Aerospace aircraft combined with carrier aircraft based on axial series coupling architecture

Abstract

The invention discloses an axial series coupling framework aerospace aircraft and carrier aircraft combined aerospace vehicle which comprises an aerospace aircraft and a carrier aircraft with variable sweepback wings. A double-body platform axial series connection design is adopted, full-system reuse is achieved through pneumatic coupling synergy and intelligent power management, and conventional airport take-off and high-altitude separation are supported. The aerospace aircraft and the carrier aircraft both have autonomous return capability, and the power system adopts a three-level switching strategy and supports air combustion supporting and liquid oxygen propelling. And full-process reusable transmission is realized. The carrier aircraft is provided with a variable sweepback wing mechanism, and the aerospace aircraft is integrated with a replaceable heat-resistant protective layer. The modular design supports the kiloton-level carrying capacity, the launching cost is remarkably reduced, and the safety is improved. The method is used for aerospace high-frequency transportation tasks, and fills the technical blank of air-launched aerospace aircraft orbit injection control.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace transportation, and particularly to an aerospace vehicle of a combined carrier aircraft of a spaceplane based on an axial series coupling architecture. Through a modular structure and an autonomous recovery technology, low-cost and low-risk aerospace transportation is achieved. Background Art

[0002] Existing space launches mainly rely on ground rockets or partially recoverable rockets, but there are the following problems: The recovery of rocket boosters consumes a large amount of fuel, and the recovery success rate is limited; the launch cost of space shuttles is high and they are not reusable, and it is easy to generate space debris; traditional carrier aerospace vehicles are difficult to achieve the efficient orbital injection of large-weight payloads.

[0003] To solve the above problems, the present invention provides an aerospace vehicle of a combined carrier aircraft of a spaceplane based on an axial series coupling architecture, which reduces fuel consumption through aerodynamic design and realizes the full recovery of the carrier aircraft and the spaceplane.

[0004] The structure of the aerospace vehicle is like the combination of a spaceplane and a Tu-160 bomber. The overall structure of the combined aerospace vehicle is like a stretched J-15 fighter jet. The nose and canard wings are part of the spaceplane. The fuselage, main wings, horizontal tail wings, and vertical tail wings are like a headless Tu-160 bomber.

[0005] Based on the existing technology, an aerospace vehicle of a combined carrier aircraft of a spaceplane based on an axial series coupling architecture is innovatively invented. The An-225 transport aircraft transports the Soviet Buran spaceplane in a parallel manner, that is, it is a parallel structure in which the Buran spaceplane is carried on the back of the An-225 transport aircraft. And this aerospace vehicle changes the spaceplane into a series structure with the carrier aircraft. The overall aerodynamic layout of the combined carrier aerospace vehicle is like a stretched J-15 fighter jet. The main wings of the carrier aircraft are variable-sweep wings, and its layout is like that of a Tu-160 bomber. This aerodynamic layout has a reasonable structure, makes full use of the lift characteristics of the spaceplane and the carrier aircraft, has small wind resistance, and is safe and reliable. Summary of the Invention

[0006] The object of the present invention is to provide an aerospace vehicle of a combined carrier aircraft of a spaceplane based on an axial series coupling architecture to solve the above problems, which can make full use of the existing technical achievements and achieve many problems such as low-cost, recoverable, energy-saving and environmental protection in space launches through innovative combination.

[0007] The technical solution adopted by the present invention to solve its technical problems is as follows: An aerospace vehicle combining a spaceplane and a carrier aircraft based on an axial series coupling architecture, including a spaceplane and a carrier aircraft. The aerospace vehicle adopts a dual-body fuselage axial series combination design with the spaceplane in the front and the carrier aircraft in the rear. The spaceplane of the aerospace vehicle includes a spaceplane nose, a spaceplane fuselage, a spaceplane main wing, a spaceplane vertical tail, a rocket engine at the tail end of the spaceplane, and a connecting buckle at the tail end of the spaceplane; or the spaceplane of the aerospace vehicle is a spaceplane including a spaceplane nose, a spaceplane fuselage, a foldable main wing or a variable sweep wing of the spaceplane, a spaceplane vertical tail, a rocket engine and a compound jet engine at the tail end of the spaceplane, and a connecting buckle at the tail end of the spaceplane.

[0008] The carrier aircraft of the aerospace vehicle includes a carrier aircraft nose, and the carrier aircraft nose is provided with a connecting buckle corresponding to the connecting buckle at the tail end of the spaceplane, a carrier aircraft fuselage, a carrier aircraft main wing, a jet engine on the carrier aircraft main wing, a rear tail wing of the carrier aircraft, and a vertical tail of the carrier aircraft; or the carrier aircraft of the aerospace vehicle includes a carrier aircraft nose, and the carrier aircraft nose is provided with a connecting buckle corresponding to the connecting buckle at the tail end of the spaceplane, a carrier aircraft fuselage, a main variable sweep wing of the carrier aircraft, a jet engine on the main variable sweep wing, a rear tail wing of the carrier aircraft, and a vertical tail of the carrier aircraft; wherein, the carrier aircraft body is configured with a cold launch system for compressed air built into the fuselage, a liquid oxygen tank, a fuel tank, and a fuel expansion tank built into the main wing; a compressed air cold launch system is provided inside the carrier aircraft nose. Through the release of the compressed air cold launch system, the spaceplane and the carrier aircraft are separated, and by using the reaction force, part of the kinetic energy of the carrier aircraft is transferred through the compressed air cold launch to further accelerate the spaceplane and cause the spaceplane to ignite after separation from the carrier aircraft, avoiding ablation damage to the carrier aircraft caused by the tail flame of the spaceplane.

[0009] According to the uses and mission requirements of the carrier aircraft, the jet engine is integrally designed with the fuselage, including that the jet engines are symmetrically arranged under the main wing of the carrier aircraft; or the jet engine is integrally designed with the fuselage, symmetrically arranged under the main wing of the carrier aircraft and one engine provided on the vertical tail; or the jet engines of the carrier aircraft are integrally designed with the fuselage, symmetrically arranged under the main wing of the carrier aircraft and two symmetric jet engines on both sides of the vertical tail; or the jet engines of the carrier aircraft are integrally designed with the fuselage, symmetrically arranged under the main wing of the carrier aircraft and three jet engines arranged in a triangular pattern between the two vertical tails.

[0010] An integrated aerodynamic coupling configuration is formed by combining a spaceplane and a carrier aircraft; at the connection between the spaceplane and the carrier aircraft of the space vehicle, a docking locking mechanism composed of a wedge-shaped connection buckle and a pin is provided for connection. The tail of the spaceplane and the head of the carrier aircraft form the space vehicle. Among them, the pin is a telescopic pin group corresponding to the wedge-shaped connection buckle. The telescopic pin group positions the wedge-shaped connection buckle by inserting the telescopic pin group into the pin sleeve group at the tail of the spaceplane. By withdrawing the telescopic pin group from the pin sleeve group inserted into the tail of the spaceplane, the unlocking of the wedge-shaped connection buckle is realized. The spaceplane and the carrier aircraft improve the connection stiffness between the spaceplane and the carrier aircraft by inserting and connecting the telescopic pin group and the pin sleeve group. The spaceplane and the carrier aircraft are separated by opening the docking locking mechanism with an electromagnetic lock at a set altitude and ejecting compressed air forward.

[0011] The main wing of the carrier aircraft and the wing of the spaceplane are aerodynamically coupled in coordination. During takeoff at a conventional airport, it taxis and accelerates through a conventional takeoff method to provide a huge lift force, enabling the space vehicle to take off, climb, and accelerate from a conventional airport; or after the space vehicle reaches a set altitude and speed, the main wing of the carrier aircraft of the space vehicle is a variable-sweep wing, which reduces flight resistance and further improves flight speed and altitude. The combined space vehicle is equipped with a three-stage power switching system of air-assisted combustion at low altitude, liquid oxygen gasification-assisted combustion at high altitude, and rocket launch flight of the spaceplane, enabling the space vehicle to use an air-assisted combustion engine at the low-altitude stage, switch to a liquid oxygen gasification-assisted combustion engine at the high-altitude stage. A compressed air cold launch system is provided inside the nose of the carrier aircraft of the space vehicle. When the space vehicle flies to a set altitude, reaches a set speed, and flies to a set longitude and latitude position, the compressed air in the compressed air cold launch system is ejected forward and released to separate the spaceplane from the carrier aircraft and further accelerate the spaceplane. After the spaceplane and the carrier aircraft are separated, the three-stage power rocket on the spaceplane ignites and launches into orbit at high altitude.

[0012] After completing the mission, the spaceplane returns to the airport through control or autonomously; after completing the mission, the carrier aircraft returns to the airport through control or autonomously, realizing the full-process reusable launch and recovery of the space vehicle composed of the spaceplane and the carrier aircraft.

[0013] The structure of the space vehicle can achieve low overall flight air resistance, strong controllability and coordination ability, greatly reduced carrier oxidant, and the recycling of the spaceplane and the carrier aircraft can be rationally operated and deployed using the existing aviation technology accumulation, realizing the organic combination of the spaceplane and the carrier aircraft, making the space launch of the space vehicle environmentally friendly, energy-saving, stable, safe, recyclable, not generating space debris, and can greatly reduce the space transportation cost of the space vehicle, solving the problems of huge investment and high cost in space engineering and the inability to fully recycle and utilize, making spaceflight simpler, more reliable, and more environmentally friendly.

[0014] An aerospace vehicle of a combined carrier aircraft for a spaceplane based on an axial series-coupling architecture. The carrier aircraft uses an air-combined oxygen-assisted combustion jet engine as the propulsion power. Among them, the jet engine includes a turbofan engine, a ramjet engine, a variable cycle engine, and a deflagration engine; it supports the power switch between air-assisted combustion in the atmosphere and high-altitude liquid oxygen gasification propulsion; the main wing of the carrier aircraft uses high-temperature-resistant composite materials and supports multiple mission cycles; the switching logic of the three-stage power system is: 0-10 km altitude: pure turbofan mode; 10-30 km altitude: ramjet-turbofan hybrid mode; 30 km altitude: liquid oxygen gasification full-assisted combustion mode.

[0015] An aerospace vehicle of a combined carrier aircraft for a spaceplane based on an axial series-coupling architecture. During its takeoff phase: the combined body takes off by taxiing on a conventional airport, and the jet engine provides thrust; when the flight altitude reaches the set altitude, the liquid oxygen gasification assisted combustion is started, and the main wing sweep angle is adjusted to the set angle; a wedge-shaped connection buckle groove is provided at the connection between the carrier aircraft and the spaceplane. An electromagnetic lock is built into the wedge-shaped connection buckle groove. When separating, the lock is released through an electric current pulse, and the compressed air injection system is started synchronously during separation; the connection stiffness is improved by inserting connection pins and pin sleeve groups; the inserted connection pins and sleeves are made of high-stiffness composite materials.

[0016] An aerospace vehicle of a combined carrier aircraft for a spaceplane based on an axial series-coupling architecture. After the carrier aircraft separates, a conical fairing is formed by the nose retraction and deformation. The fairing adopts an adaptive aerodynamic shape design to achieve controllable gliding landing.

[0017] An aerospace vehicle of a combined carrier aircraft for a spaceplane based on an axial series-coupling architecture. The carrier aircraft is internally equipped with modular fuel tanks. The carrier aircraft is internally equipped with a liquid oxygen tank (fuselage) + fuel tank (main wing). The main wing is provided with a variable sweep mechanism (the sweep angle is continuously adjustable from 5° to 70°); the spaceplane uses a high-temperature-resistant composite material main wing and is equipped with a detachable thermal protection layer and modular engines; Separation logic: when reaching the speed and altitude, the liquid oxygen pipeline is opened → the gasified oxygen is distributed → the electromagnetic lock is unlocked → cold launch separation; after the carrier aircraft separates, it retracts and deforms, and the spaceplane glides and lands through the wing aerodynamic control surfaces.

[0018] The jet engine group includes a turbofan engine, a ramjet engine, a variable cycle engine or a deflagration engine. The layout forms include: at least symmetric twin engines on the lower side of the main wing, at least symmetric twin engines on the lower side of the main wing + single engine on the vertical tail, at least symmetric twin engines on the lower side of the main wing + symmetric twin engines on the vertical tail, at least symmetric twin engines on the lower side of the main wing + triple engines between the twin vertical tails.

[0019] The two aircraft are connected by a combined mechanism of a wedge-shaped docking buckle groove and a pin, and are unlocked at a set height with the cooperation of an electromagnetic lock. After separation, the three-stage rocket of the spaceplane ignites and enters orbit; both the carrier aircraft and the spaceplane have the ability to return by aerodynamic gliding and can be quickly reorganized through standardized interfaces.

[0020] The combined body adopts an integrated aerodynamic coupling design and has a three-stage power switching system: pure turbofan propulsion from 0 to 10 km, ramjet-turbofan hybrid propulsion from 10 to 20 km, and liquid oxygen gasification assisted combustion propulsion from 20 to 30 km, realizing full-process reusable launch and recovery.

[0021] Based on the axial series coupling architecture of the spaceplane combined with the carrier aircraft, an aerospace vehicle. When the spaceplane ignites and detaches, the carrier aircraft retracts its opening and glides down; for return and reorganization: the spaceplane adjusts its attitude through aerodynamic wings, and the carrier aircraft autonomously lands and reorganizes with the spaceplane.

[0022] Based on the axial series coupling architecture of the spaceplane combined with the carrier aircraft, an aerospace vehicle. The combined aerospace vehicle adopts an artificial intelligence collaborative control system, supporting autonomous return in manned or unmanned modes.

[0023] Based on the axial series coupling architecture of the spaceplane combined with the carrier aircraft, an aerospace vehicle. The carrier aircraft has a liquid oxygen tank and a fuel tank built into its fuselage, a fuel tank built into its main wing, and jet engines symmetrically arranged on the wings, providing power for the aerospace vehicle to fly in the atmosphere; the carrier aircraft of the aerospace vehicle may be equipped with a main wing mechanism with variable sweep wings to adapt to the aerodynamic requirements of different flight stages; the spaceplane and the carrier aircraft of the aerospace vehicle separate by ignition after reaching the set height, speed, and position, enter the set orbit in space, and after completing the space mission, return to the earth airport by aerodynamic gliding of the spaceplane wings and can be reused repeatedly.

[0024] The main wing of the spaceplane is a fixed wing or a foldable wing or a variable sweep wing; the main wing of the spaceplane is made of high-temperature resistant composite materials and can be quickly reorganized with the fuselage of the carrier aircraft through a standardized interface after landing; the spaceplane is equipped with a repairable and replaceable thermal protection layer and engine, supporting multiple space mission cycles.

[0025] The power source of the spaceplane may consist of two parts, including a liquid oxygen rocket engine and an air dual-oxidizer assisted combustion jet engine, and the air dual-oxidizer assisted combustion jet engine is provided with a retractable and hidden air intake on the fuselage.

[0026] Between the spaceplane and the carrier aircraft, they fly in coordination through manned or artificial intelligence control. The space vehicle pushes the combined spaceplane to taxi and take off at the airport in a conventional manner. It uses air-assisted combustion in the low-altitude stage. After reaching the set flight speed and altitude, the main wing of the carrier aircraft has a variable sweep angle wing. When reaching the set altitude, the liquid oxygen pipeline is opened, and through the engine vaporization device, the vaporized oxygen is distributed to each engine to make up for the lack of oxygen at high altitudes. After reaching the set altitude, speed and position, the latch is opened, and through compressed air cold launch, the spaceplane is separated from the carrier aircraft; the self-carried liquid oxygen and fuel of the spaceplane are ignited to accelerate into the set orbit.

[0027] This carrier aircraft has a large takeoff weight. It uses air-assisted combustion in the atmosphere stage, reducing the consumption of oxidizer. After reaching the set altitude in the high-altitude stratosphere, the engine mixes and burns with the vaporized liquid oxygen and fuel to push the space vehicle to fly, pushing the spaceplane to the set altitude. The spaceplane of the space vehicle is separated from the carrier aircraft. The spaceplane lands by controlled gliding after launch, and the carrier aircraft lands at the airport by controlled gliding.

[0028] Based on the axial series-coupled architecture spaceplane combined with a carrier aircraft and a space vehicle, when the spaceplane returns to the earth, it lands by wing aerodynamic gliding and is quickly recombined with the carrier aircraft through a standardized interface.

[0029] Based on the axial series-coupled architecture spaceplane combined with a carrier aircraft and a space vehicle, the power source of the carrier aircraft of the space vehicle uses fuels including conventional aviation kerosene, gasoline, diesel, liquid ammonia, natural gas, alcohol, methanol, and oxidizers including air and pure oxygen. It uses an oxidizer-assisted combustion jet engine with air compounded with vaporized liquid oxygen; the carrier aircraft can be an aircraft with variable sweep angle wings to adapt to the low speed during takeoff and high speed after reaching high altitudes; the main wing mechanism of the variable sweep angle wing can dynamically adjust the sweep angle according to the flight altitude and speed to optimize the aerodynamic performance in different flight stages; the liquid oxygen propulsion system includes a vaporization device that can vaporize liquid oxygen and distribute it to the engine to make up for the lack of oxygen at high altitudes.

[0030] Technical effects: Based on the axial series-coupled architecture spaceplane combined with a carrier aircraft and a space vehicle, both the carrier aircraft and the spaceplane can be recovered, greatly reducing the launch cost; greatly improving the carrying capacity: the takeoff capacity can reach the thousand-ton level. Improving safety: After the carrier aircraft is separated, it lands autonomously, avoiding the risk of rocket explosion. Specific implementation methods

[0031] The aerospace vehicle consists of a spaceplane and a carrier aircraft, and adopts a double-body axial tandem design. The carrier aircraft is equipped with a variable-sweep wing main wing and jet engines, and supports takeoff by taxiing within the atmosphere. After flying to the set altitude, the sweep angle of the main wing is adjusted to increase speed, and the liquid oxygen propulsion system is activated to supplement oxygen at high altitudes. After the spaceplane separates by ignition and enters the orbit, it returns by aerodynamic gliding after the mission is completed. After the carrier aircraft separates, it deforms into a fairing and glides and lands at the airport. The connection part adopts a wedge-shaped buckle groove and plug-in structure to ensure connection stiffness. The control system supports artificial intelligence collaborative flight and autonomous return. Description of the Drawings

[0032] Figure 1 : Schematic top view structure diagram of the aerospace vehicle composed of a spaceplane and a carrier aircraft based on an axial tandem coupling architecture; Figure 2 : Schematic top view structure diagram of the spaceplane; Figure 3 : Schematic top view structure diagram of the carrier aircraft; Figure 4 : Schematic top view structure diagram of the carrier aircraft nose transformed into a fairing.

[0033] In the figure: 1 spaceplane fuselage, 2 spaceplane wing, 3 spaceplane vertical tail, 4 spaceplane wedge-shaped slot, 5 carrier aircraft wedge-shaped buckle, 6, carrier aircraft fuselage, 7 carrier aircraft main wing, 8, jet engine, 9 carrier aircraft vertical tail, 10 carrier aircraft horizontal tail, 11 spaceplane rocket engine, 12 carrier aircraft wedge-shaped buckle shrinkage deformation distillation hood.

Claims

1. An aerospace vehicle, a combined carrier aircraft based on an axial series coupling architecture, comprising an aerospace plane and a carrier aircraft, characterized in that: The aerospace vehicle adopts a tandem axial combination design of a double fuselage with a spaceplane in the front and a carrier aircraft in the rear; the spaceplane of the aerospace vehicle includes a spaceplane nose, a spaceplane fuselage, a spaceplane main wing, a spaceplane vertical tail, a rocket engine at the end of the spaceplane, and a connecting buckle at the end of the spaceplane; or the spaceplane of the aerospace vehicle is a composite jet engine including a spaceplane nose, a spaceplane fuselage, a foldable main wing or variable sweep wing of the spaceplane, a spaceplane vertical tail, a rocket engine at the end of the spaceplane, and a connecting buckle at the end of the spaceplane; The carrier aircraft of the aerospace vehicle includes a carrier aircraft nose, and the carrier aircraft nose is provided with a carrier aircraft nose connecting buckle corresponding to the connecting buckle at the end of the spaceplane, a carrier aircraft fuselage, a carrier aircraft main wing, a jet engine on the carrier aircraft main wing, a rear tail wing of the carrier aircraft, and a vertical tail of the carrier aircraft; or the carrier aircraft of the aerospace vehicle includes a carrier aircraft nose, and the carrier aircraft nose is provided with a carrier aircraft nose connecting buckle corresponding to the connecting buckle at the end of the spaceplane, a carrier aircraft fuselage, a variable sweep main wing of the carrier aircraft, a jet engine on the variable sweep main wing, a rear tail wing of the carrier aircraft, and a vertical tail of the carrier aircraft; wherein, the carrier aircraft body is configured with a cold launch system of compressed air built into the fuselage, a liquid oxygen tank, a fuel tank, and a fuel extension tank built into the main wing; a compressed air cold launch system is provided inside the carrier aircraft nose, and through the release of the compressed air cold launch system, the spaceplane and the carrier aircraft are separated, and by using the reaction force, part of the kinetic energy of the carrier aircraft is transferred through the compressed air cold launch to further accelerate the spaceplane, and the spaceplane is ignited after being separated from the carrier aircraft to avoid ablation damage to the carrier aircraft caused by the tail flame of the spaceplane; According to the use and mission requirements of the carrier aircraft, the jet engine is integrally designed with the fuselage, including jet engines symmetrically arranged under the main wing of the carrier aircraft; or the jet engine is integrally designed with the fuselage, symmetrically arranged under the main wing of the carrier aircraft and an engine on the vertical tail; or the jet engine of the carrier aircraft is integrally designed with the fuselage, symmetrically arranged under the main wing of the carrier aircraft and two symmetric jet engines on both sides of the vertical tail; or the jet engine of the carrier aircraft is integrally designed with the fuselage, symmetrically arranged under the main wing of the carrier aircraft and three jet engines arranged in a row between the two vertical tails; An integrated aerodynamic coupling configuration is formed by combining a spaceplane and a carrier aircraft; at the connection between the spaceplane and the carrier aircraft of the space vehicle, a docking locking mechanism composed of a wedge-shaped connection buckle and a pin is provided for connection. The tail of the spaceplane and the head of the carrier aircraft form the space vehicle. Among them, the pin is a telescopic pin group corresponding to the wedge-shaped connection buckle. The telescopic pin group positions the wedge-shaped connection buckle by inserting the telescopic pin group into the pin sleeve group at the tail of the spaceplane. By withdrawing the telescopic pin group from the pin sleeve group inserted into the tail of the spaceplane, the unlocking of the wedge-shaped connection buckle is realized. The spaceplane and the carrier aircraft improve the connection stiffness between them by inserting and connecting the telescopic pin group and the pin sleeve group. The spaceplane and the carrier aircraft are separated by opening the docking locking mechanism with an electromagnetic lock at a set altitude and jetting compressed air forward; The main wing of the carrier aircraft and the wing of the spaceplane are aerodynamically coupled in coordination, and during a conventional takeoff on a conventional airport, it taxis and accelerates to fly to provide a huge lift force, enabling the space vehicle to take off, climb, and accelerate from a conventional airport; or after the space vehicle reaches a set altitude and speed, the main wing of the carrier aircraft of the space vehicle is a variable-sweep wing, which reduces the flight resistance and further improves the flight speed and altitude. The combined space vehicle is equipped with a three-stage power switching system of air-assisted combustion at low altitude of the carrier aircraft, liquid oxygen gasification-assisted combustion at high altitude, and rocket launch flight of the spaceplane, enabling the space vehicle to use an air-assisted combustion engine at the low altitude stage, switch to a liquid oxygen gasification-assisted combustion engine at the high altitude stage. A compressed air cold launch system is provided inside the nose of the carrier aircraft of the space vehicle. When the space vehicle flies to a set altitude, reaches a set speed, and flies to a set longitude and latitude position, the compressed air inside the compressed air cold launch system is jetted forward and released to separate the spaceplane from the carrier aircraft and further accelerate the spaceplane. After the spaceplane and the carrier aircraft are separated, the three-stage power rocket on the spaceplane ignites and launches into orbit at high altitude; After completing the mission, the spaceplane returns to the airport through control or autonomously; after completing the mission, the carrier aircraft returns to the airport through control or autonomously, realizing the full-process reusable launch and recovery of the space vehicle composed of the spaceplane and the carrier aircraft; The structure of the space vehicle can achieve small overall flight air resistance, strong controllability and coordination ability, greatly reduce the carrier of oxidants, and the recovery of the spaceplane and the carrier aircraft can be reasonably operated and allocated using the existing aviation technology accumulation, realizing the organic combination of the spaceplane and the carrier aircraft, making the space vehicle environmentally friendly, energy-saving, stable, safe, recyclable, not generating space debris, and can greatly reduce the space vehicle's space transportation cost, solving the problems of huge investment and high cost in space engineering and the inability to be fully recycled, making spaceflight simpler, more reliable, and more environmentally friendly.

2. The aerospace vehicle of the combined launch vehicle of the spaceplane based on the axial series coupling architecture according to claim 1, characterized in that: The carrier aircraft uses an air-composite oxygen-assisted combustion jet engine as the propulsion power. Among them, the jet engine includes a turbofan engine, a ramjet engine, a variable cycle engine, and a pulse detonation engine; it supports the power switch between air-assisted combustion within the atmosphere and high-altitude liquid oxygen gasification propulsion; the main wing of the carrier aircraft uses high-temperature resistant composite materials and supports multiple mission cycles; the switching logic of the three-stage power system is: 0-10 km altitude: pure turbofan mode; 10-30 km altitude: ramjet-turbofan hybrid mode; 30 km altitude: liquid oxygen gasification full-assisted combustion mode.

3. The aerospace vehicle of the combined launch vehicle of the spaceplane based on the axial series coupling architecture according to claim 1, characterized in that: Takeoff stage: The combination takes off by taxiing on a conventional airport, and the jet engine provides thrust; when the flight altitude reaches the set altitude, the liquid oxygen gasification assisted combustion is started, and the main wing sweep angle is adjusted to the set angle; there is a wedge-shaped connection buckle groove at the connection between the carrier aircraft and the spaceplane. An electromagnetic lock is built into the wedge-shaped connection buckle groove and is unlocked by an electric current pulse during separation. The compressed air injection system is started synchronously during separation; the connection stiffness is improved by inserting connection pins and pin sleeve groups; the connection pins and sleeves are made of high-rigidity composite materials.

4. The aerospace vehicle of the combined launch vehicle of the spaceplane based on the axial series coupling architecture according to claim 1, wherein: After separation, the carrier aircraft forms a conical fairing through the deformation of the nose retraction opening, and the fairing adopts an adaptive aerodynamic shape design to achieve controllable gliding landing.

5. The aerospace vehicle of the combined launch vehicle of the spaceplane based on the axial series coupling architecture according to claim 1, characterized in that: The carrier aircraft is equipped with a modular fuel tank. The carrier aircraft is equipped with a liquid oxygen tank (fuselage) + fuel tank (main wing), and the main wing is provided with a variable sweep mechanism (the sweep angle is continuously adjustable from 5° to 70°); the spaceplane uses a main wing made of high-temperature resistant composite materials and is equipped with a detachable thermal protection layer and a modular engine; Separation logic: When the speed and altitude are reached, the liquid oxygen pipeline is opened → gasified oxygen is distributed → the electromagnetic lock is unlocked → cold launch separation; after the carrier aircraft is separated, it retracts and deforms, and the spaceplane glides and lands through the wing aerodynamic control surfaces; The jet engine group includes a turbofan engine, a ramjet engine, a variable cycle engine or a pulse detonation engine. The layout forms include: at least symmetric twin engines on the lower side of the main wing, at least symmetric twin engines on the lower side of the main wing + single engine on the vertical tail, at least symmetric twin engines on the lower side of the main wing + symmetric twin engines on the vertical tail, at least symmetric twin engines on the lower side of the main wing + triple engines between the twin vertical tails; The two aircraft are connected by a wedge-shaped docking buckle groove + pin composite mechanism, and are unlocked by the electromagnetic lock at the set altitude. After separation, the three-stage rocket of the spaceplane ignites and enters the orbit; both the carrier aircraft and the spaceplane have the ability of aerodynamic gliding to return, and can be quickly reorganized through standardized interfaces; The combination adopts an integrated aerodynamic coupling design and has a three-stage power switching system: 0-10 km pure turbofan propulsion, 10-20 km ramjet-turbofan hybrid propulsion, 20-30 km liquid oxygen gasification assisted combustion propulsion, realizing full-process reusable launch and recovery.

6. The aerospace plane combined carrier aircraft aerospace vehicle based on an axial series coupling architecture according to claim 1, characterized in that: The spaceplane ignites and detaches, and the carrier aircraft retracts and glides down; Return and reorganization: The spaceplane adjusts its attitude through the aerodynamic wing surfaces, and the carrier aircraft lands autonomously and reorganizes with the spaceplane.

7. The aerospace vehicle of the combined launch vehicle for spaceplane based on the axial series coupling architecture according to claim 1, wherein: The combined space vehicle adopts an artificial intelligence collaborative control system, which supports autonomous return in the manned or unmanned mode.

8. The aerospace vehicle of the combined launch vehicle of the aerospace plane based on the axial series coupling architecture according to claim 1, characterized in that: The carrier aircraft has an internal liquid oxygen tank and fuel tank in its fuselage, an internal fuel tank in its main wing, and jet engines symmetrically arranged on the wings, providing power for the aerospace vehicle to fly in the atmosphere; the carrier aircraft of the aerospace vehicle may be equipped with a main wing mechanism with variable sweep wings to adapt to the aerodynamic requirements of different flight phases; after the spaceplane and the carrier aircraft of the aerospace vehicle reach the set altitude, speed, and position, they ignite and separate, enter the set orbit in space, and after completing the aerospace mission, they return to the Earth airport through the aerodynamic gliding of the spaceplane wings and can be reused repeatedly; The main wing of the spaceplane is a fixed wing, a foldable wing, or a variable sweep wing; The main wing of the spaceplane is made of high-temperature resistant composite materials and can be quickly recombined with the carrier aircraft fuselage through a standardized interface after landing; the spaceplane is equipped with a repairable and replaceable thermal protection layer and engines, supporting multiple aerospace mission cycles; The power source of the spaceplane may consist of two parts, including a liquid oxygen rocket engine and an air dual-oxidizer assisted combustion jet engine, and the air dual-oxidizer assisted combustion jet engine is equipped with a retractable and hidden air intake on the fuselage; Between the spaceplane and the carrier aircraft, they fly in coordination through manned or artificial intelligence control. The aerospace vehicle pushes the combined spaceplane to taxi and take off together at the airport in a conventional manner, uses air for combustion assistance at low altitude, and when reaching the set flight speed and altitude, adjusts the variable sweep angle of the main wing of the carrier aircraft. When reaching the set altitude, open the liquid oxygen pipeline and, through the engine gasification device, distribute the gasified oxygen to each engine to make up for the lack of oxygen at high altitude. After reaching the set altitude, speed, and position, unlock and separate the spaceplane from the carrier aircraft through compressed air cold launch; ignite the liquid oxygen and fuel carried by the spaceplane and accelerate into the set orbit; This carrier aircraft has a large takeoff weight. It uses air for combustion assistance in the atmosphere stage, reducing the consumption of oxidants. After reaching the set altitude in the high-altitude stratosphere, the engine mixes the gasified liquid oxygen with fuel for combustion to push the aerospace vehicle to fly, pushing the spaceplane to the set altitude. The spaceplane and the carrier aircraft of the aerospace vehicle disintegrate and separate. The spaceplane lands through controllable gliding after launch, and the carrier aircraft lands at the airport through controllable gliding; 9. The aerospace vehicle of the combined launch vehicle for spaceplane based on the axial series coupling architecture according to claim 1, characterized in that: When the spaceplane returns to the Earth, it lands through the aerodynamic gliding of the wings and quickly recombines with the carrier aircraft through a standardized interface; 10. The aerospace vehicle of the combined launch vehicle of the aerospace plane based on the axial series coupling architecture according to claim 1, characterized in that: The power source of the carrier aircraft of the aerospace vehicle uses fuels including conventional aviation kerosene, gasoline, diesel, liquid ammonia, natural gas, alcohol, and methanol, and oxidants including air and pure oxygen, using an oxidant-assisted combustion jet engine with air compounded with liquid oxygen gasification for combustion assistance; the carrier aircraft may be an aircraft with variable sweep wings to adapt to the low-speed takeoff to high-speed operation at high altitude; the variable sweep wing main wing mechanism can dynamically adjust the sweep angle according to the flight height and speed to optimize the aerodynamic performance in different flight phases; the liquid oxygen propulsion system includes a gasification device that can gasify liquid oxygen and distribute it to the engines to make up for the lack of oxygen at high altitude.

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