A combined-power space launch vehicle

Abstract

The present invention is applicable to the field of aerospace technology, and provides a combined-power space vehicle, comprising: a vehicle, and a ballistic flight body connected to the bottom of the vehicle; the vehicle comprises a plurality of cabins, a pylon beam for fixedly connecting the plurality of cabins, a lift wing provided on each of the cabins, a first power device fixed on the lift wing, and a take-off and landing device provided at the bottom of each cabin and the bottom of the pylon beam, and the ballistic flight body is provided at the middle section of the bottom of the pylon beam. The present application can realize the launch of the vehicle in a horizontal manner, breaking through the limitation of the vertical launch method of the launch site and launch station, and has high versatility; and the ballistic flight body is carried to the optimal trajectory starting point, which can minimize the consumption of the propellant of the ballistic flight body; the vehicle can be recycled and reused during its service life, which can significantly reduce costs.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace technology, and in particular relates to a combined-power space vehicle. Background Art

[0002] At present, launch vehicles are usually launched from ground launch sites. However, based on the existing launch vehicle propulsion form and configuration, which adopts a single propulsion type, vertical launch will be more dependent on the launch site infrastructure. However, the launch site has limited work stations and launch windows, which will cause the launch vehicle to be unable to take off at the starting point of the optimal ballistic flight.

[0003] To address launch site constraints, existing technologies have adopted two approaches: building new launch sites and developing sea-based mobile launch technology. These efforts aim to expand launch sites across more regions and islands, allowing carrier rockets to select more suitable launch sites based on their missions. However, this approach requires significant infrastructure investment, and the number of available launch sites is limited, resulting in high costs. While sea-based mobile launch technology offers a degree of flexibility by launching carrier rockets from ships, it still cannot fully cover optimal launch sites for all missions. Furthermore, sea-based mobile launch platforms lack versatility and have a high vacancy rate. To reduce launch costs, existing technologies utilize the recovery of carrier rocket booster stages. However, the booster stages of most carrier rockets are designed as rotating bodies. For vertical launch, recovery requires vertical landing of the booster stages. After separation, recoverable carrier rockets must carry additional propellant to achieve this vertical landing, resulting in increased energy consumption. Summary of the Invention

[0004] The embodiment of the present invention provides a space vehicle, aiming to solve the problems in the prior art of limited ground launch site locations and windows, poor versatility, and high energy consumption during recovery when launching a carrier rocket.

[0005] The embodiment of the present invention is implemented as follows: a combined-power space vehicle comprises: a vehicle, and a ballistic flight body connected to the bottom of the vehicle;

[0006] The carrier includes multiple cabins, a mounting beam that fixedly connects the multiple cabins, a lift wing arranged on each of the cabins, a first power device fixed on the lift wing, and a take-off and landing device arranged at the bottom of each cabin and the bottom of the mounting beam. The ballistic flying body is arranged in the middle section of the bottom of the mounting beam.

[0007] Furthermore, the carrier further includes a stabilizing wing, which is connected to the upper end of the tail of the cabin.

[0008] Furthermore, the stabilizing wing extends longitudinally upward from the cabin body and is swept back.

[0009] Furthermore, the vehicle further includes a second power device arranged on the stabilizing wing.

[0010] Furthermore, the first power unit and the second power unit include turbofan engine units.

[0011] Furthermore, the lift wing is swept back, and each lift wing is provided with at least one first control rudder plate, and the first control rudder plate is arranged along the direction of the lift wing and along the rear edge of the lift wing.

[0012] Furthermore, each of the stabilizing wings is provided with a second control rudder plate, and the second control rudder plate is provided along the direction of the stabilizing wing and along the rear edge of the stabilizing wing.

[0013] Furthermore, the take-off and landing device includes a main landing gear arranged at the rear end of the bottom of each cabin, and a front landing gear symmetrically arranged on the bracket beam. After the carrier leaves the ground, the main landing gear is retracted into the cabin, and the front landing gear is retracted into the rectifier where the bracket beam is located.

[0014] Furthermore, the ballistic flight body includes multiple booster stages, a payload compartment and a fairing, the fairing is arranged at the top, and the payload compartment is connected and arranged between the booster stage and the fairing. The thrust is generated by propellant combustion in the booster stage, and the mission payload is enclosed in the fairing or the payload compartment.

[0015] Furthermore, the cabin includes a fuel supply device, and the fuel supply device stores fuel for the vehicle to fly.

[0016] The beneficial effects achieved by the present invention are as follows: the present application provides a combined-power space vehicle, comprising: a vehicle, and a ballistic flight body connected to the bottom of the vehicle; the vehicle comprises a plurality of cabins, a pylon beam for fixing the plurality of cabins together, a lifting wing provided on each cabin, a first power unit fixed on the lifting wing, and a take-off and landing device provided at the bottom of each cabin and the bottom of the pylon beam, and the ballistic flight body is provided at the middle section of the bottom of the pylon beam. Based on the lifting wing, the first power unit, and the take-off and landing device, the vehicle can be launched horizontally, breaking through the limitation of the vertical launch method of the launch site and the launch station, and having high versatility; and the ballistic flight body is carried to the optimal trajectory starting point, and the ballistic flight body can enter orbit in the shortest time with the least propellant consumption, thereby minimizing the propellant consumption of the ballistic flight body; after completing the carrying mission, the vehicle can select a nearby airport for landing and can be recycled and reused during its service life, which can significantly reduce costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A schematic diagram of the structure of a combined-power space vehicle during flight provided by an embodiment of the present invention;

[0018] Figure 2 A schematic diagram of the specific structure of a carrier provided in an embodiment of the present invention;

[0019] Figure 3 A side view of a combined-power space vehicle provided by an embodiment of the present invention during flight;

[0020] Figure 4 A top view of a combined-power space vehicle in flight provided by an embodiment of the present invention;

[0021] Figure 5 A front view of a combined-power space vehicle in flight provided by an embodiment of the present invention;

[0022] Figure 6 A schematic structural diagram of a ballistic flight object provided by an embodiment of the present invention;

[0023] Figure 7 A diagram showing the overall working process of a combined-power space vehicle provided by an embodiment of the present invention;

[0024] Among them, 1. Carrier, 11. Cabin, 12. Hanging beam, 13. Lift wing, 131. First control rudder, 14. First power unit, 15. Take-off and landing gear, 151. Main landing gear, 152. Front landing gear, 16. Stabilizing wing, 161. Second control rudder, 17. Second power unit, 2. Ballistic flight body, 21. First booster stage, 22. Second booster stage, 23. Payload compartment, 24. Fairing. DETAILED DESCRIPTION

[0025] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0026] The vehicle of the present invention comprises multiple cabins, a pylon beam that securely connects the cabins, a lift wing mounted on each cabin, a first power unit secured to the lift wing, and a take-off and landing mechanism mounted at the bottom of each cabin. The ballistic vehicle is positioned at the bottom of the pylon beam. The lift wing, first power unit, and take-off and landing mechanism enable the vehicle to be launched horizontally, transcending the limitations of vertical launch methods at launch sites and launch stations, resulting in high versatility. Furthermore, by transporting the ballistic vehicle to the optimal trajectory starting point, the vehicle can enter orbit in the shortest possible time and with the least propellant consumption, minimizing propellant consumption for the vehicle.

[0027] Example 1

[0028] A combined-power space vehicle comprises: a vehicle 1, and a ballistic flight body 2 connected to the bottom of the vehicle 1;

[0029] The vehicle 1 includes multiple cabins 11, a mounting beam 12 that fixedly connects the multiple cabins 11, a lift wing 13 arranged on each cabin 11, a first power device 14 fixed on the lift wing 13, and a take-off and landing device 15 arranged at the bottom of each cabin 11 and the bottom of the mounting beam 12. The ballistic flying body 2 is arranged in the middle section of the bottom of the mounting beam 12.

[0030] Among them, reference Figure 1 As shown, Figure 1 The schematic diagram of the structure of a combined power space vehicle during flight is provided in an embodiment of the present invention. Figure 1 As shown, the carrier (launch vehicle) includes a carrier 1, and a ballistic flight body 2 that is carried to a ballistic take-off point by the carrier 1 and then separated. A mission payload (satellite or other payload) is arranged in the ballistic flight body 2. After the ballistic flight body 2 is separated from the carrier 1, the mission payload is propelled to an appropriate height and speed to enter the orbit, or the mission payload enters the orbit under its own power device.

[0031] Specifically, the carrier 1 may include two cabins 11, and the cabins 11 may include flight control equipment, navigation equipment, communication equipment, power supply and distribution equipment, fuel supply equipment, etc., and the communication equipment is installed in the carrier 1 as a communication transfer terminal, which can comprehensively process the information between the ballistic aircraft 2 and the ground monitoring station. The inner sides of the cabins 11 are connected and fixed by a pylon beam 12, and the ballistic aircraft 2 is connected to the bottom of the middle section of the pylon beam 12. The pylon beam 12 is the main load-bearing structure, which can adjust the position of the ballistic aircraft 2 so that the center of gravity of the ballistic aircraft 2 is closer to the center of gravity of the carrier 1, thereby controlling the balance during the entire flight process. Optionally, a mounting interface (not shown) for fixing the ballistic aircraft 2 can be provided at the bottom of the pylon beam 12. After the ballistic aircraft 2 is sent to the optimal ballistic take-off point, the mounting interface is disengaged, completing the separation of the carrier 1 and the ballistic aircraft 2. Of course, other methods are also possible, and this is not the only limitation.

[0032] Specifically, a lift wing 13 extends from the outside of each cabin 11 to provide lift. The lift wing 13 can be swept back, and the top includes an upward-inclined winglet. The upright winglet forms a certain angle with the longitudinal section of the cabin 11 of the vehicle 1. When the airflow from the lower surface flips up from the wingtip, the combined force acting on the winglets at both ends can point upward, thereby increasing lift. This is conducive to the vehicle 1 flying in a dense atmosphere using aerodynamic principles to achieve higher efficiency. Each connection between the cabin 11 and the lift wing 13 and the pylon beam 12 can include a connecting end, which is used to achieve a fixed connection with the lift wing 13 and the pylon beam 12. At the same time, a first power device 14 is fixedly provided on each lift wing 13. Specifically, the first power device 14 can be provided at the bottom of the lift wing 13 near one end of the cabin 11. The first power device 14 can provide a power source for the vehicle 1.

[0033] refer to Figure 2 As shown, Figure 2 This is a schematic diagram of the specific structure of the carrier 1 provided in an embodiment of the present invention. Figure 2 In the figure, a take-off and landing device 15 is arranged at the rear bottom of each cabin 11, and a take-off and landing device 15 is symmetrically arranged on the pylon beam 12. The carrier 1 glides on the ground before takeoff and during landing via the take-off and landing devices. Specifically, when the carrier is launched horizontally, after the take-off and landing devices 15 glide on the ground until they reach a safe flight altitude, the landing gear is folded and retracted until the take-off and landing devices 15 are stored in the cabin 11 or in a storage space at the bottom of the cabin 11 specifically for storing the take-off and landing devices 15. When the carrier 1 is landing, the take-off and landing devices 15 can be controlled to be lowered from the storage space when approaching the runway, and the process carrier 1 glides on the airport runway, decelerating until it stops.

[0034] In this embodiment, a combined-power space launch vehicle is provided, comprising: a vehicle 1, and a ballistic flight body 2 connected to the bottom of the vehicle 1. The vehicle 1 includes multiple cabins 11, and a pylon beam 12 fixedly connected between the cabins 11 for adjusting balance, lift wings 13 extending from both sides of each cabin 11 to provide lift, a first power unit 14 fixed to the lift wings 13 for providing power, and a take-off and landing device 15 for achieving horizontal take-off and located at the bottom of each cabin 11. Horizontal take-off is achieved based on the lift wings 13, the first power unit 14, and the take-off and landing device 15, enabling the vehicle to be launched horizontally, breaking through the limitations of vertical launch methods at launch sites and launch stations, and having high versatility. In addition, by transporting the ballistic vehicle 2 to the optimal trajectory starting point, the ballistic vehicle 2 can enter orbit in the shortest time with the least propellant consumption, thereby minimizing the propellant consumption of the ballistic vehicle 2. After completing the transport mission, the carrier 1 can choose a nearby airport to land and can be recycled and reused during its service life, which can significantly reduce costs.

[0035] Example 2

[0036] Based on the above-mentioned first embodiment, the vehicle 1 provided in this embodiment further includes a stabilizing wing 16 , which is connected to the upper end of the tail of the cabin 11 .

[0037] The stabilizer 16 may be a vertical tail / horizontal tail, or a single vertical tail / double vertical tail. Figure 2 and Figure 3 As shown, Figure 3 A side view of a combined-power space vehicle in flight, provided by an embodiment of the present invention. As a preferred embodiment, a stabilizing wing 16 is fixedly attached to the upper end of the tail section of each cabin 11. The stabilizing wing 16 is sheet-shaped and extends longitudinally upward from the cabin 11. The extended end is angled toward the rear of the cabin 11, forming a swept-back angle with respect to the cabin 11. The stabilizing wing 16 can be used to increase longitudinal stability during flight and can also be used to manipulate the vehicle 1's deflection, ensuring smooth flight.

[0038] Example 3

[0039] Based on the above-mentioned second embodiment, the vehicle 1 provided in this embodiment further includes a second power device 17 provided on the stabilizing wing 16 .

[0040] refer to Figure 2 、 Figure 3 As shown, a second power unit 17 is also provided at the top of the stabilizer 16. Adding the second power unit 17 to the first power unit 14 can provide stronger power for the vehicle 1, wherein the first power unit 14 can provide greater power than the second power unit 17. Optionally, the two first power units 14 and the two second power units 17 can be air-breathing engines, such as turbofan engines. A turbofan engine pressurizes a portion of the inhaled air through an internal fan and compressor. The resulting high-pressure air acts as an oxidizer and enters the combustion chamber through the front inlet. Inside the combustion chamber, it mixes with the injected fuel and burns. Under the high heat released by the combustion of the fuel, the high-pressure gas heats up and expands, and is ejected from the annular outlet at the other end of the combustion chamber. After the injection angle is deflected by guide vanes disposed outside the combustion chamber outlet, the gas is injected into the turbine blades at the most appropriate angle, causing the turbine to rotate, thereby generating power.

[0041] In this embodiment, vehicle 1 is powered by a first power unit 14 and a second power unit 17, respectively. Both first power unit 14 and second power unit 17 are air-breathing engines. Air-breathing engines only need to carry fuel for combustion within their combustion chambers, and readily available fuel reduces launch costs. Air-breathing engines also offer high efficiency, low fuel consumption, and a long range. Furthermore, the pitch attitude of vehicle 1 can be controlled by adjusting second power unit 17.

[0042] Example 4

[0043] Based on the above embodiment 1, the lift wing 13 provided in this embodiment is swept back, and each lift wing 13 is provided with at least one first control rudder 131, which is arranged along the direction of the lift wing 13 and along the rear edge of the lift wing 13.

[0044] refer to Figure 4 As shown, Figure 4 A top view of a combined-power space vehicle in flight provided by an embodiment of the present invention. Figure 4 As can be seen, the lift wing 13 is designed to be swept backward, and at least one first control fin 131 is disposed at the rear edge of the swept lift wing 13. The first control fin 131 is arranged along the direction of the lift wing 13 and is located near the portion extending outward from the middle of the lift wing 13. In this embodiment, two first control fins 131 are arranged in a continuous pattern, but a single, three, or four fins are also possible. In this embodiment, the first control fins 131 can be used to control the pitch and roll attitude of the vehicle during flight.

[0045] Example 5

[0046] Based on the third embodiment, each stabilizing wing 16 provided in this embodiment is provided with a second control rudder 161 . The second control rudder 161 is provided along the direction of the stabilizing wing 16 and along the rear edge of the stabilizing wing 16 .

[0047] refer to Figure 2 As shown, a second control rudder 161 is arranged along the rear edge of each stabilizer wing 16. One end of the second control rudder 161 on the same cabin 11 extends to the bottom of the second power unit 17, and the other end extends to the cabin 11. The second control rudder 161 can be provided as a single rudder or multiple rudders. The second control rudder 161 can be used to control the yaw attitude of the vehicle during flight.

[0048] Example 6

[0049] Based on the above-mentioned embodiment 1, the take-off and landing device 15 provided in this embodiment includes a main landing gear 151 arranged at the rear end of the bottom of each cabin 11, and a front landing gear 152 symmetrically arranged on the pylon beam 12. After the carrier leaves the ground, the main landing gear 151 is retracted into the cabin 11, and the front landing gear 152 is retracted into the rectifier 12 where the pylon beam is located.

[0050] Specifically, refer to Figure 2 、 Figure 5 As shown, Figure 5 This is a front view of a combined-power space vehicle in flight, provided by an embodiment of the present invention. The landing gear 15 includes a main landing gear 151 located at the rear end of the bottom of each cabin 11, and a nose landing gear 152 symmetrically located on the pylon beam 12. Each main landing gear 151 may include at least two wheels at its bottom; in this embodiment, each main landing gear 151 includes three wheels. Each nose landing gear 152 may include at least one wheel at its bottom; in this embodiment, each nose landing gear 152 includes one wheel. The landing gear 15 may also include landing gear lifting and lowering equipment (not shown), brake hydraulic equipment, and piping (not shown). After the vehicle lifts off the ground after gliding a certain distance on the ground using the nose and rear landing gears, the landing gear lifting and lowering equipment can retract the main landing gear 151 into the landing gear 15 storage space at the bottom of the cabin 11, and retract the nose landing gear 152 into the landing gear 15 storage space provided in the rectifier 12 where the pylon beams are located.

[0051] In this embodiment, a take-off and landing device 15 is provided at the bottom of the cabin 11. By controlling the take-off and landing device 15, the carrier can be horizontally launched by sliding on the ground, and the ballistic flying object 2 can be carried to the optimal ballistic starting point. After completing the carrying mission, the carrier 1 can land at the airport based on the take-off and landing device 15, and perform a secondary carrying mission after recovery or refueling. It can be recycled and reused during its service life, thereby reducing costs.

[0052] Example 7

[0053] Based on the above-mentioned embodiment 1, the ballistic flight body 2 provided in this embodiment includes multiple booster stages, a payload compartment 23 and a fairing 24. The fairing 24 is arranged at the top, and the payload compartment 23 is connected and arranged between the booster stage and the fairing 24. The thrust is generated by propellant combustion in the booster stage, and the mission payload is enclosed in the fairing 24 or the payload compartment 23.

[0054] refer to Figure 6 As shown, Figure 6A schematic diagram of the structure of a ballistic vehicle 2 provided in an embodiment of the present invention. The ballistic vehicle 2 may include multiple booster stages, which are sequentially connected. In this embodiment, the ballistic vehicle 2 may include a first-stage booster stage 21 and a second-stage booster stage 22. The fairing 24, the payload bay 23, the second-stage booster stage 22, and the first-stage booster stage 21 are sequentially connected, wherein the fairing 24 is conical in shape, and the mission payload is enveloped by the fairing 24 or the payload bay 23. The first-stage booster stage 21 and the second-stage booster stage 22 generate thrust through the nozzle by burning solid or liquid propellant, propelling the mission payload to an appropriate altitude and flight speed, and finally into orbit.

[0055] Example 8

[0056] Based on the above-mentioned embodiments 1 to 7, the cabin 11 provided in this embodiment includes a fuel supply device, and the fuel supply device stores fuel for the vehicle 1 to fly.

[0057] Among them, the fuel supply device (not shown) specifically includes a fuel tank and a fuel supply pipeline. The fuel tank stores fuel for carrying the flying body to fly. The fuel supply pipeline can be connected to the combustion chambers of the two first power units 14 and the two second power units 17 respectively. The fuel in the fuel tank is transported to the first power unit 14 and the second power unit 17 through the fuel supply pipeline. The fuel is burned with the fuel under the condition of high-pressure air as an oxidant, and power is generated from the turbine injection.

[0058] To better describe the embodiments of the present invention, refer to Figure 7 As shown, Figure 7 The overall working process diagram of a combined-power space vehicle provided by an embodiment of the present invention. Specifically, the working process of the combined-power space vehicle from takeoff to landing includes: horizontal takeoff (a), climb (b), cruise (c), jump (d), separation of the ballistic vehicle 2 from the carrier 1 (e), ignition of the ballistic vehicle 2 (f), separation of the booster (g), separation of the fairing 24 (h), separation of the satellite and rocket (separation of the mission payload from the ballistic vehicle 2) (i), satellite orbit insertion (j), level flight telemetry of the carrier 1 (k), descent of the carrier 1 (l), landing and recovery of the carrier 1 (m). According to the flight trajectory and flight power, it can be divided into an aerodynamic flight segment (the stage before the separation of the ballistic vehicle 2 and the carrier 1) and a ballistic flight segment (the stage after the separation of the ballistic vehicle 2 and the carrier 1).

[0059] Specifically, at the airport, the ballistic flight body 2 and the carrier 1 are assembled into a complete carrier. The optimal ballistic take-off starting point is planned according to the flight mission, and the flight route of the carrier 1 is designed and loaded into the flight control computer of the carrier 1. The ground command and control station (Y) is used to dock and control the flight control equipment, communication equipment, etc. installed in the cabin 11 of the carrier 1 that performs the carrying mission. Based on the take-off and landing device 15, the carrier taxis on the airport runway, and the lift wing 13, the first power unit 14, and the second power unit 17 are used to control the carrier to climb. After climbing to a certain height, it cruises at subsonic speed, wherein the climbing height can be between 12,000m and 15,000m. After cruising to the vicinity of the optimal ballistic take-off point, the carrier jumps and completes the separation of the carrier 1 and the ballistic flight body 2 at a larger pitch angle.

[0060] After separation to a safe distance, the ballistic vehicle 2 ignites and, propelled by the first-stage booster 21, enters the ballistic flight phase. Once the first-stage booster 21 is depleted or reaches a shutdown condition, it shuts down and then separates from the ballistic vehicle 2. The fairing 24 then separates, and the second-stage booster 22 ignites. Under the power of the second-stage booster 22, the vehicle continues to accelerate until it is depleted or reaches a shutdown condition, shuts down, and separates from the ballistic vehicle 2. The mission payload then separates from the payload bay 23 and enters orbit, or is driven into orbit by its own propulsion system.

[0061] After separating from the ballistic object 2, the carrier 1 tracks the ballistic object 2 by means of level flight telemetry and communicates with the ballistic object 2 based on the communication equipment until the mission is completed or exceeds the communication area. The carrier 1 gradually descends and deploys the take-off and landing device 15 when approaching the airport ground. It autonomously lands at a nearby airport and is withdrawn by support personnel, or refuels and flies to the launch airport for the next mission.

[0062] In an embodiment of the present invention, the inner sides of the cabin 11 are connected and fixed by a pylon beam 12, and the ballistic flying body 2 is connected to the bottom of the middle section of the pylon beam 12. Based on the pylon beam 12, the position of the ballistic flying body 2 can be adjusted so that the center of gravity of the ballistic flying body 2 is closer to the center of gravity of the carrier 1, thereby controlling the balance during the entire flight process. Lift wings 13 extend from both sides of the cabin 11 to provide lift. A first control rudder 131 is provided on the lift wings 13 to control the pitch and roll posture of the carrier during flight. A first power unit 14 is provided at the bottom of the lift wings 13 to provide flight power. A main landing gear 151 is provided at the bottom of the cabin 11, and a front landing gear 152 is provided at the bottom of the pylon beam 12. Based on the take-off and landing device 15, the carrier 1 can take off and land horizontally, and can be recovered or perform the next carrying mission after landing, thereby improving the reuse rate. A stabilizing wing 16 is also provided at the upper rear end of the cabin 11 to increase longitudinal stability during flight and to control the pitch and yaw of the vehicle 1, ensuring smooth flight. A second power unit 17 is provided on the stabilizing wing 16. The first and second power units 14, 17 are turbofan engines, requiring only fuel for combustion reaction to generate power, reducing launch costs and fuel consumption. A second control rudder 161 is also provided on the stabilizing wing 16 to control the vehicle's yaw attitude during flight. Therefore, the present invention enables horizontal launch of the vehicle, transcending the limitations of vertical launch methods at launch sites and launch stations, resulting in high versatility. Furthermore, the ballistic vehicle 2 is carried to the optimal trajectory starting point, minimizing propellant consumption for the vehicle 2. After completing its mission, the vehicle 1 can land at a nearby airport and even refuel to carry out its next mission. It can be recycled and reused during its service life, significantly reducing costs.

[0063] The terms "including" and "having" and any variations thereof in the specification, claims, and drawings of this application are intended to cover non-exclusive inclusions. The terms "first", "second", etc. in the specification, claims, or drawings of this application are used to distinguish different objects rather than to describe a specific order. Reference to "embodiment" herein means that the specific features, structures, or characteristics described in conjunction with the embodiment may be included in at least one embodiment of the present application. It is understood explicitly and implicitly by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0064] 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 and improvements 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 combined-power space launch vehicle, characterized in that: include: A carrier, and a ballistic flying body connected to the bottom of the carrier; The carrier includes a plurality of cabins, a pylon beam for fixedly connecting the plurality of cabins, a lift wing provided on each cabin, a first power device fixed to the lift wing, and a take-off and landing device provided at the bottom of each cabin and the bottom of the pylon beam, wherein the ballistic flying object is provided at the middle section of the bottom of the pylon beam; The carrier further includes a stabilizing wing, the stabilizing wing being connected to the upper end of the tail of the cabin, and the carrier further includes a second power device arranged on the stabilizing wing; The take-off and landing device includes a main landing gear arranged at the rear end of the bottom of each cabin, and a front landing gear symmetrically arranged on the bracket beam. After the carrier leaves the ground, the main landing gear is retracted into the cabin, and the front landing gear is retracted into the rectifier where the bracket beam is located, and an installation interface for fixing the ballistic flying body is provided at the bottom of the bracket beam.

2. A combined-power space launch vehicle according to claim 1, characterized in that: The stabilizing wing extends longitudinally upward from the cabin body and is swept back.

3. A combined-power space launch vehicle according to claim 1, characterized in that: The first power plant and the second power plant include turbofan engine plants.

4. A combined-power space launch vehicle according to claim 1, characterized in that: The lift wing is a swept-back type, and each lift wing is provided with at least one first control rudder plate, and the first control rudder plate is arranged along the direction of the lift wing and along the rear edge of the lift wing.

5. The combined-power space launch vehicle according to claim 1, characterized in that: Each of the stabilizing wings is provided with a second control rudder plate, and the second control rudder plate is provided along the direction of the stabilizing wing and along the rear edge of the stabilizing wing.

6. A combined-power space launch vehicle according to claim 1, characterized in that: The ballistic flight body includes multiple booster stages, a payload compartment and a fairing. The fairing is arranged at the top, and the payload compartment is connected and arranged between the booster stage and the fairing. The booster stage generates thrust through propellant combustion, and the mission payload is enclosed in the fairing or the payload compartment.

7. A combined-power space launch vehicle according to any one of claims 1 to 6, characterized in that: The cabin includes a fuel supply device, in which fuel for the vehicle to fly is stored.

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