pendulum inclined disc engine

Abstract

This invention discloses a pendulum swashplate engine, relating to the field of aerospace engine technology. The recoil principle of rockets is only one method of generating thrust, not the only one; any force that can move an object can be called "thrust." The idea of ​​this invention is to use a gyroscope rotor composed of a base (15) and a pendulum (3). By controlling the angle between the pendulum (3) and the rotation plane of the base (15), the gyroscope stability of the gyroscope rotor composed of the base (15) and the pendulum (3) can be controlled, thereby controlling the required torque. Because, under the premise of a fixed rotation speed, torque is proportional to excitation force, the magnitude of excitation force can be controlled by controlling the magnitude of torque. The direction of excitation force can be controlled by controlling the position of the angle between the pendulum (3) and the rotation plane of the base (15), ultimately generating an excitation force or thrust with constantly changing direction and magnitude to propel the satellite in space.

Description

Technical Field

[0001] This invention relates to the field of aerospace engine technology, and in particular to a pendulum swashplate 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 pendulum (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 pendulum swashplate engine, which, by changing the angle between the rotation surfaces of the base (15) and the pendulum (3), causes a difference in the stability of the gyroscope, so that the main motor (4) generates two thrusts per revolution.

[0004] To achieve the above objectives, the present invention provides the following technical solution: A pendulum swashplate engine, characterized in that: the pendulum swashplate engine includes a thruster body (1) installed inside a satellite, the thruster body (1) contains multiple gyroscope compartments (2), a main motor (4) is mounted at the rear of the 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), a rotor motor (9) is mounted on multiple ends of the connecting rod (5), and a base (1) is mounted on the end of the output shaft of the rotor motor (9). 5) The rotor motor (9) has a bushing (7) on its outer casing that encloses the output shaft. The bushing (7) has two protruding pins that are connected to the stationary ring (8). The rotor motor (8) has a servo motor (6) on its side. The rocker arm of the servo motor (6) is connected to the control lever (17) via a pin (16). The control lever (17) is fixed to the fixed seat (20) of the stationary ring (8) via a pin (16). The stationary ring (8) and the moving ring (18) are connected by a bearing. Both the stationary ring (8) and the moving ring (18) are mounted with fixed seats (20). The base (15) is equipped with multiple pendulums (3). The hammer (3) can swing up and down. One end of the tilting rod (10) is fixed to the pendulum (3) by a pin (16), and the other end of the tilting rod (10) is fixed to the fixed seat (20) of the moving ring (18) by a pin (16). One end of the torque arm (19) is fixed to the base (15) by a pin (16), and the other end of the torque arm (19) is fixed to the fixed seat (20) of the moving ring (18) by a pin (16). 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) is connected to the main motor (4), rotor motor (9), and servo motor (6) to provide power and transmit control signals. The main motor (4), rotor motor (9), and servo 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 pendulum (3) is zero. In the inclined stage (11), the rotation surface of the pendulum (3) is tilted. At this time, the angle between the rotation surfaces of the base (15) and the pendulum (3) becomes larger. The two stages, the parallel stage (12) and the inclined stage (11), form a cycle.

[0005] In order to adjust the tilt angle of the moving ring (18), the servo motor (6) drives the stationary ring (8) to tilt by controlling the lever (17).

[0006] In order to make the pendulum (3) and the base (15) rotation surface form an angle, when the base (15) drives the pendulum (3) to rotate, the inclined moving ring (18) pulls the pendulum (3) through the inclined tie rod (10), and the rotation surface of the pendulum (3) will tilt.

[0007] In order to make the base (15) and the moving ring (18) rotate synchronously, the base (15) drives the moving ring (18) to rotate through the torque arm (19).

[0008] 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 pendulum (3) moves from bottom to top in the parallel phase (12) through the connecting rod (5), the servo motor (6) controls the angle between the pendulum (3) and the rotation plane of the base (15) to be zero by controlling the control rod (17), the stationary ring (8), the moving ring (18) and the tilting rod (10). At this time, the gyroscope stability of the gyroscope rotor composed of the base (15) and the pendulum (3) does not work.

[0009] In order to generate an upward thrust by driving the gyroscope rotor composed of the base (15) and the pendulum (3) through the connecting rod (5) from top to bottom during the tilting phase (11), the servo motor (6) controls the pull rod (17), the stationary ring (8), the moving ring (18) and the tilting pull rod (10) to make the pendulum (3) and the rotation plane of the base (15) have a large angle. At this time, the gyroscope stability of the gyroscope rotor composed of the base (15) and the pendulum (3) comes into play.

[0010] 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 pendulum (3) will generate an upward thrust when it moves from top to bottom in the tilting phase (11), and will not generate a downward thrust when it moves from bottom to top in the parallel phase (12).

[0011] 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 pendulum (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

[0012] The specific embodiments of the present invention will now be described in further detail with reference to the accompanying drawings.

[0013] 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 3This is a top view of the gyroscope cabin of the present invention; Figure 4 This is a top view of the parallel stage of the present invention; Figure 5 This is a top view of the tilting stage of the present invention; Figure 6 This is a top view of the base of the present invention; Figure 7 This is a schematic diagram showing the inclined intersection of the base and the pendulum rotation surface of the present invention; Figure 8 This is a front view of the moving ring and the stationary ring of the present invention; Figure 9 This is a schematic diagram of the back of the moving ring and the stationary ring of the present invention; The components are: 1. Thruster body, 2. Gyroscope compartment, 3. Pendulum, 4. Main motor, 5. Connecting rod, 6. Servo motor, 7. Bushing, 8. Stationary ring, 9. Rotor motor, 10. Tilt rod, 11. Tilt stage, 12. Parallel stage, 13. Conductive slip ring, 14. Wire, 15. Base, 16. Pin, 17. Control rod, 18. Moving ring, 19. Torque arm, and 20. Fixed seat. Detailed Implementation

[0014] The specific implementation method of the pendulum swashplate engine will be described in detail below with reference to the accompanying drawings.

[0015] Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 , Figure 8 , Figure 9 The following are specific embodiments and processes of the pendulum swashplate engine of the present invention: Figure 6 and Figure 7 , Figure 6 and Figure 7 The phenomenon described has been verified through hundreds of experiments. Figure 6 In this gyroscope rotor, the high-speed rotating base (15) and the pendulum (3) form a gyroscope rotor. The gyroscope rotor composed of the base (15) and the pendulum (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 pendulum (3), a precession torque is generated. The precession torque acts on the pendulum (3), causing the rotation surface of the pendulum (3) to be as... Figure 7The same tilt occurs in the center. The direction of the tilt of the rotating surface of the pendulum (3) is consistent with the direction of the precession torque. The greater the external torque on the rotating shaft of the base (15) and the pendulum (3), the greater the angle between the rotating surfaces of the base (15) and the pendulum (3), and the greater the measured thrust. When the external torque remains unchanged, decreasing the angle between the rotating surfaces of the base (15) and the pendulum (3) reduces the measured thrust. When the angle between the rotating surfaces of the base (15) and the pendulum (3) is zero, the measured thrust is zero. The tilt of the rotating surface of the pendulum (3) is actually the pendulum (3) swinging back and forth once for every revolution of the base (15). The energy that drives the pendulum (3) to swing back and forth comes from the torque output by the main motor (4). Figure 7 In the case where the rotation axis of the base (15) and the pendulum (3) does not move along the precession torque, the precession torque acts on the pendulum (3), causing the rotation surface of the pendulum (3) to tilt. At this time, the stability of the gyroscope rotor composed of the base (15) and the pendulum (3) is effective. However, the stability of an ordinary rigid body gyroscope rotor is ineffective when the rotation axis cannot move along the precession torque.

[0016] 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 2 The two main motors (4) rotating in opposite directions do not generate excitation force. However, because the gyroscope stability of the base (15) and pendulum (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 concept: "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 pendulum (3) to swing back and forth. 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 plane of the base (15) and pendulum (3) is always controlled to occur in the tilting phase (11), an upward excitation force or thrust can be continuously generated.

[0017] Figure 2 , Figure 3 and Figure 4 ,exist Figure 4 In the middle, the servo motor (6) drives the stationary ring (8) and the moving ring (18) to remain parallel to the rotation plane of the base (15) through the control rod (17). The moving ring (18) drives the rotation plane of the pendulum (3) to remain parallel to the rotation plane of the base (15) through the tilting rod (10). At this time, the gyroscope stability of the gyroscope rotor composed of the base (15) and the pendulum (3) is ineffective. Figure 2and Figure 3 In the middle, the output shaft of the main motor (4) drives the gyroscope rotor composed of the base (15) and the pendulum (3) through the connecting rod (5) to move from bottom to top in the parallel phase (12) without generating a downward thrust.

[0018] Figure 2 , Figure 3 , Figure 5 and Figure 7 ,exist Figure 5 In the middle, the servo motor (6) drives the stationary ring (8) and the moving ring (18) to tilt through the control rod (17). The moving ring (18) drives the rotation surface of the pendulum (3) to tilt through the tilting rod (10). At this time, the following will occur: Figure 7 The pendulum (3) and the rotation plane of the base (15) form a large angle. When the pendulum (3) and the rotation plane of the base (15) form an angle, the gyroscope stability of the gyroscope rotor composed of the base (15) and the pendulum (3) comes into play. At this time, Figure 2 and Figure 3 In the middle, the output shaft of the main motor (4) drives the gyroscope rotor composed of the base (15) and the pendulum (3) through the connecting rod (5) to move from top to bottom during the tilting phase (11), generating an upward thrust.

[0019] Figure 2 , Figure 4 and Figure 5 ,exist Figure 5 During the tilting phase (11), the output shaft of the main motor (4) drives the gyroscope rotor, composed of the base (15) and the pendulum (3), to move downwards via the connecting rod (5), generating an upward thrust. Figure 4 In the parallel phase (12), the output shaft of the main motor (4) drives the gyroscope rotor composed of the base (15) and the pendulum (3) to move from bottom to top through the connecting rod (5). This does not generate a downward thrust. Figure 2 The main motor (4) inside the gyroscope compartment (2) can generate two upward thrusts every time it rotates.

[0020] The process and conclusion of this invention are as follows: the power supply and computer on the satellite are connected by wire (12) to provide power and transmit control signals to the main motor (4), rotor motor (9) and servo 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. The rotor motor (9) drives the pendulum (3) and the base (15) to rotate at high speed. The base (15) drives the moving ring (18) to rotate synchronously through the torsion arm (19). During the tilting phase (11), the servo motor (6) drives the stationary ring (8) and the moving ring (18) to tilt through the control rod (17). The moving ring (18) drives the rotation surface of the pendulum (3) to tilt through the tilting rod (10). At this time, the pendulum (3) and the rotation surface of the base (15) generate a large angle. At this time, the gyroscope stability of the gyroscope rotor composed of the base (15) and the pendulum (3) comes into play. The output shaft of the main motor (4) drives the gyroscope rotor composed of the base (15) and the pendulum (3) to move from top to bottom during the tilting phase (11) through the connecting rod (5), generating an upward thrust. During the parallel phase (12), the servo motor (6) drives the stationary ring (8) and the moving ring (18) to remain parallel to the rotation plane of the base (15) via the control lever (17). The moving ring (18) drives the rotation plane of the pendulum (3) to remain parallel to the rotation plane of the base (15) via the tilting lever (10). At this time, the gyroscope stability of the gyroscope rotor composed of the base (15) and the pendulum (3) is ineffective. The output shaft of the main motor (4) drives the gyroscope rotor composed of the base (15) and the pendulum (3) to move upwards during the parallel phase (12) via 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.

[0021] 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).

[0022] 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 pendulum swashplate engine, characterized in that: The pendulum swashplate 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). Rotor motors (9) are mounted on multiple ends of the connecting rod (5). A base (15) is mounted on the end of the output shaft of the rotor motor (9). The outer casing is fitted with a bushing (7) that encloses the output shaft. The bushing (7) has two protruding pins connected to the stationary ring (8). A servo motor (6) is mounted on the side of the rotor motor (8). The rocker arm of the servo motor (6) is connected to the control lever (17) via a pin (16). The control lever (17) is fixed to the fixed seat (20) of the stationary ring (8) via a pin (16). The stationary ring (8) and the moving ring (18) are connected by a bearing. Both the stationary ring (8) and the moving ring (18) are mounted with fixed seats (20). The base (15) is fitted with multiple pendulums (3). The pendulums (3) can move up and down. The tilting lever (10) is fixed to the pendulum (3) by a pin (16) at one end and to the fixed seat (20) of the moving ring (18) by the other end. The torque arm (19) is fixed to the base (15) by a pin (16) at one end and to the fixed seat (20) of the moving ring (18) by the other end. 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 connecting rod (5). The outer surface of the gyroscope cabin (2) is connected to the main motor (4), rotor motor (9), and servo motor (6) to provide power and transmit control signals. The main motor (4), rotor motor (9), and servo 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 base (15) and the rotation surface of the pendulum (3) is zero. In the inclined stage (11), the rotation surface of the pendulum (3) is tilted. At this time, the angle between the base (15) and the rotation surface of the pendulum (3) becomes larger. The two stages, the parallel stage (12) and the inclined stage (11), form a cycle.

2. The servo motor (6), control lever (17), stationary ring (8), and moving ring (18) according to claim 1, characterized in that: The servo motor (6) controls the lever (17) to tilt the stationary ring (8), thereby adjusting the tilt angle of the moving ring (18).

3. The inclined tie rod (10), base (15), pendulum (3), and moving ring (18) according to claim 1, characterized in that: When the base (15) drives the pendulum (3) to rotate, the inclined moving ring (18) pulls the pendulum (3) through the inclined tie rod (10), and the rotation surface of the pendulum (3) will tilt, thereby creating an angle between the pendulum (3) and the rotation surface of the base (15).

4. The torque arm (19), base (15), and moving ring (18) according to claim 1, characterized in that: The base (15) drives the rotating ring (18) to rotate through the torque arm (19), so that the base (15) and the rotating ring (18) rotate synchronously.

5. The parallel stage (12) according to claim 1, characterized in that: The servo motor (6) controls the angle between the pendulum (3) and the rotation plane of the base (15) to be zero by controlling the pull rod (17), the stationary ring (8), the moving ring (18) and the tilting pull rod (10). At this time, the gyroscope stability of the gyroscope rotor composed of the base (15) and the pendulum (3) does not work. The output shaft of the main motor (4) drives the gyroscope rotor composed of the base (15) and the pendulum (3) to move from bottom to top in the parallel stage (12) through the connecting rod (5) without generating a downward thrust.

6. The tilting stage (11) according to claim 1, characterized in that: The servo motor (6) controls the pull rod (17), stationary ring (8), moving ring (18) and tilting pull rod (10) to make the pendulum (3) and the base (15) rotation plane make a large angle. At this time, the gyroscope stability of the gyroscope rotor composed of the base (15) and pendulum (3) takes effect. The output shaft of the main motor (4) drives the gyroscope rotor composed of the base (15) and pendulum (3) to move from top to bottom in the tilting stage (11) through the connecting rod (5), which will generate an upward thrust.

7. The gyroscope cabin (2) according to claims 5 and 6, characterized in that: The gyroscope rotor consisting of the base (15) and the pendulum (3) generates an upward thrust when it moves from top to bottom during the tilting phase (11). The gyroscope rotor consisting of the base (15) and the pendulum (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.

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