Umbrella type lunar surface electromagnetic emission system

Abstract

The invention 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, a preset included angle is formed between the system and 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 to the flat lunar surface, the rotating arm rotates around the rotating shaft, the spacecraft is arranged at one end of the rotating arm, and a balance weight unit is arranged at the other end of the rotating arm. The electromagnetic propelling device generates propelling force to drive the rotating arm to rotate in an accelerated mode to achieve acceleration of the spacecraft, the electric suspension device is used for generating suspension force and guiding force, the suspension force is used for balancing the gravity of the rotating arm, and the guiding force and the pulling force of the rotating arm are used for balancing the centrifugal force of the rotating arm. The spacecraft and the counterweight unit are separated from the rotating arm at the same time, and the spacecraft enters the earth orbit in a preset mode. Therefore, the problems of insufficient lunar-earth transportation and lunar-earth return launching capability and the like can be solved, and the carrying capability of the carrier is effectively improved.

Description

Technical Field

[0001] The present invention relates to the field of electromagnetic launch technology, and in particular to an umbrella-type lunar electromagnetic launch system. Background Art

[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, and can achieve the launch of various carriers such as rockets, spacecraft, and missiles. Electromagnetic launch technology has the following advantages: First, it greatly reduces the amount of propellant carried by spacecraft and improves the mass of the payload; second, the electromagnetic launch device can be reused, which can reduce the cost of a single launch; third, it has a high degree of electrification and automation, has the advantage of unmanned operation, and can be used in unmanned environments such as space.

[0003] At present, the existing technology on electromagnetic launch research is mainly aimed at the mission mode of electromagnetic launch from the ground, and there is no electromagnetic launch technology for the lunar surface (lunar surface). Summary of the invention

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

[0005] The present invention provides an umbrella-type lunar electromagnetic launch system, wherein the umbrella-type lunar electromagnetic launch system is arranged on a flat lunar surface and has a predetermined angle with the lunar surface, the umbrella-type lunar electromagnetic launch 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, the rotating arm rotates around the rotating shaft, the spacecraft is arranged at one end of the rotating arm, and a counterweight unit is arranged at the other end, the electromagnetic propulsion device generates a propulsion force to drive the rotating arm to accelerate the rotation, thereby accelerating the spacecraft, the electric suspension device is used to generate a suspension force and a guiding force, the suspension force is used to balance the gravity of the rotating arm, the guiding force and the pulling force 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 are separated from the rotating arm at the same time, and the spacecraft enters the earth orbit in a predetermined manner.

[0006] Preferably, the system further comprises a separation unlocking device, wherein before separation, the spacecraft and the counterweight unit are connected to the rotating arm via the separation unlocking device, and during separation, the spacecraft and the counterweight unit are unlocked and separated from the rotating arm via the separation unlocking device.

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

[0008] Preferably, the system also includes a track beam, which includes 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, and the electromagnetic propulsion device is a bilateral superconducting linear synchronous motor, which includes a motor stator and a motor mover, a coil winding is installed in the motor stator, and the coil winding is oblong, the motor stator is arranged on the track and the overall outer contour is a circular ring, and the motor mover is arranged at both ends of the rotating arm.

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

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

[0011] Preferably, the suspension stator is arranged on the track and has an overall circular outer contour.

[0012] Preferably, the suspension rotor and the motor rotor are the same superconducting magnet. When the superconducting magnet operates as the suspension rotor, the generated magnetic field induces eddy currents in the suspension stator, exerting repulsive force on the superconducting magnet, and the repulsive force includes a guiding force in the horizontal direction and a suspension force in the vertical direction.

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

[0014] Through the above technical scheme, the spacecraft can obtain different launch directions when it separates at different rotation angles, meeting the requirements of spacecraft launch missions in different directions. The suspension force and guiding force are generated by the electric suspension device, and the synchronization of the spacecraft and the counterweight unit can make the rotating arm always maintain a symmetrical force state before and after separation, thereby improving the mechanical properties of the rotating arm and reducing the difficulty of designing and building the lunar electromagnetic launch device, thereby solving the problems of insufficient lunar-to-Earth transportation and lunar-to-Earth return launch capabilities, and effectively improving the carrying capacity of the carrier. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The included drawings are used to provide a further understanding of the embodiments of the present invention, which constitute a part of the specification, are used to illustrate the embodiments of the present invention, and together with the text description, explain the principles of the present invention. Obviously, the drawings in the following description are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[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 launch device provided according to an embodiment of the present invention is shown;

[0018] Figure 3 A schematic diagram showing the working principle of an electric suspension device provided in an embodiment of the present invention is shown;

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

[0020] It should be noted that, in the absence of conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present invention and its application or use. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0021] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0022] Unless otherwise specifically stated, the relative arrangement of the parts and steps described in these embodiments, numerical expressions and numerical values ​​do not limit the scope of the present invention. At the same time, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship. The technology, method and equipment known to ordinary technicians in the relevant field may not be discussed in detail, but in appropriate cases, the technology, method and equipment should be regarded as a part of the authorization specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0023] exist Figure 1 In the figure, the coordinate system is a right-hand coordinate system, which stipulates that the forward direction of the spacecraft is the +x direction, and the vertical upward direction is the +z direction.

[0024] like Figure 1 and 2 As shown, an embodiment of the present invention provides an umbrella-type lunar electromagnetic launch system, wherein the umbrella-type lunar electromagnetic launch system is arranged on a flat lunar surface and has a predetermined angle with the lunar surface, the umbrella-type lunar electromagnetic launch system comprises a rotating arm device, an electromagnetic propulsion device, an electric suspension device and a spacecraft 8, the rotating arm device comprises a rotating arm 5 and a rotating shaft 6, the rotating shaft 6 is fixed on the flat lunar surface, the rotating arm 5 rotates around the rotating shaft 6, the spacecraft 8 is arranged at one end of the rotating arm 5, and a counterweight unit 9 is arranged at the other end, the electromagnetic propulsion device generates a propulsion force to drive the rotating arm 5 to accelerate the rotation, so as to accelerate the spacecraft 8, the electric suspension device is used to generate a suspension force and a guiding force, the suspension force is used to balance the gravity of the rotating arm 5, the guiding force and the pulling force 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 are separated from the rotating arm 5 at the same time, and the spacecraft 8 enters the earth orbit in a predetermined manner.

[0025] That is, the centrifugal force of the rotating arm is balanced by the guiding force generated by the electric suspension device and the rotating arm, and the gravity of the rotating arm is balanced by the suspension force generated by the electric suspension device and the rotating arm. At the exit position of the electromagnetic launch system on the lunar surface, the spacecraft is accelerated to a predetermined speed, and the electromagnetic launch spacecraft is separated from the electromagnetic launch system on the lunar surface. After separation, it enters the 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 scheme, the spacecraft can obtain different launch directions when it separates at different rotation angles, meeting the requirements of spacecraft launch missions in different directions. The suspension force and guiding force are generated by the electric suspension device, and the synchronization of the spacecraft and the counterweight unit can make the rotating arm always maintain a symmetrical force state before and after separation, thereby improving the mechanical properties of the rotating arm and reducing the difficulty of designing and building the lunar electromagnetic launch device, thereby solving the problems of insufficient lunar-to-Earth transportation and lunar-to-Earth return launch capabilities, and effectively improving the carrying capacity of the carrier.

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

[0029] That is, the fixing and separation of the spacecraft and the counterweight unit can be achieved by separating and unlocking the device.

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

[0031] That is, the arm has the same length on both sides, which is R1, with the axis of rotation as the boundary. The axis of rotation is located at the center of the track beam, and the arm of rotation is arranged above the axis of rotation.

[0032] By utilizing the symmetry of the swing arm structure, the swing arm can be further kept in a symmetrical stress state before and after separation, avoiding asymmetric stress conditions of the swing arm and the shaft, and improving the mechanical properties of the swing arm.

[0033] According to one embodiment of the present invention, the system also includes a track beam, the track beam 4 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 (that is, the main beam and the track are fixed and cannot rotate), the track is circular (the radius is R1), the electromagnetic propulsion device is a bilateral superconducting linear synchronous motor, the bilateral superconducting linear synchronous motor includes a motor stator 1 and a motor mover, a coil winding is installed in the motor stator 1, the coil winding is oblong, the motor stator 1 is arranged on the track and the overall outer contour is a circular ring (the radius is R1), and the motor mover is arranged at both ends of the rotating arm 5.

[0034] Among them, the overall outer contour of the motor stator adopts a circular ring shape, which allows the spacecraft to continuously accelerate inside the circular motor, obtain a higher launch speed, and reduce the motor thrust requirements.

[0035] Therefore, the main beam can be used to connect the two sides of the track, so that the lateral force on the track beams on both sides 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 weight of the track beams.

[0036] According to one embodiment of the present invention, the motor mover is a superconducting magnet 3, in which a superconducting coil winding is installed. A direct current is passed through the superconducting coil winding for excitation to generate an excitation magnetic field. An alternating current is passed through the motor stator 1 to generate a traveling wave magnetic field. An electromagnetic driving force is generated by controlling the spatial angle between the traveling wave magnetic field and the excitation magnetic field to drive the motor 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, the rotating arm is pushed to accelerate the rotation together with the spacecraft (the working principle of the electromagnetic propulsion device is as follows Figure 4 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 (that is, divided into four sections: upper, lower, left and right), and the suspension stator 2 is a solid metal conductor structure without coil windings.

[0039] The suspended stator may be a copper plate, a steel plate or an aluminum plate.

[0040] According to an embodiment of the present invention, the suspension stator 2 is arranged on the track and has an overall outer contour in a circular ring shape (with a radius of R1).

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

[0042] According to an embodiment of the present invention, the suspension rotor and the motor rotor are the same superconducting magnet 3 (that is, the suspension rotor and the motor rotor share the superconducting magnet). When the superconducting magnet 3 operates as the suspension rotor, the magnetic field generated induces eddy currents in the suspension stator, which exhibits a repulsive force on the superconducting magnet. The repulsive force includes a horizontal guiding force and a vertical suspension force. Figure 3 shown.

[0043] When the superconducting magnet interacts with the motor stator to generate electromagnetic force, the rotating arm is pushed to accelerate the rotation together with the spacecraft. The centrifugal force during the rotation of the rotating arm is shared by the pulling force of the rotating arm and the guiding force generated by the electric suspension device. The load distribution ratio of the rotating arm and the suspension device can be adjusted by setting the design parameters of the electric suspension device. The gravity of the rotating arm itself is shared by the suspension force generated by the rotating arm and the electric suspension 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] The embodiment of the present invention further provides a concentric circle lunar electromagnetic launch method performed by the concentric circle lunar electromagnetic launch system described in the above embodiment, 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 rotor generates electromagnetic force, driving the rotating arm to rotate, and the spacecraft and the counterweight unit accelerate the rotation along the rotating shaft;

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

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

[0050] That is, before launch, the spacecraft and the counterweight unit are respectively installed on the separation device of the swing arm and locked. The linear motor is energized, interacting with the superconducting magnet to generate a propulsion force to rotate the swing arm. The suspension stator interacts with the superconducting magnet to generate a suspension force to balance the gravity of the swing arm. The spacecraft accelerates in a circular orbit under the action of the swing arm. The centripetal force is provided to the spacecraft and the counterweight by the pulling force of the swing arm and the guiding force of the superconducting magnet. The pulling force at both ends of the swing arm is balanced by the counterweight unit. When accelerated to a predetermined speed, the separation device is unlocked, and the spacecraft and the counterweight unit are separated from the swing arm at the same time. The spacecraft enters the orbit in a predetermined manner. The swing arm is decelerated and braked by the linear motor, and the single launch mission is completed.

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

[0052] In the description of the present invention, it is necessary to understand that the directions or positional relationships indicated by directional words such as "front, back, up, down, left, right", "lateral, vertical, perpendicular, horizontal" and "top, bottom" are usually based on the directions or positional relationships shown in the drawings. They are only for the convenience of describing the present invention and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the devices or elements referred to must have a specific direction or be constructed and operated in a specific direction. Therefore, they cannot be understood as limiting the scope of protection of the present invention. The directional words "inside and outside" refer to the inside and outside relative to the contours of each component itself.

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

[0054] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0055] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An umbrella-type lunar electromagnetic launch system, characterized in that: The umbrella-type lunar electromagnetic launch system is arranged on a flat lunar surface and has a predetermined angle with the lunar surface. The umbrella-type lunar electromagnetic launch system comprises a rotating arm device, an electromagnetic propulsion device, an electric suspension device and a spacecraft (8). The rotating arm device comprises a rotating arm (5) and a rotating shaft (6). The rotating shaft (6) is fixed on the flat lunar surface. The rotating arm (5) rotates around the rotating shaft (6). The spacecraft (8) is arranged at one end of the rotating arm (5) and a counterweight unit (9) is arranged at the other end. The electromagnetic propulsion device generates a propulsion force. The electric suspension device is used to generate a suspension force and a guide force, the suspension force is used to balance the gravity of the swing arm (5), the guide force and the pulling force of the swing arm (5) are used to balance the centrifugal force of the swing arm (5), and when the spacecraft (8) is accelerated to a predetermined speed, the spacecraft (8) and the counterweight unit (9) are separated from the swing arm (5) at the same time, and the spacecraft (8) enters the earth orbit in a predetermined manner.

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 system also includes a track beam, wherein the track beam (4) includes a main beam (7) and a track, wherein one end of the main beam (7) is fixedly connected to the rotating shaft (6), and the other end is connected to the track, wherein the track is circular, and the electromagnetic propulsion device is a bilateral superconducting linear synchronous motor, wherein the bilateral superconducting linear synchronous motor includes a motor stator (1) and a motor mover, wherein a coil winding is installed in the motor stator (1), wherein the coil winding is oblong, the motor stator (1) is arranged on the track and has an overall outer contour in the shape of a circular ring, and the motor mover is arranged 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, in which a superconducting coil winding is installed. A direct current is supplied to the superconducting coil winding for excitation to generate an excitation magnetic field. An alternating current is supplied to the motor stator (1) to generate a traveling wave magnetic field. An electromagnetic driving force is generated by controlling the spatial angle between the traveling wave magnetic field and the excitation magnetic field to drive the motor move in a predetermined direction, thereby realizing electromechanical energy conversion.

6. The system according to claim 5, characterized in that The electric suspension device comprises a suspension stator (2) and a suspension mover, the suspension stator (2) comprises an upper left stator, a lower left stator, an upper right stator and a lower right stator, and the suspension stator (2) is a solid metal conductor structure without coil windings.

7. The system according to claim 6, characterized in that The suspension stator (2) is arranged on the track and has an overall circular outer contour.

8. The system according to claim 7, characterized in that The suspension rotor and the motor rotor are the same superconducting magnet. When the superconducting magnet operates as the suspension rotor, the generated magnetic field induces eddy currents in the suspension stator, exerting repulsive force on the superconducting magnet 3, and the repulsive force includes a horizontal guiding force and a vertical suspension force.

9. The system according to claim 8, characterized in that The superconducting magnet comprises 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).

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