JP2018179470A - Flying body - Google Patents

Abstract

PROBLEM TO BE SOLVED: To obtain a body structure of a flying body having improved heat insulation and light weight so as to withstand heat inflow due to aerodynamic heating. SOLUTION: A cylindrical porous metal portion 9 formed by laminating a plurality of porous metal portions 3, 4 and 5 having different porosities, and a heat insulating portion 2 fixed to the outer periphery of the porous metal portion 9 are provided. In preparation, form the body of the aurora. Further, in the porous metal portion 9, the metal portions are sequentially laminated from the outer surface to the inner surface of the cylinder so that the porosity is gradually lowered, thereby obtaining a body structure having high heat resistance to aerodynamic heating. [Selection diagram] Fig. 1

Description

  The present invention relates to a fuselage of a flying body having a heat resistant structure.

  Flying bodies flying at high speed are affected by aerodynamic heating. In order to reduce the influence by aerodynamic heating, there is known a technique of providing a heat insulating material on the outer periphery of a radome ring of a flying object (see, for example, Patent Document 1).

  Moreover, since weight reduction is desired for the flying object, it is general to use an aluminum alloy having a small specific gravity. However, when the heat resistance temperature performance requirement for aerodynamic heating is high, a titanium alloy having a specific gravity larger than that of an aluminum alloy may be used.

  Furthermore, as disclosed in Patent Document 1, there is also a method of cooling using a refrigerant in order to suppress a temperature rise due to aerodynamic heating of a flying object. However, a pipe portion for supplying the refrigerant is required, and the mass is increased by providing a space for piping the pipe portion and a mounting structure (see, for example, Patent Document 2).

JP, 2016-173189, A JP-A-6-249598

  Some flying vehicles reach supersonic velocity or hypersonic velocity in a short time of a few seconds. Some are flying at supersonic speeds for several minutes or more, and aerodynamic heating exposes the body to high temperatures.

  Since the fuselage of such a flying body is subjected to large aerodynamic loading, aerodynamic heating and thermal shock, high strength, high heat resistance and high thermal shock resistance are required. For this reason, it is common to use a heat-resistant titanium alloy as a fuselage material, or use an aluminum alloy having a low specific gravity among metals, and provide a heat insulating material on the outer periphery thereof.

  If the flight speed is further increased or the flight time is further increased and the total amount of aerodynamic heating is increased, the temperature of the fuselage of the flight body exceeds the heat resistance temperature, and the heat resistance necessary for the structure can not be secured There was a problem of causing sex. In addition, there is also a problem that heat may flow into the inside of the vehicle to cause the temperature of the internally mounted device to exceed the allowable temperature.

  In this case, it is also possible to suppress the temperature rise of the fuselage due to aerodynamic heating by thickening the fuselage and the heat insulating material to increase the heat capacity, but this increases the mass and the flight performance of the projectile There was also a problem of deterioration.

  The present invention has been made in view of the above, and it is an object of the present invention to obtain a fuselage structure of a high heat resistance to aerodynamic heating.

  The fuselage of the projectile according to the present invention comprises a cylindrical porous metal part formed by laminating a plurality of porous metal parts having different porosities, and a heat insulating part fixed to the outer periphery of the porous metal part. It is

  According to the present invention, it is possible to obtain a fuselage structure of a flying body having high heat resistance to aerodynamic heating.

FIG. 2 is a view showing the configuration of a flying object according to Embodiment 1; FIG. 2 is a cross-sectional view showing a structure of a heat-resistant fuselage of the flying object according to Embodiment 1. FIG. 7 is a cross-sectional view showing the structure of the heat-resistant body of the flying object according to Embodiment 2.

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

  FIG. 1 is a view showing the configuration of the flying object according to the first embodiment. In FIG. 1, the flying object 20 comprises a radome 30, a heat resistant fuselage 10 and a propulsion device 1. The radome 30 is provided in front of the flying object 20. The propulsion device 1 is provided at the rear of the flying object 20. The heat resistant fuselage 10 is provided between the radome 30 and the propulsion device 1, and its rear edge is fixed to the fuselage 40 at the outer periphery of the propulsion device 1.

  The radome 30 has a hollow conical shape inside, and is made of a heat-resistant dielectric material. The radome 30 has a part of the electronic device 7 housed therein and is fixed to the front edge of the heat resistant fuselage 10. The heat-resistant body 10 has a cylindrical shape. The other part of the electronic device 7 is disposed inside the heat resistant body 10, and the electronic device 7 is fixed to the inner surface of the heat resistant body 10.

  The propulsion device 1 is composed of a cylindrical body 40. In the propulsion device 1, a propulsion device section 8 consisting of a fuel tank, a propulsion engine, a nozzle and the like which are essential for propulsion of the flying object 20 is disposed inside the fuselage 40. It is attached to the inside of the The fuselage 40 has a plurality of wings 50 attached around its periphery. The wing 50 is provided, for example, with a stabilizing wing at the front and a steering wing at the rear. The body 40 has a fitting cylinder 60 whose outer diameter protruding from the front end has a small diameter.

FIG. 2 is a cross-sectional view showing the structure of the heat resistant fuselage 10 of the flying object according to the first embodiment.
In FIG. 2, the heat-resistant body 10 is composed of a heat insulating portion 2 and a porous metal portion 9. The porous metal portion 9 has a cylindrical shape. The heat insulating part 2 is fixed to the outside of the porous metal part 9 and the body 40 by adhesion. The inner periphery of the porous metal portion 9 in the heat-resistant body 10 is fitted to the outer periphery of the fitting cylinder 60 of the body 40 and fixed to the body 40. The heat-resistant body 10 is fastened to the fitting cylinder 60 of the body 40, for example, by the engagement of a male screw (bolt) and a female screw (a screw hole, a nut, etc.) (not shown).

  In the porous metal portion 9, the metal portion 3, the metal portion 4 and the metal portion 5 are integrally sintered, laminated, and integrally molded. The metal parts 3, 4 and 5 are made of porous metals having different porosities, respectively. The metal parts 3, 4 and 5 are integrally molded by, for example, laser melting and laminating a powdery tungsten alloy using a three-dimensional metal lamination molding technology.

  Here, the porosity of the metal part 3 is higher than the porosity of the metal part 4 and the heat resistance is high. The porosity of the metal part 4 is higher than the porosity of the metal part 5 and the heat resistance is high. The metal portion 5 is twice as high in rigidity as the metal portion 3, and the metal portion 5 is higher in rigidity than the metal portion 4. The metal portion 4 has higher rigidity than the metal portion 3.

  By this, the metal part 3 acts as a heat-resistant member, and the metal parts 4 and 5 act as a structural member. The outer periphery of the fitting cylinder 60 of the body 40 is inserted into and fixed to the inner periphery of the metal portion 5.

  The upper and lower layers may be formed entirely of the metal portion 5 only at the end edge portion of the heat resistant fuselage 10 on the propulsion device 1 side. Thereby, when the heat resistant fuselage 10 is fastened to the fitting cylinder 60 of the fuselage 40, it is possible to enhance the material strength and the fastening force against the compressive force of the bolt hole and the periphery thereof.

The heat insulating unit 2 suppresses the temperature rise due to the heat generated by the aerodynamic heating by the heat of vaporization. Although the heat insulation part 2 is formed of ceramics, resin containing carbon fiber, etc., or an ablation material, it is not limited to this.
The body 40 is formed of, for example, a tungsten alloy.

The fuselage structure of the flying object 20 according to the first embodiment is configured as described above, and operates as follows.
When the flying object 20 flies at supersonic speed, heat inflow due to aerodynamic heating occurs in the direction indicated by the arrow A in FIG. The heat generated by the aerodynamic heating is transferred to the metal portion 3 and the body 40 of the propulsion device 1 through the heat insulating portion 2 respectively.

  Since the metal part 3 is a porous metal and has a large porosity, the heat conductivity is lowered due to the plurality of pores, and it is difficult to transmit the temperature rise due to the aerodynamic heating to the inside. For this reason, the temperature rise of the metal parts 4 and 5 by the aerodynamic heating transmitted via the heat insulation part 2 is suppressed.

In addition, although the temperature of the metal portion 3 is higher than that of the metal portions 4 and 5, since the metal portion 3 is not treated as a structural member, the heat resistant temperature of the material may not be considered.
The metal portion 4 is intermediate between the metal portion 3 and the metal portion 5 and relays each thermally and structurally.

The metal portion 5 has a porosity twice or more lower than that of the metal portion 3 and has high rigidity and high material strength. For this reason, the metal part 5 is used as a structural strength member for fixing to the propulsion device 1.
Further, the heat resistant fuselage 10 uses integral porous metal parts 3 to 5 and arranges the metal part 3 in the portion closest to the heat insulating part 2 of the fuselage outer surface of the flying object 20, and the flying object The metal part 5 is disposed at a portion closest to the inside of the 20 trunks. Therefore, it is possible to realize the suppression of the temperature rise of the heat-resistant body 10 and the structural high rigidity similar to that of a normal metal member. As a result, it is possible to obtain the fuselage structure of the highly heat-resistant projectile 20 capable of withstanding the heat inflow due to the aerodynamic heating from the front of the projectile 20.

  In addition, the heat-resistant body 10 achieves weight reduction by using the metal portion 3 having a high porosity as the porous metal portion 9 in the porous metal portions 3 to 5 constituting the porous metal portion 9. It is possible.

The heat resistant fuselage 10 is applied to the fuselage between the radome 30 and the propulsion device 1 to enhance the heat resistance of the forward part of the flying object 20 and to reduce the weight of the forward part of the flying object 20. Thus, it is possible to reduce the weight of the flying body 20 while maintaining the steering stability of the flying body 20 by the steering blades.
Of course, the heat resistant fuselage 10 may be applied to the fuselage 40 constituting the propulsion device 1.

  As described above, the body of the flying object 20 according to the first embodiment includes the cylindrical porous metal portion 9 formed by laminating a plurality of porous metal portions (3, 4 and 5) different in porosity. A heat-resistant body 10 having a heat insulating portion 2 fixed to the outer periphery of the porous metal portion 9 is provided.

Further, the porous metal portion 9 may be characterized in that the metal portions (3, 4, 5) are sequentially laminated so that the porosity gradually decreases from the cylindrical outer surface to the inner surface.
Furthermore, the porous metal portion 9 may be characterized in that it is coupled to the body 40 of the propulsion device 1.

This has the effect of being able to obtain the fuselage structure of the flying object 20 having high heat resistance to aerodynamic heating.
Further, since the porous metal portion 9 has a plurality of pores, it is possible to suppress the temperature rise due to the aerodynamic heating transmitted to the porous metal portion 9 through the heat insulating portion 2.
Thus, the heat inflow of the porous metal portion 9 to the inside of the metal portion 5 is suppressed, and the temperature of the internally mounted device such as the electronic device 7 and the propulsion device portion 8 is prevented from rising above the allowable temperature. It becomes possible.

In addition, the porosity of the porous metal portion 9 is changed so that the porosity of the laminated metal portions 3, 4 and 5 decreases stepwise. The low metal part 5 can be used as a highly rigid structural member.
Furthermore, by using the metal part 3 having a particularly high porosity as compared with the metal parts 4 and 5 in the porous metal part 9, the weight of the fuselage of the flying object 20 can be reduced.

Second Embodiment
FIG. 3 is a view showing the structure of the heat resistant fuselage 10 of the flying object 20 according to the second embodiment of the present invention.
In the porous metal portion 9 of the heat-resistant body 10 according to the second embodiment, the impregnating agent 6 penetrates into the pores of the metal portions 3, 4 and 5. The other configuration and operation are the same as in the first embodiment, and the heat insulating portion 2 is fixed to the upper surface of the porous metal portion 9.

  In the heat-resistant fuselage 10 according to the second embodiment, the temperature rising due to the aerodynamic heating transmitted through the heat insulating portion 2 causes the impregnating agent 6 of the porous metal portion 9 to melt or vaporize, and a phase from the solid phase to the liquid phase or the gas phase Change. The temperature rise on the metal portion 5 side inside the heat-resistant body 10 is suppressed by the latent heat accompanying the phase change.

  As described above, the heat-resistant body 10 according to the second embodiment is characterized in that the porous metal portion 9 is impregnated with the impregnating agent 6.

  The latent heat of the impregnating agent 6 impregnated in the porous metal portion 9 is used to suppress the temperature rise of the porous metal portion 9 and the heat flow into the inside of the flying object 20. In this manner, it is possible to prevent the temperature rise of the internally mounted device of the flying object such as the electronic device 7 and the propulsion device unit 8 and the like exceeding the allowable temperature.

  DESCRIPTION OF SYMBOLS 1 propulsion apparatus, 2 heat insulation part, 3 metal parts, 4 metal parts, 5 metal parts, 6 metal parts, 7 electronic devices, 8 propulsion apparatus parts, 9 porous metal parts, 10 heat resistant body, 20 projectiles, 30 Radome, 40 fuselage, 50 wings, 60 fitting cylinders.

Claims (4)

A cylindrical porous metal portion formed by laminating a plurality of porous metal portions having different porosity;
A heat insulating portion fixed to the outer periphery of the porous metal portion;
Of the flying body equipped with   The fuselage fuselage according to claim 1, wherein the porous metal portion is formed by sequentially laminating the metal portions so that the porosity gradually decreases from the cylindrical outer surface to the inner surface.   The fuselage of the projectile according to claim 1 or 2, wherein the porous metal portion is impregnated with an impregnating agent.   The fuselage fuselage according to claim 3, wherein the porous metal part is coupled to the propulsion device fuselage.

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