Spacecraft and control system thereof

Abstract

The invention relates to the technical field of space flight, and discloses a spacecraft and a control system thereof.The spacecraft comprises a power outer cabin, a large round hole is formed in the middle of the top of the power outer cabin, and an outer cabin body is fixedly connected into the large round hole in the middle of the top of the power outer cabin; a plurality of circular grooves are formed in the surface of the bottom of the power outer cabin, power devices are fixedly connected into the circular grooves in the surface of the bottom of the power outer cabin, the power outer cabin comprises a rotatable power cabin, and an instantaneous full-dimensional steering system is fixedly connected to the surface of the outer wall of the rotatable power cabin; the outer cabin machine body comprises a machine body shell, an inner cabin is arranged in the middle of an inner cavity of the machine body shell, air vortexes around the machine body are triggered through an aircraft engine, cavitation bubbles are formed to wrap the machine body, and the aircraft can run in a vacuum environment all the time and can reach the speed higher than the light speed.

Description

Technical Field

[0001] The present invention relates to the field of space flight technology, and more specifically to a spacecraft and a control system thereof. Background Art

[0002] Spacecraft, also known as space vehicle or space vehicle, is a variety of aircraft that operates in space according to the laws of celestial mechanics and performs specific tasks such as exploration, development, and utilization of space and celestial bodies. Spacecraft basically operate within the solar system. Exploring space is one of the most cutting-edge practices of mankind.

[0003] One of the biggest challenges in humanity's current plans to the moon, Mars and exoplanets is time. Although today's spacecraft are undoubtedly more advanced, it is estimated that it takes six months to travel from Earth to Mars, and even longer to other planets in the solar system. The prospect of such a long journey out of the solar system needs to take into account the psychological and physiological effects of space on humans. Although some experts have proposed solutions such as hibernating colonists or generation spacecraft, at the same time, long-distance interstellar travel requires carrying a lot of fuel, and its weight requires more fuel to generate enough thrust. In order to continue galactic exploration, this paradox must be solved somehow, preferably by finding an alternative, faster propulsion system for spacecraft that can make interstellar travel faster and cheaper, that is, the next generation of spacecraft. Summary of the invention

[0004] In order to overcome the above-mentioned defects of the prior art, the present invention provides a spacecraft and a control system thereof to solve the problems existing in the above-mentioned background technology.

[0005] The present invention provides the following technical solution: a spacecraft and its control system, comprising a power outer cabin, a large circular hole is opened in the middle of the top of the power outer cabin, an outer cabin body is fixedly connected in the large circular hole in the middle of the top of the power outer cabin, eight circular grooves are opened on the bottom surface of the power outer cabin, power devices are fixedly connected in the multiple circular grooves on the bottom surface of the power outer cabin, and the structural design is simple.

[0006] Furthermore, the power outer cabin includes a rotatable power cabin, and the outer wall surface of the rotatable power cabin is fixedly connected with an instantaneous full-dimensional steering system.

[0007] Furthermore, the outer cabin body includes a fuselage shell, an inner cabin is provided in the middle of the inner cavity of the fuselage shell, a gyroscope balancing device is fixedly connected to the inner cavity of the fuselage shell near the bottom of the inner cabin, and a control cabin device is provided between the fuselage shell and the inner cabin, and the control cabin device can maintain balance.

[0008] Furthermore, the inner cabin includes a crew cabin, and a magnetic levitation isolation belt is fixedly connected to the outer wall surface of the crew cabin, and the magnetic levitation isolation belt facilitates separation of the fuselage shell.

[0009] Furthermore, the control cabin device includes a control cabin body, and a plurality of movable track counterweights are arranged inside the control cabin body for adjusting the attitude and center of gravity to realize omnidirectional maneuverability of the fuselage.

[0010] Furthermore, the power device includes a power nozzle, a nuclear battery is arranged in the middle of the power nozzle, the top of the nuclear battery is fixedly connected to eight circular grooves on the bottom surface of the power outer cabin, the bottom of the nuclear battery is fixedly connected to a blade, and the bottom of the blade is fixedly connected to a turbojet engine. The power device superimposes the forces, and the multi-force vortices form a combined force, achieving multi-directional flight.

[0011] Furthermore, a control system of a spacecraft is that when the spacecraft and its control system are used, the power outer cabin wraps the outer cabin body in configuration, the power outer cabin and the outer cabin body are in a fixed connection state, the power outer cabin and the outer cabin body are designed as one body, the outer cabin body is a sphere, the outer cabin body is raised as a whole, a control cabin device is formed between the fuselage outer shell and the inner cabin, the control cabin device can maintain balance, the control cabin device is responsible for the vertical balance direction of the inner cabin, the member cabin is the member position, the inner cabin is O-shaped, the power source of the power device includes nuclear batteries, blades, turbojet engines and power control systems, etc., the bottom of the power outer cabin is composed of eight power devices, which are evenly distributed, and the number of power devices is designed to be eight, which is the optimal power quantity configuration, which can efficiently realize the kinetic energy resultant force, more than eight power devices will cause waste and weight burden, less than eight power devices will have insufficient kinetic energy efficiency, compared with the traditional single thrust, eight power devices have more than superimposed force, multi-force vortices form a resultant force, multi-directional flight, and the blades have multi-directional, vector, and lifting maneuvers. The characteristics of the control system are that under the command of the control system, the control directions of the eight power units are always consistent, and the reverse effect of the flow of a single power is used to generate superimposed power waves, realizing the powerful propulsion of the eight power sources. Through the operation of the module, the tilt or horizontal angle of the inner cabin can be quickly changed. The movable track counterweight is used to adjust the attitude and center of gravity to realize the omnidirectional maneuverability of the fuselage. In addition, the upper eight external invisible wing modules corresponding to the bottom power unit can be retracted and opened, and the air flow can affect the angle, speed, and enhance the direction and speed control of the aircraft. The instantaneous full-dimensional steering system changes the direction of movement by adjusting the direction of the power unit. There is a magnetic levitation isolation belt on the surface of the crew cabin. The fuselage shell and the inner cabin are magnetically suspended and controlled by a gyroscope balance device. The angular momentum of the power outer cabin is large during high-speed spiral, flipping, and forward movement. The gyroscope balance device will always stably point to one direction. The inner cabin can maintain a horizontal and vertical direction and a relatively static state. Finally, a manned test flight is carried out to achieve superluminal flight and reach the expected position.

[0012] Technical effects and advantages of the present invention:

[0013] 1. The present invention uses the aircraft engine to induce an air vortex around the aircraft body, forming a cavitation bubble that wraps the aircraft body. The aircraft will always operate in a vacuum environment and will reach a speed faster than the speed of light.

[0014] 2. The present invention is advantageous in that eight power devices are provided to efficiently realize the kinetic energy resultant force. More than eight power devices will cause waste and weight burden, and less than eight will result in insufficient kinetic energy efficiency. Compared with the traditional single thrust, the eight power port vortices have more superimposed forces, and the multi-force vortices form a resultant force, allowing for multi-directional flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1It is a schematic diagram of the overall top structure of the present invention.

[0016] Figure 2 It is a schematic diagram of the overall bottom structure of the present invention.

[0017] Figure 3 It is a schematic cross-sectional view of the overall structure of the present invention.

[0018] Figure 4 It is a schematic diagram of the power outer cabin structure of the present invention.

[0019] Figure 5 It is a schematic cross-sectional view of the power device structure of the present invention.

[0020] Figure 6 It is a schematic diagram of the inner cavity structure of the present invention.

[0021] The figures are marked as follows: 1. power outer cabin; 101. rotatable power cabin; 102. instantaneous full-dimensional steering system; 2. outer cabin body; 201. fuselage shell; 202. inner cabin; 2021. crew cabin; 2022. magnetic levitation isolation belt; 203. gyroscope balancing device; 204. control cabin device; 2041. control cabin body; 2042. movable track counterweight; 3. power unit; 301. power nozzle; 302. nuclear battery; 303. blades; 304. turbojet engine. DETAILED DESCRIPTION

[0022] The technical solution of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the present invention. In addition, the forms of the various structures recorded in the following embodiments are only examples. The spacecraft and its control system involved in the present invention are not limited to the various structures recorded in the following embodiments. All other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0023] Reference Figure 1-6 As shown, the present invention provides a spacecraft and its control system, including a power outer cabin 1, a large circular hole is opened in the middle of the top of the power outer cabin 1, an outer cabin body 2 is fixedly connected in the large circular hole in the middle of the top of the power outer cabin 1, eight circular grooves are opened on the bottom surface of the power outer cabin 1, and power devices 3 are fixedly connected in the eight circular grooves on the bottom surface of the power outer cabin 1, and the structural design is simple.

[0024] In a preferred embodiment, the power outer cabin 1 includes a rotatable power cabin 101 , and an instantaneous full-dimensional steering system 102 is fixedly connected to the outer wall surface of the rotatable power cabin 101 .

[0025] In a preferred embodiment, the outer cabin body 2 includes a fuselage shell 201, an inner cabin 202 is provided in the middle of the inner cavity of the fuselage shell 201, a gyroscope balancing device 203 is fixedly connected to the inner cavity of the fuselage shell 201 near the bottom of the inner cabin 202, and a control cabin device 204 is provided between the fuselage shell 201 and the inner cabin 202, and the control cabin device 204 can maintain balance.

[0026] In a preferred embodiment, the inner cabin 202 includes a crew cabin 2021 , and a magnetic levitation isolation belt 2022 is fixedly connected to the outer wall surface of the crew cabin 2021 , and the magnetic levitation isolation belt 2022 facilitates separation of the fuselage outer shell 201 .

[0027] In a preferred embodiment, the control cabin device 204 includes a control cabin body 2041, and a plurality of movable track counterweights 2042 are provided inside the control cabin body 2041 for adjusting the attitude and center of gravity to realize omnidirectional maneuverability of the fuselage.

[0028] In a preferred embodiment, the power device 3 includes a power nozzle 301, a nuclear battery 302 is arranged in the middle of the power nozzle 301, the top of the nuclear battery 302 is fixedly connected to a plurality of circular grooves on the bottom surface of the power outer cabin 1, the bottom of the nuclear battery 302 is fixedly connected to a blade 303, and the bottom of the blade 303 is fixedly connected to a turbojet engine 304. The power device 3 superimposes the forces, and the multi-force vortices form a combined force, which enables multi-directional flight.

[0029] A control system of a spacecraft is that when the spacecraft and its control system are used, in terms of configuration, a power outer cabin 1 wraps an outer cabin body 2, the power outer cabin 1 and the outer cabin body 2 are in a fixed connection state, the power outer cabin 1 and the outer cabin body 2 are designed as one body, the outer cabin body 2 is a sphere, the outer cabin body 2 is convex as a whole, a control cabin device 204 is formed between the fuselage outer shell 201 and the inner cabin 202, the control cabin device 204 can maintain balance, the control cabin device 204 is responsible for the vertical balance direction of the inner cabin 202, the member cabin 2021 is the member position, the inner cabin 202 is O-shaped, and the power device The power source of the aircraft 3 includes a nuclear battery 302, a blade 303, a turbojet engine 304, and a power control system. The bottom of the power outer cabin 1 is composed of eight power devices 3, which are evenly distributed. The number of power devices 3 is designed to be eight, which is the optimal power quantity configuration and can efficiently realize the kinetic energy. More than eight power devices 3 will cause waste and weight burden, and less than eight power devices 3 will cause insufficient kinetic energy efficiency. Compared with the traditional single thrust, the eight power devices 3 have more superimposed forces, and the multi-force vortex forms a combined force, which allows multi-directional flight. The blades 303 have multi-directional and vector , improve the maneuverability. Under the command of the control system, the control directions of the eight power devices 3 are always consistent. The reverse effect of the flow of a single power is used to generate superimposed power waves, realizing the powerful propulsion of eight power sources. Through the operation of the module, the tilt or horizontal angle of the inner cabin 202 is quickly changed. The movable track counterweight block 2042 is used to adjust the attitude and center of gravity to achieve omnidirectional maneuverability of the fuselage. In addition, the upper eight outer stealth wing modules corresponding to the bottom power device can be retracted and opened to affect the angle, speed, and enhance the direction and speed of the aircraft through air flow. The instantaneous full-dimensional steering system 102 changes the direction of movement by adjusting the direction of the power unit 3. There is a magnetic levitation isolation belt 2022 on the surface of the crew cabin 2021. The fuselage shell 201 and the inner cabin 202 are magnetically suspended and controlled by a gyroscope balance device 203. The angular momentum of the power outer cabin 1 during high-speed spiral, flipping, and forward movement is very large. The gyroscope balance device 203 will always stably point to one direction. The inner cabin 202 can maintain a horizontal and vertical direction and a relatively static state. Finally, a manned test flight is carried out to achieve superluminal flight and reach the expected position.

Claims

1. A spacecraft, comprising a powered outer cabin (1), characterized in that: A large circular hole is provided in the middle of the top of the power outer cabin (1), and an outer cabin body (2) is fixedly connected in the large circular hole in the middle of the top of the power outer cabin (1). Eight circular grooves are provided on the bottom surface of the power outer cabin (1), and a power device (3) is fixedly connected in the multiple circular grooves on the bottom surface of the power outer cabin (1).

2. A spacecraft according to claim 1, characterized in that: The power outer cabin (1) comprises a rotatable power cabin (101), and an instantaneous full-dimensional steering system (102) is fixedly connected to the outer wall surface of the rotatable power cabin (101).

3. A spacecraft according to claim 1, characterized in that: The outer cabin body (2) comprises a fuselage shell (201), an inner cabin (202) is arranged in the middle of an inner cavity of the fuselage shell (201), a gyroscope balancing device (203) is fixedly connected to the inner cavity of the fuselage shell (201) near the bottom of the inner cabin (202), and a control cabin device (204) is arranged between the fuselage shell (201) and the inner cabin (202).

4. A spacecraft according to claim 3, characterized in that: The inner cabin (202) includes a crew cabin (2021), and a magnetic suspension isolation belt (2022) is fixedly connected to the outer wall surface of the crew cabin (2021).

5. A spacecraft according to claim 3, characterized in that: The control cabin device (204) comprises a control cabin body (2041), and a plurality of movable track counterweight blocks (2042) are arranged inside the control cabin body (2041).

6. A spacecraft according to claim 1, characterized in that: The power device (3) comprises a power nozzle (301), a nuclear battery (302) is arranged in the middle of the power nozzle (301), the top of the nuclear battery (302) is fixedly connected to a plurality of circular grooves on the bottom surface of the power outer cabin (1), the bottom of the nuclear battery (302) is fixedly connected to a blade (303), and the bottom of the blade (303) is fixedly connected to a turbojet engine (304).

7. A control system for a spacecraft according to any one of claims 1 to 6: when the spacecraft and its control system are used, in terms of configuration, the power outer cabin (1) wraps around the outer cabin body (2), the power outer cabin (1) and the outer cabin body (2) are in a fixed connection state, the power outer cabin (1) and the outer cabin body (2) are designed as one body, the outer cabin body (2) is a sphere, the outer cabin body (2) is convex as a whole, a control cabin device (204) is formed between the fuselage shell (201) and the inner cabin (202), the control cabin device (204) can maintain balance, the control cabin device (204) is responsible for the vertical balance direction of the inner cabin (202), and the crew cabin (20 21) is the member position, the inner cabin (202) is O-shaped, the power source of the power device (3) includes a nuclear battery (302), a blade (303), a turbojet engine (304) and a power control system, etc. The bottom of the power outer cabin (1) is composed of eight power devices (3) and is evenly distributed. The number of power devices (3) is designed to be eight, which is the optimal power quantity configuration and can efficiently achieve kinetic energy. More than eight power devices (3) will cause waste and weight burden, and less than eight power devices (3) will have insufficient kinetic energy efficiency. Compared with the traditional single thrust, the eight power devices (3) have more superimposed forces, and multi-force vortexes form a combined force. force, multi-directional flight, the blades (303) have the characteristics of multi-directional, vector and lifting maneuverability. Under the command of the control system, the eight power devices (3) control the direction to be consistent at any time, and use the reverse effect of the flow of a single power to generate a superimposed power wave to achieve a strong propulsion force of eight power sources. Through the operation of the module, the tilt or horizontal angle of the inner cabin (202) can be quickly changed. The movable track counterweight block (2042) is used to adjust the attitude and center of gravity to achieve omnidirectional maneuverability of the fuselage. In addition, the upper eight outer stealth wing modules corresponding to the bottom power device can be retracted and opened, and the angle, speed and degree of enhancement of the aircraft can be affected by air flow. The instantaneous full-dimensional steering system (102) changes the direction of movement by adjusting the direction of the power device (3). A magnetic suspension isolation belt (222) is provided on the surface of the crew cabin (2021). The fuselage shell (201) and the inner cabin (202) are magnetically suspended and controlled by a gyroscope balancing device (203). The angular momentum of the power outer cabin (1) is large during high-speed spiraling, flipping, and forward movement. The gyroscope balancing device (203) will always stably point in one direction. The inner cabin (202) can maintain a horizontal and vertical direction and a relatively static state. Finally, a manned test flight is carried out to achieve superluminal flight and reach the expected position.

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