JP2019120442A - Flying object - Google Patents

Abstract

To provide a flying object which prevents a radome for the flying object from being separated from a flying object body.SOLUTION: A flying object 100 of the present invention comprises: a cylindrical flying object body 1; a fixing member 6 which is a columnar first coupling member fixed on a distal end side of the flying object body 1 and extending outside in the radial direction from the flying object body 1; a coupling member 8 which is a columnar second coupling member provided at the fixing member 6 and extending outside in the radial direction from the fixing member 6; and a radome 2 for the flying object which has an insertion hole 21a into which the coupling member 8 is inserted formed thereon and is coupled to the distal end side of the flying object body 1 via the coupling member 8 and the fixing member 6. The flying object has a gap G2 formed between an inner peripheral surface of the radome 2 for the flying object and a radial outer surface of the fixing member 6.SELECTED DRAWING: Figure 2

Description

  The present invention relates to a flying body provided with a cylindrical flying body that flies by electromagnetic induction toward a target, and a flying radome provided at the tip of the flying body.

The conventional flying body disclosed in Patent Document 1 includes a flying body that flies by electromagnetic induction toward a target, an antenna provided at the tip of the flying body and a target for detecting the target, and a fly. A flying radome is provided at the tip of the body to protect the antenna. Many flying vehicles reach supersonic velocity or hypersonic velocity in a short time of a few seconds from the start of flight, and are subjected to aerodynamic heating to expose the vehicle to high temperatures. Aerodynamic heating is a phenomenon in which the atmosphere flows at high speed on the surface of the projectile, friction is generated between the surface of the projectile and the atmosphere, and the atmosphere and the projectile are heated by frictional heat. . The flying body radome provided at the tip of the flying body is one of the parts where the thermal environment is severe among the parts of the flying body, and receives large aerodynamic load, aerodynamic heating and thermal shock. Thermal shock is a phenomenon in which an object is subjected to an impulsive thermal stress due to a drastic temperature change. Therefore, high strength, heat resistance, and thermal shock resistance are required of the flying radome. Moreover, since it is necessary to transmit radio waves transmitted and received by the antenna, the flying radome is required to have radio wave transparency for the flying radome. In order to satisfy the above requirements, generally used as the material of the radome for the flying object is a ceramic which is a dielectric material having a heat resistance temperature of 1000 ° C. or more and a thermal expansion coefficient of 5 × 10 ⁻⁶ / ° C. or less Be done.

On the other hand, iron, aluminum or the like which is a high rigidity material having a thermal expansion coefficient in the range of 10 × 10 ⁻⁶ / ° C. to 30 × 10 ⁻⁶ / ° C. is used for the flight body main body. As described above, since there is a large difference in thermal expansion coefficient between the flying radome and the flying main body, if the two are directly joined, the large amount of heat is generated at the junction due to aerodynamic heating at the time of flight. Stress is generated and cracks or cracks occur in the flying radome. For this reason, in the conventional projectiles, the projectile radome can be transported through a ring made of fiber reinforced plastic (FRP) which has a relatively low thermal expansion coefficient but a high rigidity. It is fixed to the body. And, an adhesive is used to attach the flying body radome to the ring.

Japanese Patent Application Laid-Open No. 11-37699

  In the conventional projectiles, when the total amount of aerodynamic heating increases as the flight speed increases and the flight time of the projectiles increases, the temperature of the adhesive exceeds the heat resistance temperature, and the flight to the ring occurs. There is a risk that the adhesive strength of the radome for bones may decrease. In addition, when a material with high thermal conductivity is used as the material of the radome for the flying object to ease the thermal shock of the radome for the flying object, heat is easily transmitted from the flying object radome to the adhesive. The temperature of the adhesive becomes high, the temperature of the adhesive exceeds the heat resistance temperature, and the adhesive strength may be reduced. Therefore, in the case of the conventional flying object, there is a problem that the adhesion strength is lowered and the flying object radome may be detached from the flying object body. Moreover, although it is known that adhesive strength falls with age deterioration of an adhesive agent, it is difficult to estimate quantitatively the fall rate of adhesive strength. Therefore, in the case of a conventional flying object, it is necessary to allow for an initial bonding strength so that the flying object radome does not come off the ring even if the adhesive strength decreases due to the aging of the adhesive. .

  The present invention has been made in view of the above, and it is an object of the present invention to obtain a flying body that can prevent the flying body radome from being detached from the flying body main body.

  In order to solve the above-mentioned problems and achieve the object, the flying body according to the present invention has a cylindrical flying body that flies by electromagnetic induction toward the target and a tip side of the flying body. And a pillar-shaped first connecting member fixed and extending radially outward of the flight main body. The projectile is provided on the first connection member, and a columnar second connection member extending radially outward from the first connection member and an insertion hole into which the second connection member is inserted are formed. A flying radome is connected to the front end side of the flight vehicle main body via the second connecting member and the first connecting member. A gap is formed between the inner peripheral surface of the flying object radome and the radial outer surface of the first connecting member.

  The flying body according to the present invention has the effect of being able to prevent the flying body radome from being detached from the body of the flying body.

An appearance view of a flying object according to Embodiment 1 of the present invention Sectional drawing which expanded the connection part of the flight vehicle main body and the flying radome shown in FIG. The figure which shows the state which embedded the connection member in the fixing member shown in FIG. The figure which shows the state which inserts the connection member shown in FIG. 3 in the insertion hole of the radome side coupling | bond part shown in FIG. The figure which shows the state which assemble | attaches the fixing member and the radome for flying bodies shown in FIG. 4 to the flying body main body shown in FIG. The figure which shows the state which fixes the fixing member assembled | attached to the flight body main body shown in FIG. 5 to a flight body main body using a flathead screw. The figure which shows a state which attaches an embedding member and a 2nd heat insulation part to the radome side coupling part shown in FIG. 6, and attaches a 1st heat insulation part to the 1st cylindrical part shown in FIG. The figure for demonstrating the variation | change_quantity of each radius of the radome side coupling | bond part shown in FIG. 2, and a 1st cylindrical part A partially enlarged view of a flying object according to a second embodiment of the present invention Sectional drawing which expanded the connection part of the radome for flight bodies of the flight object concerning Embodiment 3 of this invention, and a flight body main part FIG. 11 is a view of the fixing member shown in FIG. Cross-sectional view of a flying object according to a first modification of the third embodiment Cross-sectional view of a flying object according to a second modification of the third embodiment Sectional drawing which expanded the connection part of the radome for flight bodies of the flight object concerning Embodiment 4 of this invention, and a flight body main part.

  Hereinafter, a flying object according to an embodiment of the present invention will be described in detail based on the drawings. The present invention is not limited by the embodiment.

Embodiment 1
FIG. 1 is an external view of a flying object according to Embodiment 1 of the present invention. FIG. 2 is an enlarged cross-sectional view of the connecting portion between the body of the flying object and the radome for flying object shown in FIG. In FIG. 1 and FIG. 2, the direction shown by the arrow D1 represents the axial direction which is the direction in which the central axis AX of the flying object 100 extends, the direction shown by the arrow D2 represents the radial direction of the flying object 100, the arrow The direction indicated by D3 represents the circumferential direction of the central axis AX. Hereinafter, the axial direction D1 is simply referred to as “axial direction”, the radial direction D2 is simply referred to as “radial direction”, and the circumferential direction D3 is simply referred to as “circumferential direction”.

  In FIG. 1, the left end of each configuration is a front end, and the right end of each configuration is a rear end. Also, the flight direction of the flying object 100 is equal to the direction from the right to the left in FIG. 1. The flying object 100 includes a cylindrical flying object body 1, a flying object radome 2 provided at the tip of the object body 1, and a first provided at the outer periphery of the flying object body 1 near the tip. And a second heat insulating portion 4 provided on the outer peripheral portion near the rear end of the radome 2 for a flying object, and an electronic device 5 provided inside the flying object 100. The flying object 100 measures the distance and direction to the target by radio waves transmitted and received by the electronic device 5, and flies toward the target by radio wave induction. The electronic device 5 is an antenna for measuring the distance and the direction to the target.

Since the flying radome 2 is a portion susceptible to aerodynamic load and aerodynamic heating that occurs when the flying object 100 flies at high speed, the tip portion is made to be able to fly at high speed with reduced aerodynamic resistance. It has a sharp streamlined shape, and its outer diameter smoothly spreads from the front end to the rear end, and the rear end is open and hollow. The flying radome 2 is required to have high strength, heat resistance, and thermal shock resistance, as well as radio wave transmission. Therefore, a ceramic having a thermal expansion coefficient of 5 × 10 ⁻⁶ / ° C. or less is used as the material of the radome 2 for a flying object. Examples of ceramics include ceramic sintered bodies such as alumina (Al ₂ O ₃ ), cordierite (2MgO · 2Al ₂ O · 5SiO ₂ ), fused silica (SiO ₂ ), silicon nitride (Si ₃ N ₄ ), etc. it can.

As a material of the flying object body 1, iron, aluminum or the like which is a high rigidity material having a thermal expansion coefficient in the range of 10 × 10 ⁻⁶ / ° C. to 30 × 10 ⁻⁶ / ° C. is used.

  As shown in FIG. 2, the flying object body 1 is provided at an axially extending cylindrical casing 10 and at an axial end of the casing 10 to couple the flying object radome 2 to the casing 10 And a body-side coupling portion 11 for The housing 10 and the main body side joint portion 11 may be manufactured by die-cast integrally using materials such as iron and aluminum, or may be combined with each other after being separately manufactured.

  The main body side coupling portion 11 includes a first cylindrical portion 11a, a projecting portion 11b, a second cylindrical portion 11c, and a device installation portion 11d.

  The first cylindrical portion 11 a axially extends from the end on the tip end side of the housing 10 toward the flying object radome 2, and the outer diameter is smaller than the outer diameter of the housing 10 and is coaxial with the housing 10 It is a cylindrical member provided in The axial front end of the first cylindrical portion 11 a faces the axial rear end of the flying object radome 2. Details of the configuration of the flying object radome 2 will be described later.

  The 1st heat insulation part 3 is provided in the radial direction outer side of the 1st cylindrical part 11a. As a material of the first heat insulating portion 3, a silicone resin having a high heat resistance temperature and excellent heat insulating properties is used. The material of the first heat insulating portion 3 may be a material whose thermal conductivity is lower than the thermal conductivity of the first cylindrical portion 11a, and is not limited to silicone resin. The first heat insulating portion 3 is annularly continuously provided in the circumferential direction on the outer peripheral surface of the first cylindrical portion 11 a. The first heat insulating portion 3 may be one in which the stretchable annular heat insulating member is stretched in the radial direction and assembled to the first cylindrical portion 11a, or the belt-shaped heat insulating member is the one of the first cylindrical portion 11a. It may be annularly wound continuously around the periphery. The axial length of the first heat insulating portion 3 is equal to the axial length of the first cylindrical portion 11a. The axial length of the first cylindrical portion 11a is the width from the connecting portion between the first cylindrical portion 11a and the housing 10 to the end portion of the first cylindrical portion 11a on the side of the radome 2 for the flying object. be equivalent to. The outer peripheral surface of the first heat insulating portion 3 is located on a virtual surface in which the outer peripheral surface of the housing 10 is extended to the first cylindrical portion 11 a in the axial direction.

  The overhanging portion 11 b is an annular plate-shaped member that extends radially inward from a portion near the tip of the inner circumferential surface of the first cylindrical portion 11 a and is provided coaxially with the housing 10.

  The second cylindrical portion 11c axially extends from the portion near the inner peripheral surface of the overhang portion 11b toward the flying object radome 2, and the outer diameter OD1 is smaller than the inner diameter ID1 of the flying object radome 2, It is a cylindrical member provided coaxially with the housing 10. In the second cylindrical portion 11c, a through hole 11c1 penetrating from the outer peripheral surface of the second cylindrical portion 11c toward the inner peripheral surface of the second cylindrical portion 11c and extending in the radial direction is formed. Three or more through holes 11c1 are formed apart from each other in the circumferential direction. Each of the plurality of through holes 11c1 has the same axial position. The separation widths of the through holes 11c1 adjacent in the circumferential direction are equal to each other. In addition, "equal" described here not only represents a strictly equal state, but also includes a range taking into consideration manufacturing tolerances of the respective parts constituting the flying object 100, assembly variations of the respective parts, and the like. It shall be

  The device mounting portion 11 d is a disk-shaped member provided on a portion near the tip of the inner peripheral surface of the second cylindrical portion 11 c. The electronic device 5 is fixed to the end face of the device installation section 11 d on the side of the flying object radome 2.

  The fixing member 6, which is a first connecting member, is provided on the radially outer side of the second cylindrical portion 11c. The fixing member 6 is a radially extending cylindrical or polygonal cylindrical member. The fixing member 6 may be manufactured by die-casting integrally using the same material as the flying object radome 2 or the flying object body 1, or the flying object radome 2 or the flight object body 1 It may be manufactured by cutting a block-like block formed of the same material.

  The radially inner surface of the fixing member 6 is in contact with the outer peripheral surface of the second cylindrical portion 11c. The radially inner surface of the fixing member 6 has a cross section orthogonal to the axial direction curved in an arc shape contacting the outer peripheral surface of the second cylindrical portion 11c.

  The fixing members 6 are provided three or more apart from each other in the circumferential direction on the outer peripheral surface of the second cylindrical portion 11c. Each of the plurality of fixing members 6 has the same axial position. The separation widths of the fixing members 6 adjacent in the circumferential direction are equal to each other. In addition, "equal" described here not only represents a strictly equal state, but also includes a range taking into consideration manufacturing tolerances of the respective parts constituting the flying object 100, assembly variations of the respective parts, and the like. It shall be

  The radial width of the fixing member 6 is the radial width of the gap G1 formed between the outer peripheral surface of the second cylindrical portion 11c and the inner peripheral surface of the radome-side joint portion 21 of the radome 2 for a flying object. It is narrower than. Therefore, a gap G2 is formed between the radially outer surface of the fixing member 6 and the inner circumferential surface of the radome-side coupling portion 21 of the flying object radome 2.

  The fixing member 6 is formed with a through hole 6 a which penetrates from the radial outer surface of the fixing member 6 toward the radial inner surface of the fixing member 6 and extends in the radial direction. The through hole 6a communicates with the through hole 11c1 formed in the second cylindrical portion 11c. In the through hole 6a, a counterbore portion 6a1 is formed in accordance with the shape of the conical head 7a of the flat screw 7. The male screw portion 7 b which is the tip of the flat head screw 7 passes through the through hole 6 a of the fixing member 6 and is screwed into the through hole 11 c 1 of the second cylindrical portion 11 c. By providing the counterbore portion 6a1, the inclined surface of the head portion 7a of the flat screw 7 contacts the inner peripheral surface of the fixing member 6 forming the through hole 6a. The contact area between the fixing member 6 and the countersunk screw 7 is increased and the frictional force generated between the fixing member 6 and the countersunk screw 7 is increased as compared to the case where a screw other than the countersunk screw 7 is used. The looseness of 7 is suppressed, and the fixation of the fixing member 6 to the second cylindrical portion 11c can be maintained. Although the countersunk screw 7 is used in the first embodiment, any screw other than the countersunk screw 7 may be used as long as the fixing member 6 can be fixed to the second cylindrical portion 11c.

  One end of two cylindrical connection members 8 is connected to a radially outer portion of the fixing member 6. The shape of the connecting member 8 is not limited to a cylinder, and may be a square pole as long as it can be inserted into the insertion hole 21a. The cross-sectional area of the cross section orthogonal to the radial direction of the connecting member 8 which is the second connecting member is smaller than the cross-sectional area of the cross section orthogonal to the radial direction of the fixing member 6. The two connecting members 8 are axially separated from each other so as to sandwich the through hole 6 a of the fixing member 6. The connecting member 8 may be manufactured by die casting using the same material as the fixing member 6 by die casting, or a block shape formed of the same material as the flying object radome 2 or the flying object body 1 It may be manufactured by cutting a lump of In the first embodiment, an example in which the connecting member 8 and the fixing member 6 are separately manufactured and then combined with each other is described.

  The flying body radome 2 which covers the periphery of the electronic device 5 and is provided so as to face the end face in the axial direction of the first cylindrical portion 11 a includes the conical first radome 20 and the radome side joint portion 21. Prepare. The first radome 20 and the radome side joint part 21 may be manufactured by integral molding, or may be combined with each other after being separately manufactured.

  The radome-side joint portion 21 extends in the axial direction from the rear end of the first radome 20 toward the flight body 1, and the outer diameter is smaller than the outer diameter of the first radome 20. And a cylindrical member provided coaxially with the

  A second heat insulating portion 4 is provided on the radial outside of the radome side coupling portion 21. As a material of the second heat insulating portion 4, a silicone resin having a high heat resistance temperature and an excellent heat insulating property is used. The material of the second heat insulating portion 4 may be a material whose thermal conductivity is lower than the thermal conductivity of the radome side joint portion 21 and is not limited to the silicone resin. The second heat insulating portion 4 is annularly continuously provided in the circumferential direction on the outer peripheral surface of the radome side coupling portion 21. The second heat insulating portion 4 may be one in which the stretchable annular heat insulating member is radially extended and assembled to the radome side joint portion 21, or a belt-like heat insulating member is provided around the radome side joint portion 21. It may be continuously wound in a ring. The axial length of the second heat insulating portion 4 is equal to the axial length of the radome side coupling portion 21. The axial length of the radome-side joint 21 is equal to the width from the connection between the first radome 20 and the radome-side joint 21 to the end of the radome-side joint 21 on the side of the flying object body 1. . The outer peripheral surface of the second heat insulating portion 4 is located on a virtual surface in which the outer peripheral surface of the first radome 20 is extended in the axial direction to the radome side coupling portion 21.

  In the radome side joint portion 21, two insertion holes 21a which penetrate from the outer peripheral surface of the radome side joint portion 21 toward the inner peripheral surface of the radome side joint portion 21 and extend in the radial direction are formed. Further, an insertion hole 21b is formed in the radome side joint portion 21 so as to penetrate from the outer peripheral surface of the radome side joint portion 21 toward the inner peripheral surface of the radome side joint portion 21 and extend in the radial direction.

  The two insertion holes 21 a are holes for inserting the other end side of the connection member 8 into the radome side coupling portion 21. The diameter of the insertion hole 21 a is set to be equal to the diameter of the connecting member 8 or slightly larger than the diameter of the connecting member 8. A slightly larger value is a value at which the connecting member 8 can be inserted into the insertion hole 21a and no play is generated in the axial direction or circumferential direction between the radome side joint portion 21 and the fixing member 6 . By setting the diameter of the insertion hole 21 a to such a value, the gap between the connecting member 8 and the inner peripheral surface of the insertion hole 21 a is reduced, and between the radome side coupling portion 21 and the fixing member 6, It is possible to prevent play in the axial or circumferential direction.

  The two insertion holes 21a are formed apart from each other in the axial direction so as to sandwich the insertion hole 21b. A plurality of sets of the two insertion holes 21a are formed at positions respectively corresponding to the plurality of fixing members 6 arranged in the circumferential direction, being separated from each other in the circumferential direction.

  The insertion hole 21 b is a hole for inserting the countersunk screw 7 from the outside of the flying radome 2 toward the second cylindrical portion 11 c. The insertion hole 21 b communicates with the through hole 6 a formed in the fixing member 6 and further communicates with the through hole 11 c 1 formed in the second cylindrical portion 11 c. A plurality of insertion holes 21 b are formed in the circumferential direction at positions corresponding to the plurality of fixing members 6 arranged in the circumferential direction, respectively. In the insertion hole 21b of the radome side joint portion 21 and the counterbore portion 6a1 of the through hole 6a, a hole filling member 9 made of silicone resin is inserted. The filling member 9 is a cylindrical member extending in the radial direction. The outer diameter of the filling member 9 before being inserted into the insertion hole 21b and the counterbore 6a1 is set to a value slightly larger than the inner diameter of the insertion hole 21b and slightly larger than the maximum inner diameter of the counterbore 6a1. Be done. The slightly larger value is a dimension that allows the hole filling member 9 to be inserted into the insertion hole 21b and the counterbore portion 6a1. The hole filling member 9 may be formed by curing a silicone resin filled in the insertion hole 21b and the counterbore portion 6a1 of the through hole 6a.

  The surface of the hole filling member 9 on the flat screw 7 side is in contact with the flat screw 7. Therefore, even if the countersunk screw 7 fastened to the fixing member 6 is slightly loosened by the vibration of the flying object 100, the countersunk screw 7 to the radially outer side is limited. Accordingly, the fixing of the fixing member 6 to the second cylindrical portion 11c can be maintained.

  Further, the radially outer end surface of the filling member 9 is located on a virtual surface in which the outer peripheral surface of the radome side coupling portion 21 is extended in the axial direction to the insertion hole 21 b. The radially outer end surface of the hole filling member 9 is in contact with the inner circumferential surface of the second heat insulating portion 4. Thereby, compared with the case where the radial outer end face of the hole filling member 9 is not in contact with the inner peripheral surface of the second heat insulating portion 4, the gap between the hole filling member 9 and the second heat insulating portion 4 is It can be made smaller. As a result, the heat transmitted from the outer peripheral surface of the radome side joint portion 21 to the inner peripheral surface is dispersed to the connecting member 8 and the embedding member 9, so the heat from the radome side joint portion 21 is transmitted only to the connecting member 8 As compared with the case, the local thermal expansion of the fixing member 6 is suppressed. Therefore, while progress of the aged deterioration of the fixing member 6 can be suppressed, the raise of the thermal stress which arises in the contact part of the connection member 8 and the insertion hole 21a can be suppressed.

  Next, the assembly procedure of the flying object 100 will be described using FIGS. 3 to 7. FIG. 3 is a view showing the connecting member embedded in the fixing member shown in FIG. FIG. 4 is a view showing a state in which the connecting member shown in FIG. 3 is inserted into the insertion hole of the radome side joint portion shown in FIG. FIG. 5 is a view showing a state where the fixing member and the flying radome shown in FIG. 4 are assembled to the flying body shown in FIG. FIG. 6 is a view showing a fixing member assembled to the body shown in FIG. 5 in a state of being fixed to the body using a countersunk screw. FIG. 7 is a view showing a state in which the hole filling member and the second heat insulating portion are attached to the radome side joint portion shown in FIG. 6 and the first heat insulating portion is attached to the first cylindrical portion shown in FIG.

  When assembling the flying object 100, first, one end side of each of two connection members 8 is embedded in the fixing member 6 as shown in FIG. Three fixing members 6 in which two connecting members 8 are embedded are manufactured. Next, the other end side of the connection member 8 embedded in the fixing member 6 is inserted into each of the two insertion holes 21 a formed in the radome side coupling portion 21 as shown in FIG. 4. This operation is performed on each of the two sets of insertion holes 21a arranged in the circumferential direction. After the connecting member 8 is inserted into the insertion hole 21a, as shown in FIG. 5, the fixing member 6 is brought close to the second cylindrical portion 11c, and the flying object radome 2 is fitted to the flying object body 1. In addition, since the gap G2 is formed between the fixing member 6 and the radome side coupling portion 21, when fitting the fixing member 6 to the second cylindrical portion 11c, the fixing member 6 moves in the radial direction by the gap G2. It is possible. Therefore, the fixing member 6 can be easily fitted into the radome side coupling portion 21.

  After the radome 2 for a flying object is fitted to the flying object body 1, a countersunk screw 7 is inserted into the insertion hole 21b of the redome-side joint 21 and the through hole 6a of the fixing member 6, as shown in FIG. The countersunk screw 7 is screwed into the through hole 11c1 of the second cylindrical portion 11c. Thereby, the fixing member 6 is fixed to the flying object body 1, and the flying object radome 2 can be moved in the radial direction via the connecting member 8, the fixing member 6, and the flat screw 7 It is connected to the main body 1. At this time, movement of the flying object radome 2 other than in the radial direction is restricted. As described above, the diameter of the insertion hole 21 a is set to be equal to the diameter of the connecting member 8 or slightly larger than the diameter of the connecting member 8.

  After the fixing member 6 is fixed to the flying object body 1, as shown in FIG. 7, the hole filling member 9 is embedded in the insertion hole 21b. After that, the second heat insulating portion 4 is fixed to the outer peripheral surface of the radome side joint portion 21 with a silicone adhesive or the like, and the first heat insulating portion 3 is fixed to the outer peripheral surface of the first cylindrical portion 11a with a silicone adhesive or the like. It is fixed. The fixation of the first heat insulating portion 3 to the first cylindrical portion 11 a may be performed before the flying object radome 2 is fitted to the flying object body 1.

  Next, the effects of the flying object 100 according to the first embodiment will be described. FIG. 8 is a view for explaining the variation of the radius of each of the radome side joint portion and the first cylindrical portion shown in FIG.

  The direction of the arrow indicated by reference numeral 103 indicates the direction in which the radome-side joint 21 spreads when the flying object 100 flies. The direction in which the radome-side joint 21 extends is equal to the radial direction of the radome-side joint 21. The length of the arrow indicated by reference numeral 103 is the difference between the radius r1 of the radome-side joint 21 before spreading in the radial direction and the radius r1 of the radome-side joint 21 spreading in the radial direction when the flying object 100 flies. The dimensions corresponding to are roughly represented. The radius r1 of the radome-side joint 21 is equal to the distance from the central axis AX to the inner circumferential surface of the radome-side joint 21. Below, the dimension equivalent to the said difference is called "the variation | change_quantity of the radius of the radome side coupling part 21."

  The direction of the arrow indicated by reference numeral 104 indicates the direction in which the second cylindrical portion 11 c spreads when the flying object 100 flies. The direction in which the second cylindrical portion 11c extends is equal to the radial direction of the second cylindrical portion 11c. The length of the arrow indicated by reference numeral 104 is the radius r2 of the second cylindrical portion 11c before it spreads in the radial direction, and the radius r2 of the second cylindrical portion 11c spreads in the radial direction when the flying object 100 flies. The dimensions corresponding to the difference of are roughly represented. The radius r2 of the second cylindrical portion 11c is equal to the distance from the central axis AX to the inner circumferential surface of the second cylindrical portion 11c. Below, the dimension equivalent to the said difference is called "the variation | change_quantity of the radius of the 2nd cylindrical part 11c."

  As described above, the flying object radome 2 and the flying object body 1 have different coefficients of thermal expansion. Further, since the second cylindrical portion 11c is provided inside the radome side joint portion 21, the total amount of aerodynamic heating received by the second cylindrical portion 11c and the radome side joint portion 21 is different. Moreover, even if such a difference in the amount of change occurs, the difference in the amount of change can be absorbed by the insertion depth of the connecting member 8 which is the second connecting portion into the insertion hole 21a.

  In the flying object 100 according to the first embodiment, as shown in FIG. 2, the fixing member 6 is fixed to the flying object body 1, and the columnar connecting member 8 extending in the radial direction from the fixing member 6 is the flying object. It is inserted into the insertion hole 21 a of the radome 2. Further, a gap G2 is formed between the radially outer surface of the fixing member 6 and the inner peripheral surface of the radome-side joint portion 21. With this configuration, even when the amount of change in radius of the radome side joint portion 21 and the amount of change in radius of the second cylindrical portion 11c are different, the inner peripheral surface of the radome side joint portion 21 is the fixing member 6 and the second cylinder It is not pushed in the radial direction by the part 11c. Therefore, no thermal stress is generated between the radome side joint portion 21 and the second cylindrical portion 11c due to aerodynamic heating at the time of flight. Therefore, in the flying object 100 according to the first embodiment, a ring made of FRP, that is, a ring for relieving thermal stress generated between the flying object body 1 and the flying object radome 2 becomes unnecessary.

  In addition, an epoxy-based adhesive having high adhesive strength is often used for bonding the ring and the flying object radome 2. However, there are few types of adhesives whose heat resistance temperature exceeds 200 ° C., and depending on the flight distance and speed of the projectile, the temperature of the adhesive may exceed the heat resistance temperature. In addition, even if a heat insulating material is provided on the outer peripheral surface of the flight body exposed directly to aerodynamic heating in order to prevent the temperature rise of the ring, if the flight distance of the flight body becomes long or the flight speed becomes high, adhesion The heat resistance temperature of the agent may be exceeded. On the other hand, in the flying object 100 according to the first embodiment, a ring is not necessary, and therefore, an adhesive for fixing the flying object radome 2 to the ring becomes unnecessary. Therefore, the flying object 100 can be manufactured which can withstand high temperature environment where the adhesive strength of the adhesive is lost. In addition, by eliminating the need for adhesives, it is not necessary to take measures such as giving an initial bond strength a margin so that the flying object radome 2 does not come off the ring even if the bond strength decreases due to aging. As a result, the manufacturing cost of the flying object 100 can be reduced, and the flying object 100 can be stored for a long time.

  In the flying object 100 according to the first embodiment, the flying object radome 2 is connected to the flying object body 1 by using three or more fixing members 6 arranged in the circumferential direction. Therefore, even if the flying object radome 2 heated at the time of flight is expanded in the radial direction, it can be prevented that the flying object radome 2 is detached from the flight object body 1, and one or two fixing members As compared with the case of using No. 6, it is possible to suppress the deviation and rattling of the flying object radome 2 in the circumferential direction. In addition, since the deviation and rattling of the flying object radome 2 in the circumferential direction are suppressed, the flying distance of the flying object 100 can be extended, and the flying object 100 can be accurately aimed toward the target. It can be induced.

  Moreover, in the flying object 100 according to the first embodiment, the radome-side joint portion 21 of the flying object radome 2 whose outer peripheral surface is covered by the second heat insulating portion 4 is a columnar connecting member 8 in the circumferential direction. It is a structure connected with the 2nd cylindrical part 11c of the flying body main body 1 via the some fixing member 6 arranged apart. Therefore, the cross-sectional area of the cross section orthogonal to the radial direction of the connection member 8 becomes smaller than the contact area of the flying object body 1 and the ring. Therefore, the amount of heat transfer of the heat of the second heat insulating part 4 that has become high temperature due to aerodynamic heating via the connecting member 8 and the fixing member 6 to the body 1 is the body of the body via the ring. It becomes smaller than the amount of heat transferred from 1 to the flying radome 2. As a result, the temperature rise of the space portion surrounded by the flying object radome 2 and the flying object body 1 is suppressed, and the electronic parts constituting the electronic device 5 and the electronic parts incorporated in the flying object body 1 Can reduce the risk of being damaged by heat.

  In addition, when the two connection members 8 are provided separately in the circumferential direction, the separation widths of the two connection members 8 have different values before and after the thermal expansion of the fixing member 6. When the two insertion holes 21a are provided circumferentially apart, the separation widths of the two insertion holes 21a become different values before and after the thermal expansion of the radome 2 for a flying object. The amount of change in radius of the radome-side joint 21 is larger than the amount of change in the axial direction of the radome-side joint 21, and therefore occurs in the contact portion between the connecting member 8 provided in the circumferential direction and the insertion hole 21a. The thermal stress is greater than when the two connection members 8 are provided axially apart. In the flying object 100 according to the first embodiment, since the two connection members 8 are provided apart from each other in the axial direction, an increase in thermal stress generated at the contact portion between the connection member 8 and the insertion hole 21a is suppressed. . Therefore, it is not necessary to provide a measure for the initial strength of the connecting member 8 and the manufacturing cost of the flying object 100 can be reduced.

  Although two connecting members 8 are used in the flying object 100 according to the first embodiment, one connecting member 8 may be used instead of the two connecting members 8. In this case, for example, one connecting member 8 may be provided between the surface of the fixing member 6 on the tip end side and the through hole 6a, or between the surface on the rear end side of the fixing member 6 and the through hole 6a. One connecting member 8 may be provided. Even when configured in this manner, the radome-side coupling portion 21 can be coupled to the projectile body 1 via the one coupling member 8 and the fixing member 6. However, when configured in this manner, a twisting moment according to the axial length from the axial center of the through hole 6a of the fixing member 6 to the axial center of the connecting member 8 is the radome side joint portion 21 and the second cylindrical portion 11c. Occurs between Therefore, a large section coefficient is required so that the connection member 8 and the countersunk screw 7 are not deformed even if the twisting moment acts on the connection member 8 and the countersunk screw 7. By providing the two connecting members 8 so as to sandwich the through holes 6 a of the fixing member 6, it is desirable to provide the two connecting members 8 because the generation of the twisting moment as described above can be suppressed.

Second Embodiment
FIG. 9 is a partially enlarged view of a flying object according to Embodiment 2 of the present invention. The figure which looked at the radome 2A for flight bodies with which the flight object 100A which concerns on Embodiment 2 with which FIG. 9 is equipped from the radial direction outer side is provided. On the lower side of FIG. 9, a cross-sectional view of a flying object radome 2A included in the flying object 100A is shown. An insertion hole 21a1 and an insertion hole 21a are formed in the flying object radome 2A instead of the two insertion holes 21a shown in FIG. The other configuration is the same as or equivalent to the configuration of the first embodiment, and the same or equivalent components are denoted by the same reference numerals and redundant description will be omitted.

  Each of the flying object radome 2A and the fixing member 6 may be made of materials having different thermal expansion coefficients. In addition, since the fixing member 6 is provided inside the radome side coupling portion 21, the total amount of aerodynamic heating received by the fixing member 6 and the radome side coupling portion 21 is different. Therefore, the amount of change of the radome side joint portion 21 in the axial direction is different from the amount of change of the fixing member 6 in the axial direction, and occurs in the contact portion between the connecting member 8 provided on the fixing member 6 and the radome 2A for the flying object. Thermal stress may increase. In the radome 2A for a flying object according to the second embodiment, the insertion hole 21a1 is processed into a shape different from the shape of the insertion hole 21a in consideration of the difference in the amount of change.

  Each of the insertion hole 21a1 and the insertion hole 21a is a hole which penetrates from the outer peripheral surface of the radome side coupling portion 21 toward the inner peripheral surface of the radome side coupling portion 21 and extends in the radial direction. A plurality of sets of the insertion holes 21a1 and the insertion holes 21a are formed separately in the circumferential direction at positions corresponding to the plurality of fixing members 6 arranged in the circumferential direction. The insertion holes 21a1 and the insertion holes 21a are formed apart from each other in the axial direction so as to sandwich the insertion holes 21b. In FIG. 9, an insertion hole 21a1 is formed on the tip end side of the flying object 100A than the insertion hole 21b.

  The insertion hole 21a is a hole having the same shape as the insertion hole 21a shown in FIG. The insertion hole 21a1 is an elliptical long hole having a width W1 larger than the width W2. The width W1 is a width in the axial direction of the insertion hole 21a1, and is wider than the diameter of the connecting member 8. The shape of the connecting member 8 inserted into the insertion hole 21a1 is cylindrical. The value of the width W1 is set in consideration of the difference in the amount of change in the axial direction of the fixed member 6 and the flying object radome 2A when the flying object 100A is flying. The width W2 is a width in the circumferential direction of the insertion hole 21a1. The width W2 is set to a value equal to the diameter of the connecting member 8 or slightly larger than the diameter of the connecting member 8. In the second embodiment, although the insertion hole 21a1 is formed near the tip of the flying object radome 2A, the insertion hole 21a1 is formed near the rear end of the flying object radome 2A, and the insertion hole 21a may be formed near the tip of the flying object radome 2A.

  As described above, in the flying object 100A according to the second embodiment, one of the two through holes into which the connecting member 8 is inserted has an elliptical shape extending in the axial direction, so the radome side coupling portion Even when the amount of change in the axial direction of each of the fixing member 21 and the fixing member 6 is different, the thermal stress generated in the flying object radome 2A can be alleviated. Therefore, the risk of breakage of the connecting member 8 and the fixing member 6 can be further reduced.

Third Embodiment
FIG. 10 is a cross-sectional view enlarging a connecting portion of a flying object radome of a flying object and a flying object body according to a third embodiment of the present invention. The flying object 100B according to the third embodiment shown in FIG. 10 includes a heat transfer suppressing portion 40 for reducing the amount of heat transferred from the fixing member 6 to the second cylindrical portion 11c. The heat transfer suppressing portion 40 is provided between the radially inner surface 60 of the fixing member 6 and the outer peripheral surface of the second cylindrical portion 11 c. The heat transfer suppressing portion 40 may be manufactured using a material having a high heat resistant temperature and a thermal conductivity lower than the thermal conductivity of the fixing member 6, and the radome 2 for a flying object or the flying object main body You may manufacture using the material similar to 1. The other configuration is the same as or equivalent to the configuration of the first embodiment, and the same or equivalent components are denoted by the same reference numerals and redundant description will be omitted.

  FIG. 11 is a view showing the fixing member shown in FIG. 10 as viewed from inside in the radial direction. As shown in FIG. 11, the heat transfer suppressing portion 40 is configured of a plurality of heat transfer suppressing members 41. The plurality of heat transfer suppressing members 41 extend in the circumferential direction and are arranged to be separated from each other in the axial direction. The plurality of heat transfer suppressing members 41 are provided in a region formed by projecting the fixing member 6 toward the second cylindrical portion 11 c. Thus, the first cross-sectional area of the cross section orthogonal to the radial direction of the heat transfer suppressing portion 40 constituted by the plurality of heat transfer suppressing members 41 is the second cross section of the cross section orthogonal to the radial direction of the fixing member 6 Smaller than the area.

  The shape of the heat transfer suppressing portion 40 is not limited to the shape shown in FIG. 11. For example, each of the plurality of heat transfer suppressing members 41 constituting the heat transfer suppressing portion 40 extends in the axial direction, and the circumferential direction May be arranged apart from one another. The heat transfer suppressing portion 40 may be a net-like sheet having a plurality of holes penetrating in the radial direction.

  FIG. 12 is a cross-sectional view of a flying object according to a first modification of the third embodiment. The heat transfer suppressing portion 6b is provided in the flying object 100B1 according to the first modified example shown in FIG. The heat transfer suppressing portion 6b may be manufactured integrally by die casting using the same material as the fixing member 6, or the surface facing the second cylindrical portion 11c of the fixing member 6, that is, the radial direction of the fixing member 6 It may be formed on the fixing member 6 by cutting the inner surface 60. The heat transfer suppressing portion 6b is configured by a plurality of heat transfer suppressing members, as in the heat transfer suppressing portion 40 shown in FIG. The plurality of heat transfer suppressing members constituting the heat transfer suppressing portion 6b may extend in the axial direction and may be arranged apart from each other in the circumferential direction. Further, the plurality of heat transfer suppressing members constituting the heat transfer suppressing portion 6b may extend in the circumferential direction and may be arranged separately from each other in the axial direction. The heat transfer suppressing portion 6b may be a net-like sheet having a plurality of holes penetrating in the radial direction. Thus, the first cross-sectional area of the cross section orthogonal to the radial direction of the heat transfer suppressing portion 6 b constituted by the plurality of heat transfer suppressing members is the second cross-sectional area of the cross section orthogonal to the radial direction of the fixing member 6 Less than.

  FIG. 13 is a cross-sectional view of a flying object according to a second modification of the third embodiment. The heat transfer suppressing portion 11c2 is provided to the flying object 100B2 according to the second modified example shown in FIG. The heat transfer suppressing portion 11c2 may be integrally manufactured by die casting using the same material as the second cylindrical portion 11c, or may be a surface facing the fixing member 6 of the second cylindrical portion 11c, that is, the second It may be formed on the second cylindrical portion 11c by cutting the outer peripheral surface 11c3 of the cylindrical portion 11c. The heat transfer suppressing portion 11c2 is configured by a plurality of heat transfer suppressing members, similarly to the heat transfer suppressing portion 40 shown in FIG. The plurality of heat transfer suppressing members constituting the heat transfer suppressing portion 11c2 may extend in the axial direction and may be arranged apart from each other in the circumferential direction. Further, the plurality of heat transfer suppressing members constituting the heat transfer suppressing portion 11c2 may extend in the circumferential direction and may be arranged to be separated from each other in the axial direction. The heat transfer suppressing portion 11c2 may be a net-like sheet having a plurality of holes penetrating in the radial direction. Thus, the first cross-sectional area of the cross section orthogonal to the radial direction of the heat transfer suppressing portion 11c2 configured by the plurality of heat transfer suppressing members is the second cross-sectional area of the cross section orthogonal to the radial direction of the fixing member 6 Less than.

  According to the flying objects 100B, 100B1 and 100B2 according to the third embodiment, by providing the heat transfer suppressing portion, the second cylindrical portion 11c of the fixing member 6 is provided as compared with the case where the heat transfer suppressing portion is not provided. The contact area to the surface is reduced, the amount of heat transferred from the fixing member 6 to the second cylindrical portion 11c is reduced, and the temperature rise of the vehicle body 1 can be further suppressed.

  Further, in the flying object 100B shown in FIG. 10, since the heat transfer suppressing portion 40 manufactured separately from the fixing member 6 and the flying object main body 1 can be used, the assumed flying distance and distance of the flying object 100B are Depending on the speed, it is possible to attach the heat transfer suppressing portion 40 or omit the heat transfer suppressing portion 40. Therefore, it can be made the minimum composition according to the use of flying object 100B.

  Further, in the flying object 100B1 shown in FIG. 12, since the heat transfer suppressing portion 6b can be simultaneously manufactured at the time of manufacturing the fixing member 6, a heat transfer suppressing structure is provided between the fixing member 6 and the second cylindrical portion 11c. Since it is possible to save time and effort to check whether or not there is, it is possible to reduce the management cost of the flying object 100B1.

  Further, in the flying object 100B2 shown in FIG. 13, since the heat transfer suppressing portion 11c2 can be simultaneously manufactured at the time of manufacturing the second cylindrical portion 11c, a heat transfer suppressing structure is provided between the fixing member 6 and the second cylindrical portion 11c. Since it is possible to save time and effort to check whether or not provided, the management cost of the flying object 100B2 can be reduced.

  The heat transfer suppressing portions 6b, 11c 2 and 40 according to the third embodiment are also applicable to the second embodiment.

Fourth Embodiment
FIG. 14 is a cross-sectional view enlarging a connecting portion of a flying object radome and a flying object body of a flying object according to a fourth embodiment of the present invention. In the flying object 100C according to the fourth embodiment, a countersunk screw 7A is used instead of the countersunk screw 7. The countersunk screw 7A is a screw longer than the countersunk screw 7. In the flying object 100C, the floating nut 50 is used. The other configuration is the same as or equivalent to the configuration of the first embodiment, and the same or equivalent components are denoted by the same reference numerals and redundant description will be omitted.

  The floating nut 50 has, for example, a nut plate 51 having a screw hole at the center in the axial direction and circumferential direction, and a support plate 52 for supporting the nut plate 51. The axial direction both ends and the circumferential direction both ends of the support plate 52 are folded back, and the nut plate 51 is held. The nut plate 51 held by the support plate 52 is movable in the axial direction and the circumferential direction. The floating nut 50 configured in this manner is attached to the radially inner surface of the second cylindrical portion 11c. Then, the male screw portion 7 b of the flathead screw 7 A is screwed into the screw hole of the nut plate 51. For example, even when the axial center of the through hole 11c1 deviates from the axial center of the male screw portion 7b due to the processing error of the through hole 11c1 of the second cylindrical portion 11c when assembling the flying object 100C. By using the floating nut 50, the radome side coupling portion 21 can be coupled to the second cylindrical portion 11c.

  The shape of the floating nut 50 according to the fourth embodiment is not limited to the illustrated example as long as the nut plate 51 can move in the axial direction and the circumferential direction. The floating nut 50 according to the fourth embodiment is also applicable to the second embodiment and the third embodiment.

  The configuration shown in the above embodiment shows an example of the contents of the present invention, and can be combined with another known technique, and one of the configurations is possible within the scope of the present invention. Parts can be omitted or changed.

  DESCRIPTION OF SYMBOLS 1 flight body main body, 2, 2A radome for projectiles, 3 1st heat insulation part, 4 2nd heat insulation part, 5 electronic devices, 6 fixing member, 6a, 11c1 through hole, 6a1 countersunk part, 6b, 11c2, 40 heat transfer suppressing portion 7, 7A flat head screw, 7a head, 7b male screw portion, 8 connecting member, 9 hole filling member, 10 case, 11 main body side connecting portion, 11a first cylindrical portion, 11b overhang Part, 11c Second cylindrical part, 11d Equipment installation part, 11c3 Outer peripheral surface, 20 First radome, 21 Radome side joint part, 21a, 21a1, 21b Insertion hole, 41 Heat transfer suppressing member, 50 Floating nut, 51 nut Plates, 52 support plates, 60 planes, 100, 100 A, 100 B, 100 B 1, 100 B 2, 100 C Flying object, G1, G2 gap.

Claims (7)

A cylindrical flight body that flies by radio induction toward the target,
A columnar first connection member fixed to the tip end side of the flight body main body;
A columnar second connection member provided on the first connection member and extending radially outward from the first connection member;
An insertion hole is formed in which the second connection member is inserted, and the flying rod radome is connected to the tip end side of the flight body through the second connection member and the first connection member. When,
Equipped with
A space is formed between the inner peripheral surface of the radome for the flying object and the radially outer surface of the first connecting member. The first connection member is formed with a through hole into which a screw inserted toward the spacecraft body is inserted.
In the first connection member, two second connection members are provided so as to be separated from each other in the axial direction of the body so as to sandwich the through hole.
The flying object according to claim 1, wherein two insertion holes are formed apart from each other in the axial direction in the radome for flying object. The second connection member is a cylindrical member,
The flying object according to claim 2, wherein one of the two insertion holes has an elliptical shape in which the width in the axial direction is wider than the width in the circumferential direction.   The heat transfer suppressing portion is provided between the first connecting member and the body of the flying object, and reduces the amount of heat transferred from the first connecting member to the body of the flying object. The flying object according to any one of claims 1 to 3, wherein   The heat transfer suppressing portion is provided integrally with the first connection member, and reduces a transfer amount of heat transferred from the first connection member to the projectile body. The flying body as described in any one of 3).   The heat transfer suppressing portion is provided integrally with the projectile main body, and reducing a transfer amount of heat transferred from the first connection member to the projectile main body. The flying body as described in any one of the above.   The flying nut according to any one of claims 1 to 6, further comprising: a floating nut to which a tip portion of a screw for fixing the first connection member is screwed on a tip end side of the flying body main body. Shobo.

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