Annular rotor engine
Through the design of the ring rotor engine, the reaction force is used to synthesize thrust and gyroscope stability adjustment, the continuous propulsion problem after the fuel is exhausted by the rocket engine is solved, and continuous flight and direction adjustment in a vacuum environment is achieved.
Patent Information
- Application Number
- CN202510404666.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-01
- Publication Date
- 2025-07-08
- Estimated Expiration
- Not applicable · inactive patent
AI Technical Summary
Rocket engines cannot continue to navigate after the limited fuel is exhausted in space, and the prior art is difficult to provide a solution for continuous advancement in a vacuum environment.
Through the design of the ring rotor engine, two reaction forces with opposite directions and different sizes are generated by vertical and parallel stages to synthesize a new upward synergy force. Every time the connecting rod structure rotates, it generates thrust on the main motor output shaft. Combined with the stability adjustment of the gyroscope, the continuous flight of the thruster is achieved.
It realizes that the upward thrust is synthesized through reaction forces in a vacuum environment, and the thruster can continue to fly in the universe and can adjust the flight direction and steering.
Smart Images
Figure CN120270543A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of aerospace engines, and particularly to a ring rotor engine. Background Art
[0002] Rocket engines 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: there are differences in the gyroscopic stability and precession of a ring rotor compared to those of a common gyroscope. The present invention is a ring rotor engine that can travel in the vacuum environment of space and only requires electricity consumption based on these differences. Summary of the Invention
[0003] The technical problem to be solved by the present invention is to provide a ring rotor engine. By synthesizing two reaction forces with opposite directions and different magnitudes generated in the vertical stage (7) and the parallel stage (8), a new upward resultant force is obtained, and the direction of the resultant force is the direction of the thrust. Each time the connecting rod structure (3) rotates one week, an upward thrust is generated on the output shaft of the main motor (4), enabling the thruster body (1) to continuously push a spacecraft to fly in the universe.
[0004] To achieve the above object, the present invention provides the following technical solutions:
[0005] Ring rotor engine, characterized in that: the ring rotor engine includes a thruster body (1) that is stationary under vacuum weightlessness conditions. Inside the thruster body (1), there are multiple gyroscope compartments (2). At the rear of the gyroscope compartment (2), a main motor (4) is installed. On the output shaft of the main motor (4), a conductive slip ring (15) is installed. 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). On the output shaft of the main motor (4), a connecting rod structure (3) is installed. At multiple ends of the connecting rod structure (3), rotating drive motors (11) are installed. Outside the output shaft of the rotating drive motor (11), an internal conductive slip ring (12) is installed. On the output shaft of the rotating drive motor (11), a triangular base (6) is installed. Bearings are installed on the contact surface between the triangular base (6) and the connecting rod structure (3). On the triangular base (6), a rotor motor (13) is installed. On the output shaft of the rotor motor (13), a Y-shaped structural member (10) is installed. On the Y-shaped structural member (10), a cross-axis frame (9) is installed. The two symmetric ends of the cross-axis frame (9) are connected to a ring rotor (5). After passing through the conductive slip ring (15) and the internal conductive slip ring (12), the wire (14) is fixed to the outer surface of the output shaft of the main motor (4) and the connecting rod structure (3), connecting the main motor (4), the rotating drive motor (11), and the rotor motor (13) to supply power and transmit control signals for them. The gyroscope compartment (2) is divided into a vertical stage (7) and a parallel stage (8). The vertical stage (7) and the parallel stage (8) form a cycle.
[0006] In order to adjust the angle between the rotation plane of the ring rotor (5) and the rotation plane of the rod structure (3), the rotation axis of the rotating drive motor (11) has a 45-degree angle with the rotation plane of the connecting rod structure (3).
[0007] In order to generate the vertical stage (7) and the parallel stage (8), the rotation axis of the rotor motor (13) has a 45-degree angle with the rotation axis of the rotating drive motor (11).
[0008] In order to generate a relatively large upward reaction force on the output shaft of the main motor (4), the rotation plane of the rotor motor (13) in the vertical stage (7) has a relatively large angle with the rotation plane of the connecting rod structure (3), approaching or reaching 90 degrees. The generated forward torque separates the rotation plane of the ring rotor (5) from the rotation plane of the rotor motor (13), generating an inclined intersection. At this time, the stability of the gyroscope comes into play. When the connecting rod structure (3) rotates in the vertical stage (7), a relatively large force is required to overcome the stability of the gyroscope.
[0009] In order to generate a relatively small downward reaction force on the output shaft of the main motor (4), the angle between the rotating surface of the rotor motor (13) in the parallel stage (8) and the rotating surface of the connecting rod structure (3) is relatively small, approaching or reaching 0 degrees. At this time, the stability of the gyroscope is relatively small or even non-existent, and a relatively small force is required for the connecting rod structure (3) to rotate in the parallel stage (8) to overcome the stability of the gyroscope.
[0010] In order to enable the connecting rod structure (3) to generate an upward thrust on the output shaft of the main motor (4) every time it rotates one week, a relatively large force is required for the connecting rod structure (3) to rotate in the vertical stage (7) to overcome the stability of the gyroscope, so as to generate a relatively large upward reaction force on the output shaft of the main motor (4). A relatively small force is required for the connecting rod structure (3) to rotate in the parallel stage (8), so as to generate a relatively small downward reaction force on the output shaft of the main motor (4). 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.
[0011] In order to generate the vertical stage (7) and the parallel stage (8), the rotation drive motor (11) drives the rotor motor (13) to rotate one week through the triangular base (6), so that the angle between the rotating surface of the rotor motor (13) and the rotating surface of the connecting rod structure (3) can cycle once between 0 degrees and 90 degrees.
[0012] In order to enable the thruster body (1) to change the moving direction and steering, by adjusting the rotational speeds of the main motor (4) and the rotation drive motor (11), the positions where the vertical stage (7) and the parallel stage (8) appear can be adjusted, so as to adjust the direction of the thrust generated by the gyroscope cabin (2).
[0013] In order to enable the cross-axis frame (9) and the annular rotor (5) to still rotate stably, when the rotating surface of the annular rotor (5) is inclined and crossed with the rotating surface of the Y-shaped structural member (10) due to the precession torque, the centers of gravity of the annular rotor (5) and the cross-axis frame (9) are at the center point of the cross-axis frame (9).
[0014] In order to achieve shutdown and rapid startup, and to avoid collision between the annular rotor (5) and other components, the rotation drive motor (11) adjusts all the rotor motors (13) to the parallel stage (8) and makes the annular rotor (5) rotate at a low speed.
[0015] 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 synthesizing two reaction forces with opposite directions and different magnitudes generated in the vertical stage (7) and the parallel stage (8), a new upward resultant force is obtained, and the direction of the resultant force is the direction of the thrust. Each time the connecting rod structure (3) rotates one week, an upward thrust is generated on the output shaft of the main motor (4), enabling the thruster body (1) to push the spacecraft to fly continuously in the universe. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] The following further describes in detail the specific embodiments of the present invention with reference to the drawings.
[0017] Figure 1 is the top view of the thruster body of the present invention;
[0018] Figure 2 is the front view of the gyroscope cabin of the present invention;
[0019] Figure 3 is the top view of the gyroscope cabin of the present invention;
[0020] Figure 4 is the front view of the vertical stage of the connecting rod structure and the annular rotor of the present invention;
[0021] Figure 5 is the front view of the parallel stage of the connecting rod structure and the annular rotor of the present invention;
[0022] Figure 6 is the schematic diagram of the Y-shaped structural member of the present invention;
[0023] Figure 7 is the top view of the annular rotor of the present invention;
[0024] Wherein, 1. Thruster body, 2. Gyroscope cabin, 3. Connecting rod structure, 4. Main motor, 5. Annular rotor, 6. Triangular base, 7. Vertical stage, 8. Parallel stage, 9. Cross-axis frame, 10. Y-shaped structural member, 11. Rotation drive motor, 12. Internal conductive slip ring, 13. Rotor motor, 14. Wire, 15. Conductive slip ring. DETAILED DESCRIPTION OF THE INVENTION
[0025] The following details the specific embodiments of the annular rotor engine with reference to the drawings.
[0026] Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 The specific embodiments and processes of the annular rotor engine of the present invention are presented:
[0027] Figure 4 , Figure 6 and Figure 7 , the stability of the ordinary integral gyroscope rotor does not work during the Figure 4 vertical stage (7). A split rotor composed of a Y-shaped structural member (10), a cross-axis frame (9), and an annular rotor (5). When the connecting rod structure (3) drives the rotor motor (13) to rotate during the vertical stage (7), the precession torque acts on the annular rotor (5), causing the rotation plane of the annular rotor (5) to separate from the rotation plane of the rotor motor (13), resulting in an inclined intersection. At this time, the stability of the gyroscope comes into play. When the rotation plane of the annular rotor (5) is inclined, the centers of gravity of the cross-axis frame (9) and the annular rotor (5) are always at the center point of the cross-axis frame (9), thus enabling the annular rotor (5) to maintain stable rotation.
[0028] Figure 4 and Figure 5 , Figure 4 For the vertical stage (7), the maximum angle between the rotation plane of the rotor motor (13) and the rotation plane of the connecting rod structure (3) is 90 degrees during the vertical stage (7). Figure 5 For the parallel stage (8), the minimum angle between the rotation plane of the rotor motor (13) and the rotation plane of the connecting rod structure (3) is 0 degrees during the parallel stage (8). Every time the rotation drive motor (11) rotates one week, it can drive the rotor motor (13) to complete a cyclic conversion between the vertical stage (7) and the parallel stage (8) through the triangular base (6).
[0029] Figure 5 , Figure 3 and Figure 4, during the vertical stage (7), the included angle between the rotation plane of the rotor motor (13) and the rotation plane of the connecting rod structure (3) is relatively large or reaches 90 degrees. At this time, the connecting rod structure (3) drives the rotor motor (13) and the annular rotor (5) to rotate together. The precession torque will separate the rotation plane of the annular rotor (5) from the rotation plane of the rotor motor (13), resulting in an inclined intersection. The stability of the gyroscope comes into play. When the connecting rod structure (3) rotates during the vertical stage (7), a relatively large force is required to overcome the stability of the gyroscope, thereby generating a relatively large upward reaction force on the output shaft of the main motor (4). During the parallel stage (8), the included angle between the rotation plane of the rotor motor (13) and the rotation plane of the connecting rod structure (3) is relatively small or reaches 0 degrees. At this time, the gyroscopic stability generated is relatively small or even non-existent. When the connecting rod structure (3) rotates during the parallel stage (8), a relatively small force is required, thereby generating a relatively small downward reaction force on the output shaft of the main motor (4). Two reaction forces with opposite directions and different magnitudes cancel each other out to generate a new upward resultant force. The direction of the resultant force is the direction of the thrust. Every time the connecting rod structure (3) rotates one week, an upward thrust can be generated on the output shaft of the main motor (4). When it is necessary to stop the machine without thrust, the rotation drive motor (11) adjusts all the rotor motors (13) to the parallel stage (8), and no thrust will be generated. At this time, keeping the rotor motors (13) rotating at a low speed can prevent the annular rotor (5) from colliding with other components. When it is necessary to start quickly, the rotation drive motor (11) adjusts some of the rotor motors (13) to the vertical stage (7), and thrust can be generated.
[0030] The process and conclusion of the present invention are powered by a wire (14). The main motor (4) of the gyroscope cabin (2) drives the connecting rod structure (3) to rotate. The rotation driving motor (11) drives the rotor motor (13) to rotate through the triangular base (6), thereby generating a vertical stage (7) and a parallel stage (8). The rotor motor (13) drives the annular rotor (5) to rotate through the Y-shaped structural member (10) and the cross-axis frame (9). In the vertical stage (7), the included angle between the rotation plane of the rotor motor (13) and the rotation plane of the connecting rod structure (3) is relatively large or reaches 90 degrees. The precession torque will separate the rotation plane of the annular rotor (5) from the rotation plane of the rotor motor (13), generating an inclined intersection. At this time, the stability of the gyroscope comes into play. When the connecting rod structure (3) rotates in the vertical stage (7), a relatively large force is required to overcome the stability of the gyroscope, thereby generating a relatively large upward reaction force on the output shaft of the main motor (4). In the parallel stage (8), the included angle between the rotation plane of the rotor motor (13) and the rotation plane of the connecting rod structure (3) is relatively large or reaches 0 degrees, and the generated gyroscope stability is relatively small or even non-existent. When the connecting rod structure (3) rotates in the parallel stage (8), a relatively small force is required, thereby generating a relatively small downward reaction force on the output shaft of the main motor (4). Two reaction forces with opposite directions and different magnitudes cancel each other out to generate a new upward resultant force. The direction of the resultant force is the direction of the thrust. Each time the connecting rod structure (3) rotates one week, an upward thrust can be generated on the output shaft of the main motor (4), thereby enabling the thruster body (1) to push the spacecraft to continuously fly in the universe.
[0031] When it is necessary to adjust the flight direction and the turning of the spacecraft, by adjusting the rotational speeds of the main motor (4) and the rotation driving motor (11), the positions where the vertical stage (7) and the parallel stage (8) appear can be adjusted, thereby adjusting the direction of the thrust generated by the gyroscope cabin (2), and thus adjusting the flight direction and the turning of the thruster body (1).
[0032] 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. Ring rotor engine, characterized in that: The described annular rotor engine includes a thruster body (1) that is stationary in a vacuum weightless state. Inside the thruster body (1), there are multiple gyroscope compartments (2). At the rear of the gyroscope compartment (2), a main motor (4) is installed. On the output shaft of the main motor (4), a conductive slip ring (15) is installed. 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). On the output shaft of the main motor (4), a connecting rod structure (3) is installed. On multiple ends of the connecting rod structure (3), rotating drive motors (11) are installed. Outside the output shaft of the rotating drive motor (11), an internal conductive slip ring (12) is installed. On the output shaft of the rotating drive motor (11), a triangular base (6) is installed. On the contact surface between the triangular base (6) and the connecting rod structure (3), a bearing is installed. On the triangular base (6), a rotor motor (13) is installed. On the output shaft of the rotor motor (13), a Y-shaped structural member (10) is installed. On the Y-shaped structural member (10), a cross-axis frame (9) is installed. The two symmetric ends of the cross-axis frame (9) are connected to an annular rotor (5). After passing through the conductive slip ring (15) and the internal conductive slip ring (12), the wire (14) is fixed to the outer surface of the output shaft of the main motor (4) and the connecting rod structure (3), connecting the main motor (4), the rotating drive motor (11), and the rotor motor (13) to provide power supply and transmit control signals for them. The gyroscope compartment (2) is divided into a vertical stage (7) and a parallel stage (8). The vertical stage (7) and the parallel stage (8) form a cycle.
2. The rotational drive motor (11) and the link structure (3) according to claim 1, characterized in that: The rotating shaft of the rotating drive motor (11) has a 45-degree angle with the rotating surface of the connecting rod structure (3), thereby adjusting the angle between the rotating surface of the annular rotor (5) and the rotating surface of the rod structure (3).
3. The rotor motor (13) and the rotary drive motor (11) according to claim 1, characterized in that: The rotating shaft of the rotor motor (13) has a 45-degree angle with the rotating shaft of the rotating drive motor (11), thereby generating the vertical stage (7) and the parallel stage (8).
4. The vertical stage (7) according to claim 1, characterized in that: In the vertical stage (7), the angle between the rotating surface of the rotor motor (13) and the rotating surface of the connecting rod structure (3) is larger, approaching or reaching 90 degrees. The generated forward driving torque causes the rotating surface of the annular rotor (5) to separate from the rotating surface of the rotor motor (13), generating an inclined intersection. At this time, the stability of the gyroscope comes into play. When the connecting rod structure (3) rotates in the vertical stage (7), a larger force is required to overcome the stability of the gyroscope, thereby generating a larger upward reaction force on the output shaft of the main motor (4).
5. The parallel stage (8) according to claim 1, characterized in that: In the parallel stage (8), the angle between the rotating surface of the rotor motor (13) and the rotating surface of the connecting rod structure (3) is smaller, approaching or reaching 0 degrees. At this time, the stability of the gyroscope is smaller or even non-existent. When the connecting rod structure (3) rotates in the parallel stage (8), a smaller force is required to overcome the stability of the gyroscope, thereby generating a smaller downward reaction force on the output shaft of the main motor (4).
6. The vertical stage (7) and the parallel stage (8) according to claim 4 and claim 5, characterized in that: When the connecting rod structure (3) rotates during the vertical stage (7), a relatively large force is required to overcome the stability of the gyroscope, thereby generating a relatively large upward reaction force on the output shaft of the main motor (4). When the connecting rod structure (3) rotates during the parallel stage (8), a relatively small force is required, thereby generating a relatively small downward reaction force on the output shaft of the main motor (4). 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. Each time the connecting rod structure (3) rotates one week, an upward thrust is generated on the output shaft of the main motor (4).
7. The rotary drive motor (11) according to claim 1, characterized in that: When the rotary drive motor (11) drives the rotor motor (13) to rotate one week through the triangular base (6), the included angle between the rotation plane of the rotor motor (13) and the rotation plane of the connecting rod structure (3) can cycle once between 0 degrees and 90 degrees, thereby generating the vertical stage (7) and the parallel stage (8).
8. The main motor (4) and the rotary drive motor (11) according to claim 7, characterized in that: By adjusting the rotational speeds of the main motor (4) and the rotary drive motor (11), the positions where the vertical stage (7) and the parallel stage (8) appear can be adjusted, thereby adjusting the direction of the thrust generated by the gyroscope cabin (2), and enabling the thruster body (1) to change the moving direction and steering.
9. The annular rotor (5), Y-shaped structural member (10) and cross-axis frame (9) according to claim 1, characterized in that: When the rotation plane of the annular rotor (5) is inclined and crossed with the rotation plane of the Y-shaped structural member (10) due to the precession torque, the centers of gravity of the annular rotor (5) and the cross-axis frame (9) are at the center point of the cross-axis frame (9), and the cross-axis frame (9) and the annular rotor (5) still maintain stable rotation.
10. The rotary drive motor (11) and the parallel stage (8) according to claim 7, characterized in that: The rotary drive motor (11) adjusts all the rotor motors (13) to the parallel stage (8) and makes the annular rotor (5) run at a low speed, thereby achieving shutdown and rapid startup, and avoiding collision between the annular rotor (5) and other components.