JPH04368299A - Double fluid type apogee propelling device - Google Patents

Abstract

PURPOSE:To provide a double fluid type apogee propelling device capable of shielding heat so as not to give the heat of an engine body to apparatuses on the liquid oxidant tank and liquid fuel tank sides and also of releasing the heat of the engine body excellently. CONSTITUTION:A skirt shape heat shield 7 to shield heat 1b the liquid oxidant tank 2 and liquid fuel tank 3 sides is arranged around an engine body 4 capable of generating thrust by means of combustion by injecting liquid oxidant 14 and liquid fuel 15 from the liquid oxidant tank 2 and the liquid fuel tank 3 through an injector 5. Furthermore, gold plating 9 as a heat insulating layer having small infrared radiation emissivity is carried out on the outer surface of this heat shield 7, and ceramic coating 10 as a heat release layer having large infrared radiation emissivity is also carried out over the inner surface of the heat shield 7.

Description

[Detailed description of the invention]

0001

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a two-component apogee propulsion device.

0002

2. Description of the Related Art A two-liquid apogee propulsion device has been known as a device for propelling space equipment such as geostationary satellites in outer space.

[0003] FIGS. 3 and 4 show an example of the two-component apogee propulsion device, in which 1 indicates the two-component apogee propulsion device;
2 is a liquid oxidizer tank, 3 is a liquid fuel tank, and 4 is a liquid oxidizer and liquid fuel from the liquid oxidizer tank 2 and the liquid fuel tank 3, which can be injected and combusted by an injector 5 to generate thrust. In the engine body, reference numeral 6 indicates a cover that covers the liquid oxidizer tank 2 and the liquid fuel tank 3, and the area around the upper side of the engine body 4 is provided with heat insulation from the liquid oxidizer tank 2 and the liquid fuel tank 3 side. A skirt-shaped heat shield 7 is provided.

[0004] In the figure, 17 is a thruster for attitude control;
Reference numeral 18 is a connection tool for mounting on a rocket or the like.

[0005]

[Problems to be Solved by the Invention] In the conventional two-component apogee propulsion device 1 described above, since the heat shield 7 made of solid stainless steel is used, the effect of blocking heat from the engine body 4 is relatively weak. There was a problem. However, if the heat shield of the engine body 4 is unnecessarily used to isolate the heat from the engine body 4 using a heat shield made of a material with a high heat isolation effect, the heat dissipation from the engine body 4 will be suppressed, which may lead to an increase in the temperature of the engine body 4. There was that.

The present invention has been made in view of the above-mentioned circumstances, and it is possible to block the heat of the engine body from being applied to the liquid oxidizer tank and the equipment on the liquid fuel tank side, and to effectively dissipate the heat of the engine body. The purpose of the present invention is to provide a two-component apogee propulsion device that can

[0007]

[Means for Solving the Problems] The present invention provides an engine capable of generating thrust by injecting and combusting a liquid oxidizer tank, a liquid fuel tank, and the liquid oxidizer and liquid fuel from both tanks through an injector. A two-component apogee propulsion device comprising a main body and a skirt-shaped heat shield arranged around the engine main body to insulate heat from both tank sides, the outer surface of the heat shield having a low infrared emissivity. The present invention is characterized in that a heat-insulating layer is formed, and a heat-radiating layer having a higher infrared emissivity than the heat-insulating layer is formed on the inner surface of the heat shield.

[0008]

[Operation] Therefore, according to the present invention, the heat of the engine body is
The heat dissipation layer formed on the inner surface of the heat shield actively absorbs heat and radiates it to space, while the liquid oxidizer tank and liquid fuel tank are insulated by the heat insulation layer formed on the outer surface of the heat shield. be done.

[0009]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Examples of the present invention will be described below with reference to the drawings.

FIGS. 1 and 2 show one embodiment of the present invention, and the same parts as in FIGS. 3 and 4 are given the same reference numerals, and their explanation will be omitted.

In the two-component apogee propulsion device 8, which is constructed in substantially the same manner as the two-component apogee propulsion device 1 shown in FIGS. Plating 9 (infrared emissivity 0.03-0
．． 05) and the inner surface of the heat shield 7 is coated with a ceramic coating 10 (infrared emissivity 0.85-0.
90).

The reason why the gold plating 9 and the ceramic coating 10 were selected as described above is that the inventors of the present invention
To create a well-balanced thermal design that can prevent the heat of the engine body 4 from being applied to the devices on the liquid oxidizer tank 2 and liquid fuel tank 3 side, and can also dissipate the heat of the engine body 4 well. We believe that it is effective to apply surface treatments with different infrared emissivities to the outer and inner surfaces of the heat shield 7, and as a result of thermal analysis as shown in Figure 2, we found that the outer surface of the heat shield 7 has different infrared emissivities. small gold plating 9
This is because it was concluded that the combination of applying a ceramic coating 10 with high infrared emissivity to the inner surface of the heat shield 7 is optimal.

That is, the vertical axis in FIG. 2 represents the infrared emissivity of the surface treatment applied to the outer surface of the heat shield 7, and the horizontal axis represents the infrared emissivity of the surface treatment applied to the inner surface of the heat shield 7. According to the results of thermal analysis, if the combination is in the area below curve A, the liquid oxidizer tank 2 and liquid fuel tank 3 side is the allowable temperature range, and if the combination is in the area above curve B, the allowable temperature range is on the engine body 4 side. It was found that the temperature range was Therefore, in the shaded area where the liquid oxidizer tank 2 and liquid fuel tank 3 sides are within the permissible temperature range, but the engine body 4 side is within the permissible temperature range, we investigated the optimal combination of materials and found that the outer surface of the heat shield 7 It was concluded that the combination of applying gold plating 9 to the heat shield 7 and applying ceramic coating 10 to the inner surface of the heat shield 7 is optimal.

11 in FIG. 1 is a two-component apogee propulsion device 8.
12 is an engine support bracket, 13 is a fixture, 14 is a liquid oxidizer, 15 is a liquid fuel, and 16 is a pipe that leads the liquid oxidizer 14 and liquid fuel 15 to the injector 5.

The heat of the engine body 4 is actively absorbed by the ceramic coating 10 applied to the inner surface of the heat shield 7 and radiated into space, while the heat from the liquid oxidizer tank 2 and the liquid fuel The tank 3 side is insulated by gold plating 9 applied to the outer surface of the heat shield 7.

In order to ensure that the heat radiated from the ceramic coating 10 is radiated toward outer space without being returned to the engine body 4, the opening angle of the skirt shape of the heat shield 7 is adjusted to an appropriate degree. Of course, it should be set at a corner.

Therefore, according to the above embodiment, the heat of the engine body 4 is transferred to the liquid oxidizer tank 2 and the liquid fuel tank 3.
It is possible to cut off the heat so as not to give it to the equipment on the side, and also to radiate the heat of the engine body 4 well.

[0018] The two-component apogee propulsion device of the present invention is not limited to the above-mentioned embodiments, but also includes a heat insulating layer formed on the outer surface of the heat shield and a heat dissipation layer formed on the inner surface of the heat shield. Of course, other than gold plating and ceramic coating, various materials included in the shaded area in the figure may be used, and various other changes may be made without departing from the gist of the present invention.

[0019]

Effects of the Invention According to the above-described two-component apogee propulsion system of the present invention, heat from the engine body can be isolated so as not to be applied to the equipment on the liquid oxidizer tank and the liquid fuel tank side. An excellent effect can be achieved in that heat can be dissipated well.

[Brief explanation of drawings]

FIG. 1 is a sectional view of an embodiment of the present invention.

FIG. 2 is a logarithmic table obtained by thermally analyzing the relationship between the infrared emissivity of the surface treatment applied to the outer surface of the heat shield and the infrared emissivity of the surface treatment applied to the inner surface of the heat shield.

FIG. 3 is a partially cutaway front view showing a conventional example.

FIG. 4 is an arrow view in the IV-IV direction of FIG. 3;

[Explanation of symbols]

2 Liquid oxidizer tank 3 Liquid fuel tank 4 Engine body 5 Injector 7 Heat shield 8 Two-component apogee propulsion device 9 Gold plating (heat insulation layer) 10 Ceramic coating (heat radiation layer) 14
Liquid oxidizer 15 Liquid fuel

Claims (1)

[Claims] 1. An engine body comprising: a liquid oxidizer tank; a liquid fuel tank; and an engine body capable of generating thrust by injecting and burning liquid oxidizer and liquid fuel from both tanks through an injector. In the two-component apogee propulsion device, a skirt-shaped heat shield is disposed around the tank to insulate heat from both sides of the tank. A two-component apogee propulsion device, characterized in that a heat radiation layer having a higher infrared emissivity than the heat insulation layer is formed on the inner surface of the shield.