A thrust device using double toroidal electromagnetic retardation effect

Abstract

The present application belongs to the technical field of electromagnetic propulsion, and relates to a thrust device using double circular ring electromagnetic delay effect, comprising: a fixed circular ring, a closed annular coil made of conductive material, having a first connection end and a second connection end, the first connection end being used for connecting one output end of a first alternating current power supply, and the second connection end being used for connecting another output end of the first alternating current power supply; a moving circular ring, a closed annular coil made of conductive material, coaxially arranged with the fixed circular ring, having a third connection end and a fourth connection end, the third connection end being used for connecting one output end of a second alternating current power supply, and the fourth connection end being used for connecting another output end of the second alternating current power supply; the outer edge of the moving circular ring is fixedly connected with a force output shaft, the force output shaft extends in the direction away from the fixed circular ring along the axial direction, and is used for connecting an external load. Without propellant working medium and external reaction force component, the thrust density is high, the thrust direction is controllable, and the structure is simple and reliable.

Description

Technical Field

[0001] This invention relates to the field of electromagnetic propulsion technology, and more specifically, to a thrust device utilizing the double-ring electromagnetic delay effect. Background Technology

[0002] Traditional electromagnetic propulsion devices, such as linear motors and maglev trains, require a fixed stator to provide reaction force to drive the rotor. Chemical or electrothermal propulsion devices, on the other hand, need to discharge propellant to generate thrust, and the consumption of propellant limits the propulsion device's range and payload. These traditional propulsion methods have inherent drawbacks such as complex structures, the need for fixed reaction force components, and reliance on propellant consumption.

[0003] In recent years, some conceptual designs known as "propellantless propulsion" have emerged in academia. However, most of these designs theoretically fail to satisfy the law of conservation of momentum, lack experimental verification, and are difficult to apply in practice. Designing a unidirectional thrust device within the framework of classical electrodynamics that requires neither a working propellant nor a fixed stator reaction force component is a pressing technical challenge in the field of electromagnetic propulsion. Summary of the Invention

[0004] To address the aforementioned deficiencies in the prior art, the present invention provides a thrust device utilizing the double-ring electromagnetic delay effect, comprising:

[0005] A fixed circular ring, a closed loop coil made of conductive material, has a first terminal and a second terminal. The first terminal is used to connect to one output terminal of a first AC power supply, and the second terminal is used to connect to the other output terminal of the first AC power supply.

[0006] A movable ring, a closed loop coil made of conductive material, is arranged coaxially with the fixed ring and has a third terminal and a fourth terminal. The third terminal is used to connect to one output terminal of a second AC power source, and the fourth terminal is used to connect to the other output terminal of the second AC power source.

[0007] The axial distance d between the fixed ring and the movable ring satisfies d = c / (4f), where f is the operating frequency of the first AC power supply and the second AC power supply, and c is the speed of light;

[0008] The outer edge of the movable ring is fixedly connected to a force output shaft, which extends axially away from the fixed ring and is used to connect an external load.

[0009] Preferably, the thrust device utilizing the electromagnetic delay effect of the double ring further includes an insulating support frame disposed between the fixed ring and the movable ring. One end of the insulating support frame is fixedly connected to the fixed ring, and the other end of the insulating support frame is slidably connected to or clearance-fitted with the movable ring. The insulating support frame is made of a non-magnetic insulating material.

[0010] Preferably, the thrust device utilizing the double-ring electromagnetic delay effect further includes a first high-frequency power supply and a second high-frequency power supply. The two output terminals of the first high-frequency power supply are electrically connected to the first terminal and the second terminal, respectively, for supplying an alternating current of I0 cos(ωt) to the fixed ring. The two output terminals of the second high-frequency power supply are electrically connected to the third terminal and the fourth terminal, respectively, for supplying an alternating current of I0cos(ωt + π / 2) to the moving ring, where I0 is the peak current, ω is the angular frequency, and ω = 2πf.

[0011] Preferably, the fixed ring is made of copper wire, and the movable ring is made of copper wire.

[0012] Preferably, the fixed ring is composed of a superconducting coil, and the movable ring is composed of a superconducting coil.

[0013] Preferably, the radius R1 of the fixed ring is equal to the radius R2 of the movable ring.

[0014] Preferably, the radius R1 of the fixed ring is not equal to the radius R2 of the movable ring.

[0015] Preferably, the cross-section of the conductors of the fixed ring and the movable ring is circular or rectangular.

[0016] Preferably, the conductors of the fixed ring and the movable ring are provided with cooling channels that extend along the axial direction of the conductors to accommodate circulating cooling media.

[0017] Preferably, the fixed ring is fixedly mounted on the external reference frame bracket, and the movable ring is axially movable on the linear guide rail via the force output shaft.

[0018] The thrust device utilizing the double-ring electromagnetic delay effect of the present invention has the following beneficial effects:

[0019] (1) No propellant required: Thrust is generated by the interaction of electromagnetic fields. No chemical fuel or propellant is consumed. No propellant tank is required, which can significantly improve the payload ratio and endurance of the spacecraft.

[0020] (2) No fixed stator reaction force component: Traditional electromagnetic propulsion devices such as linear motors require a fixed stator to provide reaction force. In this invention, although the fixed ring is fixedly installed, its function is only to provide a reference system and it is not a stator in the traditional sense. The moving ring can directly output thrust. The mechanical structure is simple, the energy conversion links are few, and the efficiency is high.

[0021] (3) High thrust density: It directly converts electrical energy into mechanical thrust. The current and thrust are in a square relationship. By increasing the current, the thrust can be increased rapidly. The thrust density potential is great.

[0022] (4) Controllable thrust direction: By changing the sign of the phase difference between the two AC power sources (changing +π / 2 to -π / 2), the thrust direction can be reversed, which is convenient for bidirectional drive or attitude adjustment.

[0023] (5) Simple and reliable structure: It consists of only two ring coils, two power supplies and a force output shaft. There is no mechanical friction between moving parts (the moving ring and the insulating support frame are in sliding fit), resulting in low mechanical loss and long service life.

[0024] (6) It conforms to classical electromagnetic theory: Based on Maxwell's electromagnetic field theory and Ampere's law, it does not involve any assumptions beyond classical physics, the principle is clear, and the engineering feasibility is strong. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort. The present invention will be further described below in conjunction with the drawings and embodiments. In the drawings:

[0026] Figure 1 This is an axial cross-sectional view of the overall structure of the thrust device utilizing the double-ring electromagnetic delay effect of the present invention.

[0027] Figure 2 This is a schematic diagram showing the phase relationship between the current and magnetic field of the two rings in this invention.

[0028] In the diagram, 1-fixed ring, 2-moving ring, 3-insulating support frame, 4-first high-frequency power supply, 5-force output shaft. Detailed Implementation

[0029] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0030] It should be noted that if the embodiments of the present invention involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicators will also change accordingly.

[0031] Furthermore, if the embodiments of this invention involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. If the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0032] Example 1

[0033] Please see Figure 1 This is an axial sectional view of the overall structure of the thrust device utilizing the double-ring electromagnetic delay effect of the present invention. Figure 1 As shown, the thrust device utilizing the double-ring electromagnetic delay effect provided in the first embodiment of the present invention includes at least a fixed ring 1 and a closed ring coil made of conductive material, having a first terminal and a second terminal. The first terminal is used to connect to one output terminal of a first AC power supply, and the second terminal is used to connect to the other output terminal of the first AC power supply.

[0034] The movable ring 2, a closed loop coil made of conductive material, is arranged coaxially with the fixed ring 1 and has a third terminal and a fourth terminal. The third terminal is used to connect to one output terminal of the second AC power supply, and the fourth terminal is used to connect to the other output terminal of the second AC power supply.

[0035] When the moving ring 2 is connected to an alternating current, it also generates a time-varying magnetic field in the space around it. As the power output component of the device, the moving ring 2 generates Ampere force through its interaction with the magnetic field of the fixed ring, and outputs thrust to the outside.

[0036] The axial distance d between the fixed ring 1 and the movable ring 2 satisfies d = c / (4f), where f is the operating frequency of the first AC power supply and the second AC power supply, and c is the speed of light;

[0037] The outer edge of the movable ring 2 is fixedly connected to a force output shaft 5, which extends axially away from the fixed ring 1 and is used to connect to an external load (such as a spacecraft cabin, a linear drive workbench, etc.) to transmit the thrust generated by the movable ring to the external load, thereby realizing the propulsion or drive function.

[0038] This spacing setting ensures that the time τ = d / c required for the electromagnetic field to propagate from one ring to another is exactly equal to a quarter period (T / 4 = 1 / (4f)), thus creating a matching relationship between the spatial propagation delay and the current phase difference. This is a key structural parameter for achieving net thrust output.

[0039] The present invention utilizes a thrust device with a double-ring electromagnetic delay effect, and further includes an insulating support frame 3. The insulating support frame 3 is disposed between a fixed ring 1 and a movable ring 2. One end of the insulating support frame 3 is fixedly connected to the fixed ring 1, and the other end of the insulating support frame 3 is slidably connected to or clearance-fitted with the movable ring 2. The insulating support frame 3 is made of a non-magnetic insulating material (such as ceramics, engineering plastics, etc.).

[0040] Its functions are: firstly, to maintain a constant axial distance between the fixed ring and the moving ring, ensuring that the distance always satisfies the precise relationship d = c / (4f); secondly, to prevent electrical short circuits between the two rings; and thirdly, due to its non-magnetic material properties, it will not interfere with the propagation of the magnetic field between the two rings. The insulating support frame and the moving ring are connected by a sliding connection or clearance fit, allowing the moving ring to move freely axially under thrust without being constrained by the insulating support frame.

[0041] The present invention utilizes a thrust device based on the electromagnetic delay effect of a double-ring structure, and further includes a first high-frequency power supply 4 and a second high-frequency power supply. The two output terminals of the first high-frequency power supply 4 are electrically connected to the first terminal and the second terminal, respectively, for supplying an alternating current of I0 cos(ωt) to the fixed ring 1. The two output terminals of the second high-frequency power supply are electrically connected to the third terminal and the fourth terminal, respectively, for supplying an alternating current of I0 cos(ωt + π / 2) to the moving ring 2, where I0 is the peak current, ω is the angular frequency, ω = 2πf, and t is the time variable.

[0042] Two AC power sources provide alternating currents with a phase difference of 90° (π / 2) to two circular rings. Combined with the 90° phase shift introduced by the spatial propagation delay, they jointly determine the phase relationship between the magnetic field and the current at the location of the two circular rings, thus determining the direction and magnitude of the Ampere force.

[0043] The fixed ring 1 is made of copper wire, and the movable ring 2 is also made of copper wire. Copper has excellent electrical conductivity and can carry large currents, making it a commonly used material for making coils.

[0044] The fixed ring 1 is composed of superconducting coils, and the movable ring 2 is also composed of superconducting coils. Superconducting coils have zero resistance below a certain temperature, can carry extremely large currents without Joule heat loss, and are beneficial for further increasing thrust.

[0045] The radius R1 of the fixed ring 1 is equal to the radius R2 of the moving ring 2. When the radii are equal, the magnetic field distribution generated by the fixed ring at the center of the moving ring is the most uniform, which is beneficial for simplifying thrust calculation and optimizing design.

[0046] The radius R1 of the fixed ring 1 is not equal to the radius R2 of the movable ring 2, in order to accommodate different installation spaces and thrust requirements.

[0047] The conductors of the fixed ring 1 and the movable ring 2 have circular or rectangular cross-sections. Circular cross-section conductors are easier to manufacture, while rectangular cross-section conductors have a larger heat dissipation surface area for the same cross-sectional area, which is beneficial for heat dissipation under high current conditions.

[0048] The conductors of the fixed ring 1 and the movable ring 2 are provided with cooling channels. These cooling channels extend along the axial direction of the conductors and are used to accommodate circulating cooling media (such as cooling water or cooling oil) to remove the Joule heat generated by the large current and prevent the conductors from overheating.

[0049] The fixed ring 1 is fixedly mounted on the external reference frame support, ensuring that the fixed ring will not shift when subjected to a reverse Ampere force, as the reaction force is absorbed by the support structure. The movable ring 2 is axially movable on the linear guide rail via the force output shaft 5, allowing the movable ring to move freely axially under thrust, thus outputting mechanical work.

[0050] The working principle of this invention is based on the finite propagation speed of electromagnetic fields and Ampere's law, which is explained in detail below.

[0051] (1) Electromagnetic field propagation delay effect:

[0052] According to Maxwell's electromagnetic theory, electromagnetic fields propagate at the speed of light *c* in a vacuum. When an alternating current flows through a fixed circular ring, it generates an alternating magnetic field in the surrounding space. This magnetic field takes time τ = d / *c* to propagate from the fixed ring to the position of the moving ring. Since the distance between the two rings is d = *c* / (4f), the propagation time τ = 1 / (4f), which is exactly one-quarter of the alternating current period.

[0053] Similarly, the alternating magnetic field generated by the moving ring also requires the same time τ = 1 / (4f) to propagate to the location of the fixed ring.

[0054] (2) Current phase relationship:

[0055] Figure 2 This is a schematic diagram illustrating the phase relationship between the current and magnetic field of the two circular rings in this invention. Figure 2 As shown, a fixed circular ring carries a current I1 = I0 cos(ωt), and a moving circular ring carries a current I2 = I0 cos(ωt + π / 2). The current in the moving circular ring leads the current in the fixed circular ring by π / 2 phase (i.e., one-quarter of a cycle).

[0056] (3) Force analysis of the moving ring:

[0057] The alternating magnetic field generated by the fixed ring propagates outward at the speed of light c, reaching the position of the moving ring after a time delay τ = d / c = 1 / (4f). Due to the propagation delay, the moving ring actually experiences the magnetic field generated by the current in the fixed ring a quarter of a cycle earlier.

[0058] The current phase of the fixed ring one-quarter of the cycle is:

[0059] .

[0060] At this time, the phase of the current in the moving ring itself is:

[0061] .

[0062] The magnetic fields and currents at the location of the moving ring are opposite in direction. According to Ampere's law, the Ampere force on a current-carrying conductor in a magnetic field is proportional to the vector product of the current and the magnetic field. When the magnetic field and current are opposite in direction, the Ampere force between them manifests as a repulsive force, pointing axially away from the fixed ring (i.e., in front of the moving ring).

[0063] Since both rings are carried by alternating current, the repulsive force is an alternating force that changes with time. However, it is important to note that the magnetic field propagating from the fixed ring to the position of the moving ring is always out of phase with the current in the moving ring itself. Therefore, the direction of the repulsive force does not change with time and always points forward of the moving ring. As a result, the average thrust is not zero.

[0064] (4) Force analysis of the fixed ring:

[0065] The alternating magnetic field generated by the moving ring propagates in the opposite direction at the speed of light c, reaching the position of the fixed ring after a time τ = d / c = 1 / (4f). Similarly, the position of the fixed ring actually experiences the magnetic field generated by the current of the moving ring a quarter of a cycle earlier.

[0066] The current phase of the moving loop one-quarter of a cycle ago is:

[0067] .

[0068] At this time, the phase of the current in the fixed ring itself is: .

[0069] The magnetic fields and currents of both are in the same direction at the location of the fixed ring. According to Ampere's law, when the magnetic field and current are in the same direction, they produce an attractive force, which points axially towards the direction of the moving ring (i.e., in front of the fixed ring).

[0070] Similarly, due to the matching of the phase relationship between the two ring currents and the propagation delay, the direction of the attraction does not change with time and always remains pointing in the direction of the moving ring, and its time average value is not zero.

[0071] (5) Direction of resultant force and thrust output:

[0072] The repulsive force on the moving ring points forward (away from the fixed ring), and the attractive force on the fixed ring also points forward (i.e., the fixed ring points towards the moving ring). The Ampere forces on both rings point in the same axial direction—forward of the moving ring.

[0073] The fixed ring is fixedly installed in an external reference frame (such as the spacecraft body). The opposing force it experiences is absorbed by the supporting structure, and the fixed ring itself does not move. The movable ring is connected to an external load through a force output shaft. The net thrust it experiences is axially forward, which can drive the external load to move.

[0074] (6) Explanation of far-field radiation momentum:

[0075] From the perspective of electromagnetic wave radiation, the distance between the two loop coils is λ / 4 (λ = c / f, where λ is the wavelength), and the feed phase difference is 90°. When the electromagnetic wave radiated by the fixed loop reaches the moving loop after traveling a distance of λ / 4, the spatial delay introduces a 90° phase shift. This causes the electromagnetic wave radiated by the moving loop to coherently enhance in a specific direction (along the axis towards the front of the moving loop) and coherently cancel in the opposite direction. This results in an asymmetry in the far-field radiation pattern along the axis.

[0076] According to the law of conservation of momentum, electromagnetic radiation possesses momentum. If the device radiates more electromagnetic momentum backward, the device itself will experience a forward reaction force (similar to the principle of a photon rocket). This radiative reaction force is in the same direction as the Ampere force mentioned above, and together they generate a unidirectional thrust along the axial direction pointing forward of the moving ring.

[0077] (7) Thrust calculation formula:

[0078] The peak magnetic flux density B0 generated by the fixed ring at the center of the moving ring is calculated using the following formula:

[0079] .

[0080] Where: B0 is the peak magnetic induction intensity generated by the fixed ring at the center of the moving ring, in T (Tesla).

[0081] μ0 is the free permeability, μ0 = 4π × 10⁻⁶ -7 H / m (Henry per meter), the unit is H / m;

[0082] I0 is the peak value of the alternating current, and its unit is A (ampere).

[0083] R2 is the radius of the moving ring, in meters (m).

[0084] d is the axial distance between the two rings, in meters (m).

[0085] In the denominator express( The 1.5th power of (i.e., the square root of the cube) is determined by the formula for the magnetic field distribution along the axis of the ring, with the unit being meters (m). 3 .

[0086] The average thrust F on the moving ring avg Calculate using the following formula: .

[0087] Wherein: F avg The time-averaged thrust is expressed in Newtons (N).

[0088] 1 / 2 is the conversion factor between the effective value and the peak value of the alternating current, which is generated by time averaging and is dimensionless.

[0089] I0 is the peak current, in A (amperes).

[0090] 2πR² is the circumference of the moving ring, representing the total length of the current-carrying conductor, in meters (m).

[0091] B0 is the peak value of magnetic flux density, in T (Tesla).

[0092] The physical meaning of this formula is: the Ampere force per unit length of the current-carrying conductor in the moving ring in the magnetic field is I0B0 / 2 (time average value), which multiplied by the total circumference 2πR2 gives the total thrust.

[0093] As can be seen from the above formula, the thrust is proportional to the square of the peak current (because B0 itself is proportional to I0), and is related to the geometric parameters of the ring radius and the turn pitch. The thrust can be significantly improved by increasing the current and optimizing the geometric dimensions.

[0094] Example 2

[0095] This embodiment provides a thrust device that utilizes the double-ring electromagnetic delay effect, suitable for large spacecraft orbital maneuvers or large high-speed linear drive platforms.

[0096] Fixed ring 1 has a radius of R1 = 10 m, and movable ring 2 has a radius of R2 = 10 m. The two rings have equal radii and are arranged coaxially.

[0097] Both the fixed ring 1 and the movable ring 2 are made of copper wire with a rectangular cross-section (50 mm wide, 20 mm high, and 1000 mm²). 2 This facilitates heat dissipation under high current conditions. A circular cooling channel (8mm in diameter) is installed inside the conductor, through which circulating cooling water carries away Joule heat and prevents the conductor temperature from becoming excessive.

[0098] Both conductor coils are single-turn loops (multi-turn structures can also be used to increase the ampere-turns, but for the sake of simplicity, this embodiment uses a single-turn loop as an example).

[0099] If the operating frequency f = 1.5 MHz, then the angular frequency ω = 2πf ≈ 9.42 × 10⁻⁶ 6 rad / s, wavelength λ = c / f ≈ 200 m.

[0100] The axial distance between the two rings is d = λ / 4 = 50 m.

[0101] The two output terminals of the first high-frequency power supply 4 are electrically connected to the first and second terminals of the fixed ring 1, respectively, and a peak current I0 = 2 × 10⁻⁶ is supplied to the fixed ring 1. 5 The alternating current of A is expressed as I1 = I0 cos(ωt).

[0102] The two output terminals of the second high-frequency power supply are electrically connected to the third and fourth terminals of the moving ring 2, respectively, and a peak current I0 = 2 × 10⁻⁶ is supplied to the moving ring 2. 5 The alternating current of A is expressed as I2 = I0cos(ωt + π / 2).

[0103] The two high-frequency power supplies adopt a master-slave synchronization method, with the same clock source providing the reference signal to ensure that the phase difference is accurate to 90°.

[0104] An insulating support frame 3 is positioned between the fixed ring 1 and the movable ring 2. It is made of high-strength alumina ceramic, is a hollow cylinder with a wall thickness of 50 mm, and its outer diameter is similar to that of the ring. One end of the insulating support frame is fixedly connected to the fixed bracket of the fixed ring 1 via a flange, and the other end is equipped with a linear bearing. The force output shaft 5 of the movable ring 2 passes through this linear bearing and can slide freely along the axial direction.

[0105] The force output shaft 5 is a solid shaft made of high-strength alloy steel with a diameter of 100 mm. One end is fixedly welded to the outer edge of the moving ring 2, and the other end is connected to an external load (such as a spacecraft cabin) through a flange.

[0106] Thrust calculation:

[0107] First, calculate the peak magnetic flux density B0 at the center of the moving ring:

[0108] The fixed ring has a radius of R1 = 10 m, the moving ring has a radius of R2 = 10 m, and the distance between them is d = 50 m.

[0109] R2 2 = 100 (m 2 ), d 2 = 2500 (m 2 R2 2 + d 2 = 2600 (m 2 );

[0110] (R2 2 + d 2 ) 3 / 2 =2600 3 / 2 =2600×√2600≈2600×50.990≈ 32574;

[0111] .

[0112] That is, B0 ≈ 0.0948 mT.

[0113] The circumference of the moving ring is L = 2πR² = 2π × 10 = 62.832 m.

[0114] Average thrust:

[0115] .

[0116] The working process is described as follows: The first high-frequency power supply 4 and the second high-frequency power supply are started, and alternating currents with a 90° phase difference are simultaneously passed through the two rings. The alternating magnetic field generated by the fixed ring 1 propagates at the speed of light, through τ = d / c = 50 / (3×10⁻⁶) 8 ) ≈ 1.667×10 -7 The time s is equal to one-quarter of the cycle (T / 4 = 1 / (4 × 1.5 × 10⁻⁶)). 6 ) = 1.667 × 10 -7 s).

[0117] The moving ring 2 actually experiences the magnetic field of the fixed ring a quarter cycle earlier. This magnetic field is out of phase with the current of the moving ring itself, generating a repulsive force that points in the direction of the moving ring along the axial direction.

[0118] At the same time, the magnetic field generated by the moving ring propagates in the opposite direction at the speed of light, reaches the position of the fixed ring in the same amount of time, is in phase with the current of the fixed ring itself, and generates an attractive force, which is also directed in front of the moving ring.

[0119] The two forces are in the same direction, with the net thrust on the moving ring moving axially forward. The reverse force on the fixed ring is absorbed by the external support. The moving ring outputs an average thrust of approximately 596 N through the force output shaft 5.

[0120] The heat dissipation measures are as follows: Under high current conditions, copper conductors generate a large amount of Joule heat. The cooling system is activated, and circulating cooling water is supplied to the cooling channels inside the conductors. The cooling water flow rate is ≥ 10 L / min, and the temperature difference between the inlet and outlet water is controlled within 10℃ to ensure that the conductor temperature does not exceed 80℃.

[0121] Example 3

[0122] This embodiment provides an optimized thrust device that utilizes the electromagnetic delay effect of a double ring, which is a medium-sized high-thrust device that achieves higher thrust in a smaller size.

[0123] Fixed ring 1 has a radius of R1 = 20 m, and movable ring 2 has a radius of R2 = 20 m.

[0124] If the operating frequency f = 10 MHz, then the wavelength λ = c / f = 30 m.

[0125] The axial distance between the two rings is d = λ / 4 = 7.5 m.

[0126] Peak current I0 = 10 6 A.

[0127] Thrust calculation:

[0128] R2 2 = 400 (m 2 ), d 2 = 56.25 (m 2 R2 2 + d 2 = 456.25 (m 2 ).

[0129] (R2 2 + d 2 ) 3 / 2 = 456.25 3 / 2 = 456.25 × √456.25.

[0130] √456.25 = 21.36, 456.25 × 21.36 ≈ 9747.

[0131] μ0 = 4 × Π × 10 7 .

[0132] .

[0133] That is, B0 ≈ 25.8 mT.

[0134] The circumference of the moving ring is L = 2π × 20 = 125.664 m.

[0135] Average thrust: .

[0136] That is approximately 162 tons of force (approximately 165 tons of force).

[0137] Verification of the match between operating frequency and spacing:

[0138] At f = 10 MHz, T = 0.1 μs, T / 4 = 0.025 μs.

[0139] τ = d / c = 7.5 / (3×10 8 = 0.025 μs, which is exactly equal to T / 4, satisfying the matching condition.

[0140] This embodiment achieves an average thrust of approximately 162 tons with a total device size of approximately 47.5 m (40 m in diameter plus 7.5 m spacing), exhibiting extremely high thrust density.

[0141] Structural reinforcement measures:

[0142] Due to the current being as high as 10 6 A. The conductors must be water-cooled copper pipes with a diameter ≥ 50 mm and a wall thickness ≥ 5 mm, and the interior must be circulated with high-pressure deionized cooling water. The insulating support frame must be made of high-strength silicon nitride ceramic with a compressive strength ≥ 2000 MPa to ensure that it does not deform under the action of huge electromagnetic forces.

[0143] Example 4

[0144] This embodiment provides an optimized thrust device that utilizes the electromagnetic delay effect of a double ring, which is a medium-sized high-thrust device that achieves higher thrust in a smaller size.

[0145] Fixed ring 1 with radius R1 = 20 m, and coiled outward 100 times with an equivalent length. Move ring 2 with radius R2 = 20 m, and coiled outward 100 times with an equivalent length (similar to the shape of two circular flying saucers).

[0146] If the operating frequency f = 10 MHz, then the wavelength λ = c / f = 30 m.

[0147] The axial distance between the two rings is d = λ / 4 = 7.5 m.

[0148] Peak current I0 = 5 × 10 4 A.

[0149] The formula for the relationship between wavelength and frequency is: .

[0150] in: (Lambda): Wavelength of an electromagnetic wave in free space, unit: meter (m).

[0151] The speed of light in a vacuum is approximately .

[0152] : Operating frequency, in this embodiment is (Right now ).

[0153] Substituting into the calculation: .

[0154] The formulas for axial spacing and end-firing array conditions are as follows: .

[0155] in: : Axial distance between the fixed ring and the moving ring, unit: meter (m).

[0156] : The wavelength calculated from the above formula.

[0157] Substitute into the calculation: .

[0158] Verification of the spacing With frequency Strict matching. Electromagnetic wave propagation time delay. The phase delay is exactly Perfectly compensates for the phase lead of the moving ring feed ( This satisfies the axial coherent reinforcement condition.

[0159] The magnetic field strength generated by a single-turn coil on the axis The calculation formula (magnetic flux density along the axis of the ring) is: .

[0160] in: : Distance from the center of the ring on the axis The peak value of the magnetic flux density generated at a given location, expressed in Tesla (T).

[0161] Vacuum permeability, a physical constant. (or H / m).

[0162] Peak current flowing through a single-turn coil, unit: ampere (A). In this embodiment... .

[0163] The radius of the coil, in meters (m). In this embodiment... .

[0164] : The distance from the target point on the axis to the coil plane (i.e., the distance between the fixed ring and the moving ring), unit: meters (m). In this embodiment .

[0165] Given: , , .

[0166]

[0167] Substitute into the original expression:

[0168] .

[0169] result: (milltesla).

[0170] Magnetic field comparison:

[0171] 10,000 A Case: 0.258 mT.

[0172] 50,000 A Case (this embodiment): 1.29 mT (proportional to current, 5 times the former).

[0173] The formula for calculating the average Ampere force per turn is: .

[0174] in: : The axial Ampere force on a single-turn coil in the time-averaged sense, in Newtons (N).

[0175] The time-averaging factor of sinusoidal alternating current (since instantaneous power is proportional to the square of the current, the average value is half of the peak value).

[0176] Peak current (A).

[0177] Circumference of a single-turn coil, in meters (m).

[0178] The peak value (T) of the magnetic induction intensity generated by the fixed ring at the position of the moving ring is calculated from the previous section.

[0179] Substitute the values: perimeter ;

[0180] ;

[0181] .

[0182] Result: The average thrust per turn is approximately .

[0183] The formula for the total thrust of a 100-turn helical coil is: .

[0184] in: Total axial thrust generated by all turns, unit: Newton (N).

[0185] The total number of turns (equivalent number of turns) of the spiral coil, in this embodiment .

[0186] The average thrust per turn calculated in the previous section.

[0187] Numerical substitution calculation ...

[0188] Converted to engineering units (tons of force): ,Right now: .

[0189] Compared to the 10,000 A case: current increased by 5 times, thrust increased. The volume increased by a factor of two (from 1.65 tons to 41.3 tons), which is fully in line with... The physical laws.

[0190] For the high power rating of 50,000 A peak current and approximately 41 tons thrust in this embodiment, simply using a low-current design is no longer feasible. Systematic enhancements are needed across multiple dimensions, including conductors, thermal management, insulation, mechanics, measurement and control, electromagnetic compatibility, and power supply matching. Specific measures are described below:

[0191] (1) Conductor selection and skin effect suppression.

[0192] At 10 MHz, the skin depth of a copper conductor is only about 21 micrometers. This means that almost no current flows through the vast majority of the cross-section of a solid, thick conductor, leading to a sharp increase in AC resistance. Therefore, the conductor must be made of large-section Litz wire (total effective cross-sectional area not less than 500 mm²), i.e., stranded from multiple thin insulated wires, to increase the effective conductive area; or a water-cooled hollow copper tube (outer diameter not less than 20 mm, wall thickness about 2 mm) can be used, serving as both a conductive channel and a coolant flow path. This measure aims to control the AC resistance within an acceptable range and significantly reduce ohmic heat loss.

[0193] (2) Dual-loop forced water cooling system.

[0194] The total conductor length of a 100-turn helical coil is approximately 12,566 meters (100 times the circumference of a single turn). At 50 kA current, even with optimized conductors, the estimated AC resistance remains between 0.5 and 1.5 Ω, and the peak instantaneous heat dissipation (…) The heat flux can reach 2.5~7.5 GW. Although the average heat loss under the pulse duty cycle is about 10~100 kW, this heat flux density still requires strong heat dissipation. The design adopts a dual-loop water cooling: the first loop is a hollow conductor with water flowing directly inside to achieve "internal cooling"; the second loop has a water-cooled plate installed on the back of the spiral frame to achieve "external cooling" to assist heat dissipation. The total cooling water flow rate must be no less than 50 L / min to ensure that the temperature rise is controlled within the allowable range of the insulation materials and structure.

[0195] (3) Insulation and withstand voltage design.

[0196] A time-varying current of 50 kA will induce an inter-turn voltage of several kV between 100 turns of the coil, posing a severe challenge to the insulation system. The conductor insulation uses a polyimide (PI) composite film wrapping, a material with excellent high-temperature resistance and corona resistance. Simultaneously, a 1 mm thick G10 epoxy fiberglass insulation partition is added to the physical spacing between turns to increase the creepage distance, prevent inter-turn breakdown or arcing, and ensure long-term operational reliability.

[0197] (4) Mechanical support and vibration-resistant structure.

[0198] The 41-ton axial thrust is a massive mechanical load, and since this force alternates at a frequency of 10 MHz, it can cause severe structural fatigue and vibration problems. Therefore, the helical frame must be made of heavy-duty titanium alloy or high-strength stainless steel to ensure sufficient rigidity and fatigue resistance. Multiple annular reinforcing ribs are installed radially to resist radial expansion deformation of the coil; 8-12 high-strength tie rods are evenly distributed axially to firmly compress all 100 turns, preventing axial movement or inter-turn relative displacement under alternating thrust.

[0199] (5) Spacing active servo control system.

[0200] The traveling wave end-fire array is extremely sensitive to the axial distance (nominal 7.5 m) between the fixed and moving rings, and the phase error must be controlled within an extremely small range. To achieve this, the system needs to be equipped with a laser interferometric rangefinder with a measurement accuracy of up to 0.01 mm for real-time monitoring of distance changes. The actuator uses a high-thrust piezoelectric ceramic stack with a stroke of no less than 1 mm and an output of no less than 10 kN. It has an extremely high response speed and can make micron-level dynamic adjustments based on ranging feedback to ensure that the distance error is stable within ±0.5 mm, thereby guaranteeing the traveling wave phase matching accuracy and avoiding thrust reduction.

[0201] (6) Electromagnetic shielding and electromagnetic compatibility (EMC) design.

[0202] A strong radio frequency current of 10 MHz and 50 kA will generate extremely strong electromagnetic radiation, posing serious interference and safety hazards to surrounding control circuits, sensors, and operators. Therefore, a multi-layered shielding structure is required: an inner layer of copper mesh (reflecting high-frequency electromagnetic waves), a middle layer of aluminum plate (absorbing and reducing eddy current losses), and an outer layer of permalloy (shielding low-frequency magnetic fields). The grounding resistance of the entire shielding structure must be less than 1 Ω to effectively suppress radiation leakage and ensure the normal operation of external equipment.

[0203] (7) High-power RF power supply and impedance matching.

[0204] A standard 50 Ω RF power source cannot directly drive a spiral coil with an impedance of only 0.1~1 Ω; otherwise, power reflection will be severe and efficiency will be extremely low. The solution is to use a high-power solid-state RF power supply based on SiC MOSFETs, which has fast switching speed and high voltage withstand capability. Combined with an L-type or T-type impedance matching network, the power supply output impedance is precisely matched with the complex impedance of the coil. At the same time, a power factor compensation capacitor is set to achieve a power supply efficiency of over 85% and realize maximum power transmission.

[0205] (8) Ensuring the accuracy of winding and assembly.

[0206] The consistency of thrust direction in a 100-turn spiral disk is highly dependent on the geometrical accuracy of each turn. A six-axis CNC winding machine is required during the winding stage to ensure uniform radius, pitch, and interlayer spacing of each turn. After assembly, a laser tracker is used to perform full-dimensional calibration of the spatial coordinates of all 100 turns, ensuring that the radial spacing error of each turn is controlled within 1 mm. This guarantees that the thrust vectors of each turn are superimposed in the same direction, avoiding thrust loss or lateral force generation due to geometric deviations.

[0207] This embodiment (10 MHz, 100 turns, 50,000 A, d = 7.5 m) can produce approximately Axial unidirectional thrust of approximately 41.3 tons.

[0208] This thrust level already possesses significant engineering practical value (such as orbital maneuvers for small satellites and electromagnetic catapult launches for drones). While a current of 50 kA falls into the high-current category, it is within the mature range of industrial pulse power (such as resistance welding machines and electrolytic rectifiers), and is entirely feasible in engineering applications when combined with Litz wire water cooling and heavy machinery structures. To further reduce heat load or increase thrust, one could consider increasing the number of turns (e.g., 200 turns, which would increase thrust to approximately 80 tons) or moderately increasing the current (e.g., 70 kA, which would increase thrust to approximately 80 tons).

[0209] Example 5

[0210] According to Maxwell's electromagnetic theory, electromagnetic fields propagate at the speed of light *c* in a vacuum. The magnetic field generated by the fixed loop current I1 = I0cos(ωt) reaches the moving loop in time τ = d / c. Since d = λ / 4 = c / (4f), τ = 1 / (4f), which is one-quarter of the cycle. The moving loop current is set as I2 = I0 cos(ωt + π / 2) (leading by 90°).

[0211] When the magnetic field of the fixed ring reaches the moving ring after a quarter-cycle delay, its phase is out of phase with the current of the moving ring itself, generating a repulsive force in a constant direction (moving ring forward). Similarly, when the magnetic field of the moving ring propagates in the opposite direction to the fixed ring, it is in phase with the current of the fixed ring, generating an attractive force in a constant direction (fixed ring also forward). The two forces are in the same direction and combine to form a unidirectional thrust.

[0212] Distributed traveling wave feeding: The fixed ring is evenly divided into M independent excitation segments along the circumference. Each segment is driven by an independent small RF power module. The phase of the output current of each module increases sequentially by 2π / M, synthesizing a traveling wave traveling along the circumference of the ring. The effect of the traveling wave magnetic field in the axial direction is equivalent to an M-turn coil, thus obtaining a thrust gain equivalent to the number of turns M without increasing the actual number of turns.

[0213] Fixed circular ring (stator): radius R1=20 m, single-turn continuous structure, divided into M=100 independent excitation segments along the circumference.

[0214] Moving ring (mover): radius R2=20 m, single-turn passive induction ring, coaxially arranged with the stator, axial spacing d=7.5 m.

[0215] Distributed power module array: 100 independent modules, each module containing a phase shifter, power amplifier (MOSFET / IGBT), and output matching network, with output capabilities of 5000 A, 500 kV, and 10 MHz.

[0216] Central controller: generates a 10 MHz reference clock and sends phase commands to each module through an optical fiber distribution network (phase difference between adjacent modules is 2π / 100), with a synchronization accuracy of <0.1°.

[0217] Insulation encapsulation: The entire structure is housed in a stainless steel vacuum chamber with a diameter of 25 m and a length of 12 m, filled with 0.5 MPa SF6 gas to ensure 500 kV high-voltage safety.

[0218] Conductor material: REBCO high-temperature superconducting tape (77K liquid nitrogen temperature range) is used. A single tape can carry 5000 A and has extremely low high-frequency AC loss. It is cooled by a liquid nitrogen circulation system.

[0219] The parameters are designed as follows:

[0220]

[0221] Thrust calculation:

[0222] 1. The mutual inductance of a single-turn circular ring – two coaxial single-turn circular rings (R=20m, d=7.5m) is:

[0223] .

[0224] 2. The equivalent mutual inductance (100 turns equivalent) is:

[0225] .

[0226] 3. Mutual inductance axial gradient:

[0227] .

[0228] 4. Induced current in the moving ring – The moving ring is a single-turn ring, and its self-inductance… The inductive reactance is much greater than the resistance (the skin depth of copper is about 20 μm at 10 MHz, but this scheme uses superconductivity, so the resistance is negligible), and the induced potential is:

[0229] .

[0230] The induced current in the moving loop (ignoring resistance) is:

[0231] .

[0232] 5. The average thrust is:

[0233] .

[0234] Converted to engineering units: .

[0235] According to the electromagnetic radiation theory, with a distance of λ / 4 between the two rings and a current phase difference of 90°, the axial forward radiation is enhanced and the rearward radiation is canceled out. The device obtains an additional radiation reaction force, the direction of which is consistent with the aforementioned Ampere force, further increasing the total thrust.

[0236] This embodiment successfully reduced the driving voltage to the 500 kV level through distributed traveling wave feeding, making the electromagnetic delay thrust device with a high current of 5000 A and an equivalent thrust of 100 turns engineering feasible.

[0237] The beneficial effects of the present invention, through the design of the above embodiments, are as follows:

[0238] (1) No propellant required: Thrust is generated by the interaction of electromagnetic fields. No chemical fuel or propellant is consumed. No propellant tank is required, which can significantly improve the payload ratio and endurance of the spacecraft.

[0239] (2) No fixed stator reaction force component: Traditional electromagnetic propulsion devices such as linear motors require a fixed stator to provide reaction force. In this invention, although the fixed ring is fixedly installed, its function is only to provide a reference system and it is not a stator in the traditional sense. The moving ring can directly output thrust. The mechanical structure is simple, the energy conversion links are few, and the efficiency is high.

[0240] (3) High thrust density: It directly converts electrical energy into mechanical thrust. The current and thrust are in a square relationship. By increasing the current, the thrust can be increased rapidly. The thrust density potential is great.

[0241] (4) Controllable thrust direction: By changing the sign of the phase difference between the two AC power sources (changing +π / 2 to -π / 2), the thrust direction can be reversed, which is convenient for bidirectional drive or attitude adjustment.

[0242] (5) Simple and reliable structure: It consists of only two ring coils, two power supplies and a force output shaft. There is no mechanical friction between moving parts (the moving ring and the insulating support frame are in sliding fit), resulting in low mechanical loss and long service life.

[0243] (6) It conforms to classical electromagnetic theory: Based on Maxwell's electromagnetic field theory and Ampere's law, it does not involve any assumptions beyond classical physics, the principle is clear, and the engineering feasibility is strong.

[0244] This invention has been described with reference to specific embodiments, but those skilled in the art will understand that various changes and equivalent substitutions can be made without departing from the scope of the invention. Furthermore, numerous modifications can be made to this invention to suit specific applications without departing from its protection scope. Therefore, this invention is not limited to the specific embodiments disclosed herein, but includes all embodiments falling within the scope of the claims.

Claims

1. A thrust device utilizing the double-ring electromagnetic delay effect, characterized in that, include: A fixed ring (1) is a closed ring coil made of conductive material, having a first terminal and a second terminal. The first terminal is used to connect to one output terminal of a first AC power supply, and the second terminal is used to connect to the other output terminal of the first AC power supply. The movable ring (2), a closed loop coil made of conductive material, is arranged coaxially with the fixed ring (1) and has a third terminal and a fourth terminal. The third terminal is used to connect to one output terminal of the second AC power supply, and the fourth terminal is used to connect to the other output terminal of the second AC power supply. The axial distance d between the fixed ring (1) and the movable ring (2) satisfies d = c / (4f), where f is the operating frequency of the first AC power supply and the second AC power supply, and c is the speed of light; The outer edge of the movable ring (2) is fixedly connected to a force output shaft (5), which extends axially away from the fixed ring (1) and is used to connect an external load.

2. The thrust device utilizing the double-ring electromagnetic delay effect according to claim 1, characterized in that, It also includes an insulating support frame (3), which is disposed between the fixed ring (1) and the movable ring (2). One end of the insulating support frame (3) is fixedly connected to the fixed ring (1), and the other end of the insulating support frame (3) is slidably connected to or clearance-fitted with the movable ring (2). The insulating support frame (3) is made of non-magnetic insulating material.

3. The thrust device utilizing the double-ring electromagnetic delay effect according to claim 1, characterized in that, It also includes a first high-frequency power supply (4) and a second high-frequency power supply. The two output terminals of the first high-frequency power supply (4) are electrically connected to the first terminal and the second terminal respectively, and are used to supply the fixed ring (1) with an alternating current of I0 cos(ωt). The two output terminals of the second high-frequency power supply are electrically connected to the third terminal and the fourth terminal respectively, and are used to supply the moving ring (2) with an alternating current of I0 cos(ωt + π / 2), where I0 is the peak current, ω is the angular frequency, and ω = 2πf.

4. The thrust device utilizing the double-ring electromagnetic delay effect according to claim 1, characterized in that, The fixed ring (1) is made of copper wire, and the movable ring (2) is made of copper wire.

5. The thrust device utilizing the double-ring electromagnetic delay effect according to claim 1, characterized in that, The fixed ring (1) is composed of a superconducting coil, and the movable ring (2) is composed of a superconducting coil.

6. The thrust device utilizing the double-ring electromagnetic delay effect according to claim 1, characterized in that, The radius R1 of the fixed ring (1) is equal to the radius R2 of the moving ring (2).

7. The thrust device utilizing the double-ring electromagnetic delay effect according to claim 1, characterized in that, The radius R1 of the fixed ring (1) is not equal to the radius R2 of the moving ring (2).

8. The thrust device utilizing the double-ring electromagnetic delay effect according to claim 1, characterized in that, The conductor cross-sections of the fixed ring (1) and the movable ring (2) are circular or rectangular.

9. The thrust device utilizing the double-ring electromagnetic delay effect according to claim 1, characterized in that, Cooling channels are provided inside the conductors of the fixed ring (1) and the movable ring (2), which extend along the axial direction of the conductors to accommodate circulating cooling medium.

10. The thrust device utilizing the double-ring electromagnetic delay effect according to claim 1, characterized in that, The fixed ring (1) is fixedly installed on the external reference frame bracket, and the movable ring (2) is axially movable on the linear guide rail via the force output shaft (5).

11. The thrust device utilizing the double-ring electromagnetic delay effect according to claim 1, characterized in that, The wires of the fixed ring (1) and the movable ring (2) are spirally or rectangularly coiled and fixed from the inside to the outside in the same plane.

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