A horizontal take-off and landing aerospace power system and aircraft suitable for single-stage orbit entry and orbit transfer

Abstract

The present invention discloses a horizontal take-off and landing aerospace power system and an aircraft suitable for single-stage orbital insertion and orbital transfer, and relates to the technical field of aviation power systems. The system includes an air inlet, a precooler, a compressor, a main turbine, a bypass combustion chamber, a bypass nozzle, a main combustion chamber, a regenerative cooling channel 1, a main nozzle, a hydrogen pump 1, a hydrogen turbine 1, an oxygen pump, a valve 1, a liquid oxygen storage tank, a liquid hydrogen storage tank, a valve 2, a valve 3, a valve 4, a hydrogen turbine 2, a hydrogen pump 2, a pressure vessel, a reactor core, a reflector, a regenerative cooling channel 2, and a nuclear thermal propulsion nozzle. By utilizing the above system, the present invention can realize switching between different power modes (air-breathing mode, liquid hydrogen and liquid oxygen rocket mode, and nuclear thermal rocket mode) in different flight phases. This multi-mode power conversion capability enables the aircraft to adapt to a full range of flight conditions from low speed to hypersonic speed and vacuum environment, thereby improving the flexibility and adaptability of the flight mission.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace power systems, and in particular to a horizontal take-off and landing aerospace power system suitable for single-stage orbit insertion and orbit transfer and an aircraft thereof. Background Art

[0002] With urgent demands for space mobility and space transportation in both the military and civilian sectors, reusable single-stage orbital propulsion systems have become a research hotspot in the aerospace field. Traditional spacecraft and aircraft typically require multi-stage rockets or different types of propulsion systems to complete the process from ground takeoff to orbital insertion. These systems are complex and heavy, limiting payload carrying capacity. During operation, each propulsion system switch introduces sudden changes in thrust, potentially leading to vehicle instability and mission complexity. Furthermore, the propulsion system and structural design make them difficult to reuse and have a limited lifespan, resulting in high launch and operational costs.

[0003] Among multiple spaceplane concepts, the combined rocket-powered, air-breathing propulsion scheme can meet the power requirements of the entire process from horizontal takeoff to orbital insertion. It features a high level of system integration, virtually no "dead weight" within the entire operating area, and no "thrust gap" issue. Among space propulsion systems, nuclear thermal propulsion systems offer advantages such as high energy density, high specific impulse, repeatable starts, high thrust, and a long operating life. They overcome the challenges of large-scale launches, long mission cycles, and high costs faced by traditional space propulsion systems in deep space exploration. They can meet the requirements of highly complex missions such as future manned Mars exploration, and possess irreplaceable advantages and enormous application potential in deep space exploration. Summary of the Invention

[0004] In view of this, the present invention aims to propose a horizontal take-off and landing aerospace power system and its aircraft suitable for single-stage orbital insertion and orbital transfer. Through an integrated multi-mode power system, the interfaces and separation devices between different propulsion systems are reduced, the structural design is simplified, and the reliability of the system is improved.

[0005] To achieve the above object, the technical solution of the present invention is achieved as follows:

[0006] A horizontal take-off and landing aerospace power system suitable for single-stage orbital insertion and orbital transfer, comprising an air inlet, a precooler, a compressor, a main turbine, a bypass combustion chamber, a bypass nozzle, a main combustion chamber, a first regenerative cooling channel, a main nozzle, a first hydrogen pump, a first hydrogen turbine, an oxygen pump, a first valve, a liquid oxygen tank, a liquid hydrogen tank, a second valve, a third valve, a fourth valve, a second hydrogen turbine, a second hydrogen pump, a nuclear reactor module, a second regenerative cooling channel, and a nuclear thermal propulsion nozzle;

[0007] The outlet of the air inlet is divided into two paths, one of which is connected to the inlet of the bypass combustion chamber, and the other is connected to the hot end inlet of the precooler; the outlet of the bypass combustion chamber is connected to the inlet of the bypass nozzle, the hot end outlet of the precooler is connected to the inlet of the compressor, the outlet of the compressor is connected to the inlet of the main combustion chamber, and the outlet of the main combustion chamber is connected to the inlet of the main nozzle;

[0008] The discharge port of the liquid oxygen storage tank is connected to the inlet of valve 1, the outlet of valve 1 is connected to the inlet of the oxygen pump, and the outlet of the oxygen pump is connected to the inlet of the main combustion chamber;

[0009] The discharge port of the liquid hydrogen storage tank is connected to the inlet of valve 2. The outlet of valve 2 is divided into two paths, one path is connected to the inlet of valve 3, and the other path is connected to the inlet of valve 4.

[0010] The outlet of valve three is connected to the inlet of hydrogen pump one, the outlet of hydrogen pump one is connected to the cold end inlet of the precooler, the cold end outlet of the precooler is connected to the inlet of regenerative cooling channel one provided outside the main nozzle and the main combustion chamber, the outlet of regenerative cooling channel one is connected to the inlet of hydrogen turbine one, the outlet of hydrogen turbine one is connected to the inlet of the main turbine, and the outlet of the main turbine is divided into two paths, one path is connected to the inlet of the bypass combustion chamber, and the other path is connected to the inlet of the main combustion chamber;

[0011] The outlet of the valve four is connected to the inlet of the hydrogen pump two, the outlet of the hydrogen pump two is connected to the nuclear thermal propulsion nozzle and the inlet of the regeneration cooling channel two arranged on the outside of the nuclear reactor module, the outlet of the regeneration cooling channel two is connected to the inlet of the hydrogen turbine two, the outlet of the hydrogen turbine two is connected to the inlet of the nuclear reactor module, and the outlet of the nuclear reactor module is connected to the inlet of the nuclear thermal propulsion nozzle.

[0012] Furthermore, the nuclear reactor module includes a pressure vessel, a reactor core and a reflective layer inside the pressure vessel, and the reflective layer is located outside the reactor core.

[0013] Furthermore, the size of the air inlet of the air inlet duct is adjustable so that the mass flow of air entering the engine meets a preset value.

[0014] Furthermore, the precooler is a non-contact precooler, and the incoming air and the cooling medium exchange heat through the wall of the heat exchanger.

[0015] Furthermore, the bypass nozzle, main nozzle and nuclear thermal propulsion nozzle are all Laval nozzles, among which the area ratio of the bypass nozzle and the main nozzle is adjustable, and the nozzles are in a fully expanded state under different flight conditions, while the area ratio of the nuclear thermal propulsion nozzle is fixed, and the profile is conical or bell-shaped.

[0016] Furthermore, the reactor core is a thermal neutron reactor or a fast neutron reactor, and the structure is an axial flow type or a radial flow type.

[0017] Furthermore, the hydrogen pump 1, the hydrogen turbine 1 and the oxygen pump are coaxially arranged, and the hydrogen turbine 1 drives the hydrogen pump 1 and the oxygen pump to do work, thereby eliminating a turbine structure and making it simpler.

[0018] Furthermore, the regenerative cooling channels arranged in both the main nozzle and the nuclear thermal propulsion nozzle can cool areas with high heat flux density such as the nozzle throat. At the same time, the hydrogen working fluid absorbs heat in the cooling channel to improve the working capacity.

[0019] Furthermore, when the equivalence ratio of the main combustion chamber is greater than one, the remaining fuel is passed into the bypass combustion chamber to avoid fuel waste.

[0020] According to another aspect of the present invention, there is provided an aerospace vehicle comprising the above-mentioned power system.

[0021] Furthermore, before the aircraft enters space, when the flight Mach number is greater than or equal to Ma0 and less than or equal to Ma5, the power system operates in an air-breathing mode, and when the flight Mach number is greater than Ma5, the power system operates in a liquid hydrogen and liquid oxygen rocket mode of a closed expansion cycle;

[0022] After the spacecraft enters space, the power system operates in a nuclear thermal rocket mode with a closed expansion cycle;

[0023] When the power system operates in the air-intake mode, valves 1 and 4 are closed, and valves 2 and 3 are open. Liquid hydrogen pressurized by hydrogen pump 1 is passed into the precooler to cool the incoming air from the intake duct. The hydrogen, which has absorbed heat and vaporized, is passed into the regeneration cooling channel 1 to cool the main nozzle, and then further absorbs heat in the main combustion chamber. The hydrogen with strong work capacity is then passed into hydrogen turbine 1 to perform work, and then the hydrogen is passed into the main turbine for further expansion and work, and finally passed into the bypass combustion chamber and the main combustion chamber to be mixed with air and then burned. The high-temperature combustion gas is discharged from the bypass nozzle and the main nozzle to generate thrust.

[0024] When the power system operates in a liquid hydrogen and liquid oxygen rocket mode with a closed expansion cycle: the air inlet is closed, the valve is opened, and the liquid hydrogen pressurized by the hydrogen pump is directly introduced into the regenerative cooling channel through a branch line to absorb heat and vaporize. The gaseous hydrogen is introduced into the hydrogen turbine to expand and perform work, and then directly introduced into the main combustion chamber through a branch line. The liquid oxygen pressurized by the oxygen pump is also introduced into the main combustion chamber. Then, the oxygen and hydrogen are mixed and burned in the main combustion chamber, and the high-temperature combustion gas is discharged from the main nozzle to generate thrust.

[0025] When the power system operates in the nuclear thermal rocket mode of the closed expansion cycle: valve one and valve three are closed, valve four is opened, the liquid hydrogen pressurized by hydrogen pump two is passed into the regeneration cooling channel two to absorb heat, and then enters the reflector layer channel to further absorb heat, hydrogen with strong working capacity is passed into the hydrogen turbine two to expand and do work, thereby driving the hydrogen pump two to pressurize the liquid hydrogen, the hydrogen at the outlet of hydrogen turbine two is passed into the nuclear reactor module, the hydrogen exchanges heat with the wall of the reactor core, and then passes into the nuclear thermal propulsion nozzle, and the high-temperature hydrogen is discharged from the nuclear thermal propulsion nozzle to generate thrust.

[0026] Compared with the prior art, the horizontal take-off and landing aerospace power system and the aircraft thereof suitable for single-stage orbit insertion and orbit transfer described in the present invention have the following advantages:

[0027] 1. The present invention has low design difficulty, strong power, and high working efficiency. It can meet the needs of future space maneuverability and space transportation. It has significant advantages in integration, adaptability, efficiency, safety, environmental protection, etc., and has broad application prospects and development potential.

[0028] 2. This invention constructs a horizontal take-off and landing aerospace propulsion system and aircraft suitable for single-stage orbital insertion and orbital transfer. The system can switch between different propulsion modes (air-breathing mode, liquid hydrogen and liquid oxygen rocket mode, and nuclear thermal rocket mode) during different flight phases. This multi-mode power conversion capability enables the aircraft to adapt to the full range of flight conditions, from low speed to hypersonic speed and vacuum environments, improving the flexibility and adaptability of flight missions. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] The accompanying drawings, which constitute part of the present invention, are provided to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are provided to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0030] Figure 1 The horizontal take-off and landing aerospace power system and the aircraft thereof suitable for single-stage orbit insertion and orbit transfer as described in the embodiments of the present invention;

[0031] Description of reference numerals:

[0032] 1-air inlet, 2-precooler, 3-compressor, 4-main turbine, 5-bypass combustion chamber, 6-bypass nozzle, 7-main combustion chamber, 8-regenerative cooling channel one, 9-main nozzle, 10-hydrogen pump one, 11-hydrogen turbine one, 12-oxygen pump, 13-valve one, 14-liquid oxygen tank, 15-liquid hydrogen tank, 16-valve two, 17-valve three, 18-valve four, 19-hydrogen turbine two, 20-hydrogen pump two, 21-pressure vessel, 22-reactor core, 23-reflector, 24-regenerative cooling channel two, 25-nuclear thermal propulsion nozzle. DETAILED DESCRIPTION

[0033] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features therein may be combined with each other.

[0034] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0035] On the one hand, the embodiment of the present invention discloses a horizontal take-off and landing aerospace power system suitable for single-stage orbit insertion and orbit transfer, such as Figure 1 As shown, it includes an air inlet 1, a precooler 2, a compressor 3, a main turbine 4, a bypass combustion chamber 5, a bypass nozzle 6, a main combustion chamber 7, a regenerative cooling channel 1 8, a main nozzle 9, a hydrogen pump 1 10, a hydrogen turbine 1 11, an oxygen pump 12, a valve 1 13, a liquid oxygen tank 14, a liquid hydrogen tank 15, a valve 2 16, a valve 3 17, a valve 4 18, a hydrogen turbine 2 19, a hydrogen pump 2 20, a pressure vessel 21, a reactor core 22, a reflector 23, a regenerative cooling channel 2 24, and a nuclear thermal propulsion nozzle 25.

[0036] The outlet of the air inlet 1 is divided into two routes, one route is connected to the inlet of the bypass combustion chamber 5, and the outlet of the bypass combustion chamber 5 is connected to the bypass nozzle 6; the other outlet of the air inlet 1 is connected to the hot end inlet of the precooler 2, and the hot end outlet of the precooler 2 is connected to the inlet of the compressor 3, and the outlet of the compressor 3 is connected to the inlet of the main combustion chamber 7, and the outlet of the main combustion chamber 7 is connected to the inlet of the main nozzle 9.

[0037] The discharge port of the liquid oxygen storage tank 14 is connected to the inlet of valve 13 , the outlet of valve 13 is connected to the inlet of the oxygen pump 12 , and the outlet of the oxygen pump 12 is connected to the inlet of the main combustion chamber 7 .

[0038] The discharge port of the liquid hydrogen storage tank 15 is connected to the inlet of valve 2 16 . The outlet of valve 2 16 is divided into two paths, one of which is connected to the inlet of valve 3 17 . The outlet of valve 3 17 is connected to the inlet of hydrogen pump 10 , which is connected to the cold end inlet of precooler 2 , which is connected to the inlet of regenerative cooling channel 1 8 , which is connected to the inlet of hydrogen turbine 11 , which is connected to the inlet of main turbine 4 . The outlet of main turbine 4 is divided into two branches, one connected to the inlet of bypass combustor 5 , and the other connected to the inlet of main combustor 7 . In this embodiment, regenerative cooling channel 1 8 is located outside the main combustor 7 and main nozzle 9 .

[0039] Another outlet of valve two 16 is connected to the inlet of valve four 18, the outlet of valve four 18 is connected to the inlet of hydrogen pump two 20, the outlet of hydrogen pump two 20 is connected to the inlet of regeneration cooling channel two 24, the outlet of regeneration cooling channel two 24 is connected to the inlet of hydrogen turbine two 19, the outlet of hydrogen turbine two 19 is connected to the inlet of nuclear reactor module, the outlet of nuclear reactor module is connected to the inlet of nuclear thermal propulsion nozzle 25. In this embodiment, regeneration cooling channel two 24 is located outside the pressure vessel 21 and the nuclear thermal propulsion nozzle 25 outside the nuclear reactor module, and the nuclear reactor module is located inside the pressure vessel 21, including the reactor core 22 and the reflective layer 23 outside the reactor core 22.

[0040] In this embodiment, the size of the air inlet of the air inlet duct 1 is adjustable so that the mass flow of air entering the engine meets a preset value.

[0041] In this embodiment, the precooler 2 is a non-contact precooler, and the incoming air and the cooling medium exchange heat through the wall of the heat exchanger.

[0042] In this embodiment, the bypass nozzle 6, the main nozzle 9 and the nuclear thermal propulsion nozzle 25 are all Laval nozzles, wherein the area ratio of the bypass nozzle 6 and the main nozzle 9 is adjustable, and the nozzles are in a fully expanded state under different flight conditions, while the area ratio of the nuclear thermal propulsion nozzle 25 is fixed, and the profiles of the bypass nozzle 6, the main nozzle 9 and the nuclear thermal propulsion nozzle 25 are conical or bell-shaped.

[0043] In this embodiment, the reactor core 22 is a thermal neutron reactor or a fast neutron reactor, and has an axial flow or radial flow structure.

[0044] In this embodiment, the main turbine 4 is connected to the compressor 3 via a shaft, that is, the power output end of the main turbine 4 is connected to the power input end of the compressor 3 .

[0045] In this embodiment, the hydrogen pump 10, hydrogen turbine 11 and oxygen pump 12 are coaxially arranged, and the hydrogen turbine 11 drives the hydrogen pump 10 and the oxygen pump 12 to do work, which makes the structure simpler.

[0046] In this embodiment, the main nozzle 9 and the nuclear thermal propulsion nozzle 25 are both provided with regenerative cooling channels, which can cool areas with high heat flux density such as the nozzle throat. At the same time, the hydrogen working fluid absorbs heat in the cooling channel to improve the working capacity.

[0047] In this embodiment, a bypass combustion chamber 5 and a bypass nozzle 6 are provided. When the equivalence ratio of the main combustion chamber is greater than one, the remaining fuel is introduced into the bypass combustion chamber to avoid fuel waste.

[0048] According to another aspect of the present invention, this embodiment further provides an aviation vehicle, which includes the above-mentioned aerospace propulsion system.

[0049] In this embodiment, before the aircraft enters space, the power system operates in an air-breathing mode when the flight Mach number is greater than or equal to Ma0 and less than or equal to Ma5; when the flight Mach number is greater than Ma5, the power system operates in a liquid hydrogen and liquid oxygen rocket mode with a closed expansion cycle; after the aircraft enters space, the power system operates in a nuclear thermal rocket mode with a closed expansion cycle.

[0050] In the embodiment of the present invention, the Karman line is used as the boundary between the atmosphere and space. When the aircraft crosses the Karman line, it means that the aircraft has entered space. When the power system operates in the air-breathing mode: valve one 13 and valve four 18 are in the closed state, valve two 16 and valve three 17 are open, and the liquid hydrogen pressurized by the hydrogen pump one 10 is passed into the precooler 2 to cool the incoming air of the intake duct 1. The hydrogen after absorbing heat and vaporization is passed into the regeneration cooling channel one 8 to cool the main nozzle 9, and then further absorbs heat in the main combustion chamber. The hydrogen with strong working capacity is then passed into the hydrogen turbine one 11 to do work, and then the hydrogen is passed into the main turbine 4 to further expand and do work, and finally passed into the bypass combustion chamber 5 and the main combustion chamber 7 to be mixed with air and then burned. The high-temperature combustion gas is discharged from the bypass nozzle 6 and the main nozzle 9 to generate thrust.

[0051] When the power system operates in the liquid hydrogen and liquid oxygen rocket mode of the closed expansion cycle: the air inlet 1 is closed, the valve 13 is opened, the liquid hydrogen pressurized by the hydrogen pump 10 is directly introduced into the regeneration cooling channel 8 through a branch line to absorb heat and vaporize, the gaseous hydrogen is introduced into the hydrogen turbine 11 to expand and do work, and then is directly introduced into the main combustion chamber 7 through a branch line, the liquid oxygen pressurized by the oxygen pump 12 is also introduced into the main combustion chamber 7, and then the oxygen and hydrogen are mixed and burned in the main combustion chamber 7, and the high-temperature combustion gas is discharged from the main nozzle 9 to generate thrust.

[0052] When the power system operates in the nuclear thermal rocket mode of the closed expansion cycle: valve one 13 and valve three 17 are closed, valve four 18 is opened, and the liquid hydrogen pressurized by hydrogen pump two 20 is passed into the regeneration cooling channel two 24 to absorb heat, and then enters the reflection layer 23 channel to further absorb heat. Hydrogen with strong working capacity is passed into the hydrogen turbine two 19 to expand and do work, thereby driving the hydrogen pump two 20 to pressurize the liquid hydrogen. The hydrogen at the outlet of hydrogen turbine two 19 is passed into the nuclear reactor module, and the hydrogen exchanges heat with the wall of the reactor core 22, and then passes into the nuclear thermal propulsion nozzle 25. The high-temperature hydrogen is discharged from the nuclear thermal propulsion nozzle 25 to generate thrust.

[0053] The working principle of the present invention is:

[0054] It is possible to switch between different power modes at different flight stages. When the flight Mach number is Ma0 to Ma5 (including Ma0 and Ma5), the power system is in the intake mode. At this time, valve 13 and valve 4 18 are closed, valve 2 16 and valve 3 17 are open, and the liquid hydrogen pressurized by hydrogen pump 10 is passed into the precooler 2 to cool the incoming air of the inlet duct 1. The hydrogen after absorbing heat and vaporization is passed into the regeneration cooling channel 8 to cool the main nozzle 9, and then further absorbs heat in the main combustion chamber. The hydrogen with strong work-doing ability is then passed into the hydrogen turbine 11 to do work, and then the hydrogen is passed into the main turbine 4 to further expand and do work, and finally passed into the regeneration cooling channel 8 to cool the main nozzle 9. Entering the bypass combustion chamber 5 and the main combustion chamber 7, the main turbine 4 is connected to the compressor 3 through a shaft to realize power transmission. The high-pressure air compressed by the compressor 3 is passed into the main combustion chamber 7 through a pipeline and mixed with the air and then burned. The high-temperature combustion gas is discharged from the main nozzle 9 to generate thrust; as the flight Mach number increases, the cooling fuel of the precooler 2 will be greater than the combustion fuel. At this time, part of the air is directly passed into the bypass combustion chamber 5 by adjusting the air inlet 1, and the remaining fuel is also passed into the bypass combustion chamber 5. The two are mixed and burned, and the high-temperature combustion gas is discharged from the bypass nozzle 6 to generate thrust. This arrangement avoids fuel waste and improves the specific impulse of the power system.

[0055] When the flight Mach number Ma is greater than 5, the total temperature of the incoming air is too high and the turbine engine cannot continue to work. At this time, a liquid hydrogen and liquid oxygen rocket mode based on a closed expansion cycle is adopted. The air inlet 1 is closed and the valve 13 is opened. The liquid hydrogen pressurized by the hydrogen pump 10 is directly introduced into the regeneration cooling channel 8 through a branch line to absorb heat and vaporize. The gaseous hydrogen is introduced into the hydrogen turbine 11 to expand and do work, and then directly introduced into the main combustion chamber 7 through a branch line. The liquid oxygen pressurized by the oxygen pump 12 is also introduced into the main combustion chamber 7. Then, oxygen and hydrogen are mixed and burned in the main combustion chamber 7. The high-temperature combustion gas is discharged from the main nozzle 9 to generate thrust. The advantage of the high specific thrust of the rocket mode is used to send the aircraft into the predetermined orbit faster.

[0056] After the spacecraft enters space, in order to achieve tasks such as rapid orbit transfer and space transportation, the spacecraft still has a high thrust requirement. At this time, when the nuclear thermal rocket mode based on the closed expansion cycle is adopted: valve one 13 and valve three 17 are closed, and valve four 18 is opened. The liquid hydrogen pressurized by hydrogen pump two 20 is passed into the regeneration cooling channel two 24 to absorb heat, and then enters the reflection layer 23 channel to further absorb heat. Hydrogen with strong working capacity is passed into hydrogen turbine two 19 to expand and do work, thereby driving hydrogen pump two 20 to pressurize the liquid hydrogen. The hydrogen at the outlet of hydrogen turbine two 19 is passed into the nuclear reactor module, and the hydrogen exchanges heat with the wall of the reactor core 22, and then passes into the nuclear thermal propulsion nozzle 25. The high-temperature hydrogen is discharged from the nuclear thermal propulsion nozzle 25 to generate thrust. The use of the nuclear thermal rocket mode can effectively utilize the advantages of the high capacity density and power density of the nuclear reactor, while reducing the amount of liquid oxygen carried, effectively reducing the take-off weight of the aircraft, and improving the thrust-to-weight ratio.

[0057] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A horizontal take-off and landing aerospace propulsion system suitable for single-stage orbital insertion and orbital transfer, characterized by: The invention comprises an air inlet (1), a precooler (2), a compressor (3), a main turbine (4), a bypass combustion chamber (5), a bypass nozzle (6), a main combustion chamber (7), a regenerative cooling channel 1 (8), a main nozzle (9), a hydrogen pump 1 (10), a hydrogen turbine 1 (11), an oxygen pump (12), a valve 1 (13), a liquid oxygen tank (14), a liquid hydrogen tank (15), a valve 2 (16), a valve 3 (17), a valve 4 (18), a hydrogen turbine 2 (19), a hydrogen pump 2 (20), a nuclear reactor module, a regenerative cooling channel 2 (24) and a nuclear thermal propulsion nozzle (25); The outlet of the air inlet (1) is divided into two paths, one path is connected to the inlet of the bypass combustion chamber (5), and the other path is connected to the hot end inlet of the precooler (2); the outlet of the bypass combustion chamber (5) is connected to the inlet of the bypass nozzle (6), the hot end outlet of the precooler (2) is connected to the inlet of the compressor (3), the outlet of the compressor (3) is connected to the inlet of the main combustion chamber (7), and the outlet of the main combustion chamber (7) is connected to the inlet of the main nozzle (9); The discharge port of the liquid oxygen storage tank (14) is connected to the inlet of valve one (13), the outlet of the valve one (13) is connected to the inlet of the oxygen pump (12), and the outlet of the oxygen pump (12) is connected to the inlet of the main combustion chamber (7); The discharge port of the liquid hydrogen storage tank (15) is connected to the inlet of valve 2 (16), and the outlet of valve 2 (16) is divided into two paths, one path is connected to the inlet of valve 3 (17), and the other path is connected to the inlet of valve 4 (18); The outlet of the valve three (17) is connected to the inlet of the hydrogen pump one (10), the outlet of the hydrogen pump one (10) is connected to the cold end inlet of the precooler (2), the cold end outlet of the precooler (2) is connected to the main nozzle (9) and the inlet of the regeneration cooling channel one (8) provided outside the main combustion chamber (7), the outlet of the regeneration cooling channel one (8) is connected to the inlet of the hydrogen turbine one (11), the outlet of the hydrogen turbine one (11) is connected to the inlet of the main turbine (4), the outlet of the main turbine (4) is divided into two paths, one path is connected to the inlet of the bypass combustion chamber (5), and the other path is connected to the inlet of the main combustion chamber (7); The outlet of the valve 4 (18) is connected to the inlet of the hydrogen pump 2 (20), the outlet of the hydrogen pump 2 (20) is connected to the nuclear thermal propulsion nozzle (25) and the inlet of the regeneration cooling channel 2 (24) arranged outside the nuclear reactor module, the outlet of the regeneration cooling channel 2 (24) is connected to the inlet of the hydrogen turbine 2 (19), the outlet of the hydrogen turbine 2 (19) is connected to the inlet of the nuclear reactor module, and the outlet of the nuclear reactor module is connected to the inlet of the nuclear thermal propulsion nozzle (25).

2. The horizontal take-off and landing aerospace propulsion system suitable for single-stage orbital insertion and orbital transfer according to claim 1, characterized in that: The nuclear reactor module comprises a pressure vessel (21), a reactor core (22) and a reflective layer (23) inside the pressure vessel (21), wherein the reflective layer (23) is located outside the reactor core (22).

3. The horizontal take-off and landing aerospace propulsion system suitable for single-stage orbital insertion and orbital transfer according to claim 1, characterized in that: The size of the air inlet of the air inlet duct (1) is adjustable.

4. The horizontal take-off and landing aerospace propulsion system suitable for single-stage orbital insertion and orbital transfer according to claim 1, characterized in that: The precooler (2) is a non-contact precooler.

5. The horizontal take-off and landing aerospace power system suitable for single-stage orbital insertion and orbital transfer according to claim 1, characterized in that: The bypass nozzle (6), the main nozzle (9) and the nuclear thermal propulsion nozzle (25) are all Laval nozzles, wherein the area ratio of the bypass nozzle (6) and the main nozzle (9) is adjustable. Under different flight conditions, the nozzles are in a fully expanded state, while the area ratio of the nuclear thermal propulsion nozzle (25) is fixed.

6. The horizontal take-off and landing aerospace propulsion system suitable for single-stage orbital insertion and orbital transfer according to claim 2, characterized in that: The reactor core (22) is a thermal neutron reactor or a fast neutron reactor, and has an axial flow or radial flow structure.

7. The horizontal take-off and landing aerospace propulsion system suitable for single-stage orbital insertion and orbital transfer according to claim 1, characterized in that: The hydrogen pump (10), the hydrogen turbine (11) and the oxygen pump (12) are coaxially arranged, and the hydrogen turbine (11) drives the hydrogen pump (10) and the oxygen pump (12) to do work.

8. The horizontal take-off and landing aerospace propulsion system suitable for single-stage orbital insertion and orbital transfer according to claim 1, characterized in that: When the equivalence ratio of the main combustion chamber is greater than one, the remaining fuel enters the bypass combustion chamber (6) through the bypass nozzle (6) for combustion.

9. An aircraft, characterized in that: The aircraft includes a horizontal take-off and landing aerospace power system suitable for single-stage orbit insertion and orbit transfer as described in any one of claims 1-8.

10. An aircraft according to claim 9, characterized in that: Before the aircraft enters space, when the flight Mach number is greater than or equal to Ma0 and less than or equal to Ma5, the power system operates in the air-breathing mode; when the flight Mach number is greater than Ma5, the power system operates in the liquid hydrogen and liquid oxygen rocket mode of the closed expansion cycle; After the spacecraft enters space, the power system operates in a nuclear thermal rocket mode with a closed expansion cycle; When the power system operates in the air intake mode: valve one (13) and valve four (18) are in a closed state, valve two (16) and valve three (17) are opened, and the liquid hydrogen pressurized by hydrogen pump one (10) is passed into the precooler (2) to cool the incoming air of the intake duct (1), and the hydrogen gas after absorbing heat and vaporizing is passed into the regeneration cooling channel one (8) to cool the main nozzle (9), and then further absorbs heat in the main combustion chamber, and then the hydrogen with strong working capacity is passed into the hydrogen turbine one (11) to do work, and then the hydrogen is passed into the main turbine (4) to further expand and do work, and finally passed into the bypass combustion chamber (5) and the main combustion chamber (7) to be mixed with air and then burned, and the high-temperature combustion gas is discharged from the bypass nozzle (6) and the main nozzle (9) to generate thrust; When the power system operates in a liquid hydrogen and liquid oxygen rocket mode of a closed expansion cycle: the air inlet (1) is closed, the valve (13) is opened, the liquid hydrogen pressurized by the hydrogen pump (10) is directly introduced into the regeneration cooling channel (8) through a branch line to absorb heat and vaporize, the gaseous hydrogen is introduced into the hydrogen turbine (11) to expand and perform work, and then directly introduced into the main combustion chamber (7) through a branch line, the liquid oxygen pressurized by the oxygen pump (12) is also introduced into the main combustion chamber (7), and then the oxygen and hydrogen are mixed and burned in the main combustion chamber (7), and the high-temperature combustion gas is discharged from the main nozzle (9) to generate thrust; When the power system operates in the nuclear thermal rocket mode of the closed expansion cycle: valve one (13) and valve three (17) are closed, valve four (18) is opened, and the liquid hydrogen pressurized by hydrogen pump two (20) is passed into the regeneration cooling channel two (24) to absorb heat, and then enters the reflection layer (23) channel to further absorb heat, and hydrogen with strong working capacity is passed into hydrogen turbine two (19) to expand and do work, thereby driving hydrogen pump two (20) to pressurize the liquid hydrogen, and the hydrogen at the outlet of hydrogen turbine two (19) is passed into the nuclear reactor module, and the hydrogen exchanges heat with the wall of the reactor core (22), and then passes into the nuclear thermal propulsion nozzle (25), and the high-temperature hydrogen is discharged from the nuclear thermal propulsion nozzle (25) to generate thrust.

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