A small vertical takeoff and landing lifting body manned aircraft

Abstract

This invention relates to a small vertical takeoff and landing (VTOL) manned aircraft, comprising a fuselage with a lifting body aerodynamic shape, four vertically downward-facing liquid rocket engines mounted at the bottom of the fuselage, and a horizontally rearward-facing turbojet engine mounted at the tail. The fuselage contains an oxidizer tank, a fuel tank, and two oil pumps, with the oxidizer tank and fuel tank connected to the two oil pumps. The front oil pump is connected to the two front liquid rocket engines via two oil lines, and the rear oil pump is connected to the two rear liquid rocket engines via two oil lines. A throttle valve is installed on the oil line between each liquid rocket engine and the oil pump. The fuel tank is also connected to the turbojet engine via a pipeline, on which a turbojet engine control unit is installed. A flight control system with built-in control programs is also installed within the fuselage. Compared with existing technologies, this invention has advantages such as vertical takeoff and landing capability, high flight speed, and long endurance.

Description

Technical Field

[0001] This invention relates to the field of manned aircraft technology, and in particular to a small vertical take-off and landing lifting body manned aircraft. Background Technology

[0002] Manned aircraft represent a significant future mode of private transportation, enabling departures and landings at any time and from nearby locations, free from strict limitations imposed by venues, routes, time, and infrastructure. Currently available electric EVTOL vertical takeoff and landing fixed-wing aircraft and small general aviation planes, while capable of carrying passengers, generally suffer from fatal shortcomings: either their speed is low, limiting them to 200-300 kilometers per hour and hindering long-distance commutes; or they require runways for takeoff and landing, resulting in long takeoff and landing distances and the inability to achieve runway-free vertical takeoff and landing. They remain significantly constrained by venues and infrastructure, unable to break free from the constraints of geographical distance and traditional traffic rules. Humanity has yet to achieve the freedom of "spontaneous travel, rapid intercity travel, and long-distance round trips in a single day." Summary of the Invention

[0003] The purpose of this invention is to overcome the defects of the prior art and provide a small vertical take-off and landing lifting body manned aircraft.

[0004] The objective of this invention can be achieved through the following technical solutions: A small vertical takeoff and landing (VTOL) manned aircraft, comprising a fuselage with a lifting body aerodynamic shape; four vertically downward liquid rocket engines are mounted at the bottom of the fuselage, and a horizontally rearward turbojet engine is mounted at the tail; the fuselage contains an oxidizer tank, a fuel tank, and two oil pumps; the oxidizer tank and the fuel tank are connected to the two oil pumps; the front oil pump is connected to two front liquid rocket engines via two oil lines, and the rear oil pump is connected to two rear liquid rocket engines via two oil lines. Each liquid rocket engine and fuel pump has a throttle valve installed in the oil line. The fuel pump stabilizes the pressure and pumps the oxidizer and fuel into four corresponding throttle valves. Each throttle valve has two independent flow control chambers to control the flow of oxidizer and fuel according to the ratio, and inject them into the corresponding liquid rocket engine for atomization, mixing and combustion. The fuel tank is also connected to the turbojet engine through a pipeline, which is equipped with the turbojet engine control unit. The fuselage is also equipped with a flight control system with built-in control programs to control the entire manned spacecraft.

[0005] Furthermore, a cockpit is provided on the top of the fuselage; a control console is provided inside the cockpit, through which commands are issued to the flight control system to control the operation of the entire manned aircraft.

[0006] Furthermore, the fuselage has two symmetrical tail fins on its top surface, which are symmetrically positioned on either side of the turbojet engine.

[0007] Furthermore, the rear two sides of the fuselage are symmetrically provided with control surfaces that can swing up and down, and the swing of the control surfaces is controlled by the flight control system.

[0008] Furthermore, the fuselage is a one-piece molded carbon fiber hard shell structure.

[0009] Furthermore, the bottom of the fuselage is also provided with a turbojet engine air intake; the turbojet engine air intake is connected to the turbojet engine.

[0010] Compared with the prior art, the present invention has the following advantages: This invention employs a rotorless, lightweight, and miniaturized layout with a lifting body aerodynamic shape, combined with a dual-power architecture consisting of four liquid rocket engines at the bottom and a turbojet engine at the tail. This enables vertical takeoff and landing without a runway, unaffected by site or infrastructure limitations, and a cruising speed of up to 1000 kilometers per hour. It allows for commuting 1000 kilometers in one hour and reaching 2000 kilometers in two hours, significantly expanding daily travel radius and possessing strong innovativeness and widespread civilian application value. Attached Figure Description

[0011] Figure 1 This is a schematic diagram of the top structure of a manned aircraft provided by the present invention; Figure 2 This is a schematic diagram of the bottom structure of the manned aircraft provided by the present invention; Figure 3 This is a schematic diagram of the internal structure of the manned spacecraft provided by the present invention.

[0012] The labels in the diagram indicate: 1. Fuselage; 2. Liquid rocket engine; 3. Turbojet engine; 4. Oxidizer tank; 5. Fuel tank; 6. Oil pump; 7. Throttle valve; 8. Turbojet engine control unit; 9. Flight control system; 10. Cockpit; 11. Control console; 12. Tail fin; 13. Control surfaces; 14. Turbojet engine air intake. Detailed Implementation

[0013] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0014] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention. Example

[0015] like Figures 1-3As shown, a small vertical takeoff and landing (VTOL) manned aircraft includes a fuselage 1 with a lifting body aerodynamic shape. It eliminates the traditional high-aspect-ratio wing and rotor propeller vertical takeoff structure, resulting in a compact size, low drag, and high-speed flight capability. The fuselage 1 has four vertically downward-facing liquid rocket engines 2 at its bottom and a horizontally rearward-facing turbojet engine 3 at its tail. The four liquid rocket engines 2 are fixedly mounted at the four corners of the fuselage 1's underside, arranged symmetrically with two forward and two aft nozzles, and their nozzles are fixed downwards with no vector deflection. The fuselage 1 contains an oxidizer tank 4, a fuel tank 5, and two oil pumps 6. The oxidizer... Tank 4 and fuel tank 5 are connected to two oil pumps 6. The front oil pump 6 is connected to two front liquid rocket engines 2 via two oil lines, and the rear oil pump 6 is connected to two rear liquid rocket engines 2 via two oil lines. Each liquid rocket engine 2 and oil pump 6 has a throttle valve 7 installed on its oil line. The oil pump 6 pumps oxidizer and fuel into four corresponding throttle valves 7 at a stable pressure. The oxidizer and fuel are not mixed within the throttle valves 7. Each throttle valve 7 has two independent flow control chambers to control the flow rate of oxidizer and fuel according to a ratio, injecting them into the liquid rocket engines 2 for atomized mixing and combustion. 2. Under the real-time control of the flight control system 9, the thrust magnitude and flight attitude are adjusted, thereby regulating the lift of each liquid rocket engine 2 and thus adjusting the attitude of the manned spacecraft during vertical takeoff and landing; the fuel tank 5 is also connected to the turbojet engine 3 through a pipeline, on which a turbojet engine control unit 8 is installed to control the fuel supplied to the turbojet engine 3, thereby adjusting the thrust magnitude, so that the turbojet engine 3 can independently provide continuous thrust to achieve high-speed stable cruise of up to 1000 km / h; the bottom of the fuselage 1 is also provided with a turbojet engine air intake 14; the turbojet engine air intake 14 is connected to the turbojet engine 3; the fuselage 1 is also provided with a turbojet engine air intake 14. The fuselage 1 is also equipped with a flight control system 9, which has a built-in control program to control the entire manned aircraft. A cockpit 10 is located on the top of the fuselage 1. A console 11 is located in the cockpit 10, which issues commands to the flight control system 9 to control the operation of the entire manned aircraft. Two symmetrical tail fins 12 are provided on the top surface of the tail of the fuselage 1, and the two tail fins 12 are symmetrically arranged on both sides of the turbojet engine 3. The rear two sides of the fuselage 1 are symmetrically provided with control surfaces 13 that can swing up and down. The control surfaces 13 are controlled by the flight control system 9 to swing and complete attitude and trajectory control in cruise mode. The fuselage 1 is a one-piece molded carbon fiber hard shell structure.

[0016] The working principle of this invention is as follows: 1. Takeoff Phase: The takeoff command is issued from the control console 11 to the flight control system 9. The flight control system 9 controls the four liquid rocket engines 2 and the turbojet engine 3 to start synchronously, and controls the four throttle valves 7 to continuously supply liquid fuel to the liquid rocket engines 2. The liquid rocket engines 2 eject downward to generate vertical upward thrust, while the pitch and roll attitude is controlled in real time. The turbojet engine 3 ejects backward to provide forward thrust, thereby achieving vertical ascent and forward acceleration of the manned aircraft. Within the human body's overload safety tolerance range, the aircraft quickly and accurately reaches the preset cruise altitude and cruise speed. The flight control system 9 collects lift, speed, and altitude parameters in real time, and gradually reduces the thrust of the liquid rocket engines 2 by gradually establishing the aerodynamic lift of the aircraft.

[0017] 2. Climbing Phase: After climbing vertically to a safe altitude, the flight control system 9 gradually increases the thrust of the two rear liquid rocket engines 2 and simultaneously decreases the thrust of the two front liquid rocket engines 2, thereby gradually increasing the preset safe pitch angle of the fuselage 1, so that the rocket thrust generates a forward component force to drive the manned vehicle to accelerate horizontally; at the same time, it continuously increases the total thrust to maintain altitude stability until the flight altitude and airspeed reach the preset mode switching threshold.

[0018] 3. Cruise Phase: When the flight altitude and vacuum speed simultaneously reach the preset transition thresholds, the flight control system 9 automatically enters the transition mode, and the turbojet engine 3 enters cruise thrust maintenance; gradually reaching the cruise speed, the total thrust of the liquid rocket engine 2 decreases synchronously and linearly, maintaining the sum of the total thrust and aerodynamic lift of the entire aircraft to match gravity and drag throughout the process, maintaining stable altitude and speed; when the speed reaches the threshold for maintaining cruise, and the total rocket thrust drops to the safe shutdown value, the four liquid rocket engines 2 shut down synchronously, completing the power handover; at this time, the single turbojet engine 3 at the tail provides cruise thrust, and the fuselage 1, relying on the aerodynamic shape structure of the lifting body, generates aerodynamic lift. The attitude control of the manned aircraft is completely achieved by the flight control system 9 controlling the control surfaces 13 on both sides, maintaining a high-speed cruise of 1000km / h.

[0019] 4. Landing Phase: After reaching the target airspace, the manned aircraft adopts a continuous linear gliding deceleration method to descend, abandoning the fixed-point hovering landing mode of traditional rotorcraft; the flight control system 9 combines real-time coordinates, speed, altitude, and inertial parameters to restart the four liquid rocket engines 2 in the preset low-altitude zone for reverse thrust braking, completing a rapid, vertical, and precise landing without a runway.

[0020] The preferred embodiments of the present invention have been described in detail above. It should be understood that those skilled in the art can make numerous modifications and variations based on the concept of the present invention without creative effort. Therefore, all technical solutions that can be obtained by those skilled in the art based on the concept of the present invention through logical analysis, reasoning, or limited experimentation on the basis of existing technology should be within the scope of protection defined by the claims.

Claims

1. A small vertical takeoff and landing lifting body manned aircraft, characterized in that, The manned aircraft includes a fuselage (1) with a lifting body aerodynamic shape; four vertically downward liquid rocket engines (2) are installed at the bottom of the fuselage (1), and a horizontally rearward turbojet engine (3) is installed at the tail; an oxidizer tank (4), a fuel tank (5), and two oil pumps (6) are installed inside the fuselage (1); the oxidizer tank (4) and the fuel tank (5) are connected to the two oil pumps (6); the front oil pump (6) is connected to the two front liquid rocket engines (2) through two oil lines, and the rear oil pump (6) is connected to the two rear liquid rocket engines (2) through two oil lines; each liquid rocket engine (2) has a lifting body aerodynamic shape structure. Throttling valves (7) are installed on the oil lines between the liquid rocket engine (2) and the oil pump (6). The oil pump (6) pressurizes and pumps the oxidizer and fuel into four corresponding throttle valves (7). Each throttle valve (7) has two independent flow control chambers. The flow of oxidizer and fuel is controlled according to the ratio and injected into the corresponding liquid rocket engine (2) for atomization, mixing and combustion. The fuel tank (5) is also connected to the turbojet engine (3) through a pipeline. The turbojet engine control unit (8) is installed on the pipeline. The fuselage (1) is also equipped with a flight control system (9). The flight control system (9) has a built-in control program for controlling the entire manned aircraft.

2. A small vertical takeoff and landing lifting body manned aircraft according to claim 1, characterized in that, The fuselage (1) is equipped with a cockpit (10) on top; the cockpit (10) is equipped with a control console (11), which issues commands to the flight control system (9) to control the operation of the entire manned aircraft.

3. A small vertical takeoff and landing lifting body manned aircraft according to claim 1, characterized in that, The fuselage (1) has two symmetrical tail wings (12) on the top surface of the tail section, and the two tail wings (12) are symmetrically arranged on both sides of the turbojet engine (3).

4. A small vertical takeoff and landing lifting body manned aircraft according to claim 1, characterized in that, The fuselage (1) has symmetrical control surfaces (13) on both sides of the rear end that can swing up and down. The control surfaces (13) are controlled to swing by the flight control system (9).

5. A small vertical takeoff and landing lifting body manned aircraft according to claim 1, characterized in that, The fuselage (1) is a one-piece carbon fiber hard shell structure.

6. A small vertical takeoff and landing lifting body manned aircraft according to claim 1, characterized in that, The fuselage (1) is also provided with a turbojet engine air inlet (14) at the bottom; the turbojet engine air inlet (14) is connected to the turbojet engine (3).

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