An electrically pumped, pressure-charged, rotary detonation rocket engine system

Abstract

The application discloses a kind of electric pump pressure type rotating detonation rocket engine system, it is related to rocket engine technical field in aerospace.This application system composition includes: rotating detonation thrust chamber, hydrogen storage tank, oxygen storage tank, hydrogen supply assembly, oxygen supply assembly, liquid hydrogen pump assembly, liquid oxygen pump assembly, hydrogen pressurizing assembly, oxygen pressurizing assembly, engine control unit and battery.The application is provided with hydrogen heat exchange channel and oxygen heat exchange channel on the side wall of rotating detonation thrust chamber, and liquid hydrogen and liquid oxygen are converted into gaseous state after heat exchange, so that combustion is more sufficient, and combustion efficiency is improved;At the same time, the power required by battery is reduced, and the mass of battery is reduced.In addition, a small part of hydrogen and oxygen after heat exchange is pressurized and then returned to the storage tank, the storage tank is pressurized, the pressure in the storage tank is stable, and the circulation of hydrogen and oxygen is realized.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and more specifically to an electric pump-driven rotary detonation rocket engine system. Background Technology

[0002] A rotating detonation rocket engine (RDRE) is a novel propulsion system that operates on a different principle than traditional rocket or jet engines. In a RDRE, combustion occurs as a continuous and self-sustaining detonation wave that propagates at high speed along specific channels within the engine. Compared to conventional rocket engines, RDREs can achieve the same theoretical specific impulse at lower injection pressures, or even a greater theoretical specific impulse at the same injection pressure, thus significantly reducing the requirements for the delivery system.

[0003] Currently, rotating detonation rocket engines mainly adopt a compression delivery scheme. In order to ensure the pre-injection pressure and regenerative cooling pressure drop of the rotating detonation combustion chamber, the tank pressure needs to reach the megapascal level. The pressure is high and the tank thickness is large. At the same time, additional compression cylinders are required. When rotating detonation rocket engines are used in the first stage or upper stage power system of launch vehicles, the additional structural mass is large.

[0004] Due to its high degree of electrification, flexible control strategies, simple mechanical structure, and low system pressure vibration, electric pump pressurization systems have attracted considerable research interest in their application in rocket engines. However, the high pre-injection pressure of traditional rocket engines places high demands on battery power and capacity. Currently, the energy density limit of lithium batteries is in the range of 0.2 kWh / kg, and the power density limit is in the range of 1 kW / kg. Therefore, the battery weight accounts for a large proportion of the electric pump pressurization system, making it unsuitable for use in launch vehicles.

[0005] In addition, the thrust chamber of existing hydrogen-oxygen rocket engines is generally only equipped with a liquid hydrogen cooling jacket, which results in insufficient combustion and low combustion efficiency due to the mixing and combustion of hydrogen and liquid oxygen.

[0006] Therefore, providing a rocket engine system that is simple in structure, has a small mass, and has high combustion efficiency is a problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0007] In view of this, the present invention aims to provide an electric pump-driven rotary detonation rocket engine system to solve the technical problems of complex structure, large structural mass, and low combustion efficiency of existing rocket engines.

[0008] To achieve the above objectives, the present invention adopts the following technical solution:

[0009] An electric pump-pressurized rotary detonation rocket engine system includes: a rotary detonation thrust chamber, a hydrogen storage tank, an oxygen storage tank, a hydrogen supply assembly, an oxygen supply assembly, a liquid hydrogen pump assembly, a liquid oxygen pump assembly, a hydrogen pressurization assembly, an oxygen pressurization assembly, an engine control unit, and a battery.

[0010] The rotating detonation thrust chamber includes an outer shell and an inner shell. A combustion chamber is formed between the outer shell and the inner shell. A hydrogen heat exchange channel is provided in the side wall of the outer shell, and a hydrogen combustion outlet communicating with the hydrogen heat exchange channel is opened at the top. An oxygen heat exchange channel is provided in the side wall of the inner shell, and an oxygen combustion outlet communicating with the oxygen heat exchange channel is opened at the top. An ignition device is also installed in the inner cavity of the inner shell.

[0011] The hydrogen storage tank has a hydrogen outlet and a hydrogen inlet at the upper end and a liquid hydrogen outlet at the lower end. The hydrogen outlet is connected to the ignition device through a hydrogen supply assembly, and the liquid hydrogen outlet is connected to the inlet of the hydrogen heat exchange channel through a liquid hydrogen pump assembly. The outer shell side wall also has a hot hydrogen outlet that connects to the hydrogen heat exchange channel. The hot hydrogen outlet is connected to the hydrogen inlet of the hydrogen storage tank through a hydrogen pressurization assembly.

[0012] The oxygen storage tank has an oxygen outlet and an oxygen inlet at the upper end and a liquid oxygen outlet at the lower end. The oxygen outlet is connected to the ignition device through an oxygen supply assembly, and the liquid oxygen outlet is connected to the inlet of the oxygen heat exchange channel through a liquid oxygen pump assembly. The inner shell sidewall also has a hot oxygen outlet that connects to the oxygen heat exchange channel. The hot oxygen outlet is connected to the oxygen inlet of the oxygen storage tank through an oxygen pressurization assembly.

[0013] The engine control unit is electrically connected to the liquid hydrogen pump assembly and the liquid oxygen pump assembly, respectively, and the battery is electrically connected to the engine control unit.

[0014] The beneficial effects achievable by this invention are as follows: Hydrogen and oxygen in the hydrogen and oxygen storage tanks are respectively supplied to the ignition device via hydrogen and oxygen supply components. Under the ignition of the ignition device, combustion generates a detonation wave, creating a stable rotating detonation within the rotating detonation thrust chamber. Liquid hydrogen is supplied to the hydrogen heat exchange channel via a liquid hydrogen pump component, and liquid oxygen is supplied to the oxygen heat exchange channel via a liquid oxygen pump component. Under the action of rotating detonation, heat exchange occurs, converting liquid hydrogen and liquid oxygen into hydrogen-oxygen gas. Most of the hydrogen-oxygen gas enters the combustion chamber along the heat exchange channel for further combustion, while a small portion of hydrogen returns to the hydrogen storage tank via a hydrogen pressurization component, and oxygen returns to the oxygen storage tank via an oxygen pressurization component, pressurizing the storage tanks. By setting up hydrogen and oxygen heat exchange channels, both liquid hydrogen and liquid oxygen can be converted into gaseous forms, resulting in more complete combustion and improved combustion efficiency. Simultaneously, the required battery power is reduced, decreasing battery weight; and the unburned hydrogen and oxygen can be recycled.

[0015] Furthermore, the hydrogen supply assembly includes a hydrogen input pipe and a hydrogen solenoid valve. The inlet end of the hydrogen input pipe is connected to the hydrogen outlet, and the outlet end is connected to the ignition device. The hydrogen solenoid valve is installed on the hydrogen input pipe.

[0016] Furthermore, the oxygen supply assembly includes an oxygen input pipe and an oxygen solenoid valve. The inlet end of the oxygen input pipe is connected to the oxygen outlet, and the outlet end is connected to the ignition device. The oxygen solenoid valve is installed on the oxygen input pipe.

[0017] Furthermore, the liquid hydrogen pump assembly includes: a liquid hydrogen supply pipeline and a liquid hydrogen pump pre-valve, a liquid hydrogen centrifugal pump, a liquid hydrogen pump post-valve, and a liquid hydrogen flow meter, which are sequentially installed along the liquid hydrogen delivery direction on the liquid hydrogen supply pipeline. The liquid hydrogen supply pipeline has its inlet end connected to the liquid hydrogen outlet of the hydrogen storage tank and its outlet end connected to the inlet of the hydrogen heat exchange channel. The liquid hydrogen pump post-valve and the liquid hydrogen flow meter are both electrically connected to the engine control unit.

[0018] Furthermore, it also includes a liquid hydrogen centrifugal pump control unit, which includes a hydrogen pump motor and a hydrogen pump motor controller. The hydrogen pump motor is driven to the liquid hydrogen centrifugal pump, and the two ends of the hydrogen pump motor controller are electrically connected to the hydrogen pump motor and the engine control unit, respectively. The battery is electrically connected to the hydrogen pump motor controller.

[0019] Furthermore, the liquid oxygen pump assembly includes: a liquid oxygen supply pipeline and a liquid oxygen pump pre-valve, a liquid oxygen centrifugal pump, a liquid oxygen pump post-valve, and a liquid oxygen flow meter, which are sequentially installed along the liquid oxygen delivery direction on the liquid oxygen supply pipeline. The liquid oxygen supply pipeline has its inlet end connected to the liquid oxygen outlet of the oxygen storage tank and its outlet end connected to the inlet of the oxygen heat exchange channel. The liquid oxygen pump post-valve and the liquid oxygen flow meter are both electrically connected to the engine control unit.

[0020] Furthermore, it also includes a liquid oxygen centrifugal pump control unit, which includes an oxygen pump motor and an oxygen pump motor controller. The oxygen pump motor is driven to the liquid oxygen centrifugal pump, and the two ends of the oxygen pump motor controller are electrically connected to the oxygen pump motor and the engine control unit, respectively. The battery is electrically connected to the oxygen pump motor controller.

[0021] Furthermore, both the hydrogen pump motor and the oxygen pump motor are permanent magnet synchronous motors.

[0022] Furthermore, the hydrogen pressurization assembly includes a hydrogen pressurization pipeline and a hydrogen pressurization valve installed on the hydrogen pressurization pipeline. The inlet end of the hydrogen pressurization pipeline is connected to the hot hydrogen outlet, and the outlet end is connected to the hydrogen inlet of the hydrogen storage tank.

[0023] Furthermore, the oxygen boosting assembly includes an oxygen boosting pipe and an oxygen boosting valve installed on the oxygen boosting pipe. The inlet end of the oxygen boosting pipe is connected to the hot oxygen outlet, and the outlet end is connected to the oxygen inlet of the oxygen storage tank.

[0024] As can be seen from the above technical solution, compared with the prior art, the present invention discloses an electric pump-driven rotary detonation rocket engine system, which has the following beneficial effects:

[0025] 1. Hydrogen and oxygen are supplied to the ignition device through the hydrogen supply component and the oxygen supply component. After ignition, the detonation wave is generated, which makes the rotating detonation thrust chamber form a stable rotating detonation. At the same time, the hydrogen heat exchange channel and the oxygen heat exchange channel can be preheated.

[0026] 2. By utilizing hydrogen and oxygen heat exchange channels, liquid hydrogen and liquid oxygen can be heated and converted into hydrogen and oxygen respectively, making combustion more complete and improving the combustion efficiency of the hydrogen-oxygen propellant combination.

[0027] 3. The hydrogen and oxygen after heat exchange are burned in the combustion chamber, which reduces the head of the centrifugal pump and the power of the centrifugal pump when it is working. Therefore, the power and mass of the battery required are relatively small, which reduces the overall mass of the rocket engine.

[0028] 4. After heat exchange, a small portion of hydrogen and oxygen will be diverted, pressurized, and returned to the storage tank to pressurize the tank, ensuring stable pressure inside the tank and preventing waste of hydrogen and oxygen, thus achieving recycling.

[0029] 5. The engine control unit can precisely control the motor speed and valve opening, and more accurately control the flow rate of liquid hydrogen and liquid oxygen, thereby achieving greater energy efficiency when adjusting engine thrust. Attached Figure Description

[0030] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0031] Figure 1 This invention provides a schematic diagram of an electric pump-driven rotary detonation rocket engine system.

[0032] Figure 2 This is a schematic diagram of the main cross-sectional structure of the rotating detonation thrust chamber provided by the present invention.

[0033] Figure 3 This is a schematic diagram of the cross-sectional structure of the rotating detonation thrust chamber provided by the present invention.

[0034] In the picture:

[0035] 1. Rotary detonation thrust chamber; 101. Outer shell; 1011. Hydrogen heat exchange channel; 1012. Hydrogen combustion outlet; 102. Inner shell; 1021. Oxygen heat exchange channel; 1022. Oxygen combustion outlet; 103. Combustion chamber; 104. Ignition device; 2. Hydrogen storage tank; 3. Oxygen storage tank; 4. Hydrogen supply assembly; 401. Hydrogen input pipeline; 402. Hydrogen solenoid valve; 5. Oxygen supply assembly; 501. Oxygen input pipeline; 502. Oxygen solenoid valve; 6. Liquid hydrogen pump assembly; 601. Liquid hydrogen pump inlet valve; 602. Liquid hydrogen centrifugal pump. 603. Liquid hydrogen pump after valve; 604. Liquid hydrogen flow meter; 605. Hydrogen pump motor; 606. Hydrogen pump motor controller; 7. Liquid oxygen pump assembly; 701. Liquid oxygen pump before valve; 702. Liquid oxygen centrifugal pump; 703. Liquid oxygen pump after valve; 704. Liquid oxygen flow meter; 705. Oxygen pump motor; 707. Oxygen pump motor controller; 8. Hydrogen pressurization assembly; 801. Hydrogen pressurization pipeline; 802. Hydrogen pressurization valve; 9. Oxygen pressurization assembly; 901. Oxygen pressurization pipeline; 902. Oxygen pressurization valve; 10. Engine control unit; 11. Battery. Detailed Implementation

[0036] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0037] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0038] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0039] Please see Figures 1-3 This invention discloses an electric pump-pressurized rotary detonation rocket engine system, comprising: a rotary detonation thrust chamber 1, a hydrogen storage tank 2, an oxygen storage tank 3, a hydrogen supply assembly 4, an oxygen supply assembly 5, a liquid hydrogen pump assembly 6, a liquid oxygen pump assembly 7, a hydrogen pressurization assembly 8, an oxygen pressurization assembly 9, an engine control unit 10, and a battery 11.

[0040] The rotating detonation thrust chamber 1 includes an outer shell 101 and an inner shell 102. A combustion chamber 103 is formed between the outer shell 101 and the inner shell 102. A hydrogen heat exchange channel 1011 is provided in the side wall of the outer shell 101, and a hydrogen combustion outlet 1012 communicating with the hydrogen heat exchange channel 1011 is opened at the top. An oxygen heat exchange channel 1021 is provided in the side wall of the inner shell 102, and an oxygen combustion outlet 1022 communicating with the oxygen heat exchange channel 1021 is opened at the top. An ignition device 104 is also installed in the inner cavity of the inner shell 102.

[0041] The hydrogen storage tank 2 has a hydrogen outlet and a hydrogen inlet at the upper end and a liquid hydrogen outlet at the lower end. The hydrogen outlet is connected to the ignition device 104 through the hydrogen supply component 4, and the liquid hydrogen outlet is connected to the inlet of the hydrogen heat exchange channel 1011 through the liquid hydrogen pump component 6. The outer shell 101 also has a hot hydrogen outlet connected to the hydrogen heat exchange channel 1011 (not shown in the figure) on the side wall. The hot hydrogen outlet is connected to the hydrogen inlet of the hydrogen storage tank 2 through the hydrogen pressurization component 8.

[0042] The oxygen storage tank 3 has an oxygen outlet and an oxygen inlet at the upper end and a liquid oxygen outlet at the lower end. The oxygen outlet is connected to the ignition device 104 through the oxygen supply component 5, and the liquid oxygen outlet is connected to the inlet of the oxygen heat exchange channel 1021 through the liquid oxygen pump component 7. The inner shell 102 also has a hot oxygen outlet connected to the oxygen heat exchange channel 1021 (not shown in the figure) on the side wall. The hot oxygen outlet is connected to the oxygen inlet of the oxygen storage tank 3 through the oxygen pressurization component 9.

[0043] The engine control unit 10 is electrically connected to the liquid hydrogen pump assembly 6 and the liquid oxygen pump assembly 7, respectively, and the battery 11 is electrically connected to the engine control unit 10.

[0044] In one specific embodiment, the hydrogen supply component 4 includes a hydrogen input pipe 401 and a hydrogen solenoid valve 402. The inlet end of the hydrogen input pipe 401 is connected to the hydrogen outlet, and the outlet end is connected to the ignition device 104. The ignition device 104 may be a detonation tube igniter. The hydrogen solenoid valve 402 is installed on the hydrogen input pipe 401, and the hydrogen is controlled to enter the ignition device 104.

[0045] In one specific embodiment, the oxygen supply component 5 includes an oxygen input pipe 501 and an oxygen solenoid valve 502. The inlet end of the oxygen input pipe 501 is connected to the oxygen outlet, and the outlet end is connected to the ignition device 104. The oxygen solenoid valve 502 is installed on the oxygen input pipe 501, and controls the entry of hydrogen into the ignition device 104 through the oxygen solenoid valve 502.

[0046] In one specific embodiment, the liquid hydrogen pump assembly 6 includes: a liquid hydrogen supply pipeline and a liquid hydrogen pump pre-valve 601, a liquid hydrogen centrifugal pump 602, a liquid hydrogen pump post-valve 603, and a liquid hydrogen flow meter 604, which are sequentially installed along the liquid hydrogen delivery direction on the liquid hydrogen supply pipeline. The liquid hydrogen supply pipeline is connected to the liquid hydrogen outlet of the hydrogen storage tank 2 at the inlet and to the inlet of the hydrogen heat exchange channel 1011 at the outlet. The liquid hydrogen pump post-valve 603 and the liquid hydrogen flow meter 604 are both electrically connected to the engine control unit 10. Through the cooperation of each valve with the centrifugal pump and the flow meter, the liquid hydrogen flow rate can be easily controlled and adjusted.

[0047] Specifically, it also includes a liquid hydrogen centrifugal pump control unit, which comprises a hydrogen pump motor 605 and a hydrogen pump motor controller 606. The hydrogen pump motor 605 is driven by the liquid hydrogen centrifugal pump 602. The two ends of the hydrogen pump motor controller 606 are electrically connected to the hydrogen pump motor 605 and the engine control unit 10, respectively, and the battery 11 is electrically connected to the hydrogen pump motor controller 606. The hydrogen pump motor controller 606 can control the head of the hydrogen pump motor 605, thereby controlling the speed of the liquid hydrogen centrifugal pump 602 and realizing the regulation of the flow rate of liquid hydrogen.

[0048] In one specific embodiment, the liquid oxygen pump assembly 7 includes: a liquid oxygen supply pipeline and a liquid oxygen pump pre-valve 701, a liquid oxygen centrifugal pump 702, a liquid oxygen pump post-valve 703, and a liquid oxygen flow meter 704, which are sequentially installed along the liquid oxygen supply pipeline in the liquid oxygen delivery direction. The liquid oxygen supply pipeline is connected to the liquid oxygen outlet of the oxygen storage tank 3 at the inlet end and to the inlet of the oxygen heat exchange channel 1021 at the outlet end. The liquid oxygen pump post-valve 703 and the liquid oxygen flow meter 704 are both electrically connected to the engine control unit 10. Through the cooperation of each valve with the centrifugal pump and the flow meter, the liquid oxygen flow rate can be easily controlled and adjusted.

[0049] Both the liquid oxygen flow meter and the liquid hydrogen flow meter are orifice plate differential pressure flow meters, and both the liquid hydrogen pump downstream valve and the liquid oxygen pump downstream valve are electric ball valves.

[0050] Specifically, it also includes a liquid oxygen centrifugal pump control unit, which comprises an oxygen pump motor 705 and an oxygen pump motor controller 706. The oxygen pump motor 705 is driven by the liquid oxygen centrifugal pump 702. The two ends of the oxygen pump motor controller 706 are electrically connected to the oxygen pump motor 705 and the engine control unit 10, respectively, and the battery 11 is electrically connected to the oxygen pump motor controller 706. The oxygen pump motor controller 706 can control the head of the oxygen pump motor 705, thereby controlling the speed of the liquid oxygen centrifugal pump 702 and realizing the regulation of the liquid oxygen flow rate.

[0051] More specifically, both the hydrogen pump motor 605 and the oxygen pump motor 705 use permanent magnet synchronous motors to achieve stepless speed regulation of the motors.

[0052] In one specific embodiment, the hydrogen boosting assembly 8 includes a hydrogen boosting pipe 801 and a hydrogen boosting valve 802 installed on the hydrogen boosting pipe 801. The inlet end of the hydrogen boosting pipe 801 is connected to the hot hydrogen outlet, and the outlet end is connected to the hydrogen inlet of the hydrogen storage tank 2. The remaining hydrogen is used to boost the hydrogen storage tank 2, thereby increasing the hydrogen utilization rate and the thrust of the engine.

[0053] In one specific embodiment, the oxygen boosting assembly 9 includes an oxygen boosting pipe 901 and an oxygen boosting valve 902 installed on the oxygen boosting pipe 901. The inlet end of the oxygen boosting pipe 901 is connected to the hot oxygen outlet, and the outlet end is connected to the oxygen inlet of the oxygen storage tank 3. The remaining oxygen is used to boost the oxygen storage tank 3, thereby increasing the oxygen utilization rate and the thrust of the engine.

[0054] The working principle of an electric pump-driven rotary detonation rocket engine system of the present invention:

[0055] When the rocket system issues the ignition command, hydrogen and oxygen from hydrogen tank 2 and oxygen tank 3 are respectively supplied to ignition device 104 via hydrogen supply assembly 4 and oxygen supply assembly 5. Under the ignition of ignition device 104, combustion generates a detonation wave, causing a stable rotating detonation to form in rotating detonation thrust chamber 1. Liquid hydrogen is supplied to hydrogen heat exchange channel 1011 via liquid hydrogen pump assembly 6, and liquid oxygen is supplied to oxygen heat exchange channel 1021 via liquid oxygen pump assembly 7. Under the action of rotating detonation, heat exchange occurs, and liquid hydrogen and liquid oxygen are converted into hydrogen and oxygen. Most of the hydrogen and oxygen enter the combustion chamber 103 along the heat exchange channel to continue combustion, while a small portion of hydrogen returns to hydrogen tank 2 via hydrogen pressurization assembly 8, and oxygen returns to oxygen tank 3 via oxygen pressurization assembly 9 to pressurize the tanks.

[0056] The liquid oxygen pump assembly 7 and the liquid oxygen pump assembly 7 of the present invention do not interfere with each other, and can realize independent control in the liquid hydrogen-liquid oxygen pumping process. This facilitates the adjustment of the hydrogen-oxygen mixing ratio to achieve complete combustion of hydrogen and oxygen, increase engine thrust, and improve pump efficiency.

[0057] The following comparison between existing engine solutions and the engine solution of this invention will more significantly demonstrate the beneficial effects of this invention:

[0058] 1. Existing engine solutions

[0059] Considering a hydrogen-oxygen rocket engine with a thrust of 80kN, using an electric pump-pressure cycle, and with only the hydrogen path participating in regeneration and cooling, the injection method is gas-liquid injection, with the hydrogen path being gas entering the combustion chamber and the oxygen path being liquid entering the combustion chamber.

[0060] The mixing ratio is set at 6.0 (equivalence ratio 1.33, residual oxygen coefficient 0.75), the engine chamber pressure is set at 4.0 MPa, and based on existing engine design experience and with reference to "Liquid Rocket Engine Design", the hydrogen injection pressure drop coefficient is set at 0.2, the oxygen injection pressure drop coefficient is set at 0.2, the cooling jacket pressure drop is set at 3.0 MPa, and the tank pressure is set at 0.5 MPa.

[0061] The calculated head of the hydrogen and oxygen pumps is:

[0062] Δp hp =Δp cj +pc (1+γ hi )-p ht =(3.0+4.0×(1+0.2)-0.5)MPa=7.3MPa

[0063] △p op =p c (1+γ oi )-p ht =(4.0×(1+0.1)-0.5)MPa=3.9MPa

[0064] Based on thermodynamic calculations, when the expansion ratio is 100, the vacuum specific impulse is 4584.19 m / s. Therefore, the required flow rate can be calculated as follows:

[0065] q m，h =2.49 kg / s, q m，o =14.96kg / s

[0066] According to the literature (Parametric Study of Dual-Expander Aerospike Nozzle Upper-Stage Rocket Engine), the efficiency of the hydrogen pump and the oxygen pump are taken as 0.65. At this point, the power of the hydrogen pump and the oxygen pump can be calculated:

[0067] W p =W hp +W op =470.3kW

[0068] The energy density of lithium batteries is taken as a typical value e b =200Wh / kg = 720kJ / kg, which allows us to calculate the required battery mass per unit time (without considering the limitations of battery power density).

[0069]

[0070] 2. Engine solution of this patent

[0071] According to calculations in the literature (Ideal Thermodynamic Performance Results for Rotating Detonation Rocket Engine Thrust Chambers Using CEA), at this chamber pressure and mixture ratio, the injection back pressure required for a rotating detonation rocket engine to achieve the same specific impulse is approximately 1 / 7.5 of that of a conventional rocket engine, or 0.53 MPa.

[0072] Considering this rotating detonation rocket engine, the head of the hydrogen and oxygen pumps can be calculated using a similar method.

[0073] Δp op =Δp cj，o +p c (1+γ oi )-p ot =(3.0+4.0×(1+0.1)-0.5)MPa=3.05MPa

[0074] The power of hydrogen and oxygen is: W p =W hp +W op =224.4kW

[0075] Battery mass required per unit time

[0076]

[0077] It can be seen that, using the same electric pump method, the required battery mass is only 48% of that of the same conventional engine solution.

[0078] Therefore, the rocket engine system designed in this invention can realize the combustion of liquid hydrogen and liquid oxygen into gaseous state through heat exchange, which improves combustion efficiency, increases engine thrust, and reduces the power required for centrifugal pump operation, thereby saving electrical energy and reducing the mass of the battery 11 to be carried.

[0079] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to the method section.

[0080] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An electric pump-driven rotary detonation rocket engine system, characterized in that, The system consists of: a rotating detonation thrust chamber (1), a hydrogen storage tank (2), an oxygen storage tank (3), a hydrogen supply assembly (4), an oxygen supply assembly (5), a liquid hydrogen pump assembly (6), a liquid oxygen pump assembly (7), a hydrogen booster assembly (8), an oxygen booster assembly (9), an engine control unit (10), and a battery (11). The rotating detonation thrust chamber (1) includes an outer shell (101) and an inner shell (102). A combustion chamber (103) is formed between the outer shell (101) and the inner shell (102). A hydrogen heat exchange channel (1011) is provided in the side wall of the outer shell (101), and a hydrogen combustion outlet (1012) communicating with the hydrogen heat exchange channel (1011) is opened at the top. An oxygen heat exchange channel (1021) is provided in the side wall of the inner shell (102), and an oxygen combustion outlet (1022) communicating with the oxygen heat exchange channel (1021) is opened at the top. An ignition device (104) is also installed in the inner cavity of the inner shell (102). The hydrogen storage tank (2) has a hydrogen outlet and a hydrogen inlet at the upper end and a liquid hydrogen outlet at the lower end. The hydrogen outlet is connected to the ignition device (104) through a hydrogen supply assembly (4). The liquid hydrogen outlet is connected to the inlet of the hydrogen heat exchange channel (1011) through a liquid hydrogen pump assembly (6). The outer shell (101) also has a hot hydrogen outlet connected to the hydrogen heat exchange channel (1011) on its side wall. The hot hydrogen outlet is connected to the hydrogen inlet of the hydrogen storage tank (2) through a hydrogen pressurization assembly (8). The oxygen storage tank (3) has an oxygen outlet and an oxygen inlet at the upper end and a liquid oxygen outlet at the lower end. The oxygen outlet is connected to the ignition device (104) through an oxygen supply assembly (5). The liquid oxygen outlet is connected to the inlet of the oxygen heat exchange channel (1021) through a liquid oxygen pump assembly (7). The inner shell (102) also has a hot oxygen outlet connected to the oxygen heat exchange channel (1021) on its side wall. The hot oxygen outlet is connected to the oxygen inlet of the oxygen storage tank (3) through an oxygen pressurization assembly (9). The engine control unit (10) is electrically connected to the liquid hydrogen pump assembly (6) and the liquid oxygen pump assembly (7), respectively, and the battery (11) is electrically connected to the engine control unit (10).

2. The electric pump-driven rotary detonation rocket engine system according to claim 1, characterized in that, The hydrogen supply assembly (4) includes a hydrogen input pipe (401) and a hydrogen solenoid valve (402). The inlet end of the hydrogen input pipe (401) is connected to the hydrogen outlet, and the outlet end is connected to the ignition device (104). The hydrogen solenoid valve (402) is installed on the hydrogen input pipe (401).

3. The electric pump-driven rotary detonation rocket engine system according to claim 1, characterized in that, The oxygen supply assembly (5) includes an oxygen input pipe (501) and an oxygen solenoid valve (502). The inlet end of the oxygen input pipe (501) is connected to the oxygen outlet, and the outlet end is connected to the ignition device (104). The oxygen solenoid valve (502) is installed on the oxygen input pipe (501).

4. The electric pump-driven rotary detonation rocket engine system according to claim 1, characterized in that, The liquid hydrogen pump assembly (6) includes: a liquid hydrogen supply pipeline and a liquid hydrogen pump inlet valve (601), a liquid hydrogen centrifugal pump (602), a liquid hydrogen pump outlet valve (603), and a liquid hydrogen flow meter (604) sequentially installed on the liquid hydrogen supply pipeline along the liquid hydrogen delivery direction. The inlet end of the liquid hydrogen supply pipeline is connected to the liquid hydrogen outlet of the hydrogen storage tank (2), and the outlet end is connected to the inlet of the hydrogen heat exchange channel (1011). The liquid hydrogen pump outlet valve (603) and the liquid hydrogen flow meter (604) are both electrically connected to the engine control unit (10).

5. The electric pump-driven rotary detonation rocket engine system according to claim 3, characterized in that, It also includes a liquid hydrogen centrifugal pump control unit, which includes a hydrogen pump motor (605) and a hydrogen pump motor controller (606). The hydrogen pump motor (605) is driven to the liquid hydrogen centrifugal pump (602). The two ends of the hydrogen pump motor controller (606) are electrically connected to the hydrogen pump motor (605) and the engine control unit (10), respectively, and the battery (11) is electrically connected to the hydrogen pump motor controller (606).

6. The electric pump-driven rotary detonation rocket engine system according to claim 5, characterized in that, The liquid oxygen pump assembly (7) includes: a liquid oxygen supply pipeline and a liquid oxygen pump front valve (701), a liquid oxygen centrifugal pump (702), a liquid oxygen pump rear valve (703), and a liquid oxygen flow meter (704) sequentially installed on the liquid oxygen supply pipeline along the liquid oxygen delivery direction. The liquid oxygen supply pipeline has its inlet end connected to the liquid oxygen outlet of the oxygen storage tank (3) and its outlet end connected to the inlet of the oxygen heat exchange channel (1021). The liquid oxygen pump rear valve (703) and the liquid oxygen flow meter (704) are both electrically connected to the engine control unit (10).

7. The electric pump-driven rotary detonation rocket engine system according to claim 6, characterized in that, It also includes a liquid oxygen centrifugal pump control unit, which includes an oxygen pump motor (705) and an oxygen pump motor controller (706). The oxygen pump motor (705) is driven to the liquid oxygen centrifugal pump (702). The two ends of the oxygen pump motor controller (706) are electrically connected to the oxygen pump motor (705) and the engine control unit (10), respectively, and the battery (11) is electrically connected to the oxygen pump motor controller (706).

8. The electric pump-driven rotary detonation rocket engine system according to claim 7, characterized in that, Both the hydrogen pump motor (605) and the oxygen pump motor (705) are permanent magnet synchronous motors.

9. The electric pump-driven rotary detonation rocket engine system according to claim 1, characterized in that, The hydrogen booster assembly (8) includes a hydrogen booster pipe (801) and a hydrogen booster valve (802) installed on the hydrogen booster pipe (801). The inlet end of the hydrogen booster pipe (801) is connected to the hot hydrogen outlet, and the outlet end is connected to the hydrogen inlet of the hydrogen storage tank (2).

10. The electric pump-driven rotary detonation rocket engine system according to claim 1, characterized in that, The oxygen booster assembly (9) includes an oxygen booster pipe (901) and an oxygen booster valve (902) installed on the oxygen booster pipe (901). The inlet end of the oxygen booster pipe (901) is connected to the hot oxygen outlet, and the outlet end is connected to the oxygen inlet of the oxygen storage tank (3).

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