the radome 1 for the projectile. The radome ring 3 is formed in a cylindrical shape. Preferably, the material used for the radome ring 3 is a metal with a low coefficient of thermal expansion. Examples of such metals include Invar (registered trademark), Super Invar, and titanium. The radome ring 3 may also be formed by laminating multiple sheets of fiber-reinforced plastic. The radome ring 3 is fixed to the fixing member 11, which will be described later, by connecting members such as bolts and pins (not shown). The radome ring 3 is also fitted onto the outer surface of the aircraft body 2 and fixed to the aircraft body 2 by bolts, pins, etc. (not shown).

[0020] The radome 1 for the projectile is a hollow-shaped component positioned at the tip of the projectile 100. The radome 1 for the projectile constitutes the outer shell of the tip portion of the projectile 100. The radome 1 for the projectile comprises a radome body 10, a fixing member 11, and a load-receiving portion 12.

[0021] The radome body 10 is hollow and dome-shaped, opening toward the radome ring 3 and the aircraft 2. The radome body 10 has a base end 10a located toward the aircraft 2 of the projectile 100 in the axial direction, and a tip end 10b located opposite the aircraft 2 in the axial direction. The base end 10a of the radome body 10 opens toward the radome ring 3 and the aircraft 2. The base end 10a of the radome body 10 is in contact with the tip of the radome ring 3 in the axial direction. The tip end 10b of the radome body 10 is pointed and closed. The radome body 10 is formed in a streamlined shape, tapering smoothly from the base end 10a toward the tip end 10b. Hereafter, the direction from the base end 10a toward the tip end 10b of the radome body 10 in the axial direction will be referred to as the front, and the direction from the tip end 10b toward the base end 10a of the radome body 10 in the axial direction will be referred to as the rear.

[0022] The radome body 10 must be made of a material that has heat resistance to temperatures of 1000°C or higher, thermal shock resistance to rapid temperature changes, and dielectric properties to allow radio waves emitted by electronic equipment to pass through. For this reason, it is preferable, but not limited to, that ceramics be used for the material of the radome body 10. A tapered portion 10d is formed on the inner circumferential surface 10c of the radome body 10. The tapered portion 10d is a part in which the inner circumferential dimension (inner diameter) decreases as it approaches the rear. The shape of the tapered portion 10d is preferably a tapered shape in which the inner circumferential dimension decreases as it approaches the rear, as in this embodiment, but it may also be a stepped shape in which the inner circumferential dimension decreases in stages as it approaches the rear. In this embodiment, the cross-sectional shape of the part of the radome body 10 excluding the tip 10b when cut along the direction perpendicular to the machine axis is a circular cross-section.

[0023] The fixing member 11 is positioned on the inner circumference of the radome body 10 to fix the radome body 10 and the radome ring 3. The fixing member 11 has a first fixing part 11a and a second fixing part 11b. In this embodiment, the first fixing part 11a and the second fixing part 11b are provided separately from each other. The first fixing part 11a and the second fixing part 11b are arranged in that order from the inner circumferential surface 10c of the radome body 10 toward the inner circumference. It is preferable that the same material as the radome ring 3 is used for the material of the first fixing part 11a and the material of the second fixing part 11b. In this way, the difference in the coefficient of linear expansion between the radome ring 3 and the first fixing part 11a and the second fixing part 11b can be eliminated, and thus the generation of thermal stress can be suppressed. The materials used for the first fixing part 11a and the second fixing part 11b may be different from those used for the radome ring 3, but it is preferable to use materials whose coefficient of thermal expansion is located between that of the radome body 10 and that of the radome ring 3.

[0024] The first fixed portion 11a includes an elastic portion 11c and a connecting portion 11d. The elastic portion 11c is in contact with the inner circumferential surface 10c of the radome body 10 and is elastically deformable in the direction perpendicular to the machine axis. The elastic portion 11c should have a structure that is easily deformable in the direction perpendicular to the machine axis and difficult to deform in the direction of the machine axis. For example, the elastic portion 11c may have a structure in which a slit is made in a part of a plate-like portion, or a structure in which the plate-like portion has a partially thinned plate thickness in the direction perpendicular to the machine axis, or a structure in which a leaf spring is bent. The elastic portion 11c protrudes outward from the connecting portion 11d. The outer circumferential surface of the elastic portion 11c decreases in outer diameter as it approaches the rear. The outer circumferential surface of the elastic portion 11c is a tapered surface having the same taper angle as the reduced portion 10d.

[0025] The connecting portion 11d extends in the axial direction from the elastic portion 11c to the inner circumference of the radome ring 3 and is a plate-shaped portion that curves along the outer circumference of the second fixing portion 11b. The connecting portion 11d is positioned with a gap between it and the inner circumferential surface 10c of the radome body 10 in a direction perpendicular to the axial direction. The connecting portion 11d is in contact with the inner circumferential surface of the radome ring 3.

[0026] Preferably, the first fixing portion 11a is divided into multiple parts in the circumferential direction. This makes it easier to position the first fixing portion 11a on the inner circumference of the radome body 10 during assembly (manufacturing) of the radome 1 for the projectile. The first fixing portion 11a is formed in a cylindrical shape. The outer circumference (outer diameter) of the elastic portion 11c in its initial state is larger than the inner circumference (inner diameter) of the contraction portion 10d. The elastic portion 11c in its initial state means the elastic portion 11c in a state that has not undergone compressive deformation. As the radome body 10, the fixing member 11, and the load-receiving portion 12 move relative to each other in the direction of the machine axis, the elastic portion 11c slides along the contraction portion 10d, compressively deforming and pressing against the inner circumferential surface 10c of the radome body 10. This fixes the radome body 10 and the fixing member 11.

[0027] The second fixing part 11b is provided on the inner circumference of the first fixing part 11a and has higher rigidity in the direction perpendicular to the machine axis than the first fixing part 11a. The second fixing part 11b plays the role of supporting the first fixing part 11a in the direction perpendicular to the machine axis so that the elastic part 11c can be elastically deformed. The second fixing part 11b is formed in a cylindrical shape. The second fixing part 11b is in contact with the entire circumference of the inner surface of the first fixing part 11a. The second fixing part 11b extends along the machine axis direction to the inner circumference of the radome ring 3. The first fixing part 11a and the second fixing part 11b are fixed to each other by connecting members such as bolts and pins (not shown).

[0028] In this embodiment, the load-receiving portion 12 is provided separately from the fixing member 11 and receives the axial load acting on the fixing member 11. The load-receiving portion 12 mainly receives the axial load (reaction force) acting on the first fixing portion 11a. Preferably, the material used for the load-receiving portion 12 is a material whose coefficient of thermal expansion is located between that of the radome body 10 and that of the radome ring 3. However, since the load-receiving portion 12 is not directly fixed to the radome body 10 and the radome ring 3, the material used for the load-receiving portion 12 may be the same material as that of the radome body 10 or the radome ring 3.

[0029] The load-bearing portion 12 is formed in a cylindrical shape. The load-bearing portion 12 is positioned with a gap between it and the inner circumferential surface 10c of the radome body 10 in a direction perpendicular to the machine axis. In this embodiment, the load-bearing portion 12 is in contact with the machine axis-oriented tip 11e of the first fixing portion 11a and the machine axis-oriented tip 11f of the second fixing portion 11b, but it is sufficient that it is in contact with at least the machine axis-oriented tip 11e of the first fixing portion 11a. The machine axis-oriented tip 11e of the first fixing portion 11a is the furthest forward end of the first fixing portion 11a (elastic portion 11c). The machine axis-oriented tip 11f of the second fixing portion 11b is the furthest forward end of the second fixing portion 11b.

[0030] The load-receiving portion 12 is fixed to the second fixing portion 11b by a bolt 4 extending in the direction of the machine axis. Figure 2 is a cross-sectional view of the tip portion of a projectile 100 equipped with a projectile radome 1 according to a modified embodiment of the first embodiment, cut along the direction of the machine axis, and shows the state before the radome body 10 and the fixing member 11 are fixed together. If it is difficult to fix the load-receiving portion 12 to the second fixing portion 11b, the load-receiving portion 12 may be fixed to the first fixing portion 11a as shown in Figure 2. In the example shown in Figure 2, the length of the second fixing portion 11b in the direction of the machine axis is shorter than the length of the first fixing portion 11a in the direction of the machine axis, and the cross-sectional shape of the load-receiving portion 12 in Figure 2 is L-shaped. The load-receiving portion 12 is in contact with the tip 11e and the inner circumferential surface of the first fixing portion 11a. The load-receiving portion 12 is fixed to the first fixing portion 11a by a bolt 4 extending in the direction perpendicular to the machine axis. Furthermore, the method of fixing the load-receiving portion 12 to the first fixing portion 11a or the second fixing portion 11b is not limited to the method using bolts 4, but may also be a method using adhesive or a method using mechanical bonding such as press-fitting.

[0031] Next, a method for manufacturing the projectile radome 1 according to this embodiment will be described with reference to Figures 1, 3 to 5. Figure 3 is a cross-sectional view of the tip portion of a projectile 100 equipped with the projectile radome 1 according to Embodiment 1, cut along the axis of the machine, showing the state in which the radome body 10 and the fixing member 11 are fixed together. Figure 4 is a partially enlarged cross-sectional view showing the fixing member 11 and its surroundings as shown in Figure 3. Figure 5 is a cross-sectional view showing an example of a method for manufacturing the projectile radome 1 according to Embodiment 1. The method for manufacturing the projectile radome 1 includes an arrangement step and a fixing step.

[0032] As shown in Figure 1, the placement process involves placing the fixing member 11 on the inner circumference of the radome body 10. In this embodiment, the placement process is performed with the load-receiving portion 12 attached to the fixing member 11. Although the outer circumference of the first fixing portion 11a is larger than the inner circumference of the reduced portion 10d, if the first fixing portion 11a is divided into multiple parts in the circumferential direction, it becomes easier to place the first fixing portion 11a on the inner circumference of the radome body 10 during the placement process.

[0033] As shown in Figures 3 and 4, the fixing process involves fixing the radome body 10 and the fixing member 11 by moving the radome body 10 and the fixing member 11 relative to each other in the direction of the machine axis. Specifically, by moving the radome body 10 and the fixing member 11 relative to each other in the direction of the machine axis, the elastic part 11c is compressed and deformed by sliding along the contraction part 10d, and the elastic part 11c presses against the inner circumferential surface 10c of the radome body 10. This fixes the radome body 10 and the fixing member 11. In Figure 4, the elastic part 11c in a state that has not been compressed and deformed is shown by a dashed line. By sliding the elastic part 11c along the contraction part 10d, the elastic part 11c is compressed and deformed from the state shown by the dashed line to the state shown by the solid line. In the fixing process, the elastic force of the compressed and deformed elastic part 11c presses the outer circumferential surface of the first fixing part 11a against the inner circumferential surface 10c of the radome body 10. In this embodiment, when the fixing process is performed, the load-receiving portion 12 attached to the fixing member 11 also moves relative to the radome body 10 in the machine axis direction.

[0034] In the fixing process, as shown in Figure 5, the fixing jig 5 may fix the radome ring 3 immovably, and the fixing member 11 and load-receiving part 12 may be moved rearward in the axial direction relative to the radome ring 3 and radome body 10. Alternatively, in the fixing process, the fixing member 11 may be fixed immovably with a fixing jig (not shown), and the radome ring 3 and radome body 10 may be moved forward in the axial direction relative to the fixing member 11 and load-receiving part 12.

[0035] Furthermore, in the fixing process, the radome body 10, the fixing member 11, and the load-receiving part 12 may be moved relative to each other in the axial direction using a moving jig 6 equipped with a moving mechanism that utilizes, for example, the elastic force of a spring, hydraulic pressure, the fastening force of a bolt, the driving force of a motor, or electromagnetic repulsion. Alternatively, in the fixing process, the radome body 10, the fixing member 11, and the load-receiving part 12 may be moved relative to each other in the axial direction by human power. In the fixing process, the radome body 10, the fixing member 11, and the load-receiving part 12 may be moved relative to each other in the axial direction using a moving mechanism provided on the radome 1 itself. In this embodiment, the attachment process of attaching the load-receiving part 12 to the fixing member 11 was performed before the placement process, and the placement process was performed with the load-receiving part 12 attached to the fixing member 11, but this is not limited to this. The attachment process may be performed after the placement process and before the fixing process, or after the fixing process. In this case, the load-receiving portion 12 may be divided into multiple parts in the circumferential direction to facilitate passage of the load-receiving portion 12 through the inner circumference of the fixing member 11.

[0036] Next, the effects of the projectile radome 1 according to this embodiment will be described.

[0037] Here, we consider the case where the projectile 100 is stored in a low-temperature environment and the projectile 100 is flying in an extremely low-temperature environment without the elastic portion 11c shown in Figure 3. We also consider the case where the radome body 10 is made of ceramics with a relatively small coefficient of thermal expansion, and the first fixing portion 11a is made of metal with a relatively large coefficient of thermal expansion. In such a case, the amount of thermal contraction of the first fixing portion 11a is greater than that of the radome body 10, so an unavoidable gap is created between the inner circumferential surface 10c of the radome body 10 and the outer circumferential surface of the first fixing portion 11a. This may cause rattling of the radome body 10 in the direction perpendicular to the machine axis. In this embodiment, the first fixing portion 11a contacts the inner circumferential surface 10c of the radome body 10 and includes an elastic portion 11c that can be elastically deformed in the direction perpendicular to the machine axis. Furthermore, in this embodiment, the inner circumferential surface 10c of the radome body 10 has a contraction portion 10d formed thereon, the inner circumferential dimension of which decreases as it approaches the rear. These configurations allow the first fixing portion 11a to be positioned on the inner circumference of the radome body 10 while under pressure at room temperature. Therefore, if a gap is to form between the inner surface 10c of the radome body 10 and the outer surface of the first fixing portion 11a in a low-temperature or cryogenic environment, the elastic portion 11c extends outward and contacts the inner surface 10c of the radome body 10. As a result, the elastic portion 11c fills the gap, suppressing rattling of the radome body 10 in the direction perpendicular to the machine axis.

[0038] Next, let's consider the case where the temperature of the projectile 100 rises during flight in the absence of the elastic portion 11c. Let's also consider the case where the radome body 10 is made of ceramics with a relatively small coefficient of thermal expansion, and the first fixing portion 11a is made of metal with a relatively large coefficient of thermal expansion. In such a case, since the thermal expansion of the first fixing portion 11a is greater than that of the radome body 10, a force acts on the radome body 10 that pushes it outward from the inner circumference to the outer circumference, which may cause the radome body 10 to crack. In this regard, in this embodiment, as described above, the first fixing portion 11a contacts the inner circumferential surface 10c of the radome body 10 and includes an elastic portion 11c that can be elastically deformed in the direction perpendicular to the machine axis. Therefore, when the temperature of the projectile 100 rises, the elastic portion 11c deforms to follow the inner circumferential surface 10c of the radome body 10 and does not stretch (expand) excessively. This reduces the force pushing the radome body 10 outward from the inner circumference to the outer circumference, thereby suppressing cracking of the radome body 10. As described above, in this embodiment, even when temperature changes occur around the projectile 100 and temperature changes occur in the projectile 100 itself, the difference in thermal expansion between the radome body 10 and the first fixing part 11a can be absorbed by the elastic part 11c. Therefore, rattling of the radome body 10 in the direction perpendicular to the machine axis can be suppressed, and cracking of the radome body 10 can be suppressed.

[0039] When an aerodynamic load perpendicular to the aircraft axis, indicated by arrow P1 in Figure 3, acts on the radome 1 for the aircraft, a bending load in the direction indicated by arrow P2 acts on the radome 1 for the aircraft. In addition, to balance with the bending load, a reaction force in the direction of the aircraft axis, indicated by arrow P3, is generated at the contact surface of the radome body 10 with the first fixing part 11a, and a reaction force in the direction of the aircraft axis, indicated by arrow P4, is generated at the contact surface of the first fixing part 11a with the radome body 10. In this embodiment, the radome 1 for the aircraft is provided with a load-receiving part 12 that is provided separately from the fixing member 11 and receives the load in the direction of the aircraft axis acting on the fixing member 11. This configuration makes it possible to increase the rigidity against the reaction force in the direction of the aircraft axis, indicated by arrow P4, and thus improve the rigidity of the radome 1 for the aircraft against bending loads. Therefore, a radome 1 for the aircraft that can withstand large bending loads can be obtained.

[0040] In this embodiment, since the structure does not use adhesive to fix the individual components of the projectile radome 1 together, the upper temperature limit of the projectile radome 1, which depends on the glass transition temperature of the adhesive, is eliminated, and the overall heat resistance of the projectile radome 1 can be improved. Furthermore, since the bonding process of bonding the individual components together with adhesive is eliminated, variations in the quality of each projectile radome 1 can be reduced, and the construction period can be shortened by omitting confirmation tests to verify the integrity of the adhesion.

[0041] In this embodiment, as shown in Figure 5, the fixing process is performed using a moving jig 6 equipped with a moving mechanism that utilizes one of the following forces: spring force, hydraulic pressure, bolt tightening force, motor driving force, or electromagnetic repulsion. As a result, the radome 1 for projectiles does not require a moving mechanism, thus reducing the number of parts and making the radome 1 lighter. Furthermore, the assembly of the radome 1 can be automated, reducing variations in quality due to human error and stabilizing the quality of the radome 1.

[0042] Embodiment 2. Next, with reference to Figures 6 and 7, the radome 1A for the projectile 100A according to Embodiment 2 will be described. This embodiment differs from Embodiment 1 described above in that a slit 11g is formed in the first fixing portion 11a to create an elastic portion 11c. In Embodiment 2, parts that overlap with Embodiment 1 described above are denoted by the same reference numerals and their description is omitted.

[0043] Figure 6 is a cross-sectional view of the tip portion of a projectile 100A equipped with a projectile radome 1A according to Embodiment 2, cut along the direction perpendicular to the machine axis. Figure 7 is a perspective view showing the first fixing part 11a in Embodiment 2. As shown in Figures 6 and 7, the first fixing part 11a is divided into multiple parts in the circumferential direction. This makes it easier to position the first fixing part 11a on the inner circumference of the radome body 10 when assembling the projectile radome 1. The first fixing part 11a has multiple divided bodies 11h arranged at equal angles in the circumferential direction. The elastic part 11c and connecting part 11d of each divided body 11h are formed in an arc shape. The first fixing part 11a as a whole is formed in a cylindrical shape. The second fixing part 11b is a single member and is not divided into multiple parts in the circumferential direction.

[0044] Each segmented body 11h has an elastic portion 11c with a slit 11g extending in the axial direction and circumferential direction. In this embodiment, there are two slits 11g, but there may be one or more than three. The multiple slits 11g are spaced apart in the direction perpendicular to the machine axis with a plate-like portion 11i in between. The plate-like portion 11i of the elastic portion 11c extends in the direction perpendicular to the machine axis while meandering back and forth between one circumferential direction and the other.

[0045] Next, the effects of the projectile 100A according to this embodiment will be described.

[0046] In this embodiment, as shown in Figures 6 and 7, a slit 11g extending in the axial direction and circumferential direction is formed in the elastic portion 11c. With this configuration, the first fixing portion 11a has rigidity against loads in the axial direction and elasticity (flexibility) against loads perpendicular to the axial direction. Therefore, when a bending load is applied to the radome 1A for the projectile, the first fixing portion 11a can suppress the amount of bending deformation of the radome 1A for the projectile, thereby improving the performance of the radome 1A for the projectile.

[0047] Embodiment 3. Next, with reference to Figure 8, the radome 1B for the projectile 100B according to Embodiment 3 will be described. This embodiment differs from Embodiments 1 and 2 described above in that the radome 1B for the projectile further includes a moving mechanism 13. In Embodiment 3, parts that overlap with Embodiments 1 and 2 described above are denoted by the same reference numerals and their description is omitted.

[0048] Figure 8 is a cross-sectional view of the tip portion of a projectile 100B equipped with a projectile radome 1B according to Embodiment 3, cut along the machine axis direction, showing the state in which the radome body 10 and the fixing member 11 are fixed together. As shown in Figure 8, the projectile radome 1B further includes a moving mechanism 13. The moving mechanism 13 moves the fixing member 11 and the load-receiving portion 12 toward the rear in the machine axis direction. The moving mechanism 13 has a male screw member 13a and a lock nut 13b.

[0049] In this embodiment, the male threaded member 13a is provided on the first fixing portion 11a, but it may also be provided on the second fixing portion 11b. The male threaded member 13a is provided on the outer circumferential surface of the coupling portion 11d of the first fixing portion 11a. The male threaded member 13a is formed in a cylindrical shape. A male threaded portion 13c is formed on the outer circumferential surface of the male threaded member 13a. The lock nut 13b is provided on the outer circumferential surface of the male threaded member 13a and connects with the male threaded portion 13c. The lock nut 13b is formed in a cylindrical shape.

[0050] When the lock nut 13b is tightened, the male threaded member 13a, the fixing member 11, and the load-receiving part 12 move integrally in the axial direction toward the rear. The lock nut 13b is connected to the machine body 2 by a bolt (not shown) and also functions as a radome ring 3. Therefore, in this embodiment, a radome ring 3 is unnecessary. Alternatively, the first fixing part 11a or the second fixing part 11b may be directly connected to the machine body 2. Furthermore, as shown in the illustrated example, a spacer 14 may be inserted between the base end 10a of the radome body 10 and the lock nut 13b in the axial direction. This prevents the radome body 10 from being scratched by rubbing against the base end 10a of the radome body 10 and the lock nut 13b when the lock nut 13b is tightened.

[0051] Next, the effects of the projectile 100B according to this embodiment will be described.

[0052] In this embodiment, as shown in Figure 8, the radome 1B for projectiles is further equipped with a moving mechanism 13 that moves the fixing member 11 and the load-bearing portion 12 toward the rear in the direction of the machine axis. This configuration allows the radome body 10 and the fixing member 11 and load-bearing portion 12 to move relatively smoothly in the direction of the machine axis, thereby improving the ease of assembly of the radome 1B for projectiles.

[0053] In this embodiment, the moving mechanism 13 includes a male screw member 13a provided on the first fixing part 11a or the second fixing part 11b, with a male screw portion 13c formed on its outer circumference, and a lock nut 13b provided on the outer circumference of the male screw member 13a and coupled with the male screw portion 13c. In this embodiment, when the lock nut 13b is tightened, the male screw member 13a, the fixing member 11, and the load-receiving part 12 move integrally in the machine axis direction toward the rear. With these configurations, the first fixing part 11a and the second fixing part 11b can be moved uniformly toward the rear over their entire circumference. Therefore, the surface pressure generated at the contact surface between the radome body 10 and the first fixing part 11a during the assembly of the radome 1B for the projectile can be made uniform in the circumferential direction. As described above, after the fixing process, an attachment process may be performed to attach the load-receiving part 12 to the fixing member 11. In this case, the moving mechanism 13 will move the fixing member 11 toward the rear in the machine axis direction. Furthermore, during the fixing process, when the lock nut 13b is tightened, the male screw member 13a and the fixing member 11 move integrally in the machine axis direction toward the rear.

[0054] Embodiment 4. Next, with reference to Figures 9 and 10, the radome 1C for the projectile 100C according to Embodiment 4 will be described. This embodiment differs from Embodiments 1 to 3 described above in that the radome 1C for the projectile further includes a connecting member 15, and that a dedicated moving jig 6 is used to move the fixing member 11 and the load-receiving part 12 during the assembly of the radome 1C for the projectile. In Embodiment 4, parts that overlap with Embodiments 1 to 3 described above are denoted by the same reference numerals and their description is omitted.

[0055] Figure 9 is a cross-sectional view of the tip portion of a projectile 100C equipped with a projectile radome 1C according to Embodiment 4, cut along the axis of the machine, showing the state in which the radome body 10 and the fixing member 11 are fixed together. Figure 10 is a cross-sectional view showing an example of a method for manufacturing the projectile radome 1C according to Embodiment 4. As shown in Figure 9, the projectile radome 1C further includes a connecting member 15. The connecting member 15 connects the fixing member 11 and the radome ring 3. The connecting member 15 is, for example, a bolt or a pin.

[0056] The first fixing portion 11a has a first connecting hole 11j that penetrates in a direction perpendicular to the machine axis. The second fixing portion 11b has a second connecting hole 11k that penetrates in a direction perpendicular to the machine axis and communicates with the first connecting hole 11j. The radome ring 3 has a third connecting hole 3a that is recessed on the outer circumference in a direction perpendicular to the machine axis and communicates with the first connecting hole 11j. The connecting member 15 is inserted through the first connecting hole 11j, the second connecting hole 11k, and the third connecting hole 3a. The connecting member 15 connects the first fixing portion 11a, the second fixing portion 11b, and the radome ring 3.

[0057] As shown in Figure 10, in the fixing process, with the radome ring 3 fixed immovably by the fixing jig 5, the fixing member 11 and the load-receiving part 12 are moved backward in the machine axis direction by the moving jig 6. Then, as shown in Figure 9, the first fixing part 11a, the second fixing part 11b, and the radome ring 3 are connected by the connecting member 15 at the position after the move. As described above, an attachment process in which the load-receiving part 12 is attached to the fixing member 11 may be performed after the fixing process. In this case, in the fixing process, the fixing member 11 will be moved backward in the machine axis direction by the moving jig 6.

[0058] Next, the effects of the projectile 100C according to this embodiment will be described.

[0059] In this embodiment, as shown in Figure 10, by using the moving jig 6 in the fixing process, the moving mechanism 13 is not required for the projectile radome 1C itself, thus reducing the number of parts and making the projectile radome 1C lighter.

[0060] Embodiment 5. Next, with reference to Figure 11, the radome 1D for the projectile 100D according to Embodiment 5 will be described. This embodiment differs from Embodiments 1 to 4 described above in that an inner circumferential protrusion 10e is formed on the inner circumferential surface 10c of the radome body 10. In Embodiment 5, parts that overlap with Embodiments 1 to 4 described above are denoted by the same reference numerals and their description is omitted.

[0061] Figure 11 is a cross-sectional view of the tip portion of a projectile 100D equipped with a projectile radome 1D according to Embodiment 5, cut along the axis of the machine, showing the state in which the radome body 10 and the fixing member 11 are fixed together. As shown in Figure 11, the load-receiving portion 12 is provided separately from the first fixing portion 11a and is in contact with the tip portion 11e of the first fixing portion 11a (elastic portion 11c) in the axis of the machine.

[0062] An inner circumferential protrusion 10e is formed on the inner circumferential surface 10c of the radome body 10, projecting inward. The inner circumferential protrusion 10e is located on the opposite side of the load-receiving portion 12, with the elastic portion 11c of the first fixing portion 11a in between, in the machine axis direction. The inner circumferential protrusion 10e is in contact with the rearmost base end 11m of the elastic portion 11c of the first fixing portion 11a. More specifically, the inner circumferential protrusion 10e is in contact with the base end 11m in the machine axis direction of the elastic portion 11c in a compressed state. The inner circumferential protrusion 10e is located behind the contraction portion 10d and is formed on the inner circumferential surface 10c of the radome body 10, closer to the base end 10a. The innermost tip of the inner circumferential protrusion 10e is in contact with the outer circumferential surface of the joint portion 11d.

[0063] Next, the effects of the projectile 100D according to this embodiment will be described.

[0064] In this embodiment, as shown in Figure 11, an inner circumferential protrusion 10e is formed on the inner circumferential surface 10c of the radome body 10, projecting inward. In this embodiment, the inner circumferential protrusion 10e is positioned on the opposite side of the load-receiving portion 12 in the axial direction, with the elastic portion 11c of the first fixing portion 11a in between, and contacts the base end 11m, which is the furthest rear of the elastic portion 11c of the first fixing portion 11a. With these configurations, when a bending load is applied to the radome 1D for a projectile, even if the reaction force in the axial direction generated at the contact surface between the radome body 10 and the first fixing portion 11a exceeds the frictional force of the contact surface, the inner circumferential protrusion 10e receives the reaction force in the axial direction. Therefore, the rigidity of the radome 1D for a projectile against bending loads can be improved. Thus, a radome 1D for a projectile that can withstand larger bending loads can be obtained. Furthermore, if the bending load were to be withstood solely by the frictional force of the contact surface between the radome body 10 and the first fixing part 11a, a large contact pressure would be required. However, if the radome body 10 has an inner circumference protrusion 10e, it becomes unnecessary to increase the contact pressure. This improves the ease of assembly of the projectile radome 1D and suppresses cracking of the radome body 10 at high temperatures.

[0065] Embodiment 6. Next, with reference to Figure 12, the radome 1E for the projectile 100E according to Embodiment 6 will be described. This embodiment differs from Embodiments 1 to 5 described above in that the load-receiving portion 12a is integrated with the first fixing portion 11a. In Embodiment 6, parts that overlap with Embodiments 1 to 5 described above are denoted by the same reference numerals and their description is omitted.

[0066] Figure 12 is a cross-sectional view of the tip portion of a projectile 100E equipped with a projectile radome 1E according to Embodiment 6, cut along the axis of the machine, showing the state in which the radome body 10 and the fixing member 11 are fixed together. As shown in Figure 12, the load-receiving portion 12a is integrated with the first fixing portion 11a and is located furthest forward of the first fixing portion 11a. The load-receiving portion 12a is positioned in front of the elastic portion 11c. The load-receiving portion 12a and the elastic portion 11c are partially separated by a groove 11n extending in the circumferential direction, but are connected on the inner circumference beyond the groove 11n.

[0067] The load-bearing portion 12a does not have elasticity that allows it to be elastically deformed in the direction perpendicular to the machine axis, like the elastic portion 11c. The load-bearing portion 12a protrudes forward of the second fixing portion 11b. It is preferable to process the material that forms the load-bearing portion 12a and the first fixing portion 11a by cutting, wire cutting, etc., to integrate the load-bearing portion 12a and the first fixing portion 11a. However, if it is not possible to integrate the two by cutting, wire cutting, etc., the separately formed load-bearing portion 12a and the first fixing portion 11a may be integrated by welding, brazing, etc. Integration means that at least a portion of the load-bearing portion 12a and the first fixing portion 11a are formed continuously without any gaps.

[0068] Next, the effects of the projectile 100E according to this embodiment will be described.

[0069] In this embodiment, as shown in Figure 12, the load-receiving portion 12a is integrated with the first fixing portion 11a and is located at the foremost position of the first fixing portion 11a. This configuration reduces the number of parts and improves the assembly of the projectile radome 1E compared to the case where the load-receiving portion 12a and the first fixing portion 11a are provided separately.

[0070] Embodiment 7. Next, with reference to Figure 13, the radome 1F for the projectile 100F according to Embodiment 7 will be described. This embodiment differs from Embodiments 1 to 6 described above in that the load-receiving portion 12 is a load-receiving portion 12b that constitutes a pin, and the load-receiving portion 12b is inserted through the first fixing portion 11a and the second fixing portion 11b. In Embodiment 7, parts that overlap with Embodiments 1 to 6 described above are denoted by the same reference numerals and their description is omitted.

[0071] Figure 13 is a cross-sectional view of the tip portion of a projectile 100F equipped with a projectile radome 1F according to Embodiment 7, cut along the axis of the machine, showing the state in which the radome body 10 and the fixing member 11 are fixed together. As shown in Figure 13, the elastic portion 11c of the first fixing portion 11a has a first through hole 11o that penetrates in a direction perpendicular to the machine axis. The second fixing portion 11b has a second through hole 11p that penetrates in a direction perpendicular to the machine axis and communicates with the first through hole 11o. The load-receiving portion 12b is a pin that is inserted through the first through hole 11o and the second through hole 11p. In this embodiment, after the arrangement process and before the fixing process, or after the fixing process, an attachment process may be performed in which the load-receiving portion 12b, which is a pin, is inserted through the first through hole 11o and the second through hole 11p to attach the load-receiving portion 12b to the fixing member 11. Alternatively, the mounting process may be performed before the placement process, with the load-receiving portion 12b, which is a pin, inserted through the first through hole 11o and the second through hole 11p before the placement process is carried out.

[0072] Next, the effects of the projectile 100F according to this embodiment will be described.

[0073] In this embodiment, as shown in Figure 13, the load-receiving portion 12b is a pin inserted through the first through hole 11o and the second through hole 11p. With this configuration, the load-receiving portion 12b does not protrude further inward than the second fixing portion 11b, and space for electronic equipment (not shown) to be placed inside the radome 1F for the projectile can be secured. Furthermore, since the load-receiving portion 12b receives the load in the direction of the machine axis acting on the fixing member 11, the rigidity against reaction forces in the direction of the machine axis can be increased, thereby improving the rigidity of the radome 1F for the projectile against bending loads.

[0074] Embodiment 8. Next, with reference to Figure 14, the radome 1G for the projectile 100G according to Embodiment 8 will be described. This embodiment differs from Embodiments 1 to 7 described above in that the load-receiving portion 12 is a load-receiving portion 12c that constitutes a pin, and the load-receiving portion 12c is inserted through the first fixing portion 11a, the second fixing portion 11b, and the radome body 10. In Embodiment 8, parts that overlap with Embodiments 1 to 7 described above are denoted by the same reference numerals and their description is omitted.

[0075] Figure 14 is a cross-sectional view of the tip portion of a projectile 100G equipped with a projectile radome 1G according to Embodiment 8, cut along the axis of the machine, showing the state in which the radome body 10 and the fixing member 11 are fixed together. As shown in Figure 14, the elastic portion 11c of the first fixing portion 11a has a first through hole 11o that penetrates in a direction perpendicular to the machine axis. The second fixing portion 11b has a second through hole 11p that penetrates in a direction perpendicular to the machine axis and communicates with the first through hole 11o. The radome body 10 has a third through hole 10f that penetrates in a direction perpendicular to the machine axis and communicates with the first through hole 11o. The load-receiving portion 12c is a pin that is inserted through the first through hole 11o, the second through hole 11p, and the third through hole 10f. In this embodiment, after the fixing process, an attachment process is performed in which the load-receiving portion 12c, which is a pin, is inserted through the first through hole 11o, the second through hole 11p, and the third through hole 10f to attach the load-receiving portion 12c to the fixing member 11.

[0076] Next, the effects of the projectile 100G according to this embodiment will be described.

[0077] In this embodiment, as shown in Figure 14, the load-receiving portion 12c is a pin inserted through the first through hole 11o, the second through hole 11p, and the third through hole 10f. This configuration provides the same effects as the embodiment 7 described above. In this embodiment, the load-receiving portion 12c, which is a pin, is also inserted through the third through hole 10f of the radome body 10. With this configuration, when a bending load is applied to the radome 1G for a projectile, even if the reaction force in the machine axis direction generated at the contact surface between the radome body 10 and the first fixing portion 11a exceeds the frictional force of the contact surface, the load-receiving portion 12c, which is a pin, receives the reaction force in the machine axis direction. Therefore, the rigidity of the radome 1G for a projectile against bending loads can be improved. Thus, a radome 1G for a projectile that can withstand larger bending loads can be obtained. Furthermore, since it can withstand larger bending loads without providing an inner circumference protrusion 10e on the radome body 10 as in embodiment 5, the material cost and processing cost of the radome body 10 can be reduced.

[0078] Embodiment 9. Next, with reference to Figure 15, the radome 1H for the projectile 100H according to Embodiment 9 will be described. This embodiment differs from Embodiments 1 to 8 described above in that a heat insulating sheet 16 is placed between the first fixing part 11a and the radome body 10. In Embodiment 9, parts that overlap with Embodiments 1 to 8 described above are denoted by the same reference numerals and their description is omitted.

[0079] Figure 15 is a cross-sectional view of the tip portion of a projectile 100H equipped with a projectile radome 1H according to Embodiment 9, cut along the axis of the machine, showing the state in which the radome body 10 and the fixing member 11 are fixed together. As shown in Figure 15, a heat insulating sheet 16 made of a material with low thermal conductivity is placed between the outer circumferential surface of the first fixing part 11a and the inner circumferential surface 10c of the radome body 10. The heat insulating sheet 16 may be attached to either the outer circumferential surface of the first fixing part 11a or the inner circumferential surface 10c of the radome body 10. The first fixing part 11a may also be made of a material with low thermal conductivity.

[0080] Next, the effects of the projectile 100H according to this embodiment will be described.

[0081] In this embodiment, as shown in Figure 15, a heat insulating sheet 16 made of a material with low thermal conductivity is placed between the outer circumferential surface of the first fixing part 11a and the inner circumferential surface 10c of the radome body 10. This configuration increases the thermal resistance along the heat transfer path from the radome body 10 to the aircraft body 2 via the first fixing part 11a, thereby suppressing heat transfer from the radome body 10 to the aircraft body 2.

[0082] Embodiment 10. Next, with reference to Figure 16, the radome 1I for the projectile 100I according to Embodiment 10 will be described. This embodiment differs from Embodiments 1 to 9 described above in that a graphite sheet 17 is placed between the first fixing part 11a and the radome body 10. In Embodiment 10, parts that overlap with Embodiments 1 to 9 described above are denoted by the same reference numerals and their description is omitted.

[0083] Figure 16 is a cross-sectional view of the tip portion of a projectile 100I equipped with a projectile radome 1I according to Embodiment 10, cut along the axis of the machine, showing the state in which the radome body 10 and the fixing member 11 are fixed together. A graphite sheet 17 is placed between the outer circumferential surface of the first fixing part 11a and the inner circumferential surface 10c of the radome body 10. The graphite sheet 17 may be attached to either the outer circumferential surface of the first fixing part 11a or the inner circumferential surface 10c of the radome body 10.

[0084] Next, the effects of the projectile 100I according to this embodiment will be described.

[0085] In this embodiment, as shown in Figure 16, a graphite sheet 17 is placed between the outer circumferential surface of the first fixing part 11a and the inner circumferential surface 10c of the radome body 10. This configuration prevents wear of the inner circumferential surface 10c of the radome body 10 caused by the sliding of the first fixing part 11a, thereby preventing a decrease in the strength of the radome body 10 due to scratches on the inner circumferential surface 10c of the radome body 10.

[0086] Embodiment 11. Next, with reference to Figures 17 and 18, the radome 1J for the projectile 100J according to Embodiment 11 will be described. This embodiment differs from Embodiments 1 to 10 described above in that the radome 1J for the projectile further includes a moving mechanism 13, and the moving mechanism 13 is an eccentric pin. In Embodiment 11, parts that overlap with Embodiments 1 to 10 described above are denoted by the same reference numerals and their description is omitted.

[0087] Figure 17 is a cross-sectional view of the tip portion of a projectile 100J equipped with a projectile radome 1J according to Embodiment 11, cut along the axis of the machine, showing the state before the radome body 10 and the fixing member 11 are fixed together. As shown in Figure 17, the radome ring 3 has a housing hole 3b that penetrates in the direction perpendicular to the machine axis. The first fixing part 11a has a first insertion hole 11q that penetrates in the direction perpendicular to the machine axis and communicates with the housing hole 3b. The second fixing part 11b has a second insertion hole 11r that penetrates in the direction perpendicular to the machine axis and communicates with the first insertion hole 11q.

[0088] The moving mechanism 13 is an eccentric pin 13d having a head 13e and a shaft 13f. The head 13e is positioned within the housing hole 3b. The central axis O1 of the head 13e coincides with the central axis of the housing hole 3b. The shaft 13f is inserted through the first insertion hole 11q and the second insertion hole 11r. The central axis O2 of the shaft 13f is offset in the direction of the machine axis relative to the central axis O1 of the head 13e. In the state before the fixing process, the central axis O2 of the shaft 13f is offset forward relative to the central axis O1 of the head 13e. The central axis O1 of the head 13e and the central axis O2 of the shaft 13f are parallel to the direction perpendicular to the machine axis.

[0089] Figure 18 is a cross-sectional view of the tip portion of a projectile 100J equipped with a projectile radome 1J according to Embodiment 11, cut along the axis of the machine, showing the state in which the radome body 10 and the fixing member 11 are fixed together. As shown in Figure 18, when the fixing process is performed by rotating the eccentric pin 13d around the direction perpendicular to the machine axis, the central axis O2 of the shaft portion 13f gradually shifts from front to rear relative to the central axis O1 of the head portion 13e. At this time, the fixing member 11 and the load-receiving portion 12 move integrally in the direction of the machine axis toward the rear. When the eccentric pin 13d is rotated to a position where the central axis O2 of the shaft portion 13f is shifted rearward relative to the central axis O1 of the head portion 13e, the elastic portion 11c slides along the contraction portion 10d, compressing and deforming and pressing against the inner circumferential surface 10c of the radome body 10. As a result, the radome body 10 and the fixing member 11 are fixed together.

[0090] Next, the effects of the projectile 100J according to this embodiment will be described.

[0091] In this embodiment, as shown in Figures 17 and 18, the moving mechanism 13 is an eccentric pin 13d having a head portion 13e and a shaft portion 13f. The head portion 13e is positioned within the housing hole 3b. The shaft portion 13f is inserted through the first insertion hole 11q and the second insertion hole 11r. When the eccentric pin 13d is rotated, the fixing member 11 and the load-receiving portion 12 move together in the axial direction toward the rear. With this configuration, the radome body 10, the fixing member 11, and the load-receiving portion 12 can be moved relatively smoothly without using large jigs, thereby improving the ease of assembly of the projectile radome 1J. As described above, after the fixing process, an attachment process may be performed in which the load-receiving portion 12 is attached to the fixing member 11. In this case, when the eccentric pin 13d is rotated during the fixing process, the fixing member 11 moves toward the rear in the axial direction.

[0092] Embodiment 12. Next, with reference to Figure 19, the radome 1K for the projectile 100K according to Embodiment 12 will be described. In this embodiment, the cross-sectional shape of the reduced portion 10d, the cross-sectional shape of the first fixing portion 11a, and the cross-sectional shape of the second fixing portion 11b when cut in the direction perpendicular to the machine axis differ from those of Embodiments 1 to 11 described above. In Embodiment 12, parts that overlap with Embodiments 1 to 11 described above are denoted by the same reference numerals and their description is omitted.

[0093] Figure 19 is a cross-sectional view of the tip portion of a projectile 100K equipped with a projectile radome 1K according to Embodiment 12, when cut along the direction perpendicular to the aircraft axis. As shown in Figure 19, the cross-sectional shape of the reduced portion 10d, the cross-sectional shape of the first fixing portion 11a, and the cross-sectional shape of the second fixing portion 11b when cut in the direction perpendicular to the aircraft axis are asymmetric. An asymmetric shape means a cross-sectional shape other than a circular cross-section. Figure 19 shows a hexagonal cross-section as an example of an asymmetric shape, but asymmetric shapes include polygonal cross-sections other than hexagonal cross-sections, elliptical cross-sections, etc.

[0094] The divided portions 11h of the first fixing portion 11a are arranged one by one between each side constituting the inner circumferential surface of the reduced portion 10d and each side constituting the outer circumferential surface of the second fixing portion 11b. In this embodiment, the cross-sectional shape of the first fixing portion 11a when cut in the direction perpendicular to the machine axis refers to the cross-sectional shape when it is assumed that the multiple divided portions 11h are connected. Note that, in the inner circumferential surface 10c of the radome body 10, it is sufficient that the cross-sectional shape of the reduced portion 10d when cut in the direction perpendicular to the machine axis is at least asymmetric.

[0095] Next, the effects of the projectile 100K according to this embodiment will be described.

[0096] In this embodiment, as shown in Figure 19, the cross-sectional shape of the reduced portion 10d, the cross-sectional shape of the first fixing portion 11a, and the cross-sectional shape of the second fixing portion 11b when cut in a direction perpendicular to the machine axis are asymmetric. This configuration makes it possible to suppress circumferential rotation of the radome body 10 after the fixing process.

[0097] Embodiment 13. Next, with reference to Figures 20 and 21, the radome 1L for the projectile 100L according to Embodiment 13 will be described. This embodiment differs from Embodiments 1 to 12 described above in that the first fixing part 11a and the second fixing part 11b are integrated. In Embodiment 13, parts that overlap with Embodiments 1 to 12 described above are denoted by the same reference numerals and their description is omitted.

[0098] Figure 20 is a cross-sectional view of the tip portion of a projectile 100L equipped with a projectile radome 1L according to Embodiment 13, cut along the axis of the machine, showing the state in which the radome body 10 and the fixing member 11 are fixed together. Figure 20 schematically shows the boundary line L between the first fixing part 11a and the second fixing part 11b. As shown in Figure 20, the first fixing part 11a and the second fixing part 11b are integrated. That is, the projectile radome 1L is equipped with a fixing member 11 in which the first fixing part 11a and the second fixing part 11b are integrated. Note that integration means that at least a portion of the first fixing part 11a and the second fixing part 11b are formed continuously without gaps. The first fixing part 11a and the second fixing part 11b are integrated by increasing the plate thickness of the fixing member 11 in the direction perpendicular to the machine axis. The load receiving part 12 is in contact with the tip 11s of the fixing member 11 in the direction of the machine axis. The tip 11s of the fixing member 11 in the direction of the machine axis is the end of the fixing member 11 that is located furthest forward.

[0099] Figure 21 is a cross-sectional view of the tip portion of a projectile 100L equipped with a projectile radome 1L according to Embodiment 13, when cut along the direction perpendicular to the aircraft axis. As shown in Figure 21, in the elastic portion 11c, the first fixing portion 11a and the second fixing portion 11b are integrated by making the plate thickness T1 in the direction perpendicular to the aircraft axis of the innermost portion of the plate-shaped portion 11i thicker than the plate thicknesses T2 and T3 in the direction perpendicular to the aircraft axis of the other portions. That is, the innermost portion of the plate-shaped portion 11i plays the role of a second fixing portion 11b with high rigidity in the direction perpendicular to the aircraft axis, while the other portions of the plate-shaped portion 11i play the role of elastically deforming in the direction perpendicular to the aircraft axis.

[0100] Next, the effects of the projectile 100L according to this embodiment will be described.

[0101] In this embodiment, as shown in Figures 20 and 21, the first fixing part 11a and the second fixing part 11b are integrated. This configuration allows for the integration of an elastic function that allows elastic deformation in the direction perpendicular to the machine axis and a function that provides high rigidity in the direction perpendicular to the machine axis into a single fixing member 11. As a result, the number of parts can be reduced and the assembly of the radome 1L for the projectile can be improved.

[0102] Embodiment 14. Next, with reference to Figure 22, the radome 1M for the projectile 100M according to Embodiment 14 will be described. This embodiment differs from Embodiments 1 to 13 described above in that the radome 1M for the projectile further comprises a heat insulating layer 18. In Embodiment 14, parts that overlap with Embodiments 1 to 13 described above are denoted by the same reference numerals and their description is omitted.

[0103] Figure 22 is a cross-sectional view of the tip portion of a projectile 100M equipped with a projectile radome 1M according to Embodiment 14, cut along the axis of the machine, showing the state in which the radome body 10 and the fixing member 11 are fixed together. As shown in Figure 22, the projectile radome 1M further includes a heat insulating layer 18 that spans the outer circumferential surface of the radome body 10 and the outer circumferential surface of the radome ring 3.

[0104] Next, the effects of the projectile 100M according to this embodiment will be described.

[0105] In this embodiment, as shown in Figure 22, the projectile radome 1M further includes a heat insulating layer 18 that spans the outer surface of the radome body 10 and the outer surface of the radome ring 3. This configuration insulates the heat input from the outer surface to the inner surface of the radome body 10 and the radome ring 3, protecting the electronic equipment inside the projectile radome 1M from heat.

[0106] Embodiment 15. Next, with reference to Figure 23, the radome 1N for the projectile 100N according to Embodiment 15 will be described. This embodiment differs from Embodiments 1 to 14 described above in that the fixing member 11 further comprises a third fixing portion 11t, and the inner circumferential protrusion 10e is sandwiched between the first fixing portion 11a and the third fixing portion 11t. In Embodiment 15, parts that overlap with Embodiments 1 to 14 described above are denoted by the same reference numerals and their description is omitted.

[0107] Figure 23 is a cross-sectional view of the tip portion of a projectile 100N equipped with a projectile radome 1N according to Embodiment 15, cut along the axis of the machine, showing the state in which the radome body 10 and the fixing member 11 are fixed together. As shown in Figure 23, the inner circumferential protrusion 10e is provided at a position located forward from the base end 10a of the radome body 10. The inner circumferential surface 10c of the radome body 10 is provided with an inner circumferential tapered portion 10g, the inner circumferential dimension of which increases as it moves backward from the inner circumferential protrusion 10e.

[0108] The fixing member 11 further has a third fixing portion 11t. The third fixing portion 11t is positioned on the opposite side from the first fixing portion 11a in the machine axis direction, with the inner circumferential protrusion 10e in between. The outer circumference dimension of the third fixing portion 11t is larger than the inner circumference dimension of the inner circumferential tapered portion 10g. The outer circumferential surface of the third fixing portion 11t is a tapered surface having the same taper angle as the inner circumferential tapered portion 10g. The third fixing portion 11t is positioned between the inner circumferential surface 10c of the radome body 10 and the outer circumferential surface of the male screw member 13a in the direction perpendicular to the machine axis. Furthermore, the third fixing portion 11t is positioned between the inner circumferential protrusion 10e and the machine axis-oriented tip of the lock nut 13b in the machine axis direction. The third fixing portion 11t protrudes rearward from the radome body 10 and is in contact with the machine axis-oriented tip of the lock nut 13b. The inner circumferential protrusion 10e is sandwiched between the first fixing part 11a and the third fixing part 11t in the direction of the machine axis.

[0109] Next, the effects of the projectile 100N according to this embodiment will be described.

[0110] In this embodiment, as shown in Figure 23, the radome 1N for projectiles further includes a third fixing part 11t positioned on the opposite side of the first fixing part 11a in the axial direction, with the inner circumferential protrusion 10e in between. The inner circumferential protrusion 10e is sandwiched between the first fixing part 11a and the third fixing part 11t in the axial direction. With these configurations, the force that moves the first fixing part 11a and the second fixing part 11b toward the rear is used to slide the third fixing part 11t along the inner circumferential tapered part 10g, thereby compressively deforming it in the direction perpendicular to the axial direction. As a result, the inner circumferential protrusion 10e is sandwiched between the first fixing part 11a and the third fixing part 11t in the axial direction, further increasing the fixing force between the fixing member 11 and the radome body 10.

[0111] In this embodiment, the third fixing portion 11t protrudes rearward from the radome body 10 and contacts the tip of the lock nut 13b in the direction of the aircraft axis. This configuration prevents scratches on the radome body 10 caused by friction between the base end 10a of the radome body 10 and the lock nut 13b when the lock nut 13b is tightened. In other words, the third fixing portion 11t performs the same role as the spacer 14 in Embodiment 3. Furthermore, by using the third fixing portion 11t instead of the spacer 14 in Embodiment 3, the axes of each component can be easily aligned during the assembly of the radome 1N for the projectile.

[0112] The configurations shown in the above embodiments are merely examples, and it is possible to combine them with other known technologies, combine different embodiments, and omit or modify parts of the configuration without departing from the gist of the invention.

[0113] The various aspects of this disclosure are summarized below as an appendix.

[0114] (Note 1) A hollow radome body having a base end located toward the aircraft body in the axial direction and a tip end located opposite the aircraft body in the axial direction, A fixing member is arranged on the inner circumference of the radome body to fix the radome body to the radome ring or the aircraft body, A load-receiving portion, which is integrated with the fixing member or provided separately from the fixing member, receives the load in the machine axis direction acting on the fixing member, Equipped with, The aforementioned fixing member is A first fixing portion that contacts the inner circumferential surface of the radome body and includes an elastic portion that is elastically deformable in the direction perpendicular to the machine axis, which is perpendicular to the machine axis direction, A second fixing portion is provided on the inner circumference of the first fixing portion and has higher rigidity in the direction perpendicular to the machine axis than the first fixing portion, It has, A radome for a projectile, characterized in that, when the direction from the base end to the tip of the radome body is considered forward along the axial direction of the aircraft, and the direction from the tip to the base of the radome body is considered rearward along the axial direction of the aircraft, the inner circumferential surface of the radome body has a tapering portion formed thereon, where the inner circumferential dimension decreases as it approaches the rear. (Note 2) A hollow radome body having a base end located toward the aircraft body in the axial direction and a tip end located opposite the aircraft body in the axial direction, A fixing member is arranged on the inner circumference of the radome body to fix the radome body to the radome ring or the aircraft body, A load-receiving portion, which is integrated with the fixing member or provided separately from the fixing member, receives the load in the machine axis direction acting on the fixing member, Equipped with, The aforementioned fixing member is A first fixing portion that contacts the inner circumferential surface of the radome body and includes an elastic portion that is elastically deformable in the direction perpendicular to the machine axis, which is perpendicular to the machine axis direction, A second fixing portion is provided on the inner circumference of the first fixing portion and has higher rigidity in the direction perpendicular to the machine axis than the first fixing portion, It has, When the direction from the base end to the tip of the radome body along the machine axis is considered the front, and the direction from the tip to the base of the radome body along the machine axis is considered the rear, a tapering portion is formed on the inner circumferential surface of the radome body in which the inner circumferential dimension decreases as it approaches the rear. A radome for a projectile, characterized in that the radome body and the fixing member move relative to each other in the direction of the machine axis, causing the elastic portion to slide along the contraction portion, compressing and deforming, and pressing against the inner circumferential surface of the radome body, thereby fixing the radome body and the fixing member together. (Note 3) The radome for a projectile according to Appendix 1 or 2, characterized in that the shape of the reduced portion is a tapered shape in which the inner circumference decreases as it approaches the rear. (Note 4) The radome for a projectile according to any one of the appendices 1 to 3, characterized in that the elastic portion has a slit that extends in the axial direction and circumferential direction. (Note 5) A radome for a flying object according to any one of appendices 1 to 4, further comprising a moving mechanism for moving the fixing member toward the rear in the axial direction of the machine. (Note 6) The aforementioned moving mechanism is A male screw member provided on the first or second fixing portion, having a male screw portion formed on its outer surface, A lock nut provided on the outer circumferential surface of the male threaded member and coupled to the male threaded portion, It has, The radome for a projectile, as described in Appendix 5, characterized in that when the lock nut is tightened, the male screw member and the fixing member move integrally toward the rear in the direction of the machine axis. (Note 7) A radome for a projectile, as described in any one of appendices 1 to 6, further comprising a connecting member that connects the fixing member and the radome ring. (Note 8) The load-receiving portion is provided separately from the first fixing portion and is in contact with the tip of the first fixing portion that is located furthest forward, as described in any one of appendices 1 to 7. (Note 9) The load-receiving portion is integrated with the first fixing portion and is located furthest forward among the first fixing portions, as described in any one of appendices 1 to 7, for a projectile radome. (Note 10) The first fixing portion has a first through hole that penetrates in a direction perpendicular to the machine axis. The second fixing portion has a second through hole that penetrates in the direction perpendicular to the machine axis and communicates with the first through hole. The radome for a projectile according to any one of the appendices 1 to 7, characterized in that the load-receiving portion is a pin inserted through the first through hole and the second through hole. (Note 11) The radome body has a third through-hole formed therein, which penetrates in the direction perpendicular to the machine axis and communicates with the first through-hole. The radome for a projectile according to Appendix 10, characterized in that the pin is also inserted through the third through hole. (Note 12) The inner circumferential surface of the radome body has an inner circumferential protrusion that projects inward, The radome for a projectile according to any one of appendices 1 to 11, characterized in that the inner circumferential protrusion is in contact with the base end of the elastic portion of the first fixing portion that is located furthest rear. (Note 13) The radome for projectiles according to any one of the appendices 1 to 12, characterized in that the first fixing portion is formed of a material with low thermal conductivity, or a heat insulating sheet made of a material with low thermal conductivity is arranged between the outer circumferential surface of the first fixing portion and the inner circumferential surface of the radome body. (Note 14) A radome for projectiles according to any one of the appendices 1 to 13, characterized in that a graphite sheet is arranged between the outer circumferential surface of the first fixing part and the inner circumferential surface of the radome body. (Note 15) The radome ring has a housing hole formed therein that penetrates in the direction perpendicular to the machine axis. The first fixing portion has a first insertion hole that penetrates in the direction perpendicular to the machine axis and communicates with the housing hole. The second fixing portion has a second insertion hole that penetrates in the direction perpendicular to the machine axis and communicates with the first insertion hole. The aforementioned moving mechanism is an eccentric pin having a head portion and a shaft portion, The head is positioned within the housing hole. The shaft portion is inserted through the first insertion hole and the second insertion hole, The radome for a projectile, as described in Appendix 5, characterized in that when the eccentric pin is rotated, the fixing member moves rearward in the direction of the machine axis. (Note 16) A radome for a projectile according to any one of appendices 1 to 15, characterized in that the cross-sectional shape of the reduced portion, the cross-sectional shape of the first fixing portion, and the cross-sectional shape of the second fixing portion when cut in the direction perpendicular to the machine axis are non-axially symmetric. (Note 17) A radome for a projectile, as described in any one of appendices 1 to 16, characterized in that the first fixing part and the second fixing part are integrated. (Note 18) A radome for a projectile according to any one of appendices 1 to 17, further comprising a heat insulating layer disposed across the outer circumferential surface of the radome body and the outer circumferential surface of the radome ring. (Note 19) The fixing member further has a third fixing portion that is positioned in the direction of the machine axis with respect to the inner circumferential protrusions, on the opposite side from the first fixing portion, The radome for a projectile according to Appendix 12, characterized in that the inner circumferential protrusion is sandwiched between the first fixing portion and the third fixing portion in the direction of the machine axis. (Note 20) The radome comprises a hollow radome body having a base end located toward the aircraft body in the axial direction and a tip located opposite the aircraft body in the axial direction; a fixing member disposed on the inner circumference of the radome body to fix the radome body to the radome ring or the aircraft body; and a load-receiving portion, which is integrated with the fixing member or provided separately from the fixing member to receive the axial load acting on the fixing member, wherein the fixing member is in contact with the inner circumferential surface of the radome body and in a direction perpendicular to the axial direction. A method for manufacturing a radome for a projectile, comprising: a first fixing portion including an elastic portion that can be elastically deformed in a direction perpendicular to a certain axis; and a second fixing portion provided on the inner circumference of the first fixing portion and having higher rigidity in the direction perpendicular to the axis than the first fixing portion, wherein when the direction from the base end to the tip of the radome body along the axis of the machine is considered forward, and the direction from the tip to the base end of the radome body along the axis of the machine is considered rearward, a reducing portion is formed on the inner circumferential surface of the radome body in which the inner circumferential dimension decreases as it approaches the rearward. The arrangement step of arranging the fixing member on the inner circumference of the radome body, A fixing step in which the radome body and the fixing member are moved relative to each other in the direction of the machine axis, thereby compressing and deforming the elastic part by sliding it along the contraction part, pressing the inner circumferential surface of the radome body with the elastic part, and fixing the radome body and the fixing member, A method for manufacturing a radome for a projectile, characterized by including the following: (Note 21) The method for manufacturing a radome for a projectile, as described in Appendix 20, characterized in that, in the fixing step, the radome body and the fixing member are moved relative to each other in the direction of the machine axis using a jig equipped with a moving mechanism based on one of the following forces: the elastic force of a spring, hydraulic pressure, the fastening force of a bolt, the driving force of a motor, and electromagnetic repulsion. [Explanation of Symbols]

[0115] 1,1A,1B,1C,1D,1E,1F,1G,1H,1I,1J,1K,1L,1M,1N Radome for projectiles, 2 Aircraft body, 3 Radome ring, 3a Third connecting hole, 3b Housing hole, 4 Bolt, 5 Fixing jig, 6 Moving jig, 10 Radome body, 10a,11m Base end, 10b,11e,11f,11s Tip, 10c Inner surface, 10d Reduced section, 10e Inner side convex section, 10f Third through hole, 10g Inner side tapered section, 11 Fixing member, 11a First fixing section, 11b Second fixing section, 11c Elastic section, 11d Joint section, 11g Slit, 11h Divided section, 11i Plate-shaped section, 11j First connecting hole, 11k Second connecting hole, 11n Groove, 11o First through hole, 11p Second through hole, 11q First insertion hole, 11r Second insertion hole, 11t Third fixing part, 12, 12a, 12b, 12c Load receiving part, 13 Moving mechanism, 13a Male threaded member, 13b Lock nut, 13c Male threaded part, 13d Eccentric pin, 13e Head, 13f Shaft part, 14 Spacer, 15 Connecting member, 16 Heat insulation sheet, 17 Graphite sheet, 18 Heat insulation layer, 100, 100A, 100B, 100C, 100D, 100E, 100F, 100G, 100H, 100I, 100J, 100K, 100L, 100M, 100N Projectile.

Claims

1. A hollow radome body having a base end located toward the aircraft body in the axial direction and a tip end located opposite the aircraft body in the axial direction, A fixing member is arranged on the inner circumference of the radome body to fix the radome body to the radome ring or the aircraft body, A load-receiving portion, which is integrated with the fixing member or provided separately from the fixing member, receives the load in the machine axis direction acting on the fixing member, Equipped with, The aforementioned fixing member is A first fixing portion that contacts the inner circumferential surface of the radome body and includes an elastic portion that is elastically deformable in the direction perpendicular to the machine axis, which is perpendicular to the machine axis direction, A second fixing portion is provided on the inner circumference of the first fixing portion and has higher rigidity in the direction perpendicular to the machine axis than the first fixing portion, It has, A radome for a projectile, characterized in that, when the direction from the base end to the tip of the radome body is considered forward along the axial direction of the aircraft, and the direction from the tip to the base of the radome body is considered rearward along the axial direction of the aircraft, the inner circumferential surface of the radome body has a tapering portion formed thereon, where the inner circumferential dimension decreases as it approaches the rear.

2. A hollow radome body having a base end located toward the aircraft body in the axial direction and a tip end located opposite the aircraft body in the axial direction, A fixing member is arranged on the inner circumference of the radome body to fix the radome body to the radome ring or the aircraft body, A load-receiving portion, which is integrated with the fixing member or provided separately from the fixing member, receives the load in the machine axis direction acting on the fixing member, Equipped with, The aforementioned fixing member is A first fixing portion that contacts the inner circumferential surface of the radome body and includes an elastic portion that is elastically deformable in the direction perpendicular to the machine axis, which is perpendicular to the machine axis direction, A second fixing portion is provided on the inner circumference of the first fixing portion and has higher rigidity in the direction perpendicular to the machine axis than the first fixing portion, It has, When the direction from the base end to the tip of the radome body along the machine axis is considered the front, and the direction from the tip to the base of the radome body along the machine axis is considered the rear, a tapering portion is formed on the inner circumferential surface of the radome body in which the inner circumferential dimension decreases as it approaches the rear. A radome for a projectile, characterized in that the radome body and the fixing member move relative to each other in the direction of the machine axis, causing the elastic portion to slide along the contraction portion, compressing and deforming, and pressing against the inner circumferential surface of the radome body, thereby fixing the radome body and the fixing member together.

3. The radome for a projectile according to claim 1 or 2, characterized in that the shape of the reduced portion is a tapered shape in which the inner circumference decreases as it approaches the rear.

4. The radome for a projectile according to claim 1 or 2, characterized in that the elastic portion has a slit extending in the axial direction and circumferential direction.

5. The radome for a flying object according to claim 1 or 2, further comprising a moving mechanism for moving the fixing member toward the rear in the axial direction of the machine.

6. The aforementioned moving mechanism is A male screw member provided on the first or second fixing portion, having a male screw portion formed on its outer surface, A lock nut provided on the outer circumferential surface of the male threaded member and coupled to the male threaded portion, It has, The radome for a flying object according to claim 5, characterized in that when the lock nut is tightened, the male screw member and the fixing member move integrally toward the rear in the direction of the machine axis.

7. The radome for a projectile according to claim 1 or 2, further comprising a connecting member for connecting the fixing member and the radome ring.

8. The radome for a projectile according to claim 1 or 2, characterized in that the load-receiving portion is provided separately from the first fixing portion and is in contact with the tip of the first fixing portion that is located furthest forward.

9. The load-receiving portion is integrated with the first fixing portion and is located furthest forward among the first fixing portions, characterized in that it is the radome for a projectile according to claim 1 or 2.

10. The first fixing portion has a first through hole that penetrates in a direction perpendicular to the machine axis. The second fixing portion has a second through hole that penetrates in the direction perpendicular to the machine axis and communicates with the first through hole. The radome for a projectile according to claim 1 or 2, characterized in that the load-receiving portion is a pin inserted through the first through hole and the second through hole.

11. The radome body has a third through-hole formed therein, which penetrates in the direction perpendicular to the machine axis and communicates with the first through-hole. The radome for a projectile according to claim 10, characterized in that the pin is also inserted through the third through hole.

12. The inner circumferential surface of the radome body has an inner circumferential protrusion that projects inward, The radome for a projectile according to claim 1 or 2, characterized in that the inner circumferential protrusion is in contact with the base end of the elastic portion of the first fixing portion that is located furthest rear.

13. The radome for projectiles according to claim 1 or 2, characterized in that the first fixing portion is formed of a material with low thermal conductivity, or a heat insulating sheet made of a material with low thermal conductivity is arranged between the outer circumferential surface of the first fixing portion and the inner circumferential surface of the radome body.

14. A radome for projectiles according to claim 1 or 2, characterized in that a graphite sheet is arranged between the outer circumferential surface of the first fixing part and the inner circumferential surface of the radome body.

15. The radome ring has a housing hole formed therein that penetrates in the direction perpendicular to the machine axis. The first fixing portion has a first insertion hole that penetrates in the direction perpendicular to the machine axis and communicates with the housing hole. The second fixing portion has a second insertion hole that penetrates in the direction perpendicular to the machine axis and communicates with the first insertion hole. The aforementioned moving mechanism is an eccentric pin having a head portion and a shaft portion, The head is positioned within the housing hole. The shaft portion is inserted through the first insertion hole and the second insertion hole, The radome for a flying object according to claim 5, characterized in that when the eccentric pin is rotated, the fixing member moves toward the rear in the direction of the machine axis.

16. The radome for a projectile according to claim 1 or 2, characterized in that the cross-sectional shape of the reduced portion, the cross-sectional shape of the first fixing portion, and the cross-sectional shape of the second fixing portion when cut in the direction perpendicular to the machine axis are non-axisymmetric.

17. The radome for a projectile according to claim 1 or 2, characterized in that the first fixing part and the second fixing part are integrated.

18. The radome for a projectile according to claim 1 or 2, further comprising a heat insulating layer disposed across the outer surface of the radome body and the outer surface of the radome ring.

19. The fixing member further has a third fixing portion that is positioned in the direction of the machine axis with respect to the inner circumferential protrusions, on the opposite side from the first fixing portion, The radome for a projectile according to claim 12, characterized in that the inner circumferential protrusion is sandwiched between the first fixing portion and the third fixing portion in the direction of the machine axis.

20. The radome comprises a hollow radome body having a base end located toward the aircraft body in the axial direction and a tip located opposite the aircraft body in the axial direction; a fixing member disposed on the inner circumference of the radome body to fix the radome body to the radome ring or the aircraft body; and a load-receiving portion, which is integrated with the fixing member or provided separately from the fixing member to receive the axial load acting on the fixing member, wherein the fixing member is in contact with the inner circumferential surface of the radome body and in a direction perpendicular to the axial direction. A method for manufacturing a radome for a projectile, comprising: a first fixing portion including an elastic portion that can be elastically deformed in a direction perpendicular to a certain axis; and a second fixing portion provided on the inner circumference of the first fixing portion and having higher rigidity in the direction perpendicular to the axis than the first fixing portion, wherein when the direction from the base end to the tip of the radome body along the axis of the machine is considered forward, and the direction from the tip to the base end of the radome body along the axis of the machine is considered rearward, a reducing portion is formed on the inner circumferential surface of the radome body in which the inner circumferential dimension decreases as it approaches the rearward. The arrangement step of arranging the fixing member on the inner circumference of the radome body, A fixing step in which the radome body and the fixing member are moved relative to each other in the direction of the machine axis, thereby compressing and deforming the elastic part by sliding it along the contraction part, pressing the inner circumferential surface of the radome body with the elastic part, and fixing the radome body and the fixing member, A method for manufacturing a radome for a projectile, characterized by including the following:

21. The method for manufacturing a radome for a projectile according to claim 20, characterized in that, in the fixing step, the radome body and the fixing member are moved relative to each other in the direction of the machine axis using a jig equipped with a moving mechanism based on one of the following forces: the elastic force of a spring, hydraulic pressure, the fastening force of a bolt, the driving force of a motor, and electromagnetic repulsion.

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