Hybrid space propulsion system with hinged electromagnetic repulsion and differential damping mechanism

Abstract

A hybrid space propulsion system enhances efficiency in spacecraft manoeuvring by integrating an electromagnetic repulsion mechanism with a hinged actuator, a differential damping mechanism, and a conveyor reset mechanism. The electromagnetic repulsion mechanism, utilizing opposing electromagnets and a hinge to store and release potential energy, imparts a forward impulse to a housing and a backward impulse to a movable mass. The differential damping mechanism, combining eddy dampers and a rocket propulsion system, retains the housing's momentum while slowing the movable mass, delivering a net system impulse through controlled propellant ejection. A conveyor mechanism resets the movable mass using internal forces, enabling repeated cycles without additional propellant. This system achieves high thrust and reduced propellant mass compared to standalone rocket propulsion systems, suitable for applications such as orbital transfers and station-keeping.

Description

[0001] HYBRID SPACE PROPULSION SYSTEM WITH HINGED ELECTROMAGNETIC REPULSION AND DIFFERENTIAL DAMPING MECHANISM Background of the Invention

[0002] 1. Field of the Invention: This invention pertains to spacecraft propulsion systems, specifically a hybrid mechanism integrating electromagnetic repulsion, differential damping, and mechanical reset to achieve efficient orbital manoeuvres with reduced propellant mass and enhanced thrust.

[0003] 2. Description of Related Art: Conventional spacecraft propulsion systems, such as cold gas thrusters, rely solely on propellant expulsion to generate impulse, resulting in high fuel consumption and limited thrust for significant velocity changes (e.g., lunar injection orbits). Other systems, like ion thrusters, offer high efficiency but low thrust, while chemical rockets provide high thrust at the cost of substantial fuel mass. There remains a need for a propulsion system that combines high thrust, low propellant use, and rapid velocity delivery within compact spacecraft designs, leveraging both electrical and mechanical energy to optimize efficiency.

[0004] Summary of the Invention

[0005] The present invention provides a hybrid space propulsion system comprising:

[0006] a. An electromagnetic repulsion mechanism utilizing a hinged actuator to maximize potential energy storage and release, accelerating a primary housing and a movable mass apart.

[0007] b. A differential damping mechanism employing eddy dampers and a rocket propulsion system to retain a substantial portion of the housing’s momentum while slowing the movable mass, imparting a net impulse via controlled propellant ejection and differential damping.

[0008] c. A conveyor reset mechanism to return the movable mass to its initial position using internal forces, enabling continuous cycling.

[0009] This hybrid process enhances efficiency by generating a large internal impulse electrically, converting it into net system momentum with minimal propellant, and resetting mechanically without additional fuel expenditure, outperforming traditional rocket propulsion systems in thrust and fuel economy.

[0010] Detailed Description

[0011] The propulsion system operates in a cyclical process designed for efficiency:

[0012] 1. Electromagnetic Repulsion Phase :

[0013] a. An electromagnetic actuator, comprising opposing electromagnets mounted on a housing and a movable mass, generates a repulsion force.

[0014] b. A hinge mechanism connects the housing and movable mass, initially holding the electromagnets in close proximity to build potential energy as the magnetic field strengthens.c. Upon reaching maximum potential energy (determined by field strength and hinge tension), the hinge releases, allowing the stored energy to convert into kinetic energy, repelling the housing forward and the movable mass backward. d. The duration and force of repulsion are optimized to constrain displacement within the spacecraft’s compact dimensions, maximizing impulse delivery. 2. Differential Damping Phase:

[0015] a. Following repulsion, a damping mechanism engages to manage the relative velocities:

[0016] i. Eddy Dampers: Induce electromagnetic drag forces, slowing the movable mass more significantly than the housing, preserving a substantial fraction of the housing’s forward momentum.

[0017] ii. Rocket Propulsion System: Ejects a controlled amount of propellant from the movable mass, supplementing damping and providing a net forward impulse to the system.

[0018] b. The combined damping ensures the housing retains a significant velocity while the movable mass is decelerated, converting internal momentum into net system momentum with minimal propellant use.

[0019] 3. Conveyor Reset Phase:

[0020] a. A mechanical conveyor mechanism, powered by onboard electrical energy (e.g., motors or springs), applies internal forces to return the movable mass to its initial position relative to the housing.

[0021] b. The reset occurs without propellant expenditure, maintaining the system’s net momentum and enabling rapid repetition of the cycle.

[0022] Operational Efficiency:

[0023] a. The EM repulsion phase leverages electrical energy to generate a large internal impulse, reducing reliance on propellant compared to standalone rocket propulsion systems.

[0024] b. The differential damping phase optimizes momentum retention and adds net impulse with a high-efficiency propellant ejection, enhancing specific impulse over traditional systems.

[0025] c. The conveyor reset ensures continuous operation without fuel loss, amplifying efficiency for sustained manoeuvres.

[0026] Applications:

[0027] a. Suitable for orbital transfers (e.g., lunar injection), station-keeping, or collision avoidance in compact spacecraft, offering high thrust and low fuel mass.

Claims

CLAIMS1. A hybrid space propulsion system for a spacecraft, comprising:a. a housing (1) configured as a primary propelled mass;b. a movable mass (2) positioned relative to the housing (1);c. an electromagnetic repulsion mechanism including:i. a pair of electromagnets, one mounted on the housing (1) and one on the movable mass (2);ii. a hinge mechanism (4) configured to hold the electromagnets in proximity to build potential energy and release them upon reaching maximum repulsion, imparting a forward impulse to the housing (1) and a backward impulse to the movable mass (2);d. a differential damping mechanism including:i. an eddy damper (5) configured to apply a greater decelerating force to the movable mass (2) than to the housing (1), retaining a portion of the housing’s (1) forward momentum achieved due to repulsion;ii. a rocket propulsion system (6) mounted on the movable mass (2), configured to eject propellant and provide a net forward impulse to the system and assist in the differential damping,e. a conveyor mechanism (8) configured to reset the movable mass (2) to its initial position relative to the housing (1) using internal forces, enabling cyclical operation.

2. The system of claim 1, wherein the electromagnetic repulsion mechanism is configured to maximize impulse delivery within a constrained displacement by adjusting the duration of repulsion force application based on the release of the hinge mechanism (2).

3. The system of claim 1, wherein the differential damping mechanism combines electrical damping from the eddy damper (5) and propellant-based damping from the rocket propulsion system (6) to optimize momentum retention in the housing (1) while imparting net system momentum.

4. The system of claim 1, wherein the conveyor mechanism (8) operates without propellant expenditure, utilizing onboard electrical or mechanical energy to reset the movable mass (2), thereby enhancing fuel efficiency.

5. A method for propelling a spacecraft efficiently, comprising the steps of:a. generating an electromagnetic repulsion force between a housing (1) and a movable mass (2) using a hinged actuator (4), wherein the hinge mechanism (2) builds potential energy until maximum repulsion is achieved, then releases to impart a forward impulse to the housing (1) and a backward impulse to the movable mass (2);b. applying differential damping to the housing (1) and movable mass (2), wherein an eddy damper (5) slows the movable mass (2) more than the housing (1), and a rocket propulsion system (6) ejects propellant from the movable mass (2) to provide a net forward impulse to the system and also helps achieve efficient differential damping;c. resetting the movable mass (2) to its initial position relative to the housing (1) using a conveyor mechanism (8) powered by internal forces, without additional propellant use;d. repeating the cycle to achieve a desired change in velocity with reduced propellant mass compared to a standalone rocket propulsion system.

6. The method of claim 5, wherein the electromagnetic repulsion force is maximized by storing potential energy in the hinge mechanism (4) until full repulsion, optimizing impulse within a compact spacecraft length.

7. The method of claim 5, wherein the differential damping step retains a substantial fraction of the housing’s (1) momentum electrically via the eddy damper (5) and the rocket propulsion system(6), minimizing the propellant mass required from the rocket propulsion system to hold the moving mass within the spacecraft.

8. The method of claim 5, wherein the resetting step preserves the net momentum gained from the propellant ejection by the rocket propulsion system (6), enabling continuous operation with enhanced specific impulse.

9. A spacecraft propulsion system, comprising:a. a housing (1) and a movable mass (2);b. means for generating an electromagnetic repulsion force between the housing (1) and the movable mass (2), including a hinged mechanism (4) to store and release potential energy for maximum impulse by repulsion or attraction; c. means for differentially damping the housing (1) and movable mass (2), combining eddy current damping (5) and propellant ejection from a rocket propulsion system (6) to retain housing (1) momentum and impart net system impulse and velocity;d. means for mechanically resetting (8) the movable mass (2) to its initial position using internal energy, facilitating repeated cycles with minimal propellant consumption.

10. The system of claim 9, wherein the means for generating electromagnetic repulsion force optimizes impulse delivery within a constrained displacement, enhancing thrust efficiency.

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