A bipropellant rocket engine

Abstract

The present invention discloses a bicomponent rocket engine, comprising a propellant storage tank, a combustion chamber and a flamethrower; an oxygen tank and a fuel tank are arranged in the propellant storage tank. The present invention can simultaneously control and adjust the amount of fuel and oxidant entering the combustion chamber by controlling the solenoid valve, thereby changing the thrust generated by the combustion; the change in piston movement caused by the change in oxygen flow rate will synchronously affect the flow rate of the fuel, so that the fuel flow rate and the oxygen flow rate enter the combustion chamber in a specific ratio, so that the fuel and oxygen are mixed and fully burned; the airbag and the isolation liquid form a double-layer isolation system to avoid chemical penetration caused by physical impact caused by the pressure change of oxygen, ensure that oxygen and fuel will not be accidentally mixed before reaching the combustion chamber, and ensure the safety and reliability of the rocket engine system.

Description

Technical Field

[0001] The invention relates particularly to the field of rocket engines. Background Art

[0002] A rocket is a vehicle that is propelled forward by the reaction force generated by the working fluid ejected by the rocket engine. It carries all the propellants by itself and does not rely on external working fluid to generate thrust. It can fly in or outside the dense atmosphere and is a vehicle for space flight.

[0003] The power unit of a rocket is a device that propels the rocket to fly and obtain a certain speed. The power unit includes an oxidizer tank, a fuel tank, a pump, a combustion chamber and a nozzle. There are two pumps, one of which is fixed between the oxidizer tank and the combustion chamber, and the other is fixed between the fuel tank and the combustion chamber. The nozzle is set at the end of the combustion chamber away from the pump. When the power unit is started, liquid oxygen and fuel will enter the pump as the pump rotates. The pump is used to increase the pressure. The high-pressure liquid propellant is pumped into the combustion chamber. When it is ignited by the ignition device, high-temperature and high-pressure gas will be generated and ejected from the tail nozzle, generating a strong thrust to push the rocket into flight.

[0004] However, the existing technology has a complex structure, especially the structure of the turbopump, which adds a lot of cost to the rocket. Summary of the invention

[0005] In order to overcome the above-mentioned shortcomings, the present invention aims to provide a technical solution that can solve the above-mentioned problems.

[0006] A bipropellant rocket engine comprises an oxygen tank, a fuel tank, a combustion chamber and a flamethrower; an oxygen tube is installed at one end of the oxygen tank, and the oxygen tube is respectively connected to the fuel tank and the combustion chamber; a piston for squeezing fuel is arranged in the fuel tank, and the connection between the fuel tank and the oxygen tube is located on the side of the piston away from the fuel; a fuel tube is arranged at one end of the fuel tank for filling fuel, and the other end of the fuel tube is connected to the combustion chamber;

[0007] The oxygen pipe is provided with a first one-way valve at one end close to the combustion chamber, and the fuel pipe is provided with a second one-way valve;

[0008] Preferably, the first one-way valve and the second one-way valve are both convex in design and are respectively provided with a first crack and a second crack, and the size of the first crack is smaller than the size of the second crack;

[0009] Preferably, the first one-way valve and the second one-way valve are made of polyvinylidene fluoride material;

[0010] Preferably, a solenoid valve is provided at one end of the oxygen tube close to the oxygen tank;

[0011] Preferably, the oxygen tank is located above the fuel tank;

[0012] Preferably, an air bag is further provided in the fuel tank, the air bag is located on the side of the piston away from the fuel, and the air bag is connected to the oxygen pipe;

[0013] Preferably, the fuel tank is filled with an isolation liquid, and the isolation liquid is located on a side of the piston facing away from the fuel.

[0014] Compared with the prior art, the advantages of the present invention are:

[0015] The present invention can simultaneously control and adjust the amount of fuel and oxidant entering the combustion chamber by controlling the electromagnetic valve, thereby changing the thrust generated by combustion.

[0016] The change in piston movement caused by the change in oxygen flow rate of the present invention will synchronously affect the flow rate of fuel, so that the fuel flow rate and the oxygen flow rate enter the combustion chamber in a specific ratio, so that the fuel and oxygen are mixed and fully burned.

[0017] The airbag and isolation fluid of the present invention form a double-layer isolation system, which avoids chemical penetration caused by physical impact caused by pressure changes of oxygen, ensures that oxygen and fuel will not accidentally mix before reaching the combustion chamber, and ensures the safety and reliability of the rocket engine system.

[0018] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0020] Figure 1 It is a structural schematic diagram of the present invention.

[0021] Figure 2 yes Figure 1 Enlarged view of circle A in center.

[0022] Figure 3 It is a three-dimensional diagram of the first one-way valve of the present invention.

[0023] Figure 4 It is a stereoscopic view of a second one-way valve of the present invention. DETAILED DESCRIPTION

[0024] The technical solutions in the embodiments of the present invention are described clearly and completely below. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0025] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limitations on the present invention.

[0026] In addition, in the description of the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", etc. should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, it can also be the internal communication of two components, it can be a wireless connection, or it can be a wired connection. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0027] In addition, the technical features involved in the different embodiments of the present invention described later can be combined with each other as long as they do not conflict with each other.

[0028] See also Figure 1-2 In an embodiment of the present invention, a bipropellant rocket engine includes an oxygen tank 110, a fuel tank 120, a combustion chamber 200 and a flamethrower 300;

[0029] The oxygen tank 110 is used to store oxygen and compress the oxygen to be in a high-pressure state. The oxygen tank 110 is equipped with an oxygen pipe 130, which simultaneously connects the oxygen tank 110, the fuel tank 120 and the combustion chamber 200. The solenoid valve 140 controls the on / off or oxygen flow of the oxygen pipe 130 near the oxygen tank 110.

[0030] The fuel tank 120 is used to store liquid fuel, such as kerosene, methanol and other common fuels; a piston 190 for squeezing the fuel is provided inside the fuel tank 120, and the piston 190 of the fuel tank 120 isolates the fuel on one side of the fuel tank 120, and the connection between the fuel tank 120 and the oxygen pipe 130 is located on the side of the piston 190 away from the fuel; one end of the fuel tank 120 filled with fuel is connected to the combustion chamber 200 through the fuel pipe 150, and the fuel pipe 150 is provided with a second one-way valve 162. Example 1

[0031] During the rocket launch phase, the bipropellant rocket engine works in the following steps:

[0032] S1. Oxygen is filled into the oxygen tank 110 and is compressed into a high-pressure state for storage. Fuel is filled into the fuel tank and a piston 190 is provided above the fuel. At this time, the solenoid valve 140 is in a closed state, preventing oxygen from entering the fuel tank 120 and the combustion chamber 200. Due to the lack of pressure, the fuel in the fuel tank 120 will not break through the resistance of the second one-way valve 162 and enter the combustion chamber 200;

[0033] S2. When the rocket engine needs to be started, the solenoid valve 140 is opened. Part of the high-pressure oxygen is injected into the airbag 170 through the oxygen pipe 130. The airbag 170 expands under pressure, pushing the piston 190 to squeeze the liquid fuel in the fuel tank 120. The fuel overcomes the resistance of the second one-way valve 162 under pressure, passes through the second crack 1620 and flows into the combustion chamber 200 along the fuel pipe 150. At the same time, part of the oxygen in the oxygen pipe 130 also overcomes the resistance of the first one-way valve 161 and enters the combustion chamber 200 at the same time;

[0034] S3, the oxygen and fuel entering the combustion chamber 200 are fully mixed, and a violent combustion reaction occurs, and the combustion releases a large amount of heat, causing the gas in the combustion chamber 200 to expand rapidly;

[0035] S4, the high-pressure gas is ejected backward through the flamethrower 300 to form high-speed gas. According to Newton's third law, the rocket engine will be subjected to a forward reaction force, thereby pushing the rocket engine to fly forward;

[0036] S5. By controlling the solenoid valve 140 in a timely manner, the amount of fuel and oxidant entering the combustion chamber 200 can be controlled and adjusted at the same time, thereby changing the thrust generated by the combustion. Example 2

[0037] like Figure 3-4 As shown, in the next embodiment of the present invention, the first one-way valve 161 and the second one-way valve 162 are both convex in design and are provided with a first crack 1610 and a second crack 1620 respectively.

[0038] Taking the second one-way valve 162 in the fuel pipe 150 as an example, the second one-way valve 162 has a concave surface on the side in contact with the fuel, and a convex surface on the side away from the fuel. When the fuel is squeezed, the pressure on the concave surface of the second one-way valve 162 is higher than the pressure on the convex surface, and the second crack 1620 expands and opens, allowing the fuel to smoothly pass through the fuel pipe 150 into the combustion chamber 200. The expansion size of the second crack 1620 depends on the degree of pressure on the fuel.

[0039] When the solenoid valve 140 is closed, the pressure in the fuel tank 120 may be lower than the pressure in the combustion chamber 200. The convex surface of the second check valve 162 is acted upon by the reverse pressure, causing the second crack 1620 to shrink and close, thereby preventing the fluid in the fuel pipe 150 from passing in the reverse direction, thus achieving the one-way cutoff function.

[0040] The first one-way valve 161 and the second one-way valve 162 have a relatively simple structure and do not require complicated alignment and adjustment during installation. Compared with the prior art, this can save rocket engine installation costs.

[0041] Since the movement change of the piston 190 caused by the change of the oxygen flow rate will synchronously affect the flow rate of the fuel, the fuel flow rate and the oxygen flow rate enter the combustion chamber 200 in a specific ratio, so that the fuel and oxygen are mixed and fully burned. The specific ratio of the fuel and oxygen entering the combustion chamber 200 depends on the design of the size of the first crack 1610 and the size of the second crack 1620.

[0042] After the rocket is started, the oxygen introduced into the oxygen pipe 130 is high-pressure oxygen. Due to the high-pressure characteristics and the small gap between oxygen molecules, oxygen can easily pass through the first crack 1610. However, in order to accurately control the oxygen flow rate and prevent the oxygen from being consumed too quickly in the early stage, which will affect the subsequent flight of the rocket, the size of the first crack 1610 is designed to be relatively small, ensuring that oxygen is supplied in an appropriate amount during the flight of the rocket and maintaining the stable operation of the engine.

[0043] At the same time, the fuel stored in the fuel tank 120 is in a liquid state. The driving force for the liquid fuel to be transported to the combustion chamber mainly comes from the pressure exerted on the piston by the original pressure of oxygen, and this pressure offsets the friction of the piston, and the pressure exerted on the fuel is ultimately less than the original pressure of oxygen. Therefore, the second crack 1620 is designed to be larger than the first crack 1610, so as to ensure that the fuel and oxygen enter the combustion chamber at the same time for mixed combustion, meeting the requirements for the normal operation of the rocket. Example 3

[0044] An air bag 170 is also provided in the fuel tank 120 , and the air bag 170 is located on the side of the piston 190 away from the fuel, and one end of the oxygen tube 130 connected to the fuel tank 120 is communicated with the air bag 170 ; an isolation liquid 180 is filled between the side of the piston 190 away from the fuel and the fuel tank 120 .

[0045] When oxygen enters the fuel tank 120 from the oxygen pipe 130, the airbag 170 bears the pressure of oxygen and compresses the piston 190 by its own expansion. The airbag 170 also has an isolation effect on oxygen and fuel, preventing the high-pressure oxygen from physically impacting the gap between the piston 190 and the tank wall and penetrating to the fuel side.

[0046] The isolation liquid 180 forms a sealing layer between the piston 190 and the wall of the fuel tank 120 , and it is difficult for oxygen molecules to pass through this layer of liquid to reach the fuel side, thereby preventing the risk caused by accidental leakage of the airbag 170 .

[0047] Therefore, the airbag 170 and the isolation liquid 180 form a double-layer isolation system, which avoids the physical impact caused by the pressure of oxygen that causes oxygen to penetrate into the fuel, ensures that oxygen and fuel will not accidentally mix before reaching the combustion chamber 200, and ensures the safety and reliability of the rocket engine system.

[0048] In the next embodiment of the present invention, the second one-way valve 162 is made of polyvinylidene fluoride material; this material not only has the advantages of high strength and high toughness, but this common material is also low in cost, saving the cost of manufacturing rocket engines.

[0049] The rocket engine of the present invention accurately controls the flow rate of oxygen through the solenoid valve 140, and allows the fuel and oxygen to flow into the combustion chamber 200 simultaneously through the original pressure of oxygen. Compared with the prior art, the present invention does not need to carry an additional turbopump, thereby reducing the weight of the rocket.

[0050] The present invention can also be applied to propellers of other hypersonic aircraft (such as aircraft and missiles with several times the speed of sound) through adjustments.

[0051] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above and that the present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, the embodiments should be considered exemplary and non-restrictive in all respects, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims be included in the present invention.

Claims

1. A bipropellant rocket engine, characterized in that: Includes oxygen tanks, fuel tanks, combustion chambers and flamethrower tubes; An oxygen tube is installed at one end of the oxygen tank, and the oxygen tube is also connected to the fuel tank and the combustion chamber respectively; A piston for squeezing fuel is provided in the fuel tank, and the connection between the fuel tank and the oxygen pipe is located on the side of the piston away from the fuel; A fuel pipe is provided at one end of the fuel tank for filling fuel, and the other end of the fuel pipe is connected to the combustion chamber; The oxygen pipe is provided with a first one-way valve at one end close to the combustion chamber, and the fuel pipe is provided with a second one-way valve; the first one-way valve and the second one-way valve are both convex in design and are provided with a first crack and a second crack respectively, and the size of the first crack is smaller than the size of the second crack; An air bag is also arranged in the fuel tank, the air bag is located on the side of the piston away from the fuel, and the air bag is connected with the oxygen pipe. The fuel tank is filled with an isolation liquid, and the isolation liquid is located on the side of the piston away from the fuel.

2. The bipropellant rocket engine according to claim 1, characterized in that: The first one-way valve and the second one-way valve are made of polyvinylidene fluoride material.

3. The bipropellant rocket engine according to claim 2, characterized in that: An electromagnetic valve is arranged at one end of the oxygen pipe close to the oxygen tank.

4. The bipropellant rocket engine according to claim 3, characterized in that: The oxygen tank is located above the fuel tank.

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