Umbrella lunar electromagnetic launch system

Abstract

The application relates to the technical field of electromagnetic emission, and discloses an umbrella type lunar surface electromagnetic emission system. The system is arranged on a flat lunar surface and has a predetermined included angle with the lunar surface. The system comprises a rotating arm device, an electromagnetic propulsion device, an electric suspension device and a spacecraft. The rotating arm device comprises a rotating arm and a rotating shaft. The rotating shaft is fixed on the flat lunar surface, and the rotating arm rotates around the rotating shaft. One end of the rotating arm is arranged with the spacecraft, and the other end is arranged with a counterweight unit. The electromagnetic propulsion device generates a propulsion force to drive the rotating arm to accelerate rotation, so as to accelerate the spacecraft. The electric suspension device is used for generating a suspension force and a guiding force. The suspension force is used for balancing the gravity of the rotating arm. The guiding force and the tension of the rotating arm are used for balancing the centrifugal force of the rotating arm. When the spacecraft is accelerated to a predetermined speed, the spacecraft and the counterweight unit are separated from the rotating arm at the same time, and the spacecraft enters an earth orbit in a predetermined mode. Therefore, the problems of insufficient moon-earth transportation and moon-earth return emission capacity can be solved, and the carrying capacity of the carrier can be effectively improved.

Description

Technical Field

[0001] This invention relates to the field of electromagnetic launch technology, and more particularly to an umbrella-type lunar electromagnetic launch system. Background Technology

[0002] Electromagnetic launch technology refers to a new type of launch technology that uses electromagnetic force to accelerate objects to ultra-high speeds, converting electromagnetic energy into kinetic energy. It enables the launch of various launch vehicles such as rockets, spacecraft, and missiles. Electromagnetic launch technology has the following advantages: First, it significantly reduces the amount of propellant carried by spacecraft, increasing the mass of the payload; second, electromagnetic launch devices are reusable, reducing the cost per launch; and third, it has a high degree of electrification and automation, offering the advantage of unattended operation and enabling its application in unmanned environments such as space.

[0003] Currently, existing research on electromagnetic launch technology mainly focuses on mission modes involving electromagnetic launch from the ground, and there is no electromagnetic launch technology for the lunar surface. Summary of the Invention

[0004] This invention provides an umbrella-type lunar electromagnetic launch system that can solve the technical problems in the prior art.

[0005] This invention provides a parachute-type lunar electromagnetic launch system, wherein the parachute-type lunar electromagnetic launch system is disposed on a flat lunar surface and at a predetermined angle to the lunar surface. The parachute-type lunar electromagnetic launch system includes a rotating arm device, an electromagnetic propulsion device, an electric levitation device, and a spacecraft. The rotating arm device includes a rotating arm and a rotating shaft. The rotating shaft is fixed on the flat lunar surface, and the rotating arm rotates around the rotating shaft. The spacecraft is disposed at one end of the rotating arm, and a counterweight unit is disposed at the other end. The electromagnetic propulsion device generates thrust to drive the rotating arm to accelerate its rotation, thereby accelerating the spacecraft. The electric levitation device generates levitation force and guiding force. The levitation force is used to balance the gravity of the rotating arm, and the guiding force and the tension of the rotating arm are used to balance the centrifugal force of the rotating arm. When the spacecraft is accelerated to a predetermined speed, the spacecraft and the counterweight unit simultaneously separate from the rotating arm, and the spacecraft enters Earth orbit in a predetermined manner.

[0006] Preferably, the system further includes a separation and unlocking device. Before separation, the spacecraft and the counterweight unit are connected to the rotating arm through the separation and unlocking device. During separation, the spacecraft and the counterweight unit are unlocked and separated from the rotating arm through the separation and unlocking device.

[0007] Preferably, the rotating arm has a left-right symmetrical structure centered on the rotating axis.

[0008] Preferably, the system further includes a track beam, which comprises a main beam and a track. One end of the main beam is fixedly connected to the rotating shaft, and the other end is connected to the track. The track is circular. The electromagnetic propulsion device is a double-sided superconducting linear synchronous motor, which includes a motor stator and a motor mover. The motor stator has a coil winding installed inside it. The coil winding is oblong. The motor stator is mounted on the track and its overall outline is annular. The motor mover is located at both ends of the rotating arm.

[0009] Preferably, the motor mover is a superconducting magnet, and a superconducting coil winding is installed inside the superconducting magnet. The superconducting coil winding is energized by direct current to generate an excitation magnetic field. The motor stator is energized by alternating current to generate a traveling wave magnetic field. By controlling the spatial angle between the traveling wave magnetic field and the excitation magnetic field, an electromagnetic driving force is generated to drive the motor mover to move in a predetermined direction, thereby realizing electromechanical energy conversion.

[0010] Preferably, the electric levitation device includes a levitation stator and a levitation mover. The levitation stator includes an upper left stator, a lower left stator, an upper right stator, and a lower right stator. The levitation stator is a solid metal conductor structure without coil windings.

[0011] Preferably, the suspended stator is disposed on the track and its overall outline is circular.

[0012] Preferably, the levitation mover and the motor mover are the same superconducting magnet. When the superconducting magnet is used as the levitation mover, the magnetic field generated induces eddy currents in the levitation stator, which exert a repulsive force on the superconducting magnet. The repulsive force includes a guiding force in the horizontal direction and a levitation force in the vertical direction.

[0013] Preferably, the superconducting magnet includes a first magnet and a second magnet, with the spacecraft and the first magnet located above and below one end of the rotating arm, respectively, and the configuration unit and the second superconducting magnet located above and below the other end of the rotating arm.

[0014] Through the above technical solutions, the spacecraft can obtain different launch directions when separating at different rotation angles, meeting the needs of spacecraft launch missions with different launch directions. By generating levitation and guiding forces through the electric levitation device and ensuring the synchronization between the spacecraft and the counterweight unit, the rotating arm can always maintain a symmetrical force state before and after separation, improving the mechanical performance of the rotating arm, reducing the design and construction difficulty of the lunar electromagnetic launch device, thereby solving problems such as insufficient lunar-to-Earth transportation and lunar-to-Earth return launch capabilities, and effectively improving the launch vehicle's carrying capacity. Attached Figure Description

[0015] The accompanying drawings, which form part of this specification, are provided to further illustrate embodiments of the invention and, together with the textual description, explain the principles of the invention. It is obvious that the drawings described below are merely some embodiments of the invention, and those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0016] Figure 1 A cross-sectional schematic diagram of an umbrella-type lunar electromagnetic launch system according to an embodiment of the present invention is shown;

[0017] Figure 2 A top view of an umbrella-type lunar electromagnetic launcher according to an embodiment of the present invention is shown;

[0018] Figure 3 A schematic diagram illustrating the working principle of the electric levitation device provided according to an embodiment of the present invention is shown;

[0019] Figure 4 A schematic diagram illustrating the working principle of an electromagnetic propulsion device according to an embodiment of the present invention is shown. Detailed Implementation

[0020] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. 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 a part of the embodiments of the present invention, and not all of them. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0022] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0023] exist Figure 1 In this system, the coordinate system is a right-handed coordinate system, and the forward direction of the vehicle's motion is defined as the +x direction, and the vertical upward direction is defined as the +z direction.

[0024] like Figure 1 and 2 As shown, this embodiment of the invention provides a parachute-type lunar electromagnetic launch system. The parachute-type lunar electromagnetic launch system is positioned on a flat lunar surface and has a predetermined angle with the lunar surface. The parachute-type lunar electromagnetic launch system includes a rotating arm device, an electromagnetic propulsion device, an electric levitation device, and a spacecraft 8. The rotating arm device includes a rotating arm 5 and a rotating shaft 6. The rotating shaft 6 is fixed on the flat lunar surface, and the rotating arm 5 rotates around the rotating shaft 6. The spacecraft 8 is mounted at one end of the rotating arm 5, and a counterweight unit 9 is mounted at the other end. The electromagnetic propulsion device generates thrust to drive the rotating arm 5 to accelerate its rotation, thereby accelerating the spacecraft 8. The electric levitation device generates levitation force and guiding force. The levitation force is used to balance the gravity of the rotating arm 5, and the guiding force and the tension of the rotating arm 5 are used to balance the centrifugal force of the rotating arm 5. When the spacecraft 8 is accelerated to a predetermined speed, the spacecraft 8 and the counterweight unit 9 simultaneously separate from the rotating arm 5, and the spacecraft 8 enters Earth orbit in a predetermined manner.

[0025] In other words, the guiding force generated by the electric levitation device and the rotating arm together balance the centrifugal force when the rotating arm rotates, and the levitation force generated by the electric levitation device and the rotating arm together balance the gravity of the rotating arm. At the exit position of the lunar electromagnetic launch system, the spacecraft is accelerated to the predetermined speed, the electromagnetic launch spacecraft separates from the lunar electromagnetic launch system, and after separation, it enters Earth orbit in a predetermined manner.

[0026] The rotating shaft is fixed on the flat lunar surface and has a predetermined angle with the lunar surface.

[0027] Through the above technical solutions, the spacecraft can obtain different launch directions when separating at different rotation angles, meeting the needs of spacecraft launch missions with different launch directions. By generating levitation and guiding forces through the electric levitation device and ensuring the synchronization between the spacecraft and the counterweight unit, the rotating arm can always maintain a symmetrical force state before and after separation, improving the mechanical performance of the rotating arm, reducing the design and construction difficulty of the lunar electromagnetic launch device, thereby solving problems such as insufficient lunar-to-Earth transportation and lunar-to-Earth return launch capabilities, and effectively improving the launch vehicle's carrying capacity.

[0028] According to one embodiment of the present invention, the system further includes a separation and unlocking device. Before separation, the spacecraft 8 and the counterweight unit 9 are connected to the rotating arm 5 through the separation and unlocking device. During separation, the spacecraft 8 and the counterweight unit 9 are unlocked and separated from the rotating arm 5 through the separation and unlocking device.

[0029] In other words, the spacecraft and the counterweight unit can be fixed and separated by the separation unlocking device.

[0030] According to one embodiment of the present invention, the rotating arm 5 has a left-right symmetrical structure centered on the rotating shaft 6.

[0031] In other words, the swing arm is divided by the pivot point, and both sides have the same length, R1. The pivot point is located at the center of the track beam, and the swing arm is positioned above the pivot point.

[0032] By utilizing the symmetry of the swing arm structure, the swing arm can maintain a symmetrical force state before and after separation, avoiding asymmetrical force on the swing arm and shaft, and improving the mechanical performance of the swing arm.

[0033] According to one embodiment of the present invention, the system further includes a track beam 4, which includes a main beam 7 and a track. One end of the main beam 7 is fixedly connected to the rotating shaft 6, and the other end is connected to the track (i.e., the main beam and the track are fixed and cannot be rotated). The track is circular (radius R1). The electromagnetic propulsion device is a double-sided superconducting linear synchronous motor. The double-sided superconducting linear synchronous motor includes a motor stator 1 and a motor mover. A coil winding is installed inside the motor stator 1. The coil winding is oblong. The motor stator 1 is disposed on the track and its overall outline is annular (radius R1). The motor mover is disposed at both ends of the rotating arm 5.

[0034] The overall outer contour of the motor stator is circular, which allows the spacecraft to accelerate continuously within the circular motor, achieving a higher launch speed and reducing the motor thrust requirements.

[0035] Therefore, the main beam can be used to connect the two sides of the track, so that the lateral forces on the two track beams can be balanced through the main beam, avoiding the track beams from being subjected to large asymmetric lateral forces, improving the mechanical properties of the track beams, and reducing the size and mass of the track beams.

[0036] According to one embodiment of the present invention, the motor mover is a superconducting magnet 3, and a superconducting coil winding is installed inside the superconducting magnet 3. The superconducting coil winding is energized by direct current to generate an excitation magnetic field. The motor stator 1 is energized by alternating current to generate a traveling wave magnetic field. By controlling the spatial angle between the traveling wave magnetic field and the excitation magnetic field, an electromagnetic driving force is generated to drive the motor mover to move in a predetermined direction, thereby realizing electromechanical energy conversion.

[0037] That is, when the superconducting magnet 3 interacts with the motor stator 1 to generate electromagnetic force, it drives the rotating arm to accelerate its rotation along with the spacecraft (the working principle of the electromagnetic propulsion device is as follows). Figure 4 (As shown).

[0038] According to one embodiment of the present invention, the electric suspension device includes a suspension stator 2 and a suspension mover. The suspension stator 2 includes an upper left stator, a lower left stator, an upper right stator, and a lower right stator (i.e., it is divided into four segments: upper, lower, left, and right). The suspension stator 2 is a solid metal conductor structure without coil windings.

[0039] The suspension stator can be made of copper plate, steel plate or aluminum plate.

[0040] According to one embodiment of the present invention, the suspension stator 2 is disposed on the track and its overall outline is annular (radius R1).

[0041] For example, the motor stator can be set in the middle of the track, and the suspended stator is located on the upper and lower sides of the motor stator.

[0042] According to one embodiment of the present invention, the levitation mover and the motor mover are the same superconducting magnet 3 (i.e., the levitation mover and the motor mover share the same superconducting magnet). When the superconducting magnet 3 operates as the levitation mover, the generated magnetic field induces eddy currents in the levitation stator, which exert a repulsive force on the superconducting magnet. The repulsive force includes a guiding force in the horizontal direction and a levitation force in the vertical direction, such as... Figure 3 As shown.

[0043] When the superconducting magnet interacts with the stator of the motor to generate electromagnetic force, it drives the rotating arm to accelerate and rotate together with the spacecraft. The centrifugal force during the rotation of the rotating arm is jointly borne by the arm's tension and the guiding force generated by the electric levitation device. The load distribution ratio between the rotating arm and the levitation device can be adjusted by setting the design parameters of the electric levitation device. The weight of the rotating arm itself is jointly borne by the levitation force generated by the rotating arm and the electric levitation device.

[0044] According to one embodiment of the present invention, the superconducting magnet includes a first magnet and a second magnet, the spacecraft 8 and the first magnet are respectively located above and below one end of the rotating arm 5, and the configuration unit 9 and the second superconducting magnet are located above and below the other end of the rotating arm 5.

[0045] This invention also provides a method for concentric lunar electromagnetic launch using the concentric lunar electromagnetic launch system described in the above embodiments, the method comprising:

[0046] S1. Connect the spacecraft and the counterweight unit to the two ends of the rotating arm of the lunar electromagnetic launch system, respectively.

[0047] S2. Under the action of the superconducting linear synchronous motor, the motor mover generates electromagnetic force, which drives the rotating arm to rotate, and the spacecraft and the counterweight unit accelerate to rotate along the rotating shaft.

[0048] S3. At the exit position of the lunar electromagnetic launch system, the spacecraft and the counterweight are accelerated to the predetermined speed, and the spacecraft and the counterweight unit separate from the rotating arm at the same time.

[0049] S4. After separation, the spacecraft enters Earth orbit in a predetermined manner.

[0050] In other words, before launch, the spacecraft and the counterweight unit are respectively installed and locked onto the separation device of the rotating arm. The linear motor is energized, and its interaction with the superconducting magnet generates propulsion, causing the rotating arm to rotate. The levitation stator interacts with the superconducting magnet to generate levitation force, balancing the gravity of the rotating arm. Under the action of the rotating arm, the spacecraft accelerates within a circular orbit. The centripetal force of the spacecraft and the counterweight is provided by the tension of the rotating arm and the guiding force of the superconducting magnet, and the tension at both ends of the rotating arm is balanced by the counterweight unit. When the predetermined speed is reached, the separation device unlocks, and the spacecraft and the counterweight unit separate from the rotating arm simultaneously. The spacecraft enters the orbit in a predetermined manner, and the rotating arm decelerates and brakes under the action of the linear motor, thus completing the single launch mission.

[0051] In this invention, the spacecraft may be, for example, a rocket, a missile, an aircraft, etc.

[0052] In the description of this invention, it should be understood that the orientation or positional relationship indicated by directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" is generally based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing this invention and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this invention; the directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0053] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0054] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0055] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A parachute-type lunar electromagnetic launch system, characterized in that, The umbrella-type lunar electromagnetic launch system is positioned on a flat lunar surface at a predetermined angle to it. The system includes a rotating arm, an electromagnetic propulsion device, an electric levitation device, and a spacecraft (8). The rotating arm includes a rotating arm (5) and a rotating shaft (6). The rotating shaft (6) is fixed to the flat lunar surface. The rotating arm (5) rotates around the rotating shaft (6). The spacecraft (8) is mounted at one end of the rotating arm (5), and a counterweight unit (9) is mounted at the other end. The electromagnetic propulsion device generates propulsion. The force drives the rotating arm (5) to accelerate and accelerate the spacecraft (8). The electric levitation device is used to generate levitation force and guiding force. The levitation force is used to balance the gravity of the rotating arm (5). The guiding force and the tension of the rotating arm (5) are used to balance the centrifugal force of the rotating arm (5). When the spacecraft (8) is accelerated to a predetermined speed, the spacecraft (8) and the counterweight unit (9) separate from the rotating arm (5) at the same time. The spacecraft (8) enters the Earth orbit in a predetermined manner. The system also includes a track beam (4) comprising a track, and the electromagnetic propulsion device is a double-sided superconducting linear synchronous motor comprising a motor stator (1) and a motor mover; The electric suspension device includes a suspension stator (2) and a suspension mover. The suspension stator (2) includes an upper left stator, a lower left stator, an upper right stator and a lower right stator. The suspension stator (2) is a solid metal conductor structure without coil windings. The suspended stator (2) is mounted on the track and its overall outline is circular; The levitation mover and the motor mover are the same superconducting magnet. When the superconducting magnet is used as the levitation mover, the magnetic field generated induces eddy currents in the levitation stator, which exert a repulsive force on the superconducting magnet. The repulsive force includes a guiding force in the horizontal direction and a levitation force in the vertical direction. The superconducting magnet includes a first magnet and a second magnet. The spacecraft (8) and the first magnet are located above and below one end of the rotating arm (5), respectively. The counterweight unit (9) and the second magnet are located above and below the other end of the rotating arm (5).

2. The system according to claim 1, characterized in that, The system also includes a separation unlocking device. Before separation, the spacecraft (8) and the counterweight unit (9) are connected to the rotating arm (5) through the separation unlocking device. During separation, the spacecraft (8) and the counterweight unit (9) are unlocked and separated from the rotating arm (5) through the separation unlocking device.

3. The system according to claim 2, characterized in that, The rotating arm (5) is a left-right symmetrical structure centered on the rotating shaft (6).

4. The system according to claim 1, characterized in that, The track beam (4) also includes a main beam (7), one end of which is fixedly connected to the rotating shaft (6), and the other end is connected to the track. The track is circular. The motor stator (1) is equipped with a coil winding. The coil winding is oblong. The motor stator (1) is set on the track and its overall outline is circular. The motor mover is set at both ends of the rotating arm (5).

5. The system according to claim 4, characterized in that, The motor mover is a superconducting magnet, and a superconducting coil winding is installed inside the superconducting magnet. The superconducting coil winding is energized by direct current to generate an excitation magnetic field. The motor stator (1) is energized by alternating current to generate a traveling wave magnetic field. By controlling the spatial angle between the traveling wave magnetic field and the excitation magnetic field, an electromagnetic driving force is generated to drive the motor mover to move in a predetermined direction, thereby realizing electromechanical energy conversion.

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