Controllable gas-liquid rocket power system

Abstract

The utility model discloses a controllable gas-liquid rocket power system which comprises an oxygen tank, a fuel bag and a combustion chamber. Liquid fuel is driven to flow by applying pressure to the fuel bag through air pressure in the oxygen tank, no extra pump is needed for conveying, energy loss generated by the pump is avoided, the overall weight of the rocket is reduced, and the rocket can carry more effective loads or reduce the invalid power of a propellant; when the device is recycled and reused, the required maintenance work is relatively simple and convenient, the maintenance cost can be greatly reduced, the maintenance period can be effectively shortened, and the reusability and the economical efficiency of the rocket are improved; in the flying process of the rocket, the fuel bag and the oxygen tank are tightly combined and interact with each other, a certain self-balance adjusting capacity is achieved, and even if the rocket is impacted or vibrated in the flying process, the system can still guarantee stable and balanced supply of fuel and oxygen through an air pressure and hydraulic pressure balance mechanism; and the reliability and the safety of the rocket in the flight process are improved.

Description

Technical Field

[0001] The utility model specifically relates to the field of rockets. Background Art

[0002] A rocket is a vehicle propelled forward by the reaction force of the fluid ejected from its rocket engine. It carries all of its own propellant and does not rely on external fluids for thrust. It can fly both within and outside the dense atmosphere, making it the vehicle for space flight.

[0003] The rocket's power unit 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 powerful thrust to propel the rocket into flight.

[0004] However, there are many problems with existing liquid rocket technology:

[0005] 1. In the prior art, the fuel tank and the oxidizer tank are usually arranged separately, which requires more connecting pipes and supporting structures and occupies a relatively large space;

[0006] 2. Fuel and liquid oxygen in existing technologies usually require specialized pumps for delivery, which increases the complexity of the system and the energy consumption caused by pump friction. The actual specific impulse is often lower than the theoretical specific impulse.

[0007] 3. The existing technology adds an extra turbo pump, which increases the weight of the rocket and takes up effective space;

[0008] 4. Existing technologies rely on complex turbopump systems and valve combinations to control the flow of liquid fuel and oxidizer, which has slow adjustment speed and limited accuracy;

[0009] 5. When existing technologies are recycled and reused, key components such as the turbopump and combustion chamber need to be fully inspected and repaired, resulting in high maintenance costs and a long maintenance cycle.

[0010] 6. When the rocket is subjected to slight impact or vibration during flight, the operation of the turbopump will be affected, resulting in an imbalance in the supply of fuel gas and oxygen. Utility Model Content

[0011] In order to overcome the above-mentioned shortcomings, the present invention aims to provide a technical solution that can solve the above-mentioned problems.

[0012] A controllable gas-liquid rocket propulsion system includes an oxygen tank, a fuel bag, and a combustion chamber; the fuel bag is equipped with a fuel pipe, the oxygen tank is equipped with an oxygen pipe, the oxygen pipe is provided with a first solenoid valve, and the other end of the oxygen pipe is connected to the combustion chamber, the first solenoid valve can control the conduction and shutoff of the oxygen pipe and the oxygen flow rate; the fuel pipe is equipped with a second solenoid valve, and the other end of the fuel pipe is connected to the combustion chamber, the second solenoid valve can control the conduction and shutoff of the fuel pipe and the fuel flow rate;

[0013] Preferably, the fuel bag is arranged in the oxygen tank and has elastic expansion and contraction properties;

[0014] Preferably, the fuel bag is filled with liquid fuel, and the oxygen tank is filled with high-pressure oxygen, so that the hydraulic pressure in the fuel bag and the gas pressure in the oxygen tank are equal.

[0015] Compared with the existing technology, the utility model has multiple advantages:

[0016] The utility model applies pressure to the fuel bag through the air pressure in the oxygen tank to drive the liquid fuel to flow, and does not require an additional pump for transportation, thus avoiding energy loss caused by the pump.

[0017] The utility model places the fuel bag inside the oxygen tank, making the overall layout more compact and effectively saving space inside the rocket.

[0018] The utility model is based on the principle of hydraulic balance between the oxygen tank air pressure and the fuel bag. When the control components such as the solenoid valve are opened, the fuel and oxygen can enter the combustion chamber in a precise proportion under the same original pressure.

[0019] The utility model has a simple structure and reduces the overall weight of the rocket, so that the rocket can carry more effective loads or reduce the propellant reactive power.

[0020] Due to the relatively simple structure of the utility model, the easily worn parts such as turbo pumps are reduced. When the rocket is reused after recovery, the required maintenance work is relatively simple, the maintenance cost can be greatly reduced, and the maintenance cycle can be effectively shortened, thereby improving the reusability and economy of the rocket.

[0021] During the rocket flight, the fuel bag of the utility model is tightly integrated with and interacts with the oxygen tank, and has a certain self-balancing and adjustment capability. Even if it is impacted or vibrated during flight, the system can still ensure a stable and balanced supply of fuel and oxygen through the air pressure and hydraulic pressure balance mechanism, thereby improving the reliability and safety of the rocket during flight.

[0022] Additional aspects and advantages of the present invention will be given in part in the following description and will become apparent from the following description or learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. 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 any creative labor.

[0024] Figure 1 It is a structural sectional view of the present utility model. DETAILED DESCRIPTION

[0025] The following is a clear and complete description of the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only a 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 making creative efforts are within the scope of protection of the present invention.

[0026] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc., indicating directions or positional relationships, are 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.

[0027] Furthermore, in the description of this utility model, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integral connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; internal connections between two components; wireless connections or wired connections. Those skilled in the art will understand the specific meanings of the above terms in this utility model based on the specific circumstances.

[0028] 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.

[0029] See also Figure 1 In an embodiment of the present application, a controllable gas-liquid rocket power system includes an oxygen tank 1, a fuel bag 2 and a combustion chamber 3;

[0030] Oxygen tank 1 stores high-pressure oxygen, serving as an oxidant. Stainless steel was chosen for cost considerations, formed through forging and welding. The tank's thickness was precisely calculated to meet the required strength to withstand pressures exceeding 100 MPa without excessive weight that would affect rocket performance. The tank is also equipped with an overpressure protection valve. If the pressure inside oxygen tank 1 exceeds the threshold, the valve will quickly open to relieve pressure and prevent the tank from bursting.

[0031] Fuel bag 2 is used to store liquid fuel. It is placed inside oxygen tank 1 and has elastic expansion and contraction capabilities. When high-pressure oxygen is introduced into oxygen tank 1, it applies uniform pressure to fuel bag 2, causing the liquid fuel inside the bag to rise hydraulically until it reaches the same pressure as the tank's internal air pressure.

[0032] During the rocket launch preparation phase, as high-pressure oxygen continues to fill oxygen tank 1, the pressure exerted by the oxygen is evenly transmitted to all surfaces of fuel bag 2 according to Pascal's law, generating a squeezing force. This uniform squeezing force compresses the liquid fuel within fuel bag 2, increasing its hydraulic pressure. The hydraulic pressure of the liquid fuel continues to rise until it reaches equilibrium with the air pressure within oxygen tank 1, ensuring the stability of the fuel during storage and providing the driving force for the subsequent stable injection of fuel into combustion chamber 3 as required.

[0033] At the same time, the close combination and interaction between the fuel bag 2 and the oxygen tank 1 simplifies the structure to a certain extent and reduces the number of connecting parts compared to traditional separate fuel storage, which helps to improve the reliability and overall performance of the system.

[0034] During rocket operation, the air pressure in oxygen tank 1 and the hydraulic pressure in fuel bag 2 remain in equilibrium. When first solenoid valve 4 and second solenoid valve 5 are open, the fuel and oxygen, under the same initial pressure, enter combustion chamber 3 through fuel pipe 7 and oxygen pipe 6 in precise proportions.

[0035] During this process, fuel and oxygen enter the combustion chamber in precise proportions through the balance of air and hydraulic pressure, as well as precise control of the first and second solenoid valves 4 and 5. This precise mixture ratio control enables more complete combustion of the fuel, more efficiently converting chemical energy into kinetic energy, thereby improving energy efficiency and reducing energy waste.

[0036] The integrated design of the fuel bag 2 within the oxygen tank 1 reduces the number of connecting components and pipe interfaces compared to traditional separate fuel storage and supply systems. This reduction effectively reduces the probability of system failures such as leaks and blockages, thereby improving the reliability and stability of system operation.

[0037] The design of fuel bag 2 within oxygen tank 1 ensures a relatively stable fuel environment during storage. On the one hand, fuel bag 2 is protected by oxygen tank 1, reducing the risk of fuel leakage due to external factors such as collisions. On the other hand, the hydraulic pressure within fuel bag 2 is balanced with the air pressure within oxygen tank 1, preventing rupture of fuel bag 2 due to excessive pressure differences and improving fuel storage safety.

[0038] The hydraulic pressure within the fuel bag 2 and the air pressure within the oxygen tank 1 are constantly balanced. This self-balancing property allows the system to self-regulate in the face of external disturbances or minor internal fluctuations. Even if the rocket experiences slight shock or vibration during flight, the system automatically adjusts the fuel and oxygen pressures to maintain a constant balance, ensuring a stable fuel supply and proper combustion, and reducing the risk of system failure due to external disturbances.

[0039] The simplified structure and smaller number of components of the utility model also reduce the processing steps and assembly workload in the production process, further reducing production costs and significantly improving rocket production efficiency. It also means that the internal layout of the rocket is more compact and can carry more payload.

[0040] The present invention is adaptable to various types of liquid fuels. As long as the fuel possesses suitable physical and chemical properties, can be stably stored within the fuel bag, and can be supplied via pressure drive, it can be used in the power system of the present invention by adjusting the parameters of the first solenoid valve 4 and the second solenoid valve 5. This provides greater flexibility in selecting fuels with different performance characteristics, allowing the most appropriate fuel to be selected based on the specific mission and performance requirements of the rocket.

[0041] 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 in all respects as illustrative and non-restrictive, and the scope of the present invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations that come within the meaning and range of equivalents of the claims be embraced within the present invention.

Claims

1. A controllable gas-liquid rocket propulsion system comprising an oxygen tank, a fuel bag, and a combustion chamber; characterized in that: The oxygen tank is equipped with an oxygen tube, a first solenoid valve is provided on the oxygen tube, and the other end of the oxygen tube is connected to the combustion chamber, and the first solenoid valve can control the conduction and shutoff of the oxygen tube and the oxygen flow rate; The fuel bag is equipped with a fuel pipe, the fuel pipe is provided with a second solenoid valve, and the other end of the fuel pipe is connected to the combustion chamber, and the second solenoid valve can control the conduction and shutoff of the fuel pipe and the fuel flow; The fuel bag is arranged in the oxygen tank and has elastic expansion and contraction properties; The fuel bag is filled with liquid fuel, and the oxygen tank is filled with high-pressure oxygen, so that the hydraulic pressure in the fuel bag and the gas pressure in the oxygen tank are equal.

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