Modular rotor engine

Abstract

A modular rotor engine, relating to the technical field of rocket engines. The rigidity and precession of a gyroscope employing a split-type rotor module (4) differ from those of a conventional gyroscope. When the split-type rotor module (4) rotates together with a connecting rod (6) in a vertical stage (15), the rigidity and precession of the gyroscope come into play, producing a result opposite to that of the conventional gyroscope. The precession torque causes the plane of rotation of an oscillating weight (10) to separate from and intersect with the plane of rotation of the split-type rotor module (4), so that a relatively large force is required to overcome the rigidity of the gyroscope when the connecting rod (6) rotates in the vertical stage (15), thereby generating a relatively large upward reaction force.

Description

Modular Rotor Engine Technical Field

[0001] This invention relates to the field of aerospace engine technology, and in particular to a modular rotor engine. Background Technology

[0002] Rocket engines consume fuel, and the limited fuel available for space travel will eventually run out. An unexpected discovery during testing revealed that the stability and precession of a split-type rotor gyroscope differ from those of a conventional gyroscope. This invention is based on this difference, creating a modular rotor engine that can operate in the vacuum of space and requires only electricity. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide a modular rotor engine that combines two reaction forces of opposite directions and different magnitudes generated by the vertical stage (15) and the parallel stage (16) to obtain a new upward resultant force. The direction of the resultant force is the direction of the thrust. Every time the connecting rod (6) rotates once, it will generate an upward thrust on the output shaft of the main motor (3), so that the propulsion body (1) can propel the spacecraft to fly continuously in the universe.

[0004] To achieve the above objectives, the present invention provides the following technical solution:

[0005] A modular rotor engine, characterized in that: the modular rotor engine includes a thruster body (1) that is stationary in a vacuum weightless state; the thruster body (1) contains multiple gyroscope compartments (2); a main motor (3) is mounted at the rear of the gyroscope compartments (2); a conductive slip ring (13) is mounted on the output shaft of the main motor (3); the output shaft of the main motor (3) passes through the gyroscope compartments (2) and is fixed to the inner wall of the gyroscope compartments (2); a base (5) is mounted on the output shaft of the main motor (3); multiple connecting rods (6) are mounted on the base (5); a rotary drive motor (7) is mounted on the connecting rods (6); an internal conductive slip ring (14) is mounted on the output shaft of the rotary drive motor (7); a rotor motor (8) is mounted at the end of the output shaft of the rotary drive motor (7); a split rotor module (4) is mounted on the output shaft of the rotor motor (8); the split rotor module (4) consists of a rotor... The split rotor module (4) consists of an inner ring (12), a rotor support (11), an outer rotor ring (9), and multiple pendulums (10). The inner ring (12) of the rotor is fixedly connected to the output shaft of the rotor motor (8). Multiple pendulums (10) are installed on the rotor support (11). Each pendulum (10) has a limiting groove (19). A limiter (18) is installed on the rotor support (11) at the position corresponding to the limiting groove (19). The wire (17) passes through the conductive slip ring (13) and the inner conductive slip ring (14) and is fixed to the output shaft of the main motor (3) and the outer surface of the connecting rod (6). It connects the main motor (3), the rotary drive motor (7), and the rotor motor (8) to provide power and transmit control signals. The gyroscope cabin (2) is divided into a vertical stage (15) and a parallel stage (16). The two stages, the vertical stage (15) and the parallel stage (16), form a cycle.

[0006] In order for the pendulum (10) to swing back and forth around the rotor support (11), the split rotor module (4) generates a precessing torque when it rotates with the connecting rod (6) in the vertical phase (15).

[0007] In order to make the connecting rod (5) rotate in a two-dimensional plane while the stability of the gyroscope still works, the rotation surface of the pendulum (10) is separated from the rotation surface of the split rotor module (4), creating an angle.

[0008] In order to generate a large upward reaction force on the output shaft of the main motor (3), the rotation axis of the split rotor module (4) in the vertical stage (15) is at a small angle or parallel to the rotation plane of the connecting rod (6). The generated precession torque causes the rotation plane of the pendulum (10) to separate from the rotation plane of the split rotor module (4), creating an angle. At this time, the stability of the gyroscope comes into play. When the connecting rod (6) rotates in the vertical stage (15), a large force is needed to overcome the stability of the gyroscope.

[0009] In order to generate a small downward reaction force on the output shaft of the main motor (3), the rotation axis of the split rotor module (4) of the parallel stage (16) and the rotation plane of the connecting rod (6) are at a large angle or reach 90 degrees. At this time, the stability of the gyroscope is small or even non-existent, and the connecting rod (6) requires a small force when rotating in the parallel stage (16).

[0010] In order for the connecting rod (6) to generate an upward thrust on the output shaft of the main motor (3) with each rotation, the connecting rod (6) needs a large force to overcome the stability of the gyroscope when rotating in the vertical phase (15), thereby generating a large upward reaction force on the output shaft of the main motor (3). When the connecting rod (6) rotates in the parallel phase (16), it needs a small force, thereby generating a small downward reaction force on the output shaft of the main motor (3). The two reaction forces with opposite directions and different magnitudes combine 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 (15) and the parallel stage (16), the main motor (3) and the rotary drive motor (7) are characterized in that: for every 360 degrees the main motor (3) rotates, the rotary drive motor (7) drives the rotor motor (8) and the split rotor module (4) to rotate 180 degrees.

[0012] In order to change the direction of movement and steering of the thruster body (1), the position of the vertical phase (15) and the horizontal phase (16) can be adjusted by adjusting the speed of the main motor (3) and the rotary drive motor (7), thereby adjusting the direction of the thrust generated by the gyroscope cabin (2).

[0013] To prevent damage from collision with the pendulum (10), the limiter (18) is covered with rubber.

[0014] The beneficial effects of adopting the above technical solution are: the present invention provides a different method and idea than rocket engine. By combining two reaction forces with opposite directions and different magnitudes generated by the vertical stage (15) and the parallel stage (16), a new upward resultant force is obtained. The direction of the resultant force is the direction of the thrust. Every time the connecting rod (6) rotates once, it will generate an upward thrust on the output shaft of the main motor (3), which can make the propulsion body (1) propel the spacecraft to fly continuously in the universe. Attached Figure Description

[0015] The specific embodiments of the present invention will now be described in further detail with reference to the accompanying drawings.

[0016] Figure 1 is a top view of the propulsion body of the present invention;

[0017] Figure 2 is a top view of the gyroscope cabin of the present invention;

[0018] Figure 3 is a front view of the gyroscope cabin of the present invention;

[0019] Figure 4 is a top view of the pendulum and limiter of the present invention;

[0020] Figure 5 is a side view of the pendulum and limiter of the present invention;

[0021] Figure 6 is a schematic diagram showing the tilt of the pendulum rotation surface of the present invention;

[0022] Figure 7 is a schematic diagram of three states of the rotor of the ordinary gyroscope of the present invention;

[0023] The components are: 1. Thruster body, 2. Gyroscope compartment, 3. Main motor, 4. Split rotor module, 5. Base, 6. Connecting rod, 7. Rotary drive motor, 8. Rotor motor, 9. Rotor outer ring, 10. Pendulum, 11. Rotor support, 12. Rotor inner ring, 13. Conductive slip ring, 14. Internal conductive slip ring, 15. Vertical stage, 16. Parallel stage, 17. Wire, 18. Limiter, and 19. Limiting groove. Detailed Implementation

[0024] The specific implementation method of the modular rotor engine is described in detail below with reference to the accompanying drawings.

[0025] Figures 1, 2, 3, 4, 5, 6, and 7 illustrate the specific implementation method and process of the modular rotor engine of the present invention:

[0026] Figure 7 shows a standard gyroscope rotor where only the stability of gyroscope A is effective, resisting external forces and preventing it from falling. Gyroscopes B and C will fall due to external forces, rendering their stability ineffective. However, testing revealed that replacing the standard gyroscope rotor with a split rotor module (4) resulted in the stability of both gyroscopes A and C being effective. It was observed that the precession torque caused the rotational plane of the pendulum (10) to separate from the rotational plane of the split rotor module (4) (the tilted dashed line in Figure 6), creating an angle. In this case, the stability of the gyroscope was effective.

[0027] In Figures 2, 3, and 4, during the vertical phase (15), the connecting rod (6) drives the rotor motor (8) and the split rotor module (4) to rotate together. The precession torque causes the rotation surface of the pendulum (10) to separate from the rotation surface of the split rotor module (4) (the inclined dashed line in Figure 6), creating an angle. At this time, the stability of the gyroscope comes into play. When the connecting rod (6) rotates during the vertical phase (15), it needs a large force to overcome the stability of the gyroscope, thus generating a large upward reaction force on the output shaft of the main motor (3). During the parallel phase (16), the angle between the rotation axis of the split rotor module (4) and the rotation surface of the connecting rod (6) is large or reaches 90 degrees (the lower half of Figure 2). The resulting gyroscope stability is small or even non-existent. When the connecting rod (6) rotates during the parallel phase (16), it needs a small force, thus generating a small downward reaction force on the output shaft of the main motor (3). Two opposing forces of 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 rotation of the connecting rod (6) generates an upward thrust on the output shaft of the main motor (3).

[0028] Figures 4 and 5 show that during the vertical phase (15), the split rotor module (4) rotates once, and the pendulum (10) swings back and forth around the rotor support (11). The limiting groove (19) and the limiter (18) can prevent the pendulum (10) from being damaged by collision with other components due to excessive swing amplitude.

[0029] The process and conclusion of this invention are as follows: Powered by wire (17), the main motor (3) of the gyroscope cabin (2) drives the connecting rod (6) to rotate via the base (5), the rotation drive motor (7) drives the rotor motor (8) to rotate, and the rotor motor (8) drives the split rotor module (4) to rotate. For every 360 degrees the main motor (3) rotates, the rotation drive motor (7) drives the rotor motor (8) and the split rotor module (4) to rotate 180 degrees, thus generating the vertical stage (15) and the parallel stage (16). In the vertical stage (15), the precession torque causes the rotation surface of the pendulum (10) to separate from the rotation surface of the split rotor module (4) (the inclined dashed line in Figure 6), creating an angle. At this time, the stability of the gyroscope comes into play. When the connecting rod (6) rotates in the vertical stage (15), it needs a large force to overcome the stability of the gyroscope, thereby generating a large upward reaction force on the output shaft of the main motor (3). During the parallel phase (16), the angle between the rotation axis of the split rotor module (4) and the rotation plane of the connecting rod (5) is large or reaches 90 degrees (lower half of Figure 2), resulting in low or even no gyroscope stability. When the connecting rod (6) rotates during the parallel phase (16), it requires a small force, thus generating a small downward reaction force on the output shaft of the main motor (3). The 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 rotation of the connecting rod (6) generates an upward thrust on the output shaft of the main motor (3), thereby enabling the thruster body (1) to propel the spacecraft to fly continuously in space.

[0030] When it is necessary to adjust the flight direction and steering of the spacecraft, the position of the vertical phase (15) and the horizontal phase (16) can be adjusted by adjusting the speed of the main motor (3) and the rotary drive motor (7), thereby adjusting the direction of the thrust generated by the gyroscope compartment (2), and thus adjusting the flight direction and steering of the propulsion body (1).

[0031] 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 modular rotor engine, characterized in that: The modular rotor engine includes a thruster body (1) that is stationary in a vacuum weightless state. The thruster body (1) contains multiple gyroscope compartments (2). A main motor (3) 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 (3). The output shaft of the main motor (3) passes through the gyroscope compartment (2) and is fixed to the inner wall of the gyroscope compartment (2). A base (5) is mounted on the output shaft of the main motor (3). Multiple connecting rods (6) are mounted on the base (5). A rotary drive motor (7) is mounted on each connecting rod (6). An internal conductive slip ring (14) is mounted on the output shaft of the rotary drive motor (7). A rotor motor (8) is mounted at the end of the output shaft of the rotary drive motor (7). A split rotor module (4) is mounted on the output shaft of the rotor motor (8). The split rotor module (4) consists of an inner rotor ring (12). The rotor support (11), rotor outer ring (9) and multiple pendulums (10) are composed of a rotor bracket (11), a rotor outer ring (9) and multiple pendulums (10). The inner ring (12) of the split rotor module (4) is fixedly connected to the output shaft of the rotor motor (8). Multiple pendulums (10) are installed on the rotor bracket (11). Each pendulum (10) has a limiting groove (19). A limiter (18) is installed on the rotor bracket (11) at the position corresponding to the limiting groove (19). The wire (17) passes through the conductive slip ring (13) and the inner conductive slip ring (14) and is fixed to the output shaft of the main motor (3) and the outer surface of the connecting rod (6). It connects the main motor (3), the rotary drive motor (7) and the rotor motor (8) to provide power and transmit control signals. The gyroscope cabin (2) is divided into a vertical stage (15) and a parallel stage (16). The two stages, the vertical stage (15) and the parallel stage (16), form a cycle.

2. The split rotor module (4) and vertical stage (15) according to claim 1, characterized in that: When the split rotor module (4) rotates with the connecting rod (6) in the vertical phase (15), the resulting advance torque allows the pendulum (10) to swing back and forth around the rotor support (11).

3. The split rotor module (4) and pendulum (10) according to claim 2, characterized in that: When the rotation surface of the pendulum (10) is separated from the rotation surface of the split rotor module (4) and an angle is formed, the connecting rod (6) rotates in a two-dimensional plane, and the stability of the gyroscope still works.

4. The vertical stage (15) according to claim 1, characterized in that: The rotation axis of the split rotor module (4) in the vertical stage (15) has a small angle or is parallel to the rotation plane of the connecting rod (6). The resulting precession torque causes the rotation plane of the pendulum (10) to separate from the rotation plane of the split rotor module (4), creating an angle. At this time, the stability of the gyroscope comes into play. When the connecting rod (6) rotates in the vertical stage (15), it needs a large force 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 (16) according to claim 1, characterized in that: The rotation axis of the split rotor module (4) in the parallel stage (16) has a large angle with the rotation surface of the connecting rod (6) or reaches 90 degrees. At this time, the stability of the gyroscope is small or even non-existent. When the connecting rod (6) rotates in the parallel stage (16), it requires a small force, thereby generating a small downward reaction force on the output shaft of the main motor (3).

6. The vertical stage (15) and parallel stage (16) according to claims 4 and 5, characterized in that: When the connecting rod (6) rotates in the vertical phase (15), it requires a large force to overcome the stability of the gyroscope, thereby generating a large upward reaction force on the output shaft of the main motor (3). When the connecting rod (6) rotates in the parallel phase (16), it requires a small force, thereby generating a small downward reaction force on the output shaft of the main motor (3). The two reaction forces with opposite directions and different magnitudes combine to obtain a new upward resultant force. The direction of the resultant force is the direction of the thrust. Every time the connecting rod (6) rotates, it will generate an upward thrust on the output shaft of the main motor (3).

7. The main motor (3) and rotary drive motor (7) according to claim 1, characterized in that: For every 360 degrees the main motor (3) rotates, the rotation drive motor (7) drives the rotor motor (8) and the split rotor module (4) to rotate 180 degrees, thereby generating a vertical stage (15) and a parallel stage (16).

8. The main motor (3) and rotary drive motor (7) according to claim 7, characterized in that: By adjusting the speed of the main motor (3) and the rotary drive motor (7), the positions of the vertical phase (15) and the horizontal phase (16) can be adjusted, thereby adjusting the direction of the thrust generated by the gyroscope cabin (2) and causing the propeller body (1) to change its direction of movement and direction.

9. The limiter (18) according to claim 1, characterized in that: The limiter (18) is covered with rubber to prevent it from colliding and being damaged by the pendulum (10).

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