Propulsion system using repulsive magnetic forces, a rotating wheel and tilting electromagnets

Abstract

The invention discloses a spacecraft propulsion system utilizing magnetic repulsion forces for efficient thrust generation. The system comprises a rotating electromagnet configured to generate a repulsive magnetic field upon activation. A stationary solenoid positioned within the housing interacts with the rotating electromagnet, generating an opposing magnetic force. A tether mechanism connects the rotating electromagnet to a rotating member, with an adjustable angle relative to the stationary solenoid. A magnetic bearing supports the rotation of the member for minimal friction. The core functionality involves generating a non-uniform magnetic field through the rotating electromagnet. The electromagnet is activated as it approaches the stationary solenoid, creating a repulsive force. This force is deactivated before full engagement and channeled through the angled tether mechanism to produce a net forward thrust for the spacecraft. The control system manages the activation sequence, timing, and tether angle adjustments to optimize propulsion efficiency. This invention offers a novel approach to spacecraft propulsion using magnetic forces, potentially lower to more efficient and controllable spacecraft maneuvering compared to traditional methods.

Description

Propulsion System using Repulsive Magnetic Forces, a rotating wheel and Tilting Electromagnets

[0001] Propulsion System using Repulsive Magnetic Forces, a rotating wheel and Tilting Electromagnets.

[0002] Conventional spacecraft propulsion systems primarily rely on chemical reactions or ion thrusters. Both approaches have limitations in terms of fuel efficiency, specific impulse (thrust per unit propellant), or complexity. There is a continuous need for innovative and potentially more efficient spacecraft propulsion technologies.

[0003] Conventional spacecraft propulsion systems primarily rely on chemical reactions or ion thrusters. Both approaches have limitations in terms of fuel efficiency, specific impulse (thrust per unit propellant), or complexity. There is a continuous need for innovative and potentially more efficient spacecraft propulsion technologies.

[0004] The present invention provides a solution to the problems of fuel inefficiency and limited thrust capabilities inherent in traditional spacecraft propulsion systems. By employing a magnetic repulsion-based mechanism, the invention offers a propulsion system that requires no propellant mass, thereby significantly reducing the spacecraft's weight and increasing its payload capacity.

[0005] Furthermore, the incorporation of a magnetic bearing to support the rotating magnet reduces friction to near zero, enhancing the system's efficiency and longevity. The adjustment mechanism for the angle of interaction ensures that the magnetic force can be finely tuned to achieve the desired thrust levels, providing a versatile solution adaptable to various mission requirements.

[0006] The future of space exploration hinges on efficient and reliable propulsion systems. Current technologies face limitations, often requiring heavy fuel loads, complex mechanisms, and high operational costs. This is where our groundbreaking new space propulsion system steps in, offering a paradigm shift in spacecraft movement.

[0007] The comprehensive solution to the technical problem involves a magnetic propulsion system that employs a rotating electromagnet and a stationary electromagnet, connected by a tether mechanism that allows for variable configurations. The system is designed to address the inefficiencies of traditional magnetic propulsion systems by creating a nonuniform magnetic field, which results in a more controlled and efficient propulsion force.

[0008] The propulsion system comprised of the following components:

[0009] Rotating Electromagnet: The core of the propulsion system, which generates a repulsion force when activated. Its rotation is central to the system’s ability to produce propulsion.

[0010] Stationary Electromagnet: Positioned to interact with the rotating electromagnet, the electromagnet is designed to exert an equal and opposite force, contributing to the system’s propulsion capabilities.

[0011] Tether Mechanism: A pivotal component that connects the rotating electromagnet to the rotating circle. The tether can be configured with a single connection or multiple connections (plurality of tethers) to allow for different operational modes.

[0012] Magnetic Bearing: Facilitates the rotation of the disk attached to the vehicle’s frame, ensuring smooth operation and reducing friction losses.

[0013] Propulsion Force Equation: The system’s effectiveness is encapsulated in the equation “ =propulsion force”, where “ ” represents the magnetic repulsion force and “ ” is the angle of the tether. This equation is central to the system’s design, allowing for the calculation and optimization of the propulsion force.

[0014] The rotating electromagnet is intended to rotate at a selective direction e.g. clockwise, from lower edge of the stationary electromagnet denoted as113ato the upper edge113bof the stationary electromagnet.

[0015] Initially, both electromagnets are off and the lower edge of rotating electromagnet is opposite of starting point114. At this time both electromagnets are turned on. Adjustment the rotating electromagnet on proper location for the first time can be done by an electric motor that is not illustrated, and by the commands from control and monitoring system 301.

[0016] The distance between the electromagnets starts increasing from107to110as the rotating magnet rotates by a slight tilt of rotating electromagnet. This creates a gradient of the magnetic field, having the strongest force concentrated at a distance of107and the weakest at110, consequently magnetic repulsion force direction is from the stronger magnetic field area to weaker field area. This criterion makes the rotating electromagnet to rotate around the wheel clockwise.

[0017] After passing the lower edge of rotating electromagnet 114a from the opposite of 113b, both electromagnets are turned off and rotating electromagnet follows rotation around wheel204.

[0018] As the rotating magnet104approaches the stationary magnet103, but before reaching the turn-on point114(before passing108distance), the electromagnets are deactivated. The rotating magnet continues its clockwise rotation until it reaches its initial position114, after passing the offset distance,108both of the electromagnets turned on and the sequence is repeated.

[0019] However, when the electromagnets103,104are fully or partially facing each other, the repulsive magnetic force from the stationary magnet103pushes the rotating electromagnet104. This force interacts with the tether106at an angle " ." This angled interaction is crucial.

[0020] The offset length108serves an important purpose. It prevents the rotating magnet from momentarily reversing its direction (counter-clockwise) when initially switched on. This ensures a smooth, consistent clockwise rotation, because the repulsion force in this area108is more than the of the rest facing area of stationary electromagnet pole i.e. the area between108to the second edge of stationary electromagnet113b.

[0021] The angled tether106decomposes the reaction force in to two components: , this component of the force acts in the direction perpendicular to the direction of thrust force, causing the rotating wheel to rotate. : this component acts in the opposite direction of the magnetic force from the rotating magnet104and It is considered a counter force (reaction force) that reduces the overall propulsion efficiency, neglecting very low friction of the magnetic bearing206. considering vacuum conditions and very low temperature in space that provides more ideal conditions to ignoring frictions, the thrust is calculated:T≈ (1- ).

[0022] The second component, causes the rotating wheel to rotate. For instance, if “ = 60 degrees, and neglecting very low friction of the magnetic bearing, thenThrust:T≈ (1- ) = 0.5 .

[0023] As soon as the second (upper) edge of the rotating electromagnet114bpasses the second (upper) edge of the stationary electromagnet113b, both electromagnets are turned off again, and the rotating electromagnet continues to rotate, until the next rotating electromagnet306a-306fis positioned after the off-set distance of108and the scenario repeats.

[0024] Overall, this system utilizes a rotating magnetic field and a strategically angled tether to generate a net forward thrust for spacecraft propulsion.

[0025] To achieve almost continuous thrust force using a plurality of rotating magnets and tethers, it is necessary to consider various factors such as the surface area of each electromagnet, the number of rotating magnets, the wheel circumference, and the proper timing for switching off and switching on the magnets.

[0026] The wheel circumference is the distance around the outer edge of the wheel204. It plays a crucial role in determining the distance covered by the wheel in one complete rotation. By understanding the wheel circumference and the speed of rotation, it is possible to calculate the distance traveled by the wheel in a given time frame.

[0027] When multiple rotating magnets are involved, along with their respective tethers, the collective forces generated by each electromagnet can contribute to a continuous thrust force. By coordinating the activation and deactivation of the electromagnets at the proper times, a smooth and consistent thrust force is applied to the system.

[0028] These advantageous effects demonstrate the invention’s potential to revolutionize the space transportation industry by providing a more efficient, controllable, and environmentally friendly alternative to traditional propulsion systems. The system’s innovative approach to utilizing magnetic forces for propulsion could pave the way for new applications and advancements in vehicle design and functionality.

[0029] Proper synchronization of the switching on and off of the magnets, taking into account the surface area of each electromagnet, the number of rotating magnets, and the wheel circumference, can help in creating a propulsion system that generates almost continuous thrust force for the desired application.

[0030] When two electromagnets are close and facing each other the magnetic field lines tend to bulge outwards at the ends, especially near the poles. This outward spread of the field lines is called fringing. The concave shape of the electromagnets in the system acts like a kind of magnetic "cup." When the electromagnets are activated, they generate a magnetic field. The concave shape helps to magnetic field channel and concentrate these field lines inwards.

[0031] The curved surface of the concave pole provides a more continuous path for the magnetic field lines to follow. This reduces the tendency for them to bulge outwards. The concave shape brings the lines closer together, further minimizing fringing. Magnetic field lines ideally prefer to form closed loops. The concave shape provides a more natural path for these loops to form within the electromagnets, reducing the need for them to stray outwards.

[0032] By minimizing fringing, the concave poles help to concentrate the magnetic field within a specific area. This creates stronger and more nonuniform magnetic field between the rotating and stationary electromagnets when they are close together. This stronger, focused field is crucial for generating a more efficient repulsive force for propulsion. Less energy is wasted on fringing field lines, lower to a more efficient use of power for generating the magnetic field.

[0033] In essence, the concave shape acts like a magnetic lens, focusing and confining the field lines within the electromagnets, lower to a stronger and more efficient interaction for the spacecraft propulsion system.

[0034] The disclosed system operates within the boundaries of conservation of momentum that states the total momentum of an isolated system remains constant if no external forces act on it.

[0035] This principle applies to an isolated system, meaning no external forces act on the system that can change its total momentum (both linear and angular). Forces exerted between objects within the system are considered internal forces. These forces can cause changes in motion within the system, but as long as there are no external forces, the total momentum of the system remains constant.

[0036] The spacecraft moves with a certain linear momentum. A tangential force applied within the spacecraft causes the wheel to rotate continuously. This internal force doesn't directly affect the linear motion of the spacecraft.

[0037] The tangential force causes a transfer of angular momentum to the wheel, making it spin. However, this angular momentum transfer happens entirely within the spacecraft. The internal force causing the wheel to rotate doesn't create an external force on the spacecraft itself. There's no "pushing back" against the spacecraft that would affect its linear motion.

[0038] The total momentum of the system (spacecraft + rotating wheel) is conserved because the internal force doesn't introduce any external momentum into the system.

[0039] According to the conservation of momentum law the rotation of the wheel caused by an internal force doesn't violate the linear motion of the spacecraft as long as the system remains isolated (no external forces). The key is that the momentum transfer due to the force happens entirely within the system, without affecting its overall linear momentum. On the other hand, rotation of wheel has no effect on the conservation of momentum because it acts like an energy sink for a portion of reaction force ( e.g. a cooling fan in a car consumes energy but has no effect on linear momentum of the car.

[0040] Linear Momentum Conservation:

[0041] Total momentum before = Total momentum after

[0042] Pbefore= mspacecraft. Vinitial

[0043] Pafter= mspacecraft. Vspacecraft+ mexhust. Vexhaust

[0044] mspacecraft. Vinitial= mspacecraft. Vspacecraft+ mexhust. Vexhaust

[0045] 0 = mspacecraft. Vspacecraft+ mexhust. Vexhaust

[0046] Vspacecraft= (mexhust. Vexhaust) / mspacecraft

[0047] The momentum goes out of system by rotating wheel because rotating wheel has no effect on the linear momentum of the spacecraft.

[0048] mexhust= mwheel

[0049] Vexhaust= Vwheel

[0050] Hence: Vspacecraft= (mwheel. Vwheel) / mspacecraft

[0051] By applying the conservation of momentum principle, we have shown that the total momentum of the system (rocket and wheel) before movement is equal to the total momentum after movement. This translates to the relationship between the final rocket velocity and the properties of the wheel speed, wheel mass and the total mass of the rocket.

[0052] The invention of a magnetic propulsion system with variable tether configurations offers several advantageous effects over traditional propulsion methods:

[0053] Enhanced Propulsion Efficiency: The system’s ability to create a nonuniform magnetic field through the strategic tilt of the stationary magnet and the rotating electromagnet results in a more efficient use of electromagnetic forces. This leads to a significant increase in propulsion efficiency, as the system can harness the full potential of the magnetic repulsion force.

[0054] Improved Vehicle Control: With the introduction of a tether mechanism that can be configured with either a single tether or a plurality of tethers, the system provides improved control over the propulsion force. This allows for precise adjustments to the vehicle’s speed and direction, offering a smoother and more responsive driving experience.

[0055] Adaptability to Various Conditions: The system’s design accommodates different operational conditions by allowing the angle of the tether to be adjusted. This adaptability ensures optimal performance across a range of environments and vehicle types, making the system versatile and practical for widespread application.

[0056] Reduced Energy Consumption: By optimizing the propulsion force equation “ - = propulsion force”, the system minimizes energy waste, lower to reduced energy consumption and longer operational periods between recharges or refueling.

[0057] Scalability and Customization: The system’s modular design allows for scalability and customization to fit various vehicle sizes and power requirements. This flexibility makes it an attractive option for manufacturers looking to implement magnetic propulsion in their vehicle designs.

[0058] Cost-Effectiveness: With fewer moving parts and a reliance on electromagnetic forces, the system potentially offers lower maintenance costs and longer service life compared to conventional propulsion systems.

[0059] Innovation and Technological Advancement: The invention represents a significant technological advancement in the field of propulsion systems. It opens up new possibilities for research and development, potentially lower to further innovations in magnetic propulsion technology.

[0060] Using an optional small electric motor to rotate the wheel in this magnetic propulsion system might have some benefits:

[0061] Smoother and More Consistent Thrust: As mentioned earlier, an electric motor could provide a more controlled and consistent rotation of the wheel. This could lead to a smoother and more consistent thrust force compared to relying solely on the repulsive force between the magnets. In some applications, a smoother thrust might translate to a more effective use of the generated thrust for maneuvering or achieving desired acceleration.

[0062] Start-up Assistance: The initial activation of the electromagnets might not provide enough force to overcome friction and start the wheel rotating. An electric motor could provide a "kickstart" to get the wheel spinning before relying on the magnetic repulsion for continuous operation.

[0063] Fine-Tuning Rotational Speed: The electric motor could allow for adjustment of the wheel's rotational speed. This flexibility might be useful for optimizing the magnetic interaction and potentially increasing overall efficiency.

[0064] Smoother and More Consistent Thrust: As mentioned earlier, an electric motor could provide a more controlled and consistent rotation of the wheel. This could lead to a smoother and more consistent thrust force compared to relying solely on the repulsive force between the magnets. In some applications, a smoother thrust might translate to a more effective use of the generated thrust for maneuvering or achieving desired acceleration.

[0065] Regenerative Braking: The motor could be used as a generator during deceleration phases, converting some of the kinetic energy back into electricity to be stored for later use.

[0066] System Stabilization: The motor could be used to provide small adjustments to the wheel's rotation for attitude control or stabilization of the spacecraft.

[0067] Fig.1

[0068] illustrates the position of a rotating electromagnet at the moment of turning-on the electromagnets.Fig. 2

[0069] shows the stationary and one rotating electromagnet connecting by a tether to rotating wheel.Fig.3

[0070] exhibits implementation of a plurality or rotating electromagnets

[0071] illustrates the position of a rotating electromagnet104at the moment of turning-on the electromagnets. The closer edge distance107is smallest separation between electromagnets makes magnetic field the most intense field in this region because electromagnets are at the closest separation and gradually the spacing between electromagnets is increased until110that the separation between electromagnets is the most separation distance. Concave shape of electromagnets prevents the magnetic field bending out and increases the efficiency and accuracy. The off-set distance108guarantees no reverse moving of the rotating electromagnet104, magnetic action force110, reaction magnetic force 112a, and 112b is illustrated in the figure. Adjustment system of tilt of rotating magnet105a, and105band the tether106is illustrated. The force diagram is labeled109and the central axis of the stationary electromagnet is labeled100.

[0072] shows the stationary and one rotating electromagnet connecting by a tether to rotating wheel. The size of rotating wheel can be much more than the electromagnets, based on adding more rotating electromagnets and tethers. The rotating wheel 204, magnetic bearing 206, the wheel rods 205a,205b,205c and 205d. are the added components to be rotate in the desired direction 203.

[0073] shows the stationary and one rotating electromagnet connecting by a tether to rotating wheel. The size of rotating wheel can be much more than the electromagnets, based on adding more rotating electromagnets and tethers. The rotating wheel 204, magnetic bearing 206, the wheel rods 205a,205b,205c and 205d. are the added components to be rotate in the desired direction 203.Examples

[0074] Example 1: Basic System with Copper Coils: This embodiment focuses on a fundamental design using readily available materials. The stationary electromagnet (103) consists of a coil made of copper wire with 1000 windings wrapped around a soft iron core with a diameter of 5 cm. The rotating electromagnet (104) is similar, but with a coil of 500 windings and a diameter of 3 cm.

[0075] The system operates with a DC current of 0.5 amperes. The distance (gap) between the stationary and rotating electromagnets (g) is maintained at a minimal value of 1 cm using adjustment screws (Fig. 4). The angle " " (109) is electronically controlled to optimize the decomposition force for spacecraft rotation. This example prioritizes simplicity and affordability for initial testing and development.

[0076] We can consider that convex shape of facing poles of electromagnets compensates the fringing out field and non-uniform field effects, such that provides a good estimation to calculation in ideal conditions hence:

[0077] where: B is the magnetic field inside the solenoid (Tesla), is the permeability of free space (4π x 10-7Tm / A), n is the number of turns (1000 for the larger magnet and 5,000 for the smaller magnet), is the current (0.5 Amperes), is the length of the solenoid (difficult to determine without knowing the coil geometry. We can estimate it by assuming the coil length is roughly equal to the core diameter). The length of electromagnets are 5 cm and 3 cm.

[0078] Repulsive Force Calculation:

[0079]

[0080] F is the repulsive force (Newtons), B1and B2are the magnetic fields within each electromagnet (previously calculated), A is the area of the pole face (assuming circular magnets), is the permeability of free space (4π x 10-7Tm / A), g is the gap between the electromagnets 1 cm.

[0081] Area of larger magnet (A1): π x (diameter / 2)² = π (5 cm / 2)² ≈ 0.00196 m².

[0082] Area of smaller magnet (A2): π (diameter / 2)² = π x (3 cm / 2)² ≈ 0.0007 m².

[0083]

[0084] If we assume the angle between tether and axis of the stationary electromagnet is 60 degrees, thrust force will be:

[0085] Thrust = 0.55 N (1 - sin 60) ≈ 0.275 N = 28 gram-force

[0086] Example 2: Repulsive Force Calculation (cored): Considering that the saturation magnetic flux density (Bsat​) of an ferromagnetic core, e.g. grain oriented electrical steel is typically around 1.9 to 2.1 Tesla. We take the conservative amount for saturation at 0.5 T because of the very small separation of electromagnets that leads to non-uniform magnetic field and magnetic field fringing out to be close to real conditions.

[0087] Repulsive Force Calculation (cored): Considering that the saturation magnetic flux density (Bsat​) of an ferromagnetic core, e.g. grain oriented electrical steel is typically around 1.9 to 2.1 Tesla. We take the conservative saturation at 0.5 T because of the very small separation of electromagnets that leads to non-uniform magnetic field and magnetic field fringing out to be close to real conditions.

[0088]

[0089]

[0090] Note: Since the identical poles are facing each other, they will repel each other. The force will be calculated just by accounting smaller area that is closer to realistic condition. F ≈ 70 Newtons (This is an estimated value based on assumed coil lengths and circular magnet faces) If we assume the angle between tether and axis of the stationary electromagnet is 60 degrees, thrust force will be:

[0091] Thrust = 70 N × (1 - sin 60) ≈ 35 N =3.57 kgf

[0092] Example 3: If very strong magnets employed, the thrust force is enough to move spacecraft in space, for instance if a big superconducting electromagnet that has 2 T, magnetic field and the cross section of loop to be 1 m2, the propulsion force will be 0.8 MN that is equal to propulsion force of a big train.

[0093]

[0094] This invention relates to a magnetic propulsion system for spacecraft and other vehicles operating in a vacuum environment. The invention is particularly applicable to applications where efficient, low-friction propulsion is desired, such as:

[0095] Attitude control and station keeping of satellites: The system's ability to generate precise and controllable thrust makes it suitable for maneuvering and stabilizing spacecraft in orbit.

[0096] Orbit transfer and deep space exploration: The contactless, frictionless nature of the propulsion system can potentially offer high efficiency and low fuel consumption for missions requiring orbit changes or deep space travel.

[0097] The propulsion system disclosed herein is particularly applicable to vehicles operating in a vacuum environment, such as spacecraft. However, the principles of the invention may also be adaptable to other applications requiring controlled, propulsion.

[0098] This invention discloses a magnetic propulsion system for spacecraft. The system utilizes electromagnets to generate a controlled thrust force. When employing high-strength electromagnets, such as superconducting electromagnets, the invention explores the potential to function as a combined gravity simulator and propulsion system for space vehicles.

Claims

A spacecraft propulsion system, comprising:a housing;a rotating electromagnet disposed within the housing, configured to generate a repulsive magnetic force when activated;a stationary solenoid disposed within the housing, positioned to interact with the rotating electromagnet and generate an opposing magnetic force;a tether mechanism connecting the rotating electromagnet to a rotating member, the tether mechanism configured with an adjustable angle relative to an axis of the stationary solenoid;a magnetic bearing disposed within the housing, supporting the rotation of the rotating member with minimal friction;a control system configured to:activate and deactivate the electromagnets based on a predetermined sequence and timing; andadjust the tether angle to optimize a net forward thrust for the spacecraft.The spacecraft propulsion system of claim 1, wherein the rotating electromagnet and the stationary solenoid have a concave shape to minimize fringe effects of the magnetic field.The spacecraft propulsion system of claim 1, wherein the tether mechanism is configured with a plurality of tethers connectable to the rotating member at different positions, facilitating the generation of a near-continuous thrust force.The spacecraft propulsion system of claim 1, further comprising a sensor system configured to measure operational parameters, such as the distance between the electromagnets and the rotational speed of the rotating member, the control system utilizing the measured parameters to optimize the activation sequence and timing of the electromagnets.The spacecraft propulsion system of claim 1, wherein the control system is further configured to synchronize the activation and deactivation of the electromagnets based on:surface area of each electromagnet;number of rotating magnets within the housing; andcircumference of the rotating member.A method for propelling a spacecraft using a magnetic propulsion system, the method comprising the steps of:rotating an electromagnet within a housing to generate a non-uniform magnetic field;activating the electromagnet as it approaches a stationary solenoid positioned within the housing, creating a repulsive force;deactivating the electromagnet before it fully faces the stationary solenoid;utilizing a tether mechanism angled relative to the stationary solenoid to convert the repulsive force into a net forward thrust for the spacecraft;adjusting the angle of the tether mechanism to optimize the thrust force; and,monitoring operational parameters, such as the distance between the electromagnets and the rotational speed of the rotating member, and utilizing the monitored parameters to adjust the activation sequence and timing of the electromagnet for optimized propulsion.The method of claim 6, wherein the activation and deactivation of the electromagnet are synchronized based on:surface area of each electromagnet;number of rotating magnets within the housing; andcircumference of the rotating member.The method of claim 6, further comprising utilizing a plurality of tethers connected to the rotating member at different positions to facilitate the generation of a near-continuous thrust force.The propulsion system utilizes a low-power electric motor for adjustment, control and braking of wheel.

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