Electric pump pressure type rotary detonation rocket engine system

Abstract

The invention discloses an electric pump pressure type rotary detonation rocket engine system, and relates to the technical field of rocket engines in aerospace. The system comprises a rotating 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. The hydrogen heat exchange channel and the oxygen heat exchange channel are formed in the side wall face of the rotating detonation thrust chamber, liquid hydrogen and liquid oxygen are converted into gas states after heat exchange, combustion is more sufficient, and then the combustion efficiency is improved; meanwhile, the power required by the battery is reduced, and the battery mass is reduced. In addition, after heat exchange, a small part of hydrogen and oxygen can be shunted, pressurized and then returned to the storage box, the storage box is pressurized, it is guaranteed that the pressure in the storage box is stable, and meanwhile cyclic utilization of the hydrogen and the oxygen is achieved.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and more particularly to an electric pump-pressure rotating detonation rocket engine system. Background Art

[0002] The Rotating Detonation Rocket Engine (RDRE) is a new type of propulsion system, and its working principle is different from that of traditional rocket engines or jet engines. In a rotating detonation engine, the combustion process is carried out in the form of a continuous and self-sustaining detonation wave, which propagates in a high-speed rotating manner along a specific channel in the engine. Compared with traditional rocket engines, rotating detonation rocket engines can achieve the same theoretical specific impulse at a lower injection pressure, or achieve a greater theoretical specific impulse at the same injection pressure, so the demand for the delivery system is significantly reduced.

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

[0004] Since the electric pump pressure cycle solution has the characteristics of high electrification, more flexible control strategy, simple mechanical structure and small system pressure vibration, many studies have begun to focus on the application of electric pump boosting system in rocket engines. However, the pre-injection pressure of traditional rocket engines is relatively high, which puts forward high requirements on battery power and power. The current energy density limit of lithium batteries is at the order of 0.2kWh / kg, and the power density limit is at the order of 1kW / kg. Therefore, the battery weight accounts for a large proportion in the electric pump pressure boosting delivery system, which is not suitable for use in launch vehicles.

[0005] In addition, the thrust chamber of existing hydrogen-oxygen rocket engines is generally only provided with a liquid hydrogen cooling jacket, so that hydrogen and liquid oxygen are mixed and burned, the combustion is not complete, and the combustion efficiency is low.

[0006] Therefore, providing a rocket engine system with a simple structure, small mass and high combustion efficiency is an urgent problem to be solved by technical personnel in this field. Summary of the invention

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

[0008] In order to achieve the above object, the present invention adopts the following technical solution:

[0009] An electric pump-pressure rotating detonation rocket engine system, comprising: a rotating detonation thrust chamber, a hydrogen tank, an oxygen tank, a hydrogen supply assembly, an oxygen supply assembly, a liquid hydrogen pump assembly, a liquid oxygen pump assembly, a hydrogen booster assembly, an oxygen booster assembly, an engine control unit and a battery;

[0010] The rotating detonation thrust chamber comprises 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 arranged in the side wall of the outer shell, a hydrogen combustion outlet connected to the hydrogen heat exchange channel is opened at the top, an oxygen heat exchange channel is arranged in the side wall of the inner shell, a combustion oxygen outlet connected to the oxygen heat exchange channel is opened at the top, and an ignition device is also installed in the inner cavity of the inner shell;

[0011] The upper end of the hydrogen storage tank is provided with a hydrogen outlet and a hydrogen inlet, and the lower end is provided with a liquid hydrogen outlet, the hydrogen outlet is connected to the ignition device through a hydrogen supply assembly, the liquid hydrogen outlet is connected to the inlet of the hydrogen heat exchange channel through a liquid hydrogen pump assembly, and the side wall of the outer shell is also provided with a hot hydrogen outlet connected to the hydrogen heat exchange channel, and the hot hydrogen outlet is connected to the hydrogen inlet of the hydrogen storage tank through a hydrogen booster assembly;

[0012] The oxygen storage tank is provided with 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 side wall is also provided with a hot oxygen outlet connected to the oxygen heat exchange channel, and the hot oxygen outlet is connected to the oxygen inlet of the oxygen storage tank through an oxygen booster 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 that can be achieved by the present invention are as follows: the hydrogen and oxygen in the hydrogen tank and the oxygen tank are respectively transported to the ignition device through the hydrogen supply assembly and the oxygen supply assembly. Under the ignition of the ignition device, the combustion generates a detonation wave, so that a stable rotary detonation is formed in the rotary detonation thrust chamber. Liquid hydrogen is transported to the hydrogen heat exchange channel through the liquid hydrogen pump assembly, and liquid oxygen is transported to the oxygen heat exchange channel through the liquid oxygen pump assembly. Under the action of rotary detonation, heat is exchanged, and liquid hydrogen and liquid oxygen are converted into hydrogen and oxygen. Most of the hydrogen and oxygen enter the combustion chamber along the heat exchange channel and continue to burn. Another small part of hydrogen returns to the hydrogen tank through the hydrogen booster assembly, and oxygen returns to the oxygen tank through the oxygen booster assembly to boost the tank. By setting the hydrogen heat exchange channel and the oxygen heat exchange channel, liquid hydrogen and liquid oxygen can be converted into gaseous form, so that the combustion is more complete, thereby improving the combustion efficiency; at the same time, the power of the required battery is reduced, and the battery mass is reduced; and the recycling of hydrogen and oxygen that do not participate in the combustion can be realized.

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

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

[0017] Furthermore, the liquid hydrogen pump assembly includes: a liquid hydrogen supply pipeline and a liquid hydrogen pump front valve, a liquid hydrogen centrifugal pump, a liquid hydrogen pump rear valve and a liquid hydrogen flowmeter installed on the liquid hydrogen supply pipeline in sequence along the liquid hydrogen transportation direction, the liquid inlet end of the liquid hydrogen supply pipeline is connected to the liquid hydrogen outlet of the hydrogen storage tank, and the liquid outlet end is connected to the inlet of the hydrogen heat exchange channel, and the liquid hydrogen pump rear valve and the liquid hydrogen flowmeter 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 transmission-connected to the liquid hydrogen centrifugal pump, and two ends of the hydrogen pump motor controller are electrically connected to the hydrogen pump motor and the engine control unit respectively, and 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 front valve, a liquid oxygen centrifugal pump, a liquid oxygen pump rear valve and a liquid oxygen flowmeter installed on the liquid oxygen supply pipeline in sequence along the liquid oxygen delivery direction, the liquid inlet end of the liquid oxygen supply pipeline is connected to the liquid oxygen outlet of the oxygen storage tank, and the liquid outlet end is connected to the inlet of the oxygen heat exchange channel, and the liquid oxygen pump rear valve and the liquid oxygen flowmeter 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 transmission-connected to the liquid oxygen centrifugal pump, and two ends of the oxygen pump motor controller are electrically connected to the oxygen pump motor and the engine control unit respectively, and 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 boosting assembly includes a hydrogen boosting pipeline and a hydrogen boosting valve installed on the hydrogen boosting pipeline, the air inlet end of the hydrogen boosting pipeline is connected to the hot hydrogen outlet, and the air outlet end is connected to the hydrogen inlet of the hydrogen tank.

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

[0024] It can be seen from the above technical solutions that, compared with the prior art, the present invention discloses an electric pump-type rotating detonation rocket engine system, which has the following beneficial effects:

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

[0026] 2. The hydrogen heat exchange channel and the oxygen heat exchange channel can be used to heat liquid hydrogen and liquid oxygen and convert them into hydrogen and oxygen respectively, so that their combustion is more complete and the combustion efficiency of the hydrogen-oxygen propellant combination is improved.

[0027] 3. The hydrogen and oxygen after heat exchange burn in the combustion chamber, which reduces the lift 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, reducing the overall mass of the rocket engine.

[0028] 4. After heat exchange, a small portion of hydrogen and oxygen will be diverted and pressurized and then returned to the tank again to pressurize the tank to ensure the pressure inside the tank is stable, while avoiding the waste of hydrogen and oxygen and achieving recycling.

[0029] 5. The engine control unit can accurately control the motor speed and valve opening, and more accurately control the flow of liquid hydrogen and liquid oxygen, so as to save energy when adjusting the engine thrust. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] 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 embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0031] Figure 1 A schematic diagram of the structure of an electric pump-pressure rotating detonation rocket engine system provided by the present invention.

[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 A schematic diagram of the cross-sectional structure of the rotating detonation thrust chamber provided by the present invention.

[0034] In the figure:

[0035] 1. Rotating detonation thrust chamber, 101. Outer shell, 1011. Hydrogen heat exchange channel, 1012. Hydrogen outlet, 102. Inner shell, 1021. Oxygen heat exchange channel, 1022. Oxygen outlet, 103. Combustion chamber, 104. Ignition device, 2. Hydrogen tank, 3. Oxygen 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 front valve, 602. Liquid hydrogen centrifugal pump, 603. Liquid hydrogen pump rear valve, 604. Liquid hydrogen flowmeter, 605. Hydrogen pump motor, 606. Hydrogen pump motor controller, 7. Liquid oxygen pump assembly, 701. Liquid oxygen pump front valve, 702. Liquid oxygen centrifugal pump, 703. Liquid oxygen pump rear valve, 704. Liquid oxygen flowmeter, 705. Oxygen pump motor, 707. Oxygen pump motor controller, 8. Hydrogen booster assembly, 801. Hydrogen booster pipeline, 802. Hydrogen booster valve, 9. Oxygen booster assembly, 901. Oxygen booster pipeline, 902. Oxygen booster valve, 10. Engine control unit, 11. Battery. DETAILED DESCRIPTION

[0036] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. 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.

[0037] In the description of the present invention, it is necessary to understand that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0038] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like 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 an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0039] See also Figure 1-Figure 3 The embodiment of the present invention discloses an electric pump-pressure rotating detonation rocket engine system, comprising: a rotating detonation thrust chamber 1, a hydrogen tank 2, an oxygen 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;

[0040] The rotating detonation thrust chamber 1 comprises 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 arranged in the side wall of the outer shell 101, a hydrogen combustion outlet 1012 connected to the hydrogen heat exchange channel 1011 is opened on the top, an oxygen heat exchange channel 1021 is arranged in the side wall of the inner shell 102, an oxygen combustion outlet 1022 connected to the oxygen heat exchange channel 1021 is opened on the top, and an ignition device 104 is also installed in the inner cavity of the inner shell 102;

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

[0042] An oxygen outlet and an oxygen inlet are provided at the upper end of the oxygen storage tank 3, and a liquid oxygen outlet is provided at the lower end. The oxygen outlet is connected to the ignition device 104 through the oxygen supply assembly 5, and the liquid oxygen outlet is connected to the inlet of the oxygen heat exchange channel 1021 through the liquid oxygen pump assembly 7. A hot oxygen outlet (not shown in the figure) connected to the oxygen heat exchange channel 1021 is also provided on the side wall of the inner shell 102, and the hot oxygen outlet is connected to the oxygen inlet of the oxygen storage tank 3 through the oxygen booster assembly 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 a specific embodiment, the hydrogen supply component 4 includes: a hydrogen input pipeline 401 and a hydrogen solenoid valve 402. The air inlet end of the hydrogen input pipeline 401 is connected to the hydrogen outlet, and the air outlet end is connected to the ignition device 104. The ignition device 104 can use a detonation tube igniter. The hydrogen solenoid valve 402 is installed on the hydrogen input pipeline 401, and the hydrogen entering the ignition device 104 is controlled by the hydrogen solenoid valve 402.

[0045] In a specific embodiment, the oxygen supply assembly 5 includes: an oxygen input pipeline 501 and an oxygen solenoid valve 502, the air inlet end of the oxygen input pipeline 501 is connected to the oxygen outlet, and the air outlet end is connected to the ignition device 104, the oxygen solenoid valve 502 is installed on the oxygen input pipeline 501, and the oxygen solenoid valve 502 is used to control the hydrogen to enter the ignition device 104.

[0046] In a specific embodiment, the liquid hydrogen pump assembly 6 includes: a liquid hydrogen supply pipeline and a liquid hydrogen pump front valve 601, a liquid hydrogen centrifugal pump 602, a liquid hydrogen pump rear valve 603 and a liquid hydrogen flowmeter 604 installed on the liquid hydrogen supply pipeline in sequence along the liquid hydrogen transportation direction. The liquid inlet end of the liquid hydrogen supply pipeline is connected to the liquid hydrogen outlet of the hydrogen storage tank 2, and the liquid outlet end is connected to the inlet of the hydrogen heat exchange channel 1011. The liquid hydrogen pump rear valve 603 and the liquid hydrogen flowmeter 604 are both electrically connected to the engine control unit 10. Through the cooperation of each valve with the centrifugal pump and the flowmeter, the liquid hydrogen flow rate is conveniently controlled and adjusted.

[0047] Specifically, 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 connected to the liquid hydrogen centrifugal pump 602 by transmission, and the two ends of the hydrogen pump motor controller 606 are respectively electrically connected to the hydrogen pump motor 605 and the engine control unit 10, 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 flow rate and flow rate regulation of liquid hydrogen.

[0048] In a specific embodiment, 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 installed on the liquid oxygen supply pipeline in sequence along the liquid oxygen delivery direction. The liquid inlet end of the liquid oxygen supply pipeline is connected to the liquid oxygen outlet of the oxygen storage tank 3, and the liquid outlet end is 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. Through the cooperation of each valve with the centrifugal pump and the flow meter, the liquid oxygen flow rate is conveniently controlled and adjusted.

[0049] Among them, the liquid oxygen flowmeter and the liquid hydrogen flowmeter both use orifice differential pressure flowmeters, and the liquid hydrogen pump rear valve and the liquid oxygen pump rear valve both use electric ball valves.

[0050] Specifically, 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 connected to the liquid oxygen centrifugal pump 702 by transmission, and the two ends of the oxygen pump motor controller 706 are respectively electrically connected to the oxygen pump motor 705 and the engine control unit 10, 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 flow rate and flow rate regulation of liquid oxygen.

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

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

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

[0054] The working principle of an electric pump-pressure rotating detonation rocket engine system of the present invention is as follows:

[0055] When the rocket as a whole issues an ignition command, the hydrogen and oxygen in the hydrogen tank 2 and the oxygen tank 3 are respectively transported to the ignition device 104 through the hydrogen supply assembly 4 and the oxygen supply assembly 5. Under the ignition of the ignition device 104, the combustion generates a detonation wave, so that a stable rotating detonation is formed in the rotating detonation thrust chamber 1. Liquid hydrogen is transported to the hydrogen heat exchange channel 1011 through the liquid hydrogen pump assembly 6, and liquid oxygen is transported to the oxygen heat exchange channel 1021 through the liquid oxygen pump assembly 7. Under the action of rotating detonation, heat is exchanged, 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 and continue to burn. Another small part of hydrogen returns to the hydrogen tank 2 through the hydrogen booster assembly 8, and oxygen returns to the oxygen tank 3 through the oxygen booster assembly 9 to boost the tanks.

[0056] The liquid oxygen pump assembly 7 of the present invention and the liquid oxygen pump assembly 7 do not interfere with each other, and can realize independent control in the process of liquid hydrogen and liquid oxygen pump, and it is convenient to adjust the hydrogen and oxygen mixing ratio to realize full combustion of hydrogen and oxygen, increase the thrust of the engine, and improve the working efficiency of the pump.

[0057] The following is a comparison between the existing engine solution and the engine solution of the present invention to more significantly demonstrate the beneficial effects of the present invention:

[0058] 1. Existing engine solutions

[0059] Consider a hydrogen-oxygen rocket engine with a thrust of 80kN, which uses an electric pump pressure cycle and only the hydrogen path participates in regenerative cooling. Therefore, the injection form 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 taken as 6.0 (equivalence ratio 1.33, excess oxygen coefficient 0.75), the engine room pressure is taken as 4.0MPa, based on the existing engine design experience and referring to "Liquid Rocket Engine Design", the hydrogen injection pressure drop coefficient is taken as 0.2, the oxygen injection pressure drop coefficient is taken as 0.2, the cooling jacket pressure drop is taken as 3.0MPa, and the tank pressure is taken as 0.5MPa.

[0061] The calculated lift of 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] According to the thermal calculation results, when the expansion ratio is 100, the vacuum specific impulse is 4584.19m / s, so the required flow rate can be calculated as:

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

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

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

[0068] The energy density of lithium battery is taken as the typical value e b =200Wh / kg=720kJ / kg, the battery mass required per unit time can be calculated (without considering the limitation of battery power density)

[0069]

[0070] 2. This patented engine solution

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

[0072] Considering such a rotating detonation rocket engine of this patent, the hydrogen and oxygen pump lifts can be calculated by a similar method as follows:

[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] Hydrogen and oxygen power: 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 mass of the battery that needs to be carried is only 48% of that of the same conventional engine solution.

[0078] It can be seen from this that the rocket engine system designed in the present invention can realize that liquid hydrogen and liquid oxygen are converted into gaseous state for combustion through heat exchange, thereby improving combustion efficiency, increasing the thrust of the engine, and reducing the power required for the centrifugal pump to work, thereby saving electric energy and reducing the mass of the battery 11 required to be carried.

[0079] In this specification, each embodiment is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other. For the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant parts can be referred to the method part.

[0080] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be 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 present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but rather to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An electric pump-type rotating detonation rocket engine system, characterized in that: The system comprises: a rotating detonation thrust chamber (1), a hydrogen tank (2), an oxygen 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) comprises 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) connected to the hydrogen heat exchange channel (1011) is provided 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) connected to the oxygen heat exchange channel (1021) is provided at the top, and an ignition device (104) is also installed in the inner cavity of the inner shell (102); The hydrogen storage tank (2) is provided with 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) via a hydrogen supply assembly (4), and the liquid hydrogen outlet is connected to the inlet of the hydrogen heat exchange channel (1011) via a liquid hydrogen pump assembly (6). The outer shell (101) side wall is also provided with a hot hydrogen outlet connected to the hydrogen heat exchange channel (1011), and the hot hydrogen outlet is connected to the hydrogen inlet of the hydrogen storage tank (2) via a hydrogen booster assembly (8); The oxygen storage tank (3) is provided with 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) via an oxygen supply assembly (5), and the liquid oxygen outlet is connected to the inlet of the oxygen heat exchange channel (1021) via a liquid oxygen pump assembly (7). The side wall of the inner shell (102) is also provided with a hot oxygen outlet connected to the oxygen heat exchange channel (1021), and the hot oxygen outlet is connected to the oxygen inlet of the oxygen storage tank (3) via an oxygen booster 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. An electric pump-type rotating detonation rocket engine system according to claim 1, characterized in that: The hydrogen supply assembly (4) comprises: a hydrogen input pipeline (401) and a hydrogen solenoid valve (402); the inlet end of the hydrogen input pipeline (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 pipeline (401).

3. The electric pump-type rotating detonation rocket engine system according to claim 1, characterized in that: The oxygen supply assembly (5) comprises: an oxygen input pipeline (501) and an oxygen solenoid valve (502); the air inlet end of the oxygen input pipeline (501) is connected to the oxygen outlet, and the air outlet end is connected to the ignition device (104); the oxygen solenoid valve (502) is installed on the oxygen input pipeline (501).

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

5. The electric pump-type rotating detonation rocket engine system according to claim 3, characterized in that: The invention 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 connected to the liquid hydrogen centrifugal pump (602) in a transmission manner, and two ends of the hydrogen pump motor controller (606) are respectively electrically connected to the hydrogen pump motor (605) and the engine control unit (10), and the battery (11) is electrically connected to the hydrogen pump motor controller (606).

6. The electric pump-type rotating detonation rocket engine system according to claim 5, characterized in that: The liquid oxygen pump assembly (7) comprises: 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) which are sequentially installed on the liquid oxygen supply pipeline along the liquid oxygen conveying direction; the liquid inlet end of the liquid oxygen supply pipeline is connected to the liquid oxygen outlet of the oxygen storage tank (3), and the liquid outlet end is 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. An electrically powered pump-type rotating detonation rocket engine system according to claim 6, characterized in that: The invention 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 connected to the liquid oxygen centrifugal pump (702) in a transmission manner, and two ends of the oxygen pump motor controller (706) are respectively electrically connected to the oxygen pump motor (705) and the engine control unit (10), and the battery (11) is electrically connected to the oxygen pump motor controller (706).

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

9. The electric pump-type rotating detonation rocket engine system according to claim 1, characterized in that: The hydrogen boosting assembly (8) comprises a hydrogen boosting pipeline (801) and a hydrogen boosting valve (802) installed on the hydrogen boosting pipeline (801), wherein the air inlet end of the hydrogen boosting pipeline (801) is connected to the hot hydrogen outlet, and the air outlet end is connected to the hydrogen inlet of the hydrogen storage tank (2).

10. The electric pump-type rotating detonation rocket engine system according to claim 1, characterized in that: The oxygen boosting assembly (9) comprises an oxygen boosting pipeline (901) and an oxygen boosting valve (902) installed on the oxygen boosting pipeline (901); the air inlet end of the oxygen boosting pipeline (901) is connected to the hot oxygen outlet, and the air outlet end is connected to the oxygen inlet of the oxygen storage tank (3).

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