CN112278332A

CN112278332A - Propellant storage tank for aerospace

Info

Publication number: CN112278332A
Application number: CN202011254080.5A
Authority: CN
Inventors: 凌亚
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-11-11
Filing date: 2020-11-11
Publication date: 2021-01-29

Abstract

The invention discloses a propellant storage box for aerospace, which comprises a high-pressure gas box, wherein a first exhaust pipe is welded on the outer wall of one side of the high-pressure gas box, a pressurizer is fixed on the outer wall of the first exhaust pipe, a pressurizing valve is installed on the outer wall, away from a pressure reducer, of the first exhaust pipe, a second exhaust pipe is welded on the outer wall of one side of the lower part of the first exhaust pipe, a material box is welded on the outer wall of the bottom of the high-pressure gas box, a heat insulation plate is welded on the inner wall of the middle part of the material box, a fuel box is arranged on the outer wall of the top of the heat insulation plate, a fuel filling pipe is welded on the outer wall of one side of the. The invention can control the temperature of the oxidant through the refrigerating sheet arranged in the refrigerating groove, the oxidant for spaceflight is in a liquid state, and the liquid oxygen can not be gasified only in a very low temperature state, so the liquid oxygen can be continuously cooled through the refrigerating effect of the refrigerating sheet.

Description

Propellant storage tank for aerospace

Technical Field

The invention relates to the technical field of propellant storage tanks, in particular to a propellant storage tank for aerospace.

Background

The development of aviation fuel goes through a long history process, various fuel systems of different types and models exist in the same period, but the development of aviation fuel is promoted by the fact that the historical change of each aviation engine brings about rapid development and innovation of aviation fuel, and the performance improvement and the change of the engines generate higher performance requirements on the fuel. The development history of the aviation fuel is derived from the development of the aviation engine, the aviation fuel needs to ensure the stability during storage, but the temperature has the greatest influence on the stability, so that a propellant storage tank needs to be invented.

Disclosure of Invention

The invention aims to solve the defects in the prior art and provides a propellant storage tank for aerospace.

In order to achieve the purpose, the invention adopts the following technical scheme:

a propellant storage box for aerospace comprises a high-pressure gas box, wherein a first exhaust pipe is welded on the outer wall of one side of the high-pressure gas box, a pressurizer is fixed on the outer wall of the first exhaust pipe, a pressurizing valve is installed on the outer wall, away from a pressure reducer, of the first exhaust pipe, a second exhaust pipe is welded on the outer wall of one side of the lower portion of the first exhaust pipe, a work bin is welded on the outer wall of the bottom of the high-pressure gas box, a heat insulation plate is welded on the inner wall of the middle portion of the work bin, a fuel tank is arranged on the outer wall of the top of the heat insulation plate, a fuel filling pipe is welded on the outer wall of one side of the top of the fuel tank, an oxidant box is arranged on the outer wall of the bottom of the heat insulation plate, an oxidant filling pipe is welded on the outer wall of one side, the outer wall of one side of the second discharge pipe is fixed with a proportional valve, the lower part of the proportional valve is fixed with a filter box, the outer walls of four sides of the oxidant box are respectively provided with a refrigerating groove, the inner wall of the refrigerating groove is provided with a refrigerating sheet, the outer walls of four sides of the fuel box are respectively provided with a thermostatic groove, and the inner wall of the thermostatic groove is provided with a thermostat.

Preferably, a second heat-insulating layer is arranged in the shell of the fuel tank, and a first heat-insulating layer is arranged in the shell of the oxidant tank.

Preferably, the bottom of the outer wall of one side of the fuel tank is provided with a discharge hole, and the inner wall of the discharge hole is welded with the outer wall of the second discharge pipe.

Preferably, the outer wall of one side of the top of the high-pressure air box is provided with a filling port, and the inner wall of the filling port is welded with a filling air pipe.

Preferably, the top of the outer wall of the other side of the oxidant box is provided with a mounting opening, and the inner wall of the mounting opening is welded with the outer wall of the second exhaust pipe.

Preferably, the outer wall of the top of the thrust chamber is welded with the outer wall of the bottom of the material box.

The invention has the beneficial effects that:

1. the temperature of the oxidant can be controlled by the refrigerating sheet arranged in the refrigerating groove, the oxidant for spaceflight is in a liquid state, and the liquid oxygen can not be gasified only in a very low temperature state, so that the liquid oxygen can be continuously cooled by the refrigerating effect of the refrigerating sheet, and the liquid oxygen is prevented from being gasified;

2. through the thermostat that the constant temperature tank inside set up, can control the temperature to the inside fuel of fuel tank, prevent to cause the influence because of the high temperature or low excessively to fuel, can filter the screening with the impurity in the fuel through the rose box, make the fuel that obtains more accurate pure.

Drawings

FIG. 1 is a front view of the overall structure of a propellant tank for aerospace use in accordance with the present invention;

FIG. 2 is a cross-sectional view of an oxidizer tank configuration for an aerospace propellant tank in accordance with the present invention;

fig. 3 is a structural cross-sectional view of a fuel tank of a propellant tank for aerospace use according to the present invention.

In the figure: 1 high-pressure gas tank, 2 first exhaust pipe, 3 decompressor, 4 pressurizing valve, 5 second exhaust pipe, 6 material box, 7 heat insulation plate, 8 fuel tank, 9 fuel filling pipe, 10 oxidant tank, 11 oxidant filling pipe, 12 first discharge pipe, 13 propelling valve, 14 thrust chamber, 15 second discharge pipe, 16 proportional valve, 17 filter tank, 18 refrigerating tank, 19 refrigerating sheet, 20 first heat preservation layer, 21 thermostatic tank, 22 thermostat and 23 second heat preservation layer.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.

Embodiment 1, referring to fig. 1-3, a propellant storage tank for aerospace, includes a high pressure gas tank 1, a first exhaust pipe 2 welded to an outer wall of one side of the high pressure gas tank 1, a pressurizer 3 fixed to an outer wall of the first exhaust pipe 2, a filling port opened to an outer wall of one side of a top of the high pressure gas tank 1, a filling pipe welded to an inner wall of the filling port, a pressurizing valve 4 mounted to an outer wall of the first exhaust pipe 2 away from the decompressor 3, a second exhaust pipe 5 welded to an outer wall of one side of a lower portion of the first exhaust pipe 2, a tank 6 welded to an outer wall of a bottom of the high pressure gas tank 1, a thermal insulation plate 7 welded to an inner wall of a middle portion of the tank 6, a fuel tank 8 arranged to an outer wall of a top of the thermal insulation plate 7, a fuel pipe 9 welded to an outer wall of one side of a top of the fuel tank 8, the bottom of the outer wall of one side of the fuel tank 8 is provided with a discharge port, the inner wall of the discharge port is welded with the outer wall of a second discharge pipe 15, the outer wall of the bottom of the thermal insulation plate 7 is provided with an oxidant tank 10, the outer wall of one side of the top of the oxidant tank 10 is welded with an oxidant filling pipe 11, the top of the outer wall of the other side of the oxidant tank 10 is provided with a mounting port, the inner wall of the mounting port is welded with the outer wall of a second exhaust pipe 5, the bottom of the outer wall of the other side of the oxidant tank 10 is welded with a first discharge pipe 12, the outer wall of the first discharge pipe 12 is fixed with a propulsion valve 13, the outer wall of one side of the first discharge pipe 12 is welded with a thrust chamber 14, the outer wall of one side of the thrust chamber 14 is welded with a second discharge pipe 15, the outer wall of the top of the thrust chamber 14 is welded with the, and refrigeration piece 19 is installed to refrigeration groove 18 inner wall, thermostatic bath 21 has all been opened to four side outer walls of fuel tank 8, and thermostat 22 is installed to thermostatic bath 21 inner wall, refrigeration piece 19 through refrigeration groove 18 internally mounted can carry out temperature control to the oxidant, the oxidant of aerospace usefulness is all in liquid state, only liquid oxygen can not gasify under extremely microthermal state, consequently, can last the cooling to liquid oxygen through the refrigeration effect of refrigeration piece 19, prevent that liquid oxygen from taking place the gasification, thermostat 22 through the inside setting of thermostatic bath 21, can control the temperature to the fuel of fuel tank 8 inside, prevent to cause the influence because of the high temperature or low excessively to the fuel, can filter the screening with the impurity in the fuel through rose box 17, make the fuel that obtains more pure.

Fuel is first fed into the fuel tank 8 through the fuel filler pipe 9, an oxidizer is then fed into the oxidizer tank 10 through the oxidizer filler pipe 11, then the gas in the high-pressure gas tank 1 is pressurized, the oxidizer and fuel inside the oxidizer tank 10 and the fuel tank 8 are temperature-controlled by the refrigerator 19 and the thermostat 22 when stored, and finally the fuel and oxidizer are injected into the thrust chamber 14 by opening the dosing valve 16 and the push valve 13 when used.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.

Claims

1. The propellant storage tank for aerospace comprises a high-pressure gas tank (1) and is characterized in that a first exhaust pipe (2) is welded on the outer wall of one side of the high-pressure gas tank (1), a pressurizer (3) is fixed on the outer wall of the first exhaust pipe (2), a pressurizing valve (4) is installed on the outer wall, away from the decompressor (3), of the first exhaust pipe (2), a second exhaust pipe (5) is welded on the outer wall of one side of the lower portion of the first exhaust pipe (2), a material box (6) is welded on the outer wall of the bottom of the high-pressure gas tank (1), a temperature insulating plate (7) is welded on the inner wall of the middle portion of the material box (6), a fuel box (8) is arranged on the outer wall of the top of the temperature insulating plate (7), a fuel filling pipe (9) is welded on the outer wall of one side of the top of the fuel box (8), an oxidant box (10) is, oxidant case (10) opposite side outer wall bottom welding has first discharging pipe (12), and first discharging pipe (12) outer wall is fixed with propulsion valve (13), first discharging pipe (12) one side outer wall welding has thrust chamber (14), and thrust chamber (14) one side outer wall welding has second discharging pipe (15), second discharging pipe (15) one side outer wall is fixed with proportional valve (16), and proportional valve (16) lower part is fixed with rose box (17), refrigeration groove (18) have all been opened to oxidant case (10) four sides outer wall, and refrigeration piece (19) are installed to refrigeration groove (18) inner wall, thermostatic bath (21) have all been opened to four sides outer wall of fuel tank (8), and thermostat (22) are installed to thermostatic bath (21) inner wall.

2. The propellant tank for aerospace use according to claim 1, wherein the fuel tank (8) has a second insulation (23) within the tank shell and the oxidizer tank (10) has a first insulation (20) within the tank shell.

3. The propellant tank for aerospace use according to claim 1, wherein the fuel tank (8) has a discharge port at the bottom of the outer wall of one side thereof, and the inner wall of the discharge port is welded to the outer wall of the second discharge pipe (15).

4. The propellant tank for aerospace as claimed in claim 1, wherein a filling port is formed in the outer wall of one side of the top of the high-pressure gas tank (1), and a filling gas pipe is welded to the inner wall of the filling port.

5. The propellant tank for aerospace use according to claim 1, wherein the oxidizer tank (10) is provided with a mounting opening at the top of the outer wall at the other side, and the inner wall of the mounting opening is welded with the outer wall of the second vent pipe (5).

6. The propellant tank for aerospace use of claim 1, wherein the outer wall of the top of the thrust chamber (14) is welded to the outer wall of the bottom of the tank (6).