JP6914187B2 - Flying body - Google Patents

Description

The present invention relates to a flying object including a cylindrical flying object body that is guided by radio waves toward a target and a flying body radome provided at the tip of the flying object body.

The conventional flying object disclosed in Patent Document 1 includes a flying body body that flies toward a target by radio wave guidance, an antenna provided at the tip of the flying body body for detecting a target, and a flying body. It is equipped with a radome for flying bodies that is provided at the tip of the body and protects the antenna. Many aurora missiles reach supersonic or hypersonic speeds within a short time of a few seconds from the start of flight, and are exposed to high temperatures due to aerodynamic heating. Aerodynamic heating is a phenomenon in which the atmosphere flows at high speed on the surface of a flying object, friction is generated between the surface of the flying object and the atmosphere, and the atmosphere and the flying object are heated by the frictional heat. .. The radome for the flying body provided at the tip of the flying body body is one of the parts of the flying body where the thermal environment is harsh, and is subjected to a large aerodynamic load, aerodynamic heating and thermal shock. Thermal shock is a phenomenon in which an object receives shocking thermal stress due to a drastic temperature change. Therefore, the radome for a flying object is required to have high strength, heat resistance, and heat impact resistance. Further, since the radome for a flying object needs to transmit the radio waves transmitted and received by the antenna, the radome for the flying object is required to have radio wave transparency. In order to meet the above requirements, ceramics, which is a dielectric material having a heat resistant temperature of 1000 ° C. or higher and a coefficient of thermal expansion of 5 × ^{10-6 / ° C. or lower, is generally used as the material of the radome for the flying body.} Will be done.

On the other hand, for the body of the flying object, iron, aluminum, or the like, which is a highly rigid material having a ^{coefficient of thermal expansion in the range of 10 × 10-6} / ° C to 30 × ^{10-6 / ° C, is used.} In this way, there is a large difference in the coefficient of thermal expansion between the radome for the flying body and the main body of the flying body. Stress is generated and cracks or cracks occur in the flying radome. For this reason, in a conventional flying body, the flying body radome is made of a flying body through a ring made of fiber reinforced plastic (FRP) having a relatively low coefficient of thermal expansion while having high rigidity. It is fixed to the main body. An adhesive is used to attach the flying radome to the ring.

Japanese Unexamined Patent Publication No. 11-37699

In a conventional radome, as the flying speed increases and the flying time of the radome increases, the total amount of aerodynamic heating increases, the temperature of the adhesive exceeds the heat resistant temperature, and the adhesive flies to the ring. The adhesive strength of the radome for the body may decrease. In addition, when a material with high thermal conductivity is used as the material of the flying body redome in order to alleviate the thermal shock of the flying body redome, heat is easily transferred from the flying body redome to the adhesive. , The temperature of the adhesive becomes high, the temperature of the adhesive exceeds the heat resistant temperature, and the adhesive strength may decrease. Therefore, in the conventional missile, there is a problem that the adhesive strength is lowered and the radome for the missile may come off from the main body of the missile. Further, it is known that the adhesive strength decreases due to aged deterioration of the adhesive, but it is difficult to quantitatively estimate the decrease rate of the adhesive strength. Therefore, in the conventional flying body, it is necessary to allow a margin in the initial adhesive strength so that the radome for the flying body does not come off from the ring even if the adhesive strength decreases due to the aging deterioration of the adhesive. ..

The present invention has been made in view of the above, and an object of the present invention is to obtain a flying body capable of preventing the flying body radome from coming off from the flying body main body.

In order to solve the above-mentioned problems and achieve the object, the flying object according to the present invention is provided on a cylindrical flying object body that is guided by radio waves toward a target and on the tip side of the flying object body. It includes a columnar first connecting member to be fixed. The flying body is provided in the first connecting member, and a columnar second connecting member extending radially outward from the first connecting member and an insertion hole into which the second connecting member is inserted are formed, and the second connecting member is formed. A radome for a flying body, which is connected to the tip end side of the flying body body via the second connecting member and the first connecting member, is provided. A gap is formed between the inner peripheral surface of the flying radome and the radial outer surface of the first connecting member.

The flying body according to the present invention has an effect that the radome for the flying body can be prevented from coming off from the flying body main body.

External view of the aurora according to the first embodiment of the present invention A cross-sectional view of the connection portion between the aurora body body and the radome for the aurora shown in FIG. 1 in an enlarged view. The figure which shows the state which the connecting member was embedded in the fixing member shown in FIG. The figure which shows the state which the connecting member shown in FIG. 3 is inserted into the insertion hole of the radome side joint part shown in FIG. The figure which shows the state which shows the state which the fixing member shown in FIG. 4 and the radome for a flying body are attached to the flying body main body shown in FIG. FIG. 5 is a diagram showing a state in which the fixing member assembled to the missile body shown in FIG. 5 is fixed to the missile body using a countersunk screw. FIG. 6 is a diagram showing a state in which a hole filling member and a 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. The figure for demonstrating the amount of change of the radius of each of the radome side joint part and the 1st cylindrical part shown in FIG. Partially enlarged view of the aurora according to the second embodiment of the present invention A cross-sectional view of the flying body radome and the connecting portion of the flying body body according to the third embodiment of the present invention in an enlarged view. The figure which shows the state which the fixing member shown in FIG. 10 was seen from the inside in the radial direction. Cross-sectional view of the flying body according to the first modification of the third embodiment Cross-sectional view of the flying body according to the second modification of the third embodiment A cross-sectional view of the flying body radome and the connecting portion of the flying body body according to the fourth embodiment of the present invention in an enlarged view.

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

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

In FIG. 1, the left end of each configuration is the front end, and the right end of each configuration is the rear end. Further, the flight direction of the aurora missile 100 is equal to the direction from the right side to the left side in FIG. The flying body 100 includes a cylindrical flying body body 1, a flying body radome 2 provided at the tip of the flying body body 1, and a first outer peripheral portion of the flying body body 1 near the tip. The heat insulating portion 3 of the above, the second heat insulating portion 4 provided on the outer peripheral portion near the rear end of the radome 2 for the flying body, and the electronic device 5 provided inside the flying body 100 are provided. The flying body 100 measures the distance and direction to the target by the radio waves transmitted and received by the electronic device 5, and flies toward the target by radio wave guidance. The electronic device 5 is an antenna for measuring the distance and the direction to the target.

Since the radome 2 for the flying object is a part that is susceptible to the aerodynamic load and aerodynamic heating generated when the flying object 100 flies at high speed, the tip portion is provided so that the aerodynamic resistance can be reduced and the flying body 100 can fly at high speed. It has a sharp streamlined shape, the outer diameter spreads smoothly from the tip to the rear end, and the rear end is open and hollow. The radome 2 for a flying object is required to have high strength, heat resistance, and heat impact resistance, and is also required to have radio wave transmission. ^{Therefore, ceramics having a coefficient of thermal expansion of 5 × 10 -6} / ° C. or less are used as the material of the radome 2 for the flying object. Examples of ceramics include ceramic sintered bodies such as alumina (Al ₂ O ₃ ), cozy light ( ₂ MgO ・ 2 Al 2 O ・ 5SiO ₂ ), fused silica (SiO ₂ ), and silicon nitride (Si ₃ N _4). can.

As the material of the flying body body 1, iron, aluminum, or the like, which is a highly rigid material having a ^{coefficient of thermal expansion in the range of 10 × 10-6} / ° C. to 30 × ^{10-6 / ° C., is used.}

As shown in FIG. 2, the flying body main body 1 is formed by connecting a cylindrical housing 10 extending in the axial direction and a radome 2 for the flying body provided at the axial end of the housing 10 to the housing 10. It is provided with a main body side connecting portion 11 for the purpose of doing so. The housing 10 and the main body side joint portion 11 may be manufactured by die-casting using a material such as iron or aluminum, or may be manufactured individually and then combined with each other.

The main body side coupling portion 11 includes a first cylindrical portion 11a, an overhanging portion 11b, a second cylindrical portion 11c, and an equipment installation portion 11d.

The first cylindrical portion 11a extends in the axial direction from the tip end side of the housing 10 toward the radome 2 for the flying body, 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 tip of the first cylindrical portion 11a faces the axial rear end of the flying radome 2. Details of the configuration of the flying radome 2 will be described later.

A first heat insulating portion 3 is provided on the radial outer side of the first cylindrical portion 11a. As the material of the first heat insulating portion 3, a silicone resin having a high heat resistant temperature and excellent heat insulating properties is used. The material of the first heat insulating portion 3 may be any material having a thermal conductivity lower than that of the first cylindrical portion 11a, and is not limited to the silicone resin. The first heat insulating portion 3 is provided in an annular shape continuously in the circumferential direction on the outer peripheral surface of the first cylindrical portion 11a. The first heat insulating portion 3 may be assembled to the first cylindrical portion 11a in a state in which an elastic annular heat insulating member is stretched in the radial direction, or a band-shaped heat insulating member may be attached to the first cylindrical portion 11a. It may be wound continuously in a ring shape around it. 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 connection portion between the first cylindrical portion 11a and the housing 10 to the end portion of the first cylindrical portion 11a on the radome 2 side 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 extends axially to the first cylindrical portion 11a.

The overhanging portion 11b is an annular plate-shaped member that extends inward in the radial direction from a portion of the inner peripheral surface of the first cylindrical portion 11a that is closer to the tip and is provided coaxially with the housing 10.

The second cylindrical portion 11c extends in the axial direction from the portion of the overhanging portion 11b near the inner peripheral surface toward the radome 2 for the flying body, and the outer diameter OD1 is smaller than the inner diameter ID1 of the radome 2 for the flying body. It is a cylindrical member provided coaxially with the housing 10. The second cylindrical portion 11c is formed with a through hole 11c1 that penetrates from the outer peripheral surface of the second cylindrical portion 11c toward the inner peripheral surface of the second cylindrical portion 11c and extends in the radial direction. 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 to each other in the circumferential direction are equal to each other. In addition, "equal" described here not only represents a state of being strictly equal, but also includes a range in which manufacturing tolerances of each part constituting the flying body 100, variations in assembly of the parts, and the like are taken into consideration. Tolerance.

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

A fixing member 6 which is a first connecting member is provided on the radial outer side of the second cylindrical portion 11c. The fixing member 6 is a cylindrical or polygonal prism-shaped member extending in the radial direction. The fixing member 6 may be manufactured by die-casting using the same material as the radome 2 for the flying body or the body 1 of the flying body, or may be integrally molded with the radome 2 for the flying body or the body 1 of the flying body. It may be manufactured by cutting a block-shaped mass formed of the same material.

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

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

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 for the flying object 2. Narrower than. Therefore, a gap G2 is formed between the radial outer surface of the fixing member 6 and the inner peripheral surface of the radome-side coupling portion 21 of the flying radome 2.

The fixing member 6 is formed with a through hole 6a that 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. A counterbore processed portion 6a1 that matches the shape of the conical head portion 7a of the countersunk screw 7 is formed in the through hole 6a. The male screw portion 7b, which is the tip end portion of the countersunk screw 7, passes through the through hole 6a of the fixing member 6 and is screwed into the through hole 11c1 of the second cylindrical portion 11c. By providing the counterbore processing portion 6a1, the inclined surface of the head 7a of the countersunk screw 7 comes into contact with the inner peripheral surface of the fixing member 6 forming the through hole 6a. Compared with the case where a screw other than the countersunk screw 7 is used, 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. The loosening of the 7 is suppressed, and the fixing member 6 can be maintained fixed to the second cylindrical portion 11c. Although the countersunk screw 7 is used in the first embodiment, a 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 connecting members 8 is connected to a portion of the fixing member 6 that is closer to the outer side in the radial direction. The shape of the connecting member 8 is not limited to a cylinder, and may be a square pillar 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 provided apart from each other in the axial direction so as to sandwich the through hole 6a of the fixing member 6. The connecting member 8 may be integrally molded by die casting using the same material as the fixing member 6, or may be a block shape formed of the same material as the radome 2 for the flying object or the flying body 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 individually manufactured and then combined with each other will be described.

The flying radome 2 that covers the periphery of the electronic device 5 and is provided so as to face the axial tip surface of the first cylindrical portion 11a has a conical first radome 20 and a radome-side joint portion 21. Be prepared. The first radome 20 and the radome side joint portion 21 may be manufactured by integral molding, or may be manufactured individually and then combined with each other.

The radome side coupling portion 21 extends axially from the rear end portion of the first radome 20 toward the flying body body 1, and has an outer diameter smaller than the outer diameter of the first radome 20. It is a cylindrical member provided coaxially with.

A second heat insulating portion 4 is provided on the radial outer side of the radome side coupling portion 21. As the material of the second heat insulating portion 4, a silicone resin having a high heat resistant temperature and excellent heat insulating properties is used. The material of the second heat insulating portion 4 may be any material having a thermal conductivity lower than that of the radome side coupling portion 21, and is not limited to the silicone resin. The second heat insulating portion 4 is provided on the outer peripheral surface of the radome side coupling portion 21 continuously in the circumferential direction in an annular shape. The second heat insulating portion 4 may be assembled to the radome side joint portion 21 in a state in which an elastic annular heat insulating member is stretched in the radial direction, or a band-shaped heat insulating member may be attached around the radome side joint portion 21. It may be wound continuously in a ring shape. 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 flyer body 1 side. .. 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 extends axially to the radome side joint portion 21.

The radome-side coupling portion 21 is formed with two insertion holes 21a that penetrate 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 extend in the radial direction. Further, the radome-side coupling portion 21 is formed with an insertion hole 21b that 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.

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

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

The insertion hole 21b is a hole for inserting the countersunk screw 7 from the outside of the flying radome 2 toward the second cylindrical portion 11c. The insertion hole 21b communicates with the through hole 6a formed in the fixing member 6 and further communicates with the through hole 11c1 formed in the second cylindrical portion 11c. A plurality of insertion holes 21b are formed at positions corresponding to each of the plurality of fixing members 6 arranged in the circumferential direction, apart from each other in the circumferential direction. A hole filling member 9 made of a silicone-based resin is inserted into the insertion hole 21b of the radome side joint portion 21 and the counterbore processing portion 6a1 of the through hole 6a. The hole filling member 9 is a columnar member extending in the radial direction. The outer diameter of the hole filling member 9 before being inserted into the insertion hole 21b and the counterbore processing portion 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 processing portion 6a1. Will be done. The slightly larger value is a dimension in which the hole filling member 9 can be inserted into the insertion hole 21b and the counterbore processing portion 6a1. The hole filling member 9 may be formed by curing the silicone-based resin filled in the insertion hole 21b and the counterbore processing portion 6a1 of the through hole 6a.

The surface of the hole filling member 9 on the countersunk screw 7 side is in contact with the countersunk screw 7. Therefore, even if the countersunk screw 7 fastened to the fixing member 6 is slightly loosened by the vibration of the flying body 100, the countersunk screw 7 to the outside in the radial direction is restricted. Therefore, the fixing member 6 can be maintained fixed to the second cylindrical portion 11c.

Further, the radial outer end surface of the hole filling member 9 is located on a virtual surface in which the outer peripheral surface of the radome side coupling portion 21 is axially extended to the insertion hole 21b. The radial outer end surface of the hole filling member 9 is in contact with the inner peripheral surface of the second heat insulating portion 4. As a result, the gap between the hole filling member 9 and the second heat insulating portion 4 is provided as compared with the case where the radial outer end surface of the hole filling member 9 is not in contact with the inner peripheral surface of the second heat insulating portion 4. It can be made smaller. As a result, the heat transferred from the outer peripheral surface to the inner peripheral surface of the radome side coupling portion 21 is dispersed between the connecting member 8 and the hole filling member 9, so that the heat from the radome side coupling portion 21 is transferred only to the connecting member 8. Compared with the case, the local thermal expansion of the fixing member 6 is suppressed. Therefore, the progress of aging deterioration of the fixing member 6 can be suppressed, and the increase in thermal stress generated at the contact portion between the connecting member 8 and the insertion hole 21a can be suppressed.

Next, the procedure for assembling the flying body 100 will be described with reference to FIGS. 3 to 7. FIG. 3 is a diagram showing a state in which a connecting member is embedded in the fixing member shown in FIG. FIG. 4 is a diagram 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 diagram showing a state in which the fixing member shown in FIG. 4 and the radome for the flying body are assembled to the flying body main body shown in FIG. FIG. 6 is a diagram showing a state in which the fixing member assembled to the missile body shown in FIG. 5 is fixed to the missile body by using a countersunk screw. FIG. 7 is a diagram 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 body 100, first, one end side of each of the two connecting 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 connecting member 8 embedded in the fixing member 6 is inserted into each of the two insertion holes 21a formed in the radome side connecting portion 21 as shown in FIG. This work 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 radome 2 for the flying body is fitted into the flying body body 1. Since a gap G2 is formed between the fixing member 6 and the radome side coupling portion 21, the fixing member 6 moves in the radial division direction of the gap G2 when the fixing member 6 is fitted into the second cylindrical portion 11c. It is possible. Therefore, the fixing member 6 can be easily fitted into the radome side coupling portion 21.

After the radome 2 for the flying body is fitted into the flying body body 1, a countersunk screw 7 is inserted into the insertion hole 21b of the radome side joint portion 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. As a result, the fixing member 6 is fixed to the flying body body 1, and the flying body radome 2 is movable in the radial direction via the connecting member 8, the fixing member 6, and the countersunk screw 7. It is connected to the main body 1. At this time, the movement of the flying radome 2 other than the radial direction is restricted. This is because, as described above, the diameter of the insertion hole 21a 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.

After the fixing member 6 is fixed to the flying body body 1, the hole filling member 9 is embedded in the insertion hole 21b as shown in FIG. 7. 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-based 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-based adhesive or the like. It is fixed. The first heat insulating portion 3 may be fixed to the first cylindrical portion 11a before the flying radome 2 is fitted to the flying body main body 1.

Next, the effect of the flying body 100 according to the first embodiment will be described. FIG. 8 is a diagram for explaining the amount of change in 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 the reference numeral 103 indicates the direction in which the radome-side coupling portion 21 spreads when the flying object 100 flies. The direction in which the radome-side joint 21 spreads 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 redome-side connecting portion 21 before expanding in the radial direction and the radius r1 of the redome-side connecting portion 21 expanding in the radial direction when the flying object 100 flies. It is a rough representation of the dimensions corresponding to. The radius r1 of the radome-side coupling portion 21 is equal to the distance from the central axis AX to the inner peripheral surface of the radome-side coupling portion 21. Hereinafter, the dimension corresponding to the difference is referred to as "the amount of change in the radius of the radome side coupling portion 21".

The direction of the arrow indicated by reference numeral 104 indicates the direction in which the second cylindrical portion 11c expands when the flying object 100 flies. The direction in which the second cylindrical portion 11c spreads is equal to the radial direction of the second cylindrical portion 11c. The lengths of the arrows indicated by reference numeral 104 are the radius r2 of the second cylindrical portion 11c before expanding in the radial direction and the radius r2 of the second cylindrical portion 11c expanding in the radial direction when the flying object 100 flies. It is a rough representation of the dimensions corresponding to the difference between. The radius r2 of the second cylindrical portion 11c is equal to the distance from the central axis AX to the inner peripheral surface of the second cylindrical portion 11c. Hereinafter, the dimension corresponding to the difference is referred to as "the amount of change in the radius of the second cylindrical portion 11c".

As described above, the flying body radome 2 and the flying body body 1 have different coefficients of thermal expansion. Further, since the second cylindrical portion 11c is provided inside the radome side coupling portion 21, the total amount of aerodynamic heating received by each of the second cylindrical portion 11c and the radome side coupling portion 21 is different. Further, 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 body 100 according to the first embodiment, as shown in FIG. 2, the fixing member 6 is fixed to the flying body body 1, and the columnar connecting member 8 extending in the radial direction from the fixing member 6 is the flying body. It is inserted into the insertion hole 21a of the radome 2. Further, a gap G2 is formed between the radial outer surface of the fixing member 6 and the inner peripheral surface of the radome side coupling portion 21. With this configuration, even if the amount of change in the radius of the radome-side coupling portion 21 and the amount of change in the radius of the second cylindrical portion 11c are different, the inner peripheral surface of the radome-side coupling portion 21 is the fixing member 6 and the second cylinder. It is not pushed in the radial direction by the portion 11c. Therefore, thermal stress due to aerodynamic heating during flight does not occur between the radome-side coupling portion 21 and the second cylindrical portion 11c. Therefore, in the flying body 100 according to the first embodiment, an FRP ring, that is, a ring for relaxing the thermal stress generated between the flying body main body 1 and the flying body radome 2 becomes unnecessary.

In addition, an epoxy-based adhesive having high adhesive strength is often used to bond the ring to the radome 2 for the flying object. However, there are few types of adhesives having a heat resistant temperature exceeding 200 ° C., and the temperature of the adhesive may exceed the heat resistant temperature depending on the flying distance and flying speed of the flying object. In addition, even if a heat insulating material is provided on the outer peripheral surface of the flying object that is directly exposed to aerodynamic heating to prevent the temperature of the ring from rising, if the flying distance of the flying object becomes long or the flying speed increases, it will adhere. The heat resistant temperature of the agent may be exceeded. On the other hand, in the flying object 100 according to the first embodiment, since the ring is unnecessary, the adhesive for fixing the flying object radome 2 to the ring becomes unnecessary. Therefore, it is possible to manufacture the flying body 100 that can withstand a high temperature environment in which the adhesive strength of the adhesive is lost. In addition, since the adhesive is no longer required, it is not necessary to take measures such as providing a margin in the initial adhesive strength so that the radome 2 for the flying body does not come off from the ring even if the adhesive strength decreases due to aged deterioration. 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 period of time.

Further, the flying body 100 according to the first embodiment has a structure in which the flying body radome 2 is connected to the flying body main body 1 by using three or more fixing members 6 arranged in the circumferential direction. Therefore, even if the radome 2 for the flying body heated at the time of flying expands in the radial direction, it is possible to prevent the radome 2 for the flying body from coming off from the flying body body 1 and one or two fixing members. Compared with the case of using No. 6, it is possible to suppress the bias and rattling of the flying radome 2 in the circumferential direction. In addition, since the bias and rattling of the radome 2 for the flying body in the circumferential direction are suppressed, the flying distance of the flying body 100 can be extended, and the flying body 100 can be accurately aimed at the target. Can be induced.

Further, in the flying object 100 according to the first embodiment, the radome-side connecting portion 21 of the flying object radome 2 whose outer peripheral surface is covered by the second heat insulating portion 4 is connected to the columnar connecting member 8 in the circumferential direction. The structure is connected to the second cylindrical portion 11c of the flying body main body 1 via a plurality of fixing members 6 arranged apart from each other. Therefore, the cross-sectional area of the cross section orthogonal to the radial direction of the connecting member 8 is smaller than the contact area between the flying body body 1 and the ring. Therefore, the amount of heat transferred to the flyer body 1 via the connecting member 8 and the fixing member 6 is the amount of heat transferred to the flyer body 1 via the ring. It is smaller than the amount of heat transferred from 1 to the radome 2 for the flying body. As a result, the temperature rise between the space surrounded by the flying radome 2 and the flying body 1 is suppressed, and the electronic components constituting the electronic device 5 and the electronic components built in the flying body 1 are formed. Can reduce the risk of damage due to heat.

When the two connecting members 8 are provided apart from each other in the circumferential direction, the separation widths of the two connecting members 8 have different values before and after the thermal expansion of the fixing member 6. Further, when the two insertion holes 21a are provided apart from each other in the circumferential direction, the separation widths of the two insertion holes 21a have different values before and after the thermal expansion of the flying radome 2. Since the amount of change in the radius of the radome-side joint portion 21 is larger than the amount of change in the axial direction of the radome-side joint portion 21, it occurs at the contact portion between the connecting member 8 provided apart in the circumferential direction and the insertion hole 21a. The thermal stress is larger than when the two connecting members 8 are provided apart in the axial direction. In the flying body 100 according to the first embodiment, since the two connecting members 8 are provided apart from each other in the axial direction, an increase in thermal stress generated at the contact portion between the connecting member 8 and the insertion hole 21a is suppressed. .. Therefore, it is not necessary to take measures such as providing a margin in the initial strength of the connecting member 8, and the manufacturing cost of the flying body 100 can be reduced.

Although two connecting members 8 are used in the flying body 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 front end side surface of the fixing member 6 and the through hole 6a, or between the rear end side surface of the fixing member 6 and the through hole 6a. One connecting member 8 may be provided. Even in this configuration, the radome-side coupling portion 21 can be connected to the flying body main body 1 via one connecting member 8 and the fixing member 6. However, in this configuration, the torsional moment corresponding 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 coupling portion 21 and the second cylindrical portion 11c. Occurs between and. Therefore, even if the torsional moment acts on the connecting member 8 and the countersunk screw 7, a large section coefficient is required so that the connecting member 8 and the countersunk screw 7 are not deformed. It is desirable to provide the two connecting members 8 because the generation of the above-mentioned torsional moment can be suppressed by providing the two connecting members 8 so as to sandwich the through hole 6a of the fixing member 6.

Embodiment 2.
FIG. 9 is a partially enlarged view of the aurora according to the second embodiment of the present invention. On the upper side of FIG. 9, a view of the flying body radome 2A included in the flying body 100A according to the second embodiment as viewed from the outside in the radial direction is shown. The lower side of FIG. 9 shows a cross-sectional view of the flying body radome 2A included in the flying body 100A. The flying radome 2A is formed with an insertion hole 21a1 and an insertion hole 21a instead of the two insertion holes 21a shown in FIG. Other configurations are the same as or equivalent to the configuration of the first embodiment, and the same or equivalent components are designated by the same reference numerals, and duplicate description will be omitted.

Each of the flying radome 2A and the fixing member 6 may be made of a material having a different coefficient of thermal expansion. Further, since the fixing member 6 is provided inside the radome side coupling portion 21, the total amount of aerodynamic heating received by each of the fixing member 6 and the radome side coupling portion 21 is different. Therefore, the amount of change in the radome-side coupling portion 21 in the axial direction is different from the amount of change in the fixing member 6 in the axial direction, and occurs at the contact portion between the connecting member 8 provided on the fixing member 6 and the radome for the flying object 2A. Thermal stress can be high. In the flying radome 2A 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 such a difference in the amount of change.

Each of the insertion hole 21a1 and the insertion hole 21a is a hole that penetrates 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 extends in the radial direction. A plurality of sets of the insertion holes 21a1 and the insertion holes 21a are formed at positions corresponding to each of the plurality of fixing members 6 arranged in the circumferential direction, apart from each other in the circumferential direction. The insertion hole 21a1 and the insertion hole 21a are formed apart from each other in the axial direction so as to sandwich the insertion hole 21b. In FIG. 9, the insertion hole 21a1 is formed on the tip end side of the flying body 100A with respect to 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 elongated hole having a width W1 wider than the width W2. The width W1 is the axial width 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 fixing member 6 and the radome 2A for the flying body when the flying body 100A is flying. The width W2 is the width of the insertion hole 21a1 in the circumferential direction. 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, the insertion hole 21a1 is formed near the tip of the radome for the flying body 2A, but the insertion hole 21a1 is formed near the rear end of the radome for the flying body 2A and the insertion hole is formed. 21a may be formed near the tip of the flying radome 2A.

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

Embodiment 3.
FIG. 10 is a cross-sectional view of the radome for the flying body and the connecting portion of the flying body main body according to the third embodiment of the present invention in an enlarged view. 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 radial inner surface 60 of the fixing member 6 and the outer peripheral surface of the second cylindrical portion 11c. The heat transfer suppressing unit 40 may be manufactured using a material having a high heat resistant temperature and a thermal conductivity lower than that of the fixing member 6, or may be manufactured using a flyer radome 2 or a flyer body. It may be manufactured using the same material as in 1. Other configurations are the same as or equivalent to the configuration of the first embodiment, and the same or equivalent components are designated by the same reference numerals, and duplicate description will be omitted.

FIG. 11 is a diagram showing a state in which the fixing member shown in FIG. 10 is viewed from the inside in the radial direction. As shown in FIG. 11, the heat transfer suppressing unit 40 is composed 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 apart 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 11c. As described above, the first cross-sectional area of the cross section orthogonal to the radial direction of the heat transfer suppressing portion 40 composed of the plurality of heat transfer suppressing members 41 is the second 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 unit 40 is not limited to the shape shown in FIG. 11, and for example, the plurality of heat transfer suppressing members 41 constituting the heat transfer suppressing unit 40 extend in the axial direction and in the circumferential direction. They may be arranged apart from each other. Further, the heat transfer suppressing unit 40 may be a mesh-like sheet having a plurality of holes penetrating in the radial direction.

FIG. 12 is a cross-sectional view of the flying body according to the first modification of the third embodiment. The flying body 100B1 according to the first modification shown in FIG. 12 is provided with a heat transfer suppressing portion 6b. The heat transfer suppressing portion 6b may be integrally manufactured by die casting using the same material as the fixing member 6, or the surface of the fixing member 6 facing the second cylindrical portion 11c, 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. Like the heat transfer suppressing unit 40 shown in FIG. 11, the heat transfer suppressing unit 6b is composed of a plurality of heat transfer suppressing members. The plurality of heat transfer suppressing members constituting the heat transfer suppressing unit 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 unit 6b may extend in the circumferential direction and are arranged apart from each other in the axial direction. Further, the heat transfer suppressing portion 6b may be a mesh-like sheet having a plurality of holes penetrating in the radial direction. As described above, the first cross-sectional area of the cross section orthogonal to the radial direction of the heat transfer suppressing portion 6b composed of 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. Smaller than

FIG. 13 is a cross-sectional view of the flying body according to the second modification of the third embodiment. The flying body 100B2 according to the second modification shown in FIG. 13 is provided with a heat transfer suppressing unit 11c2. The heat transfer suppressing portion 11c2 may be integrally manufactured by die casting using the same material as the second cylindrical portion 11c, or the surface of the second cylindrical portion 11c facing the fixing member 6, that is, the second second cylinder portion 11c. 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 unit 11c2 is composed of a plurality of heat transfer suppressing members, similarly to the heat transfer suppressing unit 40 shown in FIG. The plurality of heat transfer suppressing members constituting the heat transfer suppressing unit 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 unit 11c2 may extend in the circumferential direction and may be arranged apart from each other in the axial direction. Further, the heat transfer suppressing portion 11c2 may be a mesh-like sheet having a plurality of holes penetrating in the radial direction. As described above, the first cross-sectional area of the cross section orthogonal to the radial direction of the heat transfer suppressing portion 11c2 composed of 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. Smaller than

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

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

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

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

The heat transfer suppressing units 6b, 11c2, 40 according to the third embodiment can also be applied to the second embodiment.

Embodiment 4.
FIG. 14 is a cross-sectional view of the radome for the flying body and the connecting portion of the flying body main body according to the fourth embodiment of the present invention in an enlarged view. In the flying body 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. Further, in the flying body 100C, a floating nut 50 is used. Other configurations are the same as or equivalent to the configuration of the first embodiment, and the same or equivalent components are designated by the same reference numerals, and duplicate description will be omitted.

The floating nut 50 includes, for example, a nut plate 51 having screw holes in the center in the axial direction and the circumferential direction, and a support plate 52 that supports the nut plate 51. Both ends in the axial direction and both ends in the circumferential direction of the support plate 52 are folded back to hold the nut plate 51. 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 way is attached to the radial inner surface of the second cylindrical portion 11c. Then, the male screw portion 7b of the countersunk screw 7A is screwed into the screw hole of the nut plate 51. For example, when assembling the flying object 100C, even if the axial center of the through hole 11c1 is deviated from the axial center of the male screw portion 7b due to a machining error of the through hole 11c1 of the second cylindrical portion 11c. By using the floating nut 50, the radome side coupling portion 21 can be connected 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. Further, 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-described embodiment shows an example of the content of the present invention, can be combined with another known technique, and is one of the configurations without departing from the gist of the present invention. It is also possible to omit or change the part.

1 Flying body body, 2, 2A Flying body radome, 3 1st heat insulating part, 4 2nd heat insulating part, 5 Electronic equipment, 6 Fixing member, 6a, 11c1 Through hole, 6a1 Counterbore processing part, 6b, 11c2,40 Heat transfer suppression part, 7,7A countersunk screw, 7a head, 7b male screw part, 8 connecting member, 9 hole filling member, 10 housing, 11 main body side connecting part, 11a first cylindrical part, 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 suppression member, 50 floating nut, 51 nut Plate, 52 support plate, 60 faces, 100, 100A, 100B, 100B1, 100B2, 100C flyer, G1, G2 gap.

Claims (7)

A cylindrical missile body that flies toward the target by radio wave guidance,
A columnar first connecting member fixed to the tip side of the flying body body and
A columnar second connecting member provided on the first connecting member and extending radially outward from the first connecting member,
An insertion hole into which the second connecting member is inserted is formed, and the radome for the flying body is connected to the tip end side of the flying body body via the second connecting member and the first connecting member. When,
With
A flying body characterized in that a gap is formed between the inner peripheral surface of the flying body radome and the radial outer surface of the first connecting member. A plurality of the first connecting members are provided on the tip side of the flying body body so as to be separated from each other in the circumferential direction.
The first connecting member is formed with a through hole for inserting a screw to be inserted toward the flying body body.
Two of the first connecting members are provided apart from each other in the axial direction of the flying body body so that the second connecting member sandwiches the through hole.
The first aspect of the present invention, wherein the radome for the flying body is formed with a plurality of pairs of the two insertion holes separated from each other in the axial direction corresponding to the plurality of the first connecting members. Radome body. The second connecting member is a columnar member.
The flying object according to claim 2, wherein one of the two insertion holes in each set has an elliptical shape in which the width in the axial direction is wider than the width in the circumferential direction. .. It is characterized by being provided between the first connecting member and the flying body main body and provided with a heat transfer suppressing portion that reduces the amount of heat transferred from the first connecting member to the flying body main body. The flying object according to any one of claims 1 to 3. Claims 1 to claim include a heat transfer suppressing portion that is provided integrally with the first connecting member and reduces the amount of heat transferred from the first connecting member to the flying body main body. The flying object according to any one of 3. Claims 1 to 3 include a heat transfer suppressing unit that is provided integrally with the flying body main body and reduces the amount of heat transferred from the first connecting member to the flying body main body. The flying object described in any one of the items. The flight according to any one of claims 1 to 6, wherein the tip end side of the flying body main body is provided with a floating nut into which the tip end portion of the screw for fixing the first connecting member is screwed. Sho body.

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