Radome for projectiles

Abstract

To provide a radome for flying objects that can securely fix the radome body and the aircraft without rattling, even under the load applied during flight. [Solution] The radome 1 for a flying object is a radome 1 for a flying object that is positioned at the tip 2a of the aircraft body 2 of a flying object 100, and comprises a radome body 10 having a plurality of recesses 10d on its inner wall surface 10c, and a fixing member 11 that connects the radome body 10 to the aircraft body 2. The fixing member 11 comprises a support member 11C attached to the aircraft body 2, a projection 11c having a contact surface 11o that contacts the recesses 10d, and an elastic member 11d positioned between the support member 11C and the projection 11c and biasing the projection 11c toward the recesses 10d.

Description

Technical Field

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

Background Art

[0002] Conventionally, a projectile that flies by radio wave induction toward a set target is known. The projectile includes a fuselage and a dome for the projectile disposed at the tip of the fuselage. The projectile is equipped with electronic devices such as an antenna for measuring the relative position between the projectile and the target, and the electronic devices are stored in the dome for the projectile. The electronic devices are protected from the heat and external forces during flight by the dome for the projectile.

[0003] Since the projectile flies at supersonic to hypersonic speeds, it is subjected to aerodynamic heating due to friction with the air during flight. In particular, the dome for the projectile is heated up to about 1000°C by aerodynamic heating and also receives a large aerodynamic load during flight. Therefore, the dome for the projectile is required to have high heat resistance and high strength. In addition, since the projectile measures 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 for the projectile, and the dome for the projectile is also required to have radio wave transmissivity that allows the radio waves emitted by the electronic devices to pass through.

[0004] In order to meet the required performance of such a dome for a projectile, the material of the dome for the projectile generally uses ceramics such as alumina, cordierite, fused silica, and silicon nitride sintered body with a linear expansion coefficient of 5×10 -6 / K or less. On the other hand, from the viewpoints of weight reduction and low cost, the material of the fuselage generally uses a metal with a linear expansion coefficient of 10×10 -6 to 30×10 -6 / K such as an aluminum alloy.

[0005] When a radome for a projectile and the aircraft are directly fixed together due to the large difference in their coefficients of thermal expansion, aerodynamic heating during flight generates significant thermal stress at the point of connection, which can cause the radome, which is made of brittle ceramic material, to fracture. Therefore, it is common practice to indirectly connect the radome and the aircraft via a radome ring made of fiber-reinforced plastic or a metal with high rigidity and a relatively low coefficient of thermal expansion, thereby mitigating the thermal stress acting on the radome.

[0006] Traditionally, adhesives are often used to secure the radome and radome ring of a projectile. As the surface temperature of the projectile rises due to aerodynamic heating, the temperature of the adhesive used to secure the radome and radome ring also rises. Since the surface temperature of the projectile is heated to around 1000°C, this exceeds the temperature at which the adhesive can maintain its bonding strength, resulting in a decrease in the fixing strength between the radome and radome ring, and ultimately making it impossible to maintain the fixation between the radome and radome ring.

[0007] To solve these problems, Patent Document 1 discloses a technique for fixing the radome for a projectile to the aircraft by providing an elastic member between the axial end of the radome for the projectile and the axial end of the aircraft, and tightening the radome ring to the aircraft to press the radome for the projectile axially toward the aircraft and compress the elastic member. [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, in the technology disclosed in Patent Document 1, the radome for the projectile is fixed by pressing it axially toward the aircraft, resulting in a structure with play between the radome and the aircraft perpendicular to the axis. As a result, the alignment between the radome and the aircraft perpendicular to the axis shifts due to aerodynamic heating and aerodynamic loads during flight (hereinafter, these may be collectively referred to as "loads"), which may cause errors when measuring the relative position between the projectile and the target using radio waves that pass through the radome.

[0010] This disclosure has been made in view of the above, and aims to provide a radome for a flying object that can fix the radome body and the aircraft body without rattling even under load acting during flight. [Means for solving the problem]

[0011] To solve the above-mentioned problems and achieve the objective, the radome for a projectile according to this disclosure is a radome for a projectile that is disposed at the tip of the airframe of a projectile, and comprises a radome body having a plurality of recesses on its inner wall surface, and a fixing member that connects the radome body to the airframe. The fixing member comprises a support member attached to the airframe, a projection having a contact surface that contacts the recesses, and an elastic member disposed between the support member and the projection and biasing the projection into the recesses. [Effects of the Invention]

[0012] The radome for projectiles described herein has the effect of being able to fix the radome body and the aircraft body without rattling, even under the load acting during flight. [Brief explanation of the drawing]

[0013] [Figure 1] Cross-sectional perspective view showing the tip portion of a projectile equipped with a projectile radome according to Embodiment 1. [Figure 2] A cross-sectional view of a projectile radome according to Embodiment 1, cut along the axial direction, showing a partially enlarged cross-sectional view of the area where the first fixing member is located. [Figure 3] A cross-sectional view of a projectile radome according to Embodiment 1, cut along the axial direction, showing a partially enlarged cross-sectional view of the area where the second fixing member is located. [Figure 4] This is a cross-sectional view of a radome for a projectile according to Embodiment 1, cut along a direction perpendicular to the axis, and is a partially enlarged cross-sectional view of the area where the first fixing member and the second fixing member are arranged in the circumferential direction. [Modes for carrying out the invention]

[0014] A projectile radome according to an embodiment will be described in detail below with reference to the drawings.

[0015] Embodiment 1. Figure 1 is a cross-sectional perspective view showing the tip portion of a projectile 100 equipped with a projectile radome 1 according to Embodiment 1. Figure 2 is a cross-sectional view of the projectile radome 1 according to Embodiment 1 cut along the axial direction, and is a partially enlarged cross-sectional view of the area where the first fixing member 11A is located. Figure 3 is a cross-sectional view of the projectile radome 1 according to Embodiment 1 cut along the axial direction, and is a partially enlarged cross-sectional view of the area where the second fixing member 11B is located. In Figure 1, only one half of the projectile 100 is shown. Hereafter, when describing the direction of each component of the projectile 100, the direction parallel to the central axis C of the radome body 10 described later will be referred to as the axial direction, the direction perpendicular to the central axis C will be referred to as the direction perpendicular to the axis, and the rotational direction about the central axis C will be referred to as the circumferential direction R. The X, Y, and Z axes shown in each figure are three mutually perpendicular axes. The X axis is parallel to the central axis C. The direction along the X axis (X-axis direction) is parallel to the axial direction and is the direction in which the projectile 100 flies. The Y and Z axes are perpendicular to the central axis C. The direction along the Y axis (Y-axis direction) is one direction perpendicular to the axial direction and is included in the direction perpendicular to the axis. The direction along the Z axis (Z-axis direction) is one direction perpendicular to the axial direction and is included in the direction perpendicular to the axis. For each axis, the direction of the arrow is considered positive, and the direction opposite to the arrow is considered negative. In this embodiment, the positive direction of the X axis is considered the front side in the axial direction, and the negative direction of the X axis is considered the rear side in the axial direction. Also, the inside side of the projectile 100 in the direction perpendicular to the axis is considered the inside, and the outside side of the projectile 100 in the direction perpendicular to the axis is considered the outside.

[0016] The projectile 100 shown in Figure 1 flies towards a set target using radio guidance. The projectile 100 comprises a fuselage 2, an antenna 3, and a projectile radome 1. In Figure 1, the antenna 3 is schematically represented by a dashed line.

[0017] The airframe 2 is the main body part of the flying object 100. A dome 1 for the flying object is attached to one end of the airframe 2. The airframe 2 is formed in a cylindrical shape, and a rocket motor or a rocket engine is provided at the other end (not shown). Also, steering wings and fixed wings are attached to the outer periphery of the fuselage of the airframe 2. The tip 2a of the airframe 2 facing the dome 1 for the flying object is open. A metal with high specific strength is used as the material of the airframe 2. Such metals are, for example, aluminum alloy and titanium alloy. The configuration of the airframe 2 is not particularly limited. The airframe 2 may be appropriately selected from known airframes 2.

[0018] The antenna 3 is an electronic device provided inside the dome 1 for the flying object to measure the distance and azimuth to the target.

[0019] The dome 1 for the flying object is a hollow member disposed at the tip 2a of the airframe 2 to protect the antenna 3. The dome 1 for the flying object is disposed so as to close the opening of the airframe 2. The dome 1 for the flying object constitutes the outer shell of the tip portion of the flying object 100.

[0020] The dome 1 for the flying object includes a dome main body 10 and a plurality of fixing members 11.

[0021] The dome main body 10 is formed in a streamlined shape that tapers as it moves away from the airframe 2 along the axial direction. The dome main body 10 is formed in a hollow shape that opens toward the airframe 2. The base end 10a of the dome main body 10 facing the airframe 2 is open. The tip 10b of the dome main body 10 facing away from the airframe 2 is closed. Since the dome main body 10 is required to have resistance to aerodynamic heating and aerodynamic load, it is preferable that ceramics be used as the material of the dome main body 10, but it is not limited thereto.

[0022] The inner wall surface 10c of the radome body 10 is provided with a plurality of recesses 10d that are recessed in the shape of a rotational surface. As shown in Figure 2, the shape of the recesses 10d is a rotational surface in which the diameter decreases from the inside to the outside in the direction perpendicular to the axis. In this specification, a rotational surface means a surface that is formed when a straight line or curved surface is rotated around a predetermined axis. In this embodiment, the shape of the recesses 10d is hemispherical, but it may be a rotational surface other than a hemisphere. For example, the shape of the recesses 10d may be a frustoconical shape. The recesses 10d are formed by partially recessing the inner wall surface 10c of the radome body 10 from the inside to the outside in the direction perpendicular to the axis. A heat-resistant sealant 4 is filled between the base end 10a of the radome body 10 and the tip 2a of the aircraft body 2.

[0023] As shown in Figure 1, the multiple fixing members 11 are positioned inside the radome body 10 and the aircraft body 2, and are capable of fixing the radome body 10 and the aircraft body 2 together. Some of the multiple fixing members 11 are the first fixing members 11A. The remaining part of the multiple fixing members 11 are the second fixing members 11B. The first fixing members 11A and the second fixing members 11B differ only in the inclination direction of the parts to which the projections 11c described later are attached (first mounting part 11h and second mounting part 11j), and other components (materials, dimensions other than the parts to which the projections 11c are attached, etc.) are the same. The differences between the first fixing members 11A and the second fixing members 11B will be explained in detail later. In the example shown in Figure 1, if the remaining half of the projectile 100, which is not shown, is included, there are six first fixing members 11A and six second fixing members 11B, and the number of first fixing members 11A and the number of second fixing members 11B are the same. The number of first fixing members 11A and the number of second fixing members 11B may be more than six, or they may be different numbers.

[0024] As shown in Figure 2, the first fixing member 11A includes a first support member 11a, a projection 11c, an elastic member 11d, and a sheet-like member 11e.

[0025] The first support member 11a is a plate-shaped member that is positioned across the radome body 10 and the aircraft body 2 and can be fixed to the aircraft body 2. The first support member 11a supports the projection 11c and the elastic member 11d, connecting the projection 11c and the elastic member 11d to the aircraft body 2. Since the first support member 11a needs to withstand aerodynamic loads, it is preferable, but not limited to, that high-strength stainless steel, titanium alloy, etc. be used as the material for the first support member 11a. The first support member 11a has a plurality of screw holes 11f into which screws 5 are inserted in the axial central portion and the rear portion. The plurality of screw holes 11f are arranged in a line in the axial direction. The screw holes 11f are through holes that penetrate the first support member 11a in a direction perpendicular to the axis. On the other hand, the aircraft body 2 has a plurality of screw holes 2b into which screws 5 are inserted. The screw holes 2b and the screw holes 11f face each other in a direction perpendicular to the axis. The screw hole 2b is a bottomed hole. The first fixing member 11A and the machine body 2 are fixed to each other by screwing the screw 5 into the screw hole 11f of the first support member 11a and the screw hole 2b of the machine body 2.

[0026] A first mounting portion 11h is formed on the front portion of the first support member 11a, to which a projection 11c and an elastic member 11d are attached. The first mounting portion 11h is inclined in a direction that moves away from the central axis C of the radome body 10 as it approaches the tip 10b (see Figure 1) of the radome body 10 (towards the front in the axial direction). A first mounting hole 11i is formed in the first mounting portion 11h for passing a part of the projection 11c through. The first mounting hole 11i is a through hole that penetrates the first mounting portion 11h in a direction perpendicular to the inclination direction of the first mounting portion 11h. In the example shown in Figure 2, the first mounting portion 11h is inclined in a direction that moves away from the central axis C of the radome body 10 as it approaches the tip 10b of the radome body 10, but the inclination direction of the first mounting portion 11h may be appropriately changed according to the direction of the load applied to the projectile radome 1.

[0027] The projection 11c is the part that is pressed against the inner surface 10e of the recess 10d by the biasing force of the elastic member 11d. Since the projection 11c needs to withstand aerodynamic loads at high temperatures due to aerodynamic heating, it is preferable, but not limited to, that a nickel-based alloy with high high-temperature strength be used as the material for the projection 11c. The projection 11c has a support column 11m and a pad 11n.

[0028] The support column 11m is a portion that is movably attached to the first mounting hole 11i. The support column 11m guides the movement of the pad 11n. That is, as the pad 11n moves between the inner surface 10e of the recess 10d and the first mounting portion 11h due to the expansion and contraction of the elastic member 11d, the support column 11m can guide the movement of the pad 11n by moving along the inner circumferential surface of the first mounting hole 11i. The shape of the support column 11m is cylindrical in this embodiment, but is not limited to this. The tip of the support column 11m protrudes from the first mounting hole 11i toward the inner surface 10e of the recess 10d.

[0029] The pad 11n is a rotating surface-shaped portion provided at the tip of the support column 11m and in contact with the inner surface 10e of the recess 10d. In this embodiment, the pad 11n indirectly contacts the inner surface 10e of the recess 10d via the sheet-like member 11e. The shape of the pad 11n is generally cylindrical with a rotating surface-shaped tip in this embodiment, but is not limited to this. A rotating surface-shaped contact surface 11o is formed at the tip of the pad 11n and contacts the inner surface 10e of the recess 10d. In this embodiment, the contact surface 11o indirectly contacts the inner surface 10e of the recess 10d via the sheet-like member 11e. The shape of the contact surface 11o is a rotating surface-shaped portion whose diameter decreases towards the recess 10d. The shape of the contact surface 11o is hemispherical in this embodiment, but may be a rotating surface-shaped portion other than hemispherical. For example, the shape of the contact surface 11o may be a frustoconical shape. The shape of the contact surface 11o may be appropriately changed to match the shape of the recess 10d. The curvature of the contact surface 11o is equivalent to the curvature of the inner surface 10e of the recess 10d.

[0030] The pad 11n is formed with a larger diameter than the support column 11m. A flange 11p is formed at the boundary portion of the pad 11n with the support column 11m, extending perpendicular to the extension direction of the support column 11m. Due to the biasing force of the elastic member 11d, the rotational surface contact surface 11o of the projection 11c is pressed against the rotational surface inner surface 10e of the recess 10d via the sheet-like member 11e. This fixes the first fixing member 11A and the radome body 10 to each other.

[0031] The elastic member 11d is a member that is stretchably positioned between the first support member 11a and the projection 11c, and biases the projection 11c toward the recess 10d. The elastic member 11d is attached to the outer surface of the support column 11m and is positioned between the first mounting portion 11h and the flange 11p of the pad 11n. In the example shown in Figure 2, the elastic member 11d is a disc spring, but it may be a material other than a disc spring as long as it is possible to press the projection 11c toward the inner surface 10e of the recess 10d. Since the elastic member 11d needs to exhibit elasticity (springiness) at high temperatures due to aerodynamic heating, it is preferable, but not limited to, that the material of the elastic member 11d be a nickel-based alloy.

[0032] The sheet-like member 11e is a thin, plate-like member positioned between the contact surface 11o of the projection 11c and the inner surface 10e of the recess 10d. The sheet-like member 11e is positioned to absorb variations in shape between the contact surface 11o of the projection 11c and the inner surface 10e of the recess 10d, thereby preventing localized stress concentration at the contact surface 11o. The sheet-like member 11e is flexible. Since the sheet-like member 11e needs to withstand high temperatures due to aerodynamic heating, it is preferable to use a material such as graphite that is flexible and has high heat resistance for the sheet-like member 11e, but it is not limited to this as long as it is a flexible and heat-resistant material.

[0033] As shown in Figure 3, the second fixing member 11B includes a second support member 11b, a projection 11c, an elastic member 11d, and a sheet-like member 11e. The second fixing member 11B differs from the first fixing member 11A only in the configuration of the second support member 11b; therefore, only the second support member 11b will be described here, and the descriptions of the projection 11c, the elastic member 11d, and the sheet-like member 11e will be omitted. Hereafter, when the first support member 11a and the second support member 11b are not distinguished, they will each be referred to as support member 11C.

[0034] The second support member 11b is a plate-shaped member that is positioned across the radome body 10 and the aircraft body 2 and can be fixed to the aircraft body 2. The second support member 11b supports the projection 11c and the elastic member 11d, connecting the projection 11c and the elastic member 11d to the aircraft body 2. Since the second support member 11b needs to withstand aerodynamic loads, it is preferable, but not limited to, that high-strength stainless steel or titanium alloy be used as the material for the second support member 11b. Multiple screw holes 11g into which screws 5 are inserted are formed in the axial central portion and the rear portion of the second support member 11b. The multiple screw holes 11g are arranged in a line in the axial direction. The screw holes 11g are through holes that penetrate the second support member 11b in a direction perpendicular to the axis. The screw holes 2b and screw holes 11g of the aircraft body 2 face each other in a direction perpendicular to the axis. The screw holes 2b are bottomed holes. The second fixing member 11B and the aircraft body 2 are fixed together by screwing the screw 5 into the screw hole 11g of the second support member 11b and the screw hole 2b of the aircraft body 2.

[0035] A second mounting portion 11j is formed on the front portion of the second support member 11b, to which a projection 11c and an elastic member 11d are attached. The second mounting portion 11j is inclined in a direction that approaches the central axis C of the radome body 10 as it moves toward the tip 10b (see Figure 1) of the radome body 10 (towards the front in the axial direction). A second mounting hole 11k is formed in the second mounting portion 11j for passing a part of the projection 11c through. The second mounting hole 11k is a through hole that penetrates the second mounting portion 11j in a direction perpendicular to the inclination direction of the second mounting portion 11j. In the example shown in Figure 3, the second mounting portion 11j is inclined in a direction that approaches the central axis C of the radome body 10 as it moves toward the tip 10b of the radome body 10, but the inclination direction of the second mounting portion 11j may be appropriately changed according to the direction of the load applied to the projectile radome 1. Figure 4 is a cross-sectional view of the radome 1 for a projectile according to Embodiment 1, cut along a direction perpendicular to the axis, and is a partially enlarged cross-sectional view of the area where the first fixing member 11A and the second fixing member 11B are arranged side by side in the circumferential direction R. As shown in Figure 4, the first fixing member 11A and the second fixing member 11B are arranged alternately in the circumferential direction R of the radome body 10.

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

[0037] In this embodiment, as shown in Figure 1, the radome 1 for a flying object comprises a radome body 10 having a plurality of recesses 10d on its inner wall surface 10c, and a fixing member 11 that connects the radome body 10 to the aircraft body 2. Furthermore, as shown in Figures 2 and 3, the fixing member 11 comprises a support member 11C attached to the aircraft body 2, a projection 11c having a contact surface 11o that contacts the recesses 10d, and an elastic member 11d positioned between the support member 11C and the projection 11c, which biases the projection 11c toward the recesses 10d. With these configurations, the contact surface 11o of the projection 11c is pressed against the inner surface 10e of the recesses 10d by the biasing force of the elastic member 11d, thereby fixing the fixing member 11 and the radome body 10 toward each other. On the other hand, since the support member 11C is fixed to the aircraft body 2 by screws 5, the fixing member 11 and the aircraft body 2 toward each other. In other words, the radome body 10 and the aircraft body 2 are fixed to each other via the fixing member 11.

[0038] Furthermore, in this embodiment, the inner surface 10e of the recess 10d and the contact surface 11o of the projection 11c are in rotational contact. In particular, in this embodiment, as shown in Figure 4, since multiple fixing members 11 are arranged in the circumferential direction R of the radome body 10, the inner surface 10e of the recess 10d and the contact surface 11o of the projection 11c are in rotational contact at multiple locations in the circumferential direction R of the radome body 10. Therefore, due to the geometrical constraint relationship between the recess 10d and the projection 11c, the radome body 10 is fixed to the fixing members 11 with respect to the projection 11c. This fixing of the radome body 10 due to such a geometrical constraint relationship is maintained as long as the inner surface 10e of the recess 10d and the contact surface 11o of the projection 11c are in contact.

[0039] In this embodiment, as shown in Figures 2 and 3, each fixing member 11 has a sheet-like member 11e positioned between the contact surface 11o of the projection 11c and the inner surface 10e of the recess 10d, and the projection 11c is pressed against the inner surface 10e of the recess 10d via the sheet-like member 11e by the biasing force of the elastic member 11d. With this configuration, the inner surface 10e of the recess 10d and the contact surface 11o of the projection 11c are in rotational contact via the sheet-like member 11e, so that the sheet-like member 11e can absorb variations in shape between the contact surface 11o of the projection 11c and the inner surface 10e of the recess 10d, and can prevent localized stress concentration at the contact surface 11o.

[0040] Here, referring to Figures 2 to 4, the loads applied to the radome 1 for the projectile during flight are broadly classified into heat and force, and the effects of heat and force applied to the radome 1 for the projectile are explained. Note that force is divided into forces generated in the axial direction (X-axis direction) and forces generated in the direction perpendicular to the axis (YZ-plane direction).

[0041] When heat is applied to the projectile radome 1 shown in Figures 2 and 3, causing it to become hot, the radome body 10 expands perpendicular to its axis, and other components (support member 11C, projection 11c, etc.) deform due to differences in their coefficients of linear expansion. At this time, as the radome body 10 expands, the elastic member 11d stretches toward the inner surface 10e of the recess 10d, maintaining contact between the inner surface 10e of the recess 10d and the contact surface 11o of the projection 11c. As a result, the radome body 10 is fixed to the fixing member 11 without any rattling.

[0042] In this embodiment, as shown in Figure 2, some of the multiple fixing members 11 are first fixing members 11A having a first mounting portion 11h to which the projection 11c is attached, and the first mounting portion 11h is inclined in a direction that moves away from the central axis C of the radome body 10 as it approaches the tip 10b of the radome body 10 (see Figure 1). Also, as shown in Figure 3, the remaining part of the multiple fixing members 11 is a second fixing member 11B having a second mounting portion 11j to which the projection 11c is attached, and the second mounting portion 11j is inclined in a direction that moves closer to the central axis C of the radome body 10 as it approaches the tip 10b of the radome body 10 (see Figure 1). With these configurations, when an axial force is applied to the radome 1 for a projectile, if the applied force is directed forward in the axial direction (towards the tip 10b of the radome body 10), a compressive force acts on the elastic member 11d of the first fixing member 11A shown in Figure 2, causing the elastic member 11d to contract and absorb the force. If the applied force is directed backward in the axial direction (towards the base end 10a of the radome body 10), a compressive force acts on the elastic member 11d of the second fixing member 11B shown in Figure 3, causing the elastic member 11d to contract and absorb the force. Furthermore, when an axial force is applied to the radome 1 for a projectile, among the multiple elastic members 11d, the elastic member 11d on which a tensile force acts according to the direction of the force (direction of the load) extends toward the inner surface 10e of the recess 10d. Specifically, if the applied force is directed forward in the axial direction, a tensile force acts on the elastic member 11d of the second fixing member 11B shown in Figure 3, causing the elastic member 11d to stretch. If the applied force is directed backward in the axial direction, a tensile force acts on the elastic member 11d of the first fixing member 11A shown in Figure 2, causing the elastic member 11d to stretch. This maintains the contact between the inner surface 10e of the recess 10d and the contact surface 11o of the projection 11c. As a result, the radome body 10 is fixed to the fixing member 11 without any rattling.

[0043] Furthermore, when a force perpendicular to the axis is applied to the radome 1 for the projectile shown in Figure 4, among the multiple elastic members 11d arranged in the circumferential direction R, the elastic member 11d that experiences compressive force in accordance with the direction of the force contracts to absorb the force. In addition, when a force perpendicular to the axis is applied to the radome 1 for the projectile during flight, among the multiple elastic members 11d, the elastic member 11d that experiences tensile force in accordance with the direction of the force extends toward the inner surface 10e of the recess 10d. As a result, the contact state between the inner surface 10e of the recess 10d and the contact surface 11o of the projection 11c is maintained. Therefore, the radome body 10 is fixed to the fixing member 11 without rattling.

[0044] When the combined heat and force load described above is applied to the radome 1 for the projectile shown in Figures 2 and 3, the expansion and contraction movements of each elastic member 11d occur in a combined manner, so that the radome body 10 is fixed to the fixing member 11 without rattling. In other words, in this embodiment, even if deformation of the radome body 10 occurs due to high temperature, the expansion of each elastic member 11d allows the radome body 10 and the fixing member 11 to be fixed without rattling, and the expansion and contraction of the elastic members 11d also allows the radome body 10 and the fixing member 11 to be fixed without rattling in response to forces in all directions. On the other hand, the fixing member 11 and the aircraft body 2 are fixed without rattling by screws 5. Therefore, the radome body 10 and the aircraft body 2 can be fixed without rattling via the fixing member 11.

[0045] Next, a modified example of this embodiment will be described.

[0046] In the above embodiment, as shown in Figures 2 and 3, a sheet-like member 11e is placed between the contact surface 11o of the projection 11c and the inner surface 10e of the recess 10d, but the sheet-like member 11e may be omitted. In this configuration, the pad 11n directly contacts the inner surface 10e of the recess 10d. That is, the contact surface 11o directly contacts the inner surface 10e of the recess 10d.

[0047] In the above embodiment, as shown in Figures 2 and 3, a first fixing member 11A and a second fixing member 11B are provided, each having a different inclination direction for the portion to which the projection 11c is attached. However, it is also possible to provide only one fixing member 11, each having the same inclination direction for the portion to which the projection 11c is attached.

[0048] In the above embodiment, as shown in Figure 4, the first fixing member 11A and the second fixing member 11B are arranged alternately in the circumferential direction of the radome body 10, but they do not necessarily have to be arranged alternately in the circumferential direction of the radome body 10.

[0049] The configurations shown in the above embodiments are merely examples, and can be combined with other known technologies. It is also possible to omit or modify parts of the configuration without departing from the gist of the invention.

[0050] The various aspects of this disclosure are summarized below as an appendix.

[0051] (Note 1) A radome for a projectile, which is positioned at the tip of the aircraft's fuselage. The radome body has multiple recesses on its inner wall surface, A fixing member for connecting the radome body to the aircraft, Equipped with, The aforementioned fixing member is A support member attached to the aforementioned aircraft, A projection having a contact surface that contacts the recess, An elastic member is disposed between the support member and the projection, and biases the projection towards the recess. A radome for a projectile, characterized by having the following features. (Note 2) A radome for a projectile, which is positioned at the tip of the aircraft's fuselage. A radome body formed in a hollow shape that opens toward the aircraft, with multiple recesses provided on its inner wall surface that are recessed in a rotational plane shape, A plurality of fixing members are arranged inside the radome body and the aircraft body, and are capable of fixing the radome body and the aircraft body together. Equipped with, Each of the aforementioned fixing members is A support member is positioned across the radome body and the aircraft body and is fixable to the aircraft body, A projection including a rotating surface that contacts the inner surface of the recess, An elastic member is positioned between the support member and the projection so as to be expandable and contractible, and biases the projection toward the recess. It has, The radome for a projectile is characterized in that the projection is pressed against the inner surface of the recess by the biasing force of the elastic member. (Note 3) The shape of the aforementioned depression is hemispherical. The radome for projectiles according to Appendix 1 or 2, characterized in that the shape of the contact surface is hemispherical. (Note 4) Each of the aforementioned fixing members is The sheet-like member is disposed between the contact surface of the projection and the inner surface of the recess, The radome for a projectile according to any one of the appendices 1 to 3, characterized in that the projection is pressed against the inner surface of the recess via the sheet-like member by the biasing force of the elastic member. (Note 5) Some of the multiple fixing members are first fixing members having a first mounting portion to which the projection is attached, The remaining portion of the plurality of fixing members is a second fixing member having a second mounting portion to which the projection is attached, The first mounting portion is inclined in a direction that moves away from the central axis of the radome body as it approaches the tip of the radome body, The radome for projectiles according to any one of the appendices 1 to 4, characterized in that the second mounting portion is inclined in a direction that approaches the central axis of the radome body as it moves toward the tip of the radome body. (Note 6) The radome for projectiles according to Appendix 5, characterized in that the first fixing member and the second fixing member are alternately arranged in the circumferential direction of the radome body. [Explanation of symbols]

[0052] 1 Radome for projectile, 2 Aircraft body, 2a, 10b Tip, 2b Screw hole, 3 Antenna, 4 Sealant, 5 Screw, 10 Radome body, 10a Base, 10c Inner wall surface, 10d Recess, 10e Inner surface, 11 Fixing member, 11A First fixing member, 11B Second fixing member, 11C Support member, 11a First support member, 11b Second support member, 11c Projection, 11d Elastic member, 11e Sheet-like member, 11f, 11g Screw hole, 11h First mounting part, 11i First mounting hole, 11j Second mounting part, 11k Second mounting hole, 11m Support column, 11n Pad, 11o Contact surface, 11p Flange, 100 Projectile.

Claims

1. A radome for a projectile, which is positioned at the tip of the aircraft's fuselage. The radome body has multiple recesses on its inner wall surface, A fixing member for connecting the radome body to the aircraft, Equipped with, The aforementioned fixing member is A support member attached to the aforementioned aircraft, A projection having a contact surface that contacts the recess, An elastic member is disposed between the support member and the projection, and biases the projection towards the recess. A radome for a projectile, characterized by having the following features.

2. A radome for a projectile, which is positioned at the tip of the aircraft's fuselage. A radome body formed in a hollow shape that opens toward the aircraft, with multiple recesses provided on its inner wall surface that are recessed in a rotational plane shape, A plurality of fixing members are arranged inside the radome body and the aircraft body, and are capable of fixing the radome body and the aircraft body together. Equipped with, Each of the aforementioned fixing members is A support member is positioned across the radome body and the aircraft body and is fixable to the aircraft body, A projection including a rotating surface that contacts the inner surface of the recess, An elastic member is provided which the support member and the projection are arranged to be expandable and contractible, and which biases the projection toward the recess. It has, The radome for a projectile is characterized in that the projection is pressed against the inner surface of the recess by the biasing force of the elastic member.

3. The shape of the aforementioned depression is hemispherical, The radome for a projectile according to claim 1 or 2, characterized in that the shape of the contact surface is hemispherical.

4. Each of the aforementioned fixing members is The sheet-like member is disposed between the contact surface of the projection and the inner surface of the recess, The radome for a projectile according to claim 1 or 2, characterized in that the projection is pressed against the inner surface of the recess via the sheet-like member by the biasing force of the elastic member.

5. Some of the multiple fixing members are first fixing members having a first mounting portion to which the projection is attached, The remaining portion of the plurality of fixing members is a second fixing member having a second mounting portion to which the projection is attached, The first mounting portion is inclined in a direction that moves away from the central axis of the radome body as it approaches the tip of the radome body. The radome for a projectile according to claim 1 or 2, characterized in that the second mounting portion is inclined in a direction that approaches the central axis of the radome body as it moves toward the tip of the radome body.

6. The radome for a projectile according to claim 5, characterized in that the first fixing member and the second fixing member are alternately arranged in the circumferential direction of the radome body.

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