JP6747368B2 - The fuselage of the flying body - Google Patents

Description

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

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

Further, since it is desired that the flying body be lightweight, it is common to use an aluminum alloy having a small specific gravity. However, when there is a high demand for heat resistant temperature performance for aerodynamic heating, a titanium alloy having a larger specific gravity than an aluminum alloy may be used.

Further, as disclosed in Patent Document 1, there is also a method of cooling using a refrigerant in order to suppress a temperature increase 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 connecting the pipe portion and a mounting structure (see Patent Document 2, for example).

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

Some flying objects reach supersonic or hypersonic speed in a short time of a few seconds and fly. Some of them fly at supersonic speed for several minutes or longer, and the aircraft is exposed to high temperatures due to aerodynamic heating.

Since the body of such a flying body is subjected to a large aerodynamic load, 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 titanium alloy having high heat resistance or an aluminum alloy having a low specific gravity among metals as the body material to provide a heat insulating material on the outer periphery thereof.

If the flight speed becomes faster or the flight time becomes longer and the total amount of aerodynamic heating increases, the temperature of the fuselage of the flying body will exceed the heat resistant temperature, and it will be impossible to secure the heat resistance strength necessary for the structure. There was a problem of causing sex. There is also a problem in that heat may flow into the flying body and the temperature of the internal equipment may exceed the allowable temperature.

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

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

A fuselage of a flying object 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 a thing.

According to the present invention, there is an effect that a fuselage structure of a flying body having high heat resistance against aerodynamic heating can be obtained.

It is a figure which shows the structure of the flying body which concerns on Embodiment 1. FIG. 3 is a cross-sectional view showing the structure of the heat resistant fuselage body of the flying object according to the first embodiment. FIG. 6 is a cross-sectional view showing the structure of a heat resistant fuselage body of a flying object according to a second embodiment.

Hereinafter, a fuselage structure of a flying object according to Embodiment 1 of the present invention will be described in detail with reference to the drawings. The present invention is not limited to the first embodiment.

FIG. 1 is a diagram showing a structure of a flying object according to the first embodiment. In FIG. 1, the flying body 20 is composed of a radome 30, a heat-resistant body 10, and a propulsion device 1. The radome 30 is provided in front of the flying body 20. The propulsion device 1 is provided behind the flying body 20. The heat-resistant body 10 is provided between the radome 30 and the propulsion device 1, and its rear edge is fixed to the body 40 on the outer periphery of the propulsion device 1.

The radome 30 has a hollow conical shape and is made of a dielectric material having high heat resistance. The radome 30 accommodates a part of the electronic device 7 inside and is fixed to the front edge of the heat-resistant body 10. The heat resistant body 10 has a cylindrical shape. The other part of the electronic device 7 is arranged 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 includes a cylindrical body 40. In the propulsion device 1, a propulsion device section 8 including a fuel tank, a propulsion engine, a nozzle, and the like, which are indispensable for propelling the flying vehicle 20, is disposed inside the fuselage 40. Is installed inside the. A plurality of wings 50 are attached to the outer periphery of the body 40. The wing 50 has, for example, a stabilizing wing at the front part and a steering wing at the rear part. 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 body 10 of the flying object according to the first embodiment.
In FIG. 2, the heat resistant body 10 is composed of a heat insulating part 2 and a porous metal part 9. The porous metal part 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 circumference of the porous metal portion 9 of the heat resistant body 10 is fitted to the outer circumference of the fitting cylinder 60 of the body 40 and is fixed to the body 40. The heat-resistant body 10 is fastened to the fitting cylinder 60 of the body 40, for example, by engaging a male screw (bolt) and a female screw (screw hole, nut, etc.) not shown.

The porous metal part 9 is formed by integrally sintering the metal part 3, the metal part 4, and the metal part 5 and laminating them. The metal parts 3, 4, and 5 are made of porous metals having different porosities. The metal parts 3, 4, and 5 are integrally molded by, for example, using a three-dimensional metal additive manufacturing technique, laser melting a powdery tungsten alloy and laminating it.

Here, the porosity of the metal part 3 is higher than that of the metal part 4, and the heat resistance is high. The porosity of the metal part 4 is higher than that of the metal part 5, and the heat resistance is high. The rigidity of the metal part 5 is more than double that of the metal part 3, and the rigidity of the metal part 5 is higher than that of the metal part 4. The metal portion 4 has higher rigidity than the metal portion 3.

Thereby, the metal part 3 acts as a heat resistant member, and the metal parts 4 and 5 act as structural members. The outer circumference of the fitting cylinder 60 of the body 40 is inserted and fixed to the inner circumference of the metal part 5.

Note that the upper and lower layers may be entirely formed by the metal part 5 only at the edge portion of the heat-resistant body 10 on the propulsion device 1 side. Accordingly, when the heat resistant body 10 is fastened to the fitting tube 60 of the body 40, it is possible to increase the material strength and the fastening force against the compressive force of the bolt hole and its periphery.

The heat insulating section 2 suppresses a temperature rise due to heat generated by aerodynamic heating by vaporization heat. The heat insulating portion 2 is formed of ceramics, carbon fiber-containing resin, or the like, or an ablation material, but is not limited to this.
The body 40 is formed of, for example, a tungsten alloy.

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

Since the metal part 3 is a porous metal and has a high porosity, the plurality of holes have a low thermal conductivity, and it is difficult to convey the temperature rise due to aerodynamic heating to the inside. Therefore, the temperature rise of the metal parts 4 and 5 due to the aerodynamic heating transmitted through the heat insulating part 2 is suppressed.

Further, although the temperature of the metal portion 3 rises higher than that of the metal portions 4 and 5, since it is not treated as a structural member, it is not necessary to consider the heat resistant temperature of the material.
The metal portion 4 is located between the metal portion 3 and the metal portion 5, and relays each of them thermally and structurally.

The metal part 5 has a porosity more than twice as low as that of the metal part 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.
The heat-resistant fuselage 10 uses the integrated porous metal parts 3 to 5 and arranges the metal part 3 on the outer surface of the fuselage 20 closest to the heat insulating part 2 and The metal part 5 is arranged at a portion of the 20 closest to the inside of the body. Therefore, it is possible to suppress the temperature rise of the heat-resistant body 10 and achieve the structural high rigidity similar to that of a normal metal member. As a result, it is possible to obtain a fuselage structure of the flying body 20 having high heat resistance capable of withstanding heat inflow due to aerodynamic heating from the front of the flying body 20.

In addition, in the heat-resistant body 10, in the porous metal parts 3 to 5 forming the porous metal part 9, the metal part 3 having a high porosity is used for the porous metal part 9 to reduce the weight. It is possible.

By applying the heat resistant fuselage 10 to the fuselage between the radome 30 and the propulsion device 1, the heat resistance of the front part of the flying body 20 is increased and the front part of the flying body 20 is reduced in weight. Therefore, it is possible to reduce the weight of the flying object 20 while maintaining the steering stability of the flying wings of the flying object 20.
Of course, the heat-resistant body 10 may be applied to the body 40 that constitutes the propulsion device 1.

As described above, the fuselage of the flying body 20 according to the first embodiment includes the cylindrical porous metal portion 9 formed by laminating a plurality of porous metal portions (3, 4, 5) having different porosities. 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 part 9 may be characterized in that the metal parts (3, 4, 5) are laminated in order from the outer surface of the cylinder toward the inner surface thereof so that the porosity gradually decreases.
Further, the porous metal part 9 may be connected to the body 40 of the propulsion device 1.

As a result, the fuselage structure of the flying body 20 having high heat resistance against aerodynamic heating can be obtained.
Further, since the porous metal portion 9 has a plurality of holes, it is possible to suppress the temperature rise due to aerodynamic heating transmitted to the porous metal portion 9 via 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 electronic equipment 7, the propulsion equipment portion 8 and the like mounted on the inside of the flying body is prevented from exceeding the allowable temperature. It becomes possible.

In addition, since the porous metal portion 9 is changed so that the porosity of the laminated metal portions 3, 4, and 5 gradually decreases, the porosity of the metal portions 3 and 4 is particularly higher than that of the metal portions 3 and 4. The low metal part 5 can be used as a highly rigid structural member.
Further, by using the metal part 3 having a particularly high porosity as compared with the metal parts 4 and 5 for the porous metal part 9, the weight of the body of the flying body 20 can be reduced.

Embodiment 2.
FIG. 3 is a diagram showing the structure of the heat resistant fuselage 10 of the flying body 20 according to the second embodiment of the present invention.
In the porous metal part 9 of the heat-resistant body 10 according to the second embodiment, the impregnating agent 6 has penetrated into the pores of the metal parts 3, 4, and 5. Other configurations and operations are the same as those 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 body 10 according to the second embodiment, the impregnating agent 6 of the porous metal part 9 is melted or vaporized due to the temperature rise due to aerodynamic heating transmitted through the heat insulating part 2, and the solid phase is changed to the liquid phase or the gas phase. Change. Due to the latent heat accompanying the phase change, the temperature rise on the metal portion 5 side inside the heat resistant body 10 is suppressed.

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

By utilizing the latent heat of the impregnating agent 6 with which the porous metal portion 9 is impregnated, the temperature rise of the porous metal portion 9 and the heat flow into the flying body 20 are suppressed. Thus, it becomes possible to prevent the temperature of the electronic equipment 7, the propulsion equipment 8 and other internal equipment mounted on the flying body from exceeding the allowable temperature.

1 propulsion device, 2 heat insulation part, 3 metal part, 4 metal part, 5 metal part, 6 metal part, 7 electronic equipment, 8 propulsion equipment part, 9 porous metal part, 10 heat resistant fuselage, 20 flying body, 30 Radome, 40 body, 50 wings, 60 fitting cylinder.

Claims (2)

A cylindrical porous metal part formed by laminating a plurality of porous metal parts having different porosities,
A heat insulating portion fixed to the outer periphery of the porous metal portion,
Equipped with
The porous metal portion is formed by a plurality of metal portions that are sequentially laminated and integrally sintered so that the porosity gradually decreases from the outer surface to the inner surface of the cylinder, and the inner metal portion is driven. A fuselage of a flying body that is joined to the fuselage of the device . The fuselage of the flying body according to claim 1 , wherein the porous metal part has an impregnating agent penetrated into the pores of the metal part .

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