Annular rotor tilt engine
By designing a ring rotor tilting engine and changing the angle between the base and the rotation plane of the ring rotor, and by utilizing the stability difference of the gyroscope, the main motor generates thrust twice per revolution, thus solving the propulsion problem after the rocket engine runs out of fuel and realizing continuous propulsion and spacecraft control driven by electricity.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- 张敬
- Filing Date
- 2026-05-24
- Publication Date
- 2026-06-19
AI Technical Summary
Rocket engines cannot continue to generate thrust after their fuel is depleted in space, and current technology cannot work effectively in a vacuum environment under electric power.
Design a ring rotor tilting engine that creates a difference in the stability of the gyroscope by changing the angle between the base and the rotation plane of the ring rotor, and generates two thrusts per revolution of the main motor.
It enables continuous thrust generation in a vacuum environment under electric drive, solves the propulsion problem after rocket engine fuel is exhausted, and can adjust the thrust direction to control the flight of spacecraft.
Smart Images
Figure CN122232891A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aerospace engine technology, and in particular to a ring rotor tilting engine. Background Technology
[0002] Rocket engines consume fuel, and the limited fuel of a rocket will eventually run out when it travels in space. Based on an unexpected discovery during testing, the gyroscope stability of the gyroscope rotor composed of the base (15) and the ring rotor (3) is adjustable. This invention is based on this unexpected discovery and is a pendulum swashplate engine that can generate thrust in the vacuum environment of space with only the consumption of electricity. As long as the satellite can provide power, it can continuously generate thrust. Summary of the Invention
[0003] The technical problem to be solved by the present invention is to provide a ring rotor tilting engine, which changes the angle between the rotation surfaces of the base (15) and the ring rotor (3) to make the stability of the gyroscope vary, so that the main motor (4) generates two thrusts every one revolution.
[0004] To achieve the above objectives, the present invention provides the following technical solution: A ring rotor tilting engine, characterized in that: the ring rotor tilting engine includes a thruster body (1) installed inside a satellite, the thruster body (1) contains multiple gyroscope compartments (2), a main motor (4) is installed at the rear of the gyroscope compartment (2), a conductive slip ring (13) 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 (5) is installed on the output shaft of the main motor (4), the connecting rod ( 5) is equipped with a rotor motor (9) at multiple ends. The output shaft of the rotor motor (9) is equipped with a base (15). A cross shaft (16) is mounted on the base (15). The other two ends of the cross shaft (16) are mounted on the annular rotor (3). The outer frame (7) is mounted on the connecting rod (5). An inner frame (8) and an adjusting motor (6) are mounted on the outer frame (7). The output shaft of the adjusting motor (6) is connected to the rotating shaft of the inner frame (8). Two bearings are installed on the inner side of the inner frame (8). (10) One side of the inner frame (8) has a hole through which the rotating shaft of the rotor motor (9) passes. The other end of the two bearings (10) is connected and fixed to the annular rotor (3). The wire (14) is used to connect the satellite's computer, power supply and thruster body (1). After passing through the conductive slip ring (13), the wire (14) is fixed to the output shaft of the main motor (4) and the outer surface of the connecting rod (5), connecting the main motor (4), rotor motor (9) and adjusting motor (6) to provide power and transmit control signals. The main motor (4), rotor motor (9), and adjustment motor (6) are all equipped with angle sensors. The gyroscope cabin (2) is divided into a parallel stage (12) and an inclined stage (11). In the parallel stage (12), the angle between the rotation surfaces of the base (15) and the ring rotor (3) is zero. In the inclined stage (11), the rotation surface of the ring rotor (3) is tilted. At this time, the angle between the rotation surfaces of the base (15) and the ring rotor (3) becomes larger. The two stages, the parallel stage (12) and the inclined stage (11), form a cycle.
[0005] In order to adjust the angle between the rotation surfaces of the base (15) and the annular rotor (3), the adjustment motor (6) drives the annular rotor (3) to rotate by a certain angle through the inner frame (8) and the bearing (10).
[0006] In order to prevent the output shaft of the main motor (4) from generating a downward thrust when the gyroscope rotor composed of the base (15) and the ring rotor (3) moves from bottom to top in the parallel phase (12) via the connecting rod (5), the adjustment motor (6) drives the ring rotor (3) to rotate through the inner frame (8) and the bearing (10), so that the angle between the ring rotor (3) and the rotation plane of the base (15) is zero. At this time, the gyroscope stability of the gyroscope rotor composed of the base (15) and the ring rotor (3) does not play a role.
[0007] In order to generate an upward thrust when the output shaft of the main motor (4) drives the gyroscope rotor composed of the base (15) and the ring rotor (3) to move from top to bottom during the tilting phase (11) via the connecting rod (5), the adjustment motor (6) drives the ring rotor (3) to rotate in the direction of the advance torque through the inner frame (8) and the bearing (10), so that the ring rotor (3) and the rotation surface of the base (15) produce a large angle. At this time, the gyroscope stability of the gyroscope rotor composed of the base (15) and the ring rotor (3) comes into play.
[0008] In order to generate two upward thrusts for each rotation of the main motor (4) in the gyroscope cabin (2), the gyroscope rotor composed of the base (15) and the ring rotor (3) will generate an upward thrust when moving from top to bottom in the tilting phase (11), and will not generate a downward thrust when moving from bottom to top in the parallel phase (12).
[0009] The beneficial effects of adopting the above technical solution are: the present invention provides a different method and idea than rocket engine. By changing the angle between the rotation surfaces of the base (15) and the annular rotor (3), the stability of the gyroscope is made to have a difference in magnitude, so that the main motor (4) generates two thrusts every time it rotates. Attached Figure Description
[0010] The specific embodiments of the present invention will now be described in further detail with reference to the accompanying drawings.
[0011] Figure 1 This is a top view of the propulsion body of the present invention; Figure 2 This is a front view of the thruster body of the present invention; Figure 3 This is a top view of the gyroscope cabin of the present invention; Figure 4 This is a front view of the parallel stage of the present invention; Figure 5 This is a schematic diagram of the intersection of the rotating surfaces during the tilting stage of the present invention; Figure 6 This is a schematic diagram of the parallel rotation surface of the parallel stage of the present invention; Figure 7 This is a top view of the base and cross axis of the present invention; Figure 8 This is a structural diagram of the internal frame of the present invention; Among them, 1. Thruster body, 2. Gyroscope compartment, 3. Ring rotor, 4. Main motor, 5. Connecting rod, 6. Adjustment motor, 7. Outer frame, 8. Inner frame, 9. Rotor motor, 10. Bearing, 11. Inclined stage, 12. Parallel stage, 13. Conductive slip ring, 14. Wire, 15. Base, 16. Cross shaft. Detailed Implementation
[0012] The specific implementation method of the annular rotor tilting engine is described in detail below with reference to the accompanying drawings.
[0013] Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 , Figure 8 The following are specific embodiments and processes of the annular rotor tilting engine of the present invention: Figure 2 , Figure 5 and Figure 7 ,exist Figure 7 In this gyroscope rotor, the high-speed rotating base (15) and the ring rotor (3) form a gyroscope rotor. The gyroscope rotor composed of the base (15) and the ring rotor (3) has the stability and precession of a gyroscope. When an external torque changes the direction of the rotation axis of the base (15) and the ring rotor (3), a precession torque is generated. The precession torque acts on the ring rotor (3), causing the rotation surface of the ring rotor (3) to be as... Figure 5 The same tilt occurs in the same direction. The direction of the tilt of the rotating surface of the annular rotor (3) is consistent with the direction of the precession torque. The greater the external torque on the rotating shafts of the base (15) and the annular rotor (3), the greater the angle between the rotating surfaces of the base (15) and the annular rotor (3), and the greater the measured thrust. When the angle between the rotating surfaces of the base (15) and the annular rotor (3) is zero, the measured thrust is zero. The energy that pushes the annular rotor (3) to tilt comes from the torque output by the main motor (4). Figure 5 In the case where the rotation axis of the base (15) and the ring rotor (3) does not move along the precession torque, the precession torque acts on the ring rotor (3), causing the rotation surface of the ring rotor (3) to tilt. At this time, the stability of the gyroscope rotor composed of the base (15) and the ring rotor (3) is effective. However, the stability of the ordinary rigid body gyroscope rotor is ineffective when the rotation axis cannot move along the precession torque.
[0014] Figure 2 and Figure 3 , Figure 3 The center of gravity of the connecting rod (5) and other components mounted on it is exactly on the output shaft of the main motor (4). The distance from the center of gravity of the connecting rod (5) to the output shaft of the main motor (4) is zero. Figure 2The two main motors (4) rotating in opposite directions do not generate excitation force. However, because the gyroscope stability of the base (15) and the ring rotor (3) is effective in the tilting phase (11), a larger torque or external torque is required in the tilting phase (11) than in the parallel phase (12). This involves a less commonly used principle: "Under the premise of a fixed rotational speed, torque is proportional to excitation force." In the tilting phase (11), the torque output by the main motor (4) not only drives the connecting rod (5) to rotate but also drives the ring rotor (3) to tilt. Therefore, a larger torque is required than in the parallel phase (12). The larger torque generates excitation force. As long as the tilt of the rotation surfaces of the base (15) and the ring rotor (3) is always controlled to occur in the tilting phase (11), an upward excitation force or thrust can be continuously generated.
[0015] Figure 2 and Figure 6 ,exist Figure 6 In the middle, the adjusting motor (6) drives the ring rotor (3) to rotate through the inner frame (8) and bearing (10), so that the angle between the ring rotor (3) and the rotation plane of the base (15) is zero. At this time, the gyroscope stability of the gyroscope rotor composed of the base (15) and the ring rotor (3) does not play a role. Figure 2 In the middle, the output shaft of the main motor (4) drives the gyroscope rotor composed of the base (15) and the ring rotor (3) through the connecting rod (5) to move from bottom to top in the parallel phase (12) without generating a downward thrust.
[0016] Figure 2 and Figure 5 In Figure 5, the adjusting motor (6) drives the annular rotor (3) to rotate in the direction of the advance torque through the inner frame (8) and bearing (10), so that the annular rotor (3) and the rotation plane of the base (15) produce a large angle. At this time, the gyroscope stability of the gyroscope rotor composed of the base (15) and the annular rotor (3) comes into play. Figure 2 In the middle, the output shaft of the main motor (4) drives the gyroscope rotor composed of the base (15) and the ring rotor (3) through the connecting rod (5) to move from top to bottom during the tilting stage (11), which will generate an upward thrust.
[0017] The process and conclusion of this invention are as follows: the power supply and computer on the satellite are connected by wires (12) to provide power and transmit control signals to the main motor (4), rotor motor (9) and adjustment motor (6) inside the thruster body (1). The main motor (4) in the two adjacent gyroscope compartments (2) drives the connecting rod (5) to rotate in opposite directions, and the rotor motor (9) drives the ring rotor (3) and the base (15) to rotate at high speed. During the tilting phase (11), the adjustment motor (6) drives the ring rotor (3) to rotate in the direction of the precession torque through the inner frame (8) and the bearing (10), so that the ring rotor (3) and the rotation surface of the base (15) produce a large angle. At this time, the gyroscope stability of the gyroscope rotor composed of the base (15) and the ring rotor (3) takes effect. The output shaft of the main motor (4) drives the gyroscope rotor composed of the base (15) and the ring rotor (3) to move from top to bottom during the tilting phase (11), which will generate an upward thrust. In the parallel phase (12), the adjusting motor (6) drives the ring rotor (3) to rotate through the inner frame (8) and bearing (10), so that the angle between the ring rotor (3) and the rotation plane of the base (15) is zero. At this time, the gyroscope stability of the gyroscope rotor composed of the base (15) and the ring rotor (3) does not work. The output shaft of the main motor (4) drives the gyroscope rotor composed of the base (15) and the ring rotor (3) to move from bottom to top in the parallel phase (12) through the connecting rod (5) without generating a downward thrust. Figure 2 In the gyroscope compartment (2), the tilting phase (11) generates an upward thrust, while the parallel phase (12) does not generate a downward thrust. Therefore, the main motor (4) can generate two upward thrusts per revolution, thereby enabling the thruster body (1) to propel the satellite in space.
[0018] When it is necessary to adjust the flight direction and steering of the spacecraft, the direction of the thrust generated by the gyroscope compartment (2) can be adjusted by adjusting the position of the parallel phase (12) and the tilt phase (11), thereby adjusting the flight direction and steering of the propulsion body (1).
[0019] The above are merely preferred embodiments of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the inventive concept of the present invention, and these all fall within the protection scope of the present invention.
Claims
1. A ring rotor tilting engine, characterized in that: The annular rotor tilting engine includes a thruster body (1) installed inside the satellite. The thruster body (1) contains multiple gyroscope compartments (2). A main motor (4) is mounted at the rear of each gyroscope compartment (2). A conductive slip ring (13) is mounted 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 (5) is mounted on the output shaft of the main motor (4). Rotary rotors are mounted on multiple ends of the connecting rod (5). The rotor motor (9) has a base (15) at the end of its output shaft. A cross shaft (16) is mounted on the base (15). The other two ends of the cross shaft (16) are mounted on the annular rotor (3). The outer frame (7) is mounted on the connecting rod (5). An inner frame (8) and an adjusting motor (6) are mounted on the outer frame (7). The output shaft of the adjusting motor (6) is connected to the rotating shaft of the inner frame (8). Two bearings (10) are mounted on the inner side of the inner frame (8). One side of the frame (8) has a hole through which the rotating shaft of the rotor motor (9) passes. The other ends of the two bearings (10) are connected and fixed to the annular rotor (3). The wire (14) is used to connect the satellite's computer, power supply, and thruster body (1). After passing through the conductive slip ring (13), the wire (14) is fixed to the output shaft of the main motor (4) and the outer surface of the connecting rod (5), connecting the main motor (4), rotor motor (9), and adjusting motor (6) to provide power and transmit control signals. The machine (4), rotor motor (9), and adjustment motor (6) are all equipped with angle sensors. The gyroscope cabin (2) is divided into a parallel stage (12) and an inclined stage (11). In the parallel stage (12), the angle between the rotation surfaces of the base (15) and the ring rotor (3) is zero. In the inclined stage (11), the rotation surface of the ring rotor (3) is tilted. At this time, the angle between the rotation surfaces of the base (15) and the ring rotor (3) becomes larger. The two stages, the parallel stage (12) and the inclined stage (11), form a cycle.
2. The adjusting motor (6), inner frame (8), bearing (10), and annular rotor (3) according to claim 1, characterized in that: The adjusting motor (6) drives the annular rotor (3) to rotate at a certain angle through the inner frame (8) and bearing (10), thereby adjusting the angle between the rotation surfaces of the base (15) and the annular rotor (3).
3. The parallel stage (12) according to claims 1 and 2, characterized in that: The adjustment motor (6) drives the ring rotor (3) to rotate through the inner frame (8) and bearing (10), so that the angle between the ring rotor (3) and the rotation surface of the base (15) is zero. At this time, the gyroscope stability of the gyroscope rotor composed of the base (15) and the ring rotor (3) does not work. The output shaft of the main motor (4) drives the gyroscope rotor composed of the base (15) and the ring rotor (3) to move from bottom to top in the parallel stage (12) through the connecting rod (5) without generating a downward thrust.
4. The tilting stage (11) according to claims 1 and 2, characterized in that: The adjusting motor (6) drives the ring rotor (3) to rotate in the direction of the advance torque through the inner frame (8) and bearing (10), so that the ring rotor (3) and the rotating surface of the base (15) produce a large angle. At this time, the gyroscope stability of the gyroscope rotor composed of the base (15) and the ring rotor (3) takes effect. The output shaft of the main motor (4) drives the gyroscope rotor composed of the base (15) and the ring rotor (3) to move from top to bottom in the tilting stage (11) through the connecting rod (5), which will generate an upward thrust.
5. The gyroscope cabin (2) according to claims 3 and 4, characterized in that: The gyroscope rotor, composed of the base (15) and the ring rotor (3), generates an upward thrust when it moves from top to bottom during the tilting phase (11). The gyroscope rotor, composed of the base (15) and the ring rotor (3), does not generate a downward thrust when it moves from bottom to top during the parallel phase (12). The main motor (4) in the gyroscope cabin (2) generates two upward thrusts per revolution.