Split type rotor gyroscope stability delaying propeller
By designing a split rotor gyroscope stability hysteresis thruster, the reaction force synthesis in the axial and parallel stages is used to solve the problem of fuel-free propulsion of rocket engines in space, and continuous flight and direction adjustment in a vacuum environment are achieved.
Patent Information
- Application Number
- CN202510246718.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-04
- Publication Date
- 2025-04-25
- Estimated Expiration
- Not applicable · inactive patent
AI Technical Summary
When rocket engines navigate in space, they are difficult to continue to advance due to limited fuel. The stability and precession of the split rotor gyroscope are different from that of ordinary gyroscopes, making it difficult to achieve fuel-free propulsion in a vacuum environment.
A split rotor gyroscope stability hysteresis thrust is designed. Two reaction forces with opposite directions and different sizes are generated through the axial stage and the parallel stage, and a new upward synergistic force is obtained to achieve propulsion. The thruster includes a plurality of gyroscope compartments, main motors, connecting rods and rotor motors. Through the rotation of the connecting rods and the drive of the rotor motors, a counteracting reaction force is generated to form a thrust force.
Fuel-free propulsion is achieved in a vacuum environment, which enables the thruster body to push the spacecraft to continuously fly in the universe, and can adjust the direction of the thrust to change the flight direction and steering of the spacecraft.
Smart Images
Figure CN119872933A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of aerospace engines, in particular to a split rotor gyroscope stability hysteresis thruster. Background Art
[0002] Rocket engines consume fuel, and the limited fuel of rockets sailing in space will eventually run out. According to an unexpected discovery during the test experiment: the stability and precession of the split rotor gyroscope are different from those of ordinary gyroscopes. The present invention is based on this difference to produce a split rotor gyroscope stability hysteresis thruster that can sail in the vacuum environment of space without fuel. Summary of the invention
[0003] The technical problem to be solved by the present invention is to provide a split rotor gyro stability hysteresis thruster, wherein two reaction forces of opposite directions and different magnitudes generated by an axial stage (16) and a parallel stage (17) are synthesized to obtain a new upward resultant force, the direction of the resultant force being the direction of the thrust. Each time the connecting rod (5) rotates one circle, an upward thrust is generated on the output shaft of the main motor (3), so that the thruster body (1) can push the spacecraft to continue flying in the universe.
[0004] To achieve the above object, the present invention provides the following technical solutions:
[0005] The split-rotor gyroscope stability hysteresis thruster is characterized in that: the split-rotor gyroscope stability hysteresis thruster comprises a thruster body (1) which is stationary in a vacuum weightlessness state, a plurality of gyroscope cabins (2) are arranged inside the thruster body (1), a main motor (3) is arranged at the rear of the gyroscope cabin (2), a conductive slip ring (13) is arranged on the output shaft of the main motor (3), the output shaft of the main motor (3) passes through the gyroscope cabin (2) and is fixed to the inner wall of the gyroscope cabin (2), a base (4) is arranged on the output shaft of the main motor (3), a plurality of connecting rods (5) are arranged on the base (4), a rotation drive motor (6) and an inner frame (7) are arranged on the connecting rod (5), the rotation drive motor (6) is connected to the inner frame (7), one end of the inner frame (7) is connected to the inner frame (7), and a conductive slip ring (13) is arranged on the output shaft of the main motor (3). An inner frame conductive slip ring (11) is installed, a rotor motor (10) is installed in the middle of the inner frame (7), a rotor base (8) is installed on the output shaft of the rotor motor (10), the rotor base (8) has a plurality of trapezoidal grooves (14), the pendulum (9) is fixedly installed in the trapezoidal groove (14) through an axle pin (15), the wire (12) passes through the conductive slip ring (13) and the inner frame conductive slip ring (11), and is fixed to the output shaft of the main motor (3) and the outer surface of the connecting rod (5), connecting the main motor (3), the rotation drive motor (6) and the rotor motor (10) to provide power and transmit control signals, and the gyroscope cabin (2) is divided into an axial stage (16) and a parallel stage (17), and the axial stage (16) and the parallel stage (17) form a cycle.
[0006] In order to enable the pendulum (9) of the split gyroscope rotor to swing back and forth, a plurality of trapezoidal grooves (14) on the rotor base (8), the shaft pin (15) and the pendulum (9) form a movable split gyroscope rotor.
[0007] In order to make the connecting rod (5) rotate in a two-dimensional plane while the stability of the gyroscope is still effective, the rotor motor (10) rotates along with the connecting rod (5), and the generated precession torque acts on the pendulum (9), so that the rotating surface of the pendulum (9) is separated from the rotating surface of the rotor base (8), thereby generating an angle.
[0008] In order to generate a larger upward reaction force on the output shaft of the main motor (3), the connecting rod (5) in the axial stage (16) drives the rotor motor (10) and the rotor base (8) to rotate together. When the angle between the rotating surface of the rotor base (8) and the rotating surface of the connecting rod (5) is large, the precession torque generated causes the rotating surface of the pendulum (9) to separate from the rotating surface of the rotor base (8), generating an angle. At this time, the stability of the gyroscope comes into play. When the connecting rod (5) rotates in the axial stage (16), a larger force is required to overcome the stability of the gyroscope.
[0009] In order to generate a smaller downward reaction force on the output shaft of the main motor (3), the connecting rod (5) in the parallel stage (17) drives the rotor motor (10) and the rotor base (8) to rotate together. When the angle between the rotating surface of the rotor base (8) and the rotating surface of the connecting rod (5) is small or even parallel, the precession torque generated is small or even non-existent. At this time, the stability of the gyroscope is small or even non-existent, and the connecting rod (5) needs a smaller force when rotating in the parallel stage (17).
[0010] In order to generate an upward thrust on the output shaft of the main motor (3) every time the connecting rod (5) rotates one circle, a larger force is required when the connecting rod (5) rotates in the axial stage (16) to overcome the stability of the gyroscope, thereby generating a larger upward reaction force on the output shaft of the main motor (3). A smaller force is required when the connecting rod (5) rotates in the parallel stage (17), thereby generating a smaller downward reaction force on the output shaft of the main motor (3). The two reaction forces of 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 axial stage (16) and the parallel stage (17), the rotary drive motor (6) drives the rotor motor (10) and the rotor base (8) to rotate 180 degrees through the inner frame (7) every time the main motor (3) rotates 360 degrees.
[0012] In order to change the moving direction and turning direction of the thruster body (1), by adjusting the rotation speed of the main motor (3) and the rotary drive motor (6), the positions of the axial stage (16) and the parallel stage (17) can be adjusted, thereby adjusting the direction in which the thrust generated by the gyro cabin (2) is adjusted.
[0013] In order to prevent the pendulum (9) from colliding and being damaged with the rotor base (8) due to excessive swing amplitude, a rubber block is installed on the inner wall of the trapezoidal groove (14).
[0014] In order to facilitate the installation of more pendulums (9) on the rotor base (8) and increase the moment of inertia, the pendulum (9) is a metal hammer-shaped object with a large upper side and a small lower side.
[0015] The beneficial effect of adopting the above technical solution is that the present invention provides another method and idea different from that of a rocket engine, wherein a new upward resultant force is obtained by synthesizing two reaction forces of opposite directions and different magnitudes generated by the axial stage (16) and the parallel stage (17), and the direction of the resultant force is the direction of the thrust. Each time the connecting rod (5) rotates one circle, an upward thrust is generated on the output shaft of the main motor (3), so that the thruster body (1) can push the spacecraft to continue flying in the universe. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] The specific implementation modes of the present invention are further described in detail below in conjunction with the accompanying drawings.
[0017] Figure 1 is a top view of the propeller body of the present invention;
[0018] Figure 2 is a top view of the gyroscope cabin of the present invention;
[0019] Figure 3 is a front view of the gyroscope cabin of the present invention;
[0020] Figure 4 is a schematic diagram of the stability hysteresis of the axial stage gyroscope of the present invention;
[0021] Figure 5 is a side view of the rotor base of the present invention;
[0022] Figure 6 is a front view of the rotor base of the present invention;
[0023] Among them, 1. thruster body, 2. gyroscope cabin, 3. main motor, 4. base, 5. connecting rod, 6. rotation drive motor, 7. inner frame, 8. rotor base, 9. pendulum, 10. rotor motor, 11. inner frame conductive slip ring, 12. wire, 13. conductive slip ring, 14. trapezoidal groove, 15. shaft pin, 16. axial stage, 17. parallel stage. DETAILED DESCRIPTION
[0024] The specific implementation of the split rotor gyroscope stability hysteresis thruster is described in detail below with reference to the accompanying drawings.
[0025] Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 The specific implementation method and process of the split rotor gyroscope stability hysteresis thruster of the present invention are presented:
[0026] Figure 2 , Figure 3 and Figure 4 In the axial stage (16), the connecting rod (5) drives the rotor motor (10) and the rotor base (8) to rotate together ( Figure 4 The precession moment will cause the rotating plane of the pendulum (9) to separate from the rotating plane of the rotor base (8) ( Figure 4The two dotted lines of the rotor base (8) and the connecting rod (5) form an angle. At this time, the stability of the gyroscope comes into play. When the connecting rod (5) rotates in the axial stage (16), a large force is required to overcome the stability of the gyroscope, thereby generating a large upward reaction force on the output shaft of the main motor (3). In the parallel stage (17), the angle between the rotating surface of the rotor base (8) and the rotating surface of the connecting rod (5) is small or even parallel ( Figure 2 The lower half of the connecting rod (5) generates less or even no gyroscopic stability, and the connecting rod (5) needs less force to rotate in the parallel stage (17), thereby generating a smaller downward reaction force on the output shaft of the main motor (3). The two reaction forces of opposite directions and different magnitudes cancel each other out to generate a new upward resultant force, and the direction of the resultant force is the direction of the thrust. The connecting rod (5) can generate an upward thrust on the output shaft of the main motor (3) every time it rotates one circle.
[0027] Figure 4 and Figure 5 In the axial stage (16), the pendulum (9) swings back and forth in the trapezoidal groove (14) every time the rotor base (8) rotates one circle. The rubber block on the inner wall of the trapezoidal groove (14) can prevent the pendulum (9) from colliding with the rotor base (8) and being damaged due to excessive swing amplitude.
[0028] The process and conclusion of the present invention are as follows: the main motor (3) of the gyroscope cabin (2) drives the connecting rod (5) to rotate through the base (4) by supplying power through the wire (12); the rotary drive motor (6) drives the rotor motor (10) to rotate through the inner frame (7); the rotor motor (10) drives the rotor base (8) and the pendulum (9) to rotate; for every 360-degree rotation of the main motor (3), the rotary drive motor (6) drives the rotor motor (10) and the rotor base (8) to rotate 180 degrees through the inner frame (7); thus, an axial stage (16) and a parallel stage (17) can be generated. In the axial stage (16), the precession torque causes the rotational plane of the pendulum (9) to separate from the rotational plane of the rotor base (8) ( Figure 4 The two dotted lines of the rotor base (8) and the connecting rod (5) form an angle. At this time, the stability of the gyroscope comes into play. When the connecting rod (5) rotates in the axial stage (16), a large force is required to overcome the stability of the gyroscope, thereby generating a large upward reaction force on the output shaft of the main motor (3). In the parallel stage (17), the angle between the rotating surface of the rotor base (8) and the rotating surface of the connecting rod (5) is small or even parallel ( Figure 2The lower half of the connecting rod (5) generates less or even no gyroscopic stability, and the connecting rod (5) needs less force to rotate in the parallel stage (17), thereby generating a smaller downward reaction force on the output shaft of the main motor (3). The two reaction forces of opposite directions and different magnitudes cancel each other out to generate a new upward resultant force, and the direction of the resultant force is the direction of the thrust. The connecting rod (5) can generate an upward thrust on the output shaft of the main motor (3) every time it rotates one circle, so that the thruster body (1) pushes the spacecraft to continue flying in the universe.
[0029] When the flight direction and steering of the spacecraft need to be adjusted, the positions of the axial stage (16) and the parallel stage (17) can be adjusted by adjusting the rotation speed of the main motor (3) and the rotary drive motor (6), thereby adjusting the direction in which the thrust generated by the gyro cabin (2) is adjusted, thereby adjusting the flight direction and steering of the thruster body (1).
[0030] The above are only preferred embodiments of the present invention. It should be pointed out that a person skilled in the art can make several 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. Split rotor gyro stability hysteresis thruster, characterized by: The split rotor gyro stability hysteresis thruster comprises a thruster body (1) which is stationary in a vacuum weightlessness state, a plurality of gyro cabins (2) are arranged inside the thruster body (1), a main motor (3) is arranged at the rear of the gyro cabin (2), a conductive slip ring (13) is arranged on the output shaft of the main motor (3), the output shaft of the main motor (3) passes through the gyro cabin (2) and is fixed to the inner wall of the gyro cabin (2), a base (4) is arranged on the output shaft of the main motor (3), a plurality of connecting rods (5) are arranged on the base (4), a rotation drive motor (6) and an inner frame (7) are arranged on the connecting rods (5), the rotation drive motor (6) is connected to the inner frame (7), and an inner frame conductive slip ring (11) is arranged at one end of the inner frame (7). ), a rotor motor (10) is installed in the middle of the inner frame (7), a rotor base (8) is installed on the output shaft of the rotor motor (10), the rotor base (8) has a plurality of trapezoidal grooves (14), the pendulum (9) is fixedly installed in the trapezoidal groove (14) through an axle pin (15), the wire (12) passes through a conductive slip ring (13) and an inner frame conductive slip ring (11), and is fixed to the output shaft of the main motor (3) and the outer surface of the connecting rod (5), connecting the main motor (3), the rotary drive motor (6) and the rotor motor (10) to provide power and transmit control signals, and the gyroscope cabin (2) is divided into an axial stage (16) and a parallel stage (17), and the axial stage (16) and the parallel stage (17) form a cycle.
2. The rotor base (8) and the pendulum (9) according to claim 1, characterized in that: The plurality of trapezoidal grooves (14), the shaft pin (15) and the pendulum (9) on the rotor base (8) form a movable split-type gyroscope rotor, so that the pendulum (9) of the split-type gyroscope rotor can swing back and forth.
3. The connecting rod (5), the rotor motor (10), the rotor base (8) and the pendulum (9) according to claim 1, characterized in that: When the rotor motor (10) rotates together with the connecting rod (5), the generated precession torque acts on the pendulum (9), causing the rotating surface of the pendulum (9) to separate from the rotating surface of the rotor base (8), thereby generating an angle, thereby causing the connecting rod (5) to rotate in a two-dimensional plane, and the stability of the gyroscope still works.
4. The axial stage (16) according to claim 1, characterized in that: The connecting rod (5) in the axial stage (16) drives the rotor motor (10) and the rotor base (8) to rotate together. When the angle between the rotating surface of the rotor base (8) and the rotating surface of the connecting rod (5) is large, the precession torque generated causes the rotating surface of the pendulum (9) to separate from the rotating surface of the rotor base (8), thereby generating an angle. At this time, the stability of the gyroscope comes into play. When the connecting rod (5) rotates in the axial stage (16), a large force is required to overcome the stability of the gyroscope, thereby generating a large upward reaction force on the output shaft of the main motor (3).
5. The parallel stage (17) according to claim 1, characterized in that: The connecting rod (5) in the parallel stage (17) drives the rotor motor (10) and the rotor base (8) to rotate together. When the angle between the rotating surface of the rotor base (8) and the rotating surface of the connecting rod (5) is small or even parallel, the precession torque generated is small or even non-existent. At this time, the stability of the gyroscope is small or even non-existent. When the connecting rod (5) rotates in the parallel stage (17), a small force is required, thereby generating a small downward reaction force on the output shaft of the main motor (3).
6. Axial stage (16) and parallel stage (17) according to claim 4 and claim 5, characterized in that: When the connecting rod (5) rotates in the axial stage (16), 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 (3). When the connecting rod (5) rotates in the parallel stage (17), a smaller force is required, thereby generating a smaller downward reaction force on the output shaft of the main motor (3). The two reaction forces of 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. Every time the connecting rod (5) rotates one circle, an upward thrust is generated on the output shaft of the main motor (3).
7. The main motor (3) and the rotary drive motor (6) according to claim 1, characterized in that: Every time the main motor (3) rotates 360 degrees, the rotary drive motor (6) drives the rotor motor (10) and the rotor base (8) to rotate 180 degrees through the inner frame (7), thereby generating an axial stage (16) and a parallel stage (17).
8. The main motor (3) and the rotary drive motor (6) according to claim 7, characterized in that: By adjusting the rotation speed of the main motor (3) and the rotary drive motor (6), the positions of the axial stage (16) and the parallel stage (17) can be adjusted, thereby adjusting the direction of thrust generated by the gyro cabin (2) and causing the thruster body (1) to change its moving direction and steering direction.
9. The trapezoidal groove (14) according to claim 1, characterized in that: The inner wall of the trapezoidal groove (14) is provided with a rubber block to prevent the pendulum (9) from colliding and being damaged by the rotor base (8) due to excessive swing amplitude.
10. The pendulum (9) according to claim 1, characterized in that: The pendulum (9) is The metal hammer with a large upper part and a small lower part is convenient for installing more pendulums (9) on the rotor base (8). Increase the moment of inertia.
Citation Information
Cited By
Split-rotor gyroscope stability hysteresis thruster
WO2026183693A1