Electromagnetic control rotor thruster
Through the electromagnetically controlled rotor thruster, the problem of fuel exhaustion of rocket engines is solved and fuel-free propulsion and the direction adjustment of spacecraft is realized.
Patent Information
- Application Number
- CN202510562047.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-30
- Publication Date
- 2025-07-29
AI Technical Summary
The problem of fuel exhaustion when rocket engines are sailing in space makes it difficult for the prior art to provide continuous propulsion in a vacuum environment.
By electromagnetically controlling the rotor thruster, the stability changes of the gyroscope composed of the pendulum and the base are used to generate reaction forces with opposite directions and different sizes to synthesize upward synergistic forces, so as to achieve the propulsion of the thruster in a vacuum environment.
It realizes fuel-free propulsion in a vacuum environment, can push spacecraft to fly in the universe, and can adjust the flight direction and steering.
Smart Images
Figure CN120383020A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of aerospace engines, and particularly to an electromagnetic control rotor thruster. Background Art
[0002] Rocket engines need to consume fuel, and the limited fuel of a rocket will eventually run out during space travel. According to an accidental discovery during a test experiment: the gyroscopic stability generated by a rotor composed of a pendulum and a base is related to the angle between the pendulum and the rotation plane of the base. The present invention is an electromagnetic control rotor thruster that can navigate in the vacuum environment of space without fuel based on this discovery. Summary of the Invention
[0003] The technical problem to be solved by the present invention is to provide an electromagnetic control rotor thruster. By synthesizing two reaction forces with opposite directions and different magnitudes generated during the shrinking swing stage (7) and the amplifying swing stage (8), a new upward resultant force is obtained, and the direction of the resultant force is the direction of the thrust. When the main motor (4) rotates, an upward thrust can be generated, enabling the thruster body (1) to push a spacecraft to fly in the universe.
[0004] To achieve the above object, the present invention provides the following technical solutions:
[0005] An electromagnetic control rotor thruster, characterized in that: the electromagnetic control rotor thruster includes a thruster body (1) that is stationary in a vacuum and weightless state. Inside the thruster body (1), there are multiple gyroscope compartments (2). A main motor (4) is installed at the rear of the gyroscope compartment (2). A conductive slip ring (11) is installed on the output shaft of the main motor (4). The output shaft of the main motor (4) passes through the gyroscope compartment (2) and is fixed to the inner wall of the gyroscope compartment (2). A connecting rod (3) is installed on the output shaft of the main motor (4). Multiple rotor motors (13) are installed on the connecting rod (3). An internal conductive slip ring (14) is installed outside the output shaft of the rotor motor (13). A base (5) is installed on the output shaft of the rotor motor (13). An electromagnet module (9) is installed on the base (5). Each electromagnet module (9) is integrated with a laser ranging function. The pendulum (6) is fixed in a groove of the base (5) through a pin and a bearing. A magnet (10) is installed on the pendulum (6). After passing through the conductive slip ring (11) and the internal conductive slip ring (14), the wire (12) is fixed to the outer surfaces of the output shaft of the main motor (4) and the connecting rod (3), connecting the main motor (4), the rotor motor (13), and the electromagnet module (9) to provide power supply and transmit control signals for them. The gyroscope compartment (2) is divided into a shrinking swing stage (7) and an amplifying swing stage (8), and the two stages of the shrinking swing stage (7) and the amplifying swing stage (8) form a cycle.
[0006] In order to obtain a relatively large upward reaction force when the main motor (4) drives the base (5) and the pendulum (6) to rotate through the connecting rod (3), in the amplification swing stage (8), the electromagnet module (9) amplifies the swing amplitude of the pendulum (6) through the magnetic field and the magnet (10), so that the gyroscopic stability of the base (5) and the pendulum (6) becomes larger.
[0007] In order to obtain a relatively small downward reaction force when the main motor (4) drives the base (5) and the pendulum (6) to rotate through the connecting rod (3), in the reduction swing stage (7), the electromagnet module (9) reduces the swing amplitude of the pendulum (6) through the magnetic field and the magnet (10), so that the gyroscopic stability of the base (5) and the pendulum (6) becomes smaller.
[0008] In order to generate an upward thrust when the main motor (4) rotates, in the amplification swing stage (8), the output shaft of the main motor (4) obtains a relatively large upward reaction force, and in the reduction swing stage (7), the output shaft of the main motor (4) obtains a relatively small downward reaction force. Two reaction forces with opposite directions and different magnitudes are combined to obtain a new upward resultant force, and the direction of the resultant force is the direction of the thrust.
[0009] In order to generate the reduction swing stage (7) and the amplification swing stage (8), the electromagnet module (9) reduces or amplifies the swing amplitude of the pendulum (6) through the magnetic field and the magnet (10).
[0010] In order to make the gyroscopic stability of the gyro rotor composed of the base (5) and the pendulum (6) work, the rotation axis of the rotor motor (13) is parallel to the rotation plane of the main motor (4). When the main motor (4) drives the base (5) and the pendulum (6) to rotate through the connecting rod (3), the generated precession torque makes the pendulum (6) swing back and forth.
[0011] In order to make the thruster body (1) change the moving direction and steering, by adjusting the positions where the reduction swing stage (7) and the amplification swing stage (8) occur, the direction of the thrust generated by the gyroscope cabin (2) is adjusted.
[0012] In order to facilitate the control of the swing amplitude of the pendulum (6) by the electromagnet module (9) using the magnetic field, the pendulum (6) is installed with a magnet (10).
[0013] The beneficial effects of adopting the above technical solutions are as follows: The present invention provides a method and idea different from that of a rocket engine. By driving the rotor composed of the pendulum (6) and the base (5) by the main motor (4) to rotate in the reduction swing stage (7) and the amplification swing stage (8), two reaction forces with opposite directions and different magnitudes can be generated and combined to obtain a new upward resultant force, and the direction of the resultant force is the direction of the thrust, so that the thruster body (1) can push the spacecraft to fly in the universe. Description of the Drawings
[0014] The specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.
[0015] Figure 1 It is a top view of the thruster body of the present invention;
[0016] Figure 2 It is a front view of the thruster body of the present invention;
[0017] Figure 3 It is a top view of the gyroscope cabin of the present invention;
[0018] Figure 4 It is a side view of the base and pendulum structure of the present invention;
[0019] Figure 5 It is a front view of the base structure of the present invention;
[0020] Figure 6 It is a schematic diagram of the intersection of the rotating surfaces of the present invention;
[0021] Among them, 1. Thruster body, 2. Gyroscope cabin, 3. Connecting rod, 4. Main motor, 5. Base, 6. Pendulum, 7. Reducing swing stage, 8. Amplifying swing stage, 9. Electromagnet module, 10. Magnet, 11. Conductive slip ring, 12. Wire, 13. Rotor motor, 14. Internal conductive slip ring. Specific embodiments
[0022] The specific embodiments of the electromagnetic control rotor thruster will be described in detail below in conjunction with the accompanying drawings.
[0023] Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 Show the specific embodiments and processes of the electromagnetic control rotor thruster of the present invention:
[0024] Figure 2 and Figure 6 , in Figure 2 , the main motor (4) drives the base (5) and the pendulum (6) to rotate through the connecting rod (3). In the amplifying swing stage (8), the electromagnet module (9) amplifies the swing amplitude of the pendulum (6) through the magnetic field and the magnet (10) ( Figure 5 ), and at the same time, the gyroscopic stability of the base (5) and the pendulum (6) becomes larger, so that the main motor (4) obtains a larger upward reaction force when rotating in the amplifying swing stage (8). In the reducing swing stage (7), the electromagnet module (9) reduces the swing amplitude of the pendulum (6) through the magnetic field and the magnet (10) ( Figure 5) At the same time, the gyroscopic stability of the base (5) and the pendulum (6) becomes smaller, enabling the main motor (4) to obtain a smaller downward reaction force when rotating during the shrinking swing stage (7). When the main motor (4) rotates, two reaction forces with opposite directions and different magnitudes can be obtained during the shrinking swing stage (7) and the magnifying swing stage (8).
[0025] Figure 6 , after multiple tests, for the gyro rotor composed of the base (5) and the pendulum (6), when it is subjected to an external force in a two-dimensional plane and cannot precess, the rotation plane of the pendulum (6) will separate and cross the rotation plane of the base (5). At the same time, the gyroscopic stability comes into play, which is exactly the opposite of that of an ordinary gyro rotor. When an ordinary gyro rotor is subjected to an external force in a two-dimensional plane and cannot precess, the gyroscopic stability does not work. After multiple tests, it is concluded that the magnitude of the gyroscopic stability generated by the gyro rotor composed of the base (5) and the pendulum (6) is proportional to the angle between the rotation plane of the pendulum (6) and the rotation plane of the base (5).
[0026] For the process and conclusion of the present invention, power is supplied through the wire (12). The main motor (4) in the gyroscope cabin (2) drives the rotor motor (13) to rotate through the connecting rod (3). The rotor motor (13) drives the pendulum (6) to rotate through the base (5). During the magnifying swing stage (8), the electromagnet module (9) magnifies the swing amplitude of the pendulum (6) through the magnetic field and the magnet (10). At the same time, the gyroscopic stability of the base (5) and the pendulum (6) becomes larger, enabling the main motor (4) to obtain a larger upward reaction force when rotating during the magnifying swing stage (8). During the shrinking swing stage (7), the electromagnet module (9) reduces the swing amplitude of the pendulum (6) through the magnetic field and the magnet (10). At the same time, the gyroscopic stability of the base (5) and the pendulum (6) becomes smaller, enabling the main motor (4) to obtain a smaller downward reaction force when rotating during the shrinking swing stage (7). When the main motor (4) drives the base (5) and the pendulum (6) to rotate, two reaction forces with opposite directions and different magnitudes can be obtained. These two reaction forces cancel each other out to generate a new upward resultant force, and the direction of the resultant force is the direction of the thrust, enabling the thruster body (1) to push the spacecraft to fly in the universe.
[0027] When it is necessary to adjust the flight direction of the spacecraft and the spacecraft turns, by adjusting the positions where the shrinking swing stage (7) and the magnifying swing stage (8) occur, thereby adjusting the direction of the thrust generated by the gyroscope cabin (2), the flight direction and the turning of the thruster body (1) can be adjusted.
[0028] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the inventive concept of the present invention, several deformations and improvements can still be made, and these all belong to the protection scope of the present invention.
Claims
1. Electromagnetic control rotor thruster, characterized in that: The electromagnetic control rotor thruster includes a thruster body (1) that is stationary in a vacuum weightless state. Inside the thruster body (1), there are multiple gyroscope compartments (2). A main motor (4) is installed at the rear of the gyroscope compartment (2). A conductive slip ring (11) is installed on the output shaft of the main motor (4). The output shaft of the main motor (4) passes through the gyroscope compartment (2) and is fixed to the inner wall of the gyroscope compartment (2). A connecting rod (3) is installed on the output shaft of the main motor (4). Multiple rotor motors (13) are installed on the connecting rod (3). An internal conductive slip ring (14) is installed outside the output shaft of the rotor motor (13). A base (5) is installed on the output shaft of the rotor motor (13). An electromagnet module (9) is installed on the base (5). Each electromagnet module (9) integrates a laser ranging function. The pendulum (6) is fixed in the groove of the base (5) through a pin and a bearing. A magnet (10) is installed on the pendulum (6). After passing through the conductive slip ring (11) and the internal conductive slip ring (14), the wire (12) is fixed to the outer surfaces of the output shaft of the main motor (4) and the connecting rod (3), connecting the main motor (4), the rotor motor (13), and the electromagnet module (9) to provide power supply and transmit control signals for them. The gyroscope compartment (2) is divided into a shrinking swing stage (7) and an amplifying swing stage (8). The two stages of the shrinking swing stage (7) and the amplifying swing stage (8) form a cycle.
2. According to the amplified swing stage (8) described in claim 1, characterized in that: In the amplifying swing stage (8), the electromagnet module (9) amplifies the swing amplitude of the pendulum (6) through the magnetic field and the magnet (10), making the gyroscopic stability of the base (5) and the pendulum (6) larger. When the main motor (4) drives the base (5) and the pendulum (6) to rotate through the connecting rod (3), a larger upward reaction force is obtained.
3. The reduced swing phase (7) according to claim 1, characterized in that: In the shrinking swing stage (7), the electromagnet module (9) reduces the swing amplitude of the pendulum (6) through the magnetic field and the magnet (10), making the gyroscopic stability of the base (5) and the pendulum (6) smaller. When the main motor (4) drives the base (5) and the pendulum (6) to rotate through the connecting rod (3), a smaller downward reaction force is obtained.
4. The reduced swing phase (7) and the enlarged swing phase (8) according to claim 2 and claim 3, characterized in that: In the amplifying swing stage (8), the output shaft of the main motor (4) obtains a larger upward reaction force. In the shrinking swing stage (7), the output shaft of the main motor (4) obtains a smaller downward reaction force. Two reaction forces with opposite directions and different magnitudes are combined to obtain a new upward resultant force. The direction of the resultant force is the direction of the thrust. When the main motor (4) rotates, an upward thrust can be generated.
5. The pendulum (6) and the electromagnet module (9) according to claim 1, characterized in that: The electromagnet module (9) reduces or amplifies the swing amplitude of the pendulum (6) through the magnetic field and the magnet (10), generating the shrinking swing stage (7) and the amplifying swing stage (8).
6. The rotor motor (13) and the main motor (4) according to claim 1, characterized in that: The rotation axis of the rotor motor (13) is parallel to the rotation plane of the main motor (4). When the main motor (4) drives the base (5) and the pendulum (6) to rotate through the connecting rod (3), the generated driving torque causes the pendulum (6) to swing back and forth. At this time, the gyroscopic stability of the gyroscope rotor composed of the base (5) and the pendulum (6) comes into play.
7. The reduced swing phase (7) and the enlarged swing phase (8) according to claim 1, characterized in that: By adjusting the positions of the reduced swing phase (7) and the amplified swing phase (8), the direction of the thrust generated by the gyroscope cabin (2) is adjusted, so that the propeller body (1) changes its moving direction and steering.
8. The pendulum (6) according to claim 1, characterized in that: The pendulum (6) is equipped with a magnet (10), which facilitates controlling the swing amplitude of the pendulum (6) by utilizing a magnetic field through an electromagnet module (9).