Reaction coupling type momentum transfer propulsion system and method

Abstract

The invention discloses a reaction coupling type momentum transfer propulsion system and method, and relates to the technical field of aerospace propulsion, and the reaction coupling type momentum transfer propulsion system comprises a double-momentum operation orbit, a synchronous deflection unit and a momentum conversion medium; the propelling method comprises the steps that the double tracks are unfolded, the momentum conversion medium is accurately accelerated through force equal in size and opposite in direction, counter-acting force is offset as much as possible, the double tracks synchronously deflect to the target direction to a preset angle after a certain speed is reached, the momentum conversion medium is decelerated to be relatively static, and the counter-acting force borne by the tracks in the process serves as propelling power; reverse synchronous acceleration and reverse synchronous deflection are adopted, counter-acting force is coupled and counteracted as far as possible to maintain system stability, pure electric energy is adopted for driving, no mass loss exists in the propelling process, and repeated propelling can be achieved, so that the higher acceleration upper limit is achieved. The method is suitable for medium-long distance space electromagnetic propulsion, deep sea equipment propulsion and other scenes.

Description

Technical Field

[0001] This application relates to the field of aerospace propulsion technology, specifically a reaction-coupled momentum transfer propulsion system suitable for the space environment. Background Technology

[0002] Deep space exploration missions present new challenges to space propulsion technology. While current mainstream chemical propulsion systems are technologically mature, their low specific impulse results in enormous fuel loads, severely limiting spacecraft payload and range. Although the emerging electric propulsion technology has significantly improved specific impulse and alleviated the fuel-quality issue, it still cannot eliminate dependence on propellants. In the unreliable environment of deep space, propellant depletion becomes an insurmountable obstacle.

[0003] Therefore, fuel-free propulsion is considered crucial for deep space exploration. Theoretically, pure electric propulsion is the ideal solution. However, due to the law of conservation of momentum, traditional spacecraft must jettison mass backward to gain forward acceleration. This means that even the most advanced electromagnetic acceleration schemes essentially require consuming the spacecraft's own mass as a propellant. This leads to a fundamental dilemma in long-distance deep space travel: the finite nature of the propellant will ultimately limit range and maneuverability. Summary of the Invention

[0004] Therefore, it is necessary to address the aforementioned technical problems by providing a method that can enhance internal kinetic energy through reaction force coupling and indirectly accelerate the spacecraft through momentum transfer, thereby achieving stable propulsion without releasing mass, even when the working propellant cannot be replenished.

[0005] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is a reaction-coupled momentum transfer propulsion system, comprising:

[0006] Dual-momentum orbit, synchronous deflection unit, momentum conversion medium;

[0007] The dual-momentum running track consists of two straight tracks, the ends of which are connected by the synchronous deflection unit and lie on the same straight line. The track specifications are consistent, including an electromagnetic drive coil and a circumferentially distributed electromagnetic stabilization array.

[0008] The synchronous deflection unit includes two high-precision servo motors, which control the deflection angle of the track from the connected end of the track respectively;

[0009] The momentum conversion medium consists of two conductors or magnets of the same size, mass, and density, located within the dual orbits, and capable of electromagnetic interaction.

[0010] During propulsion, the dual tracks are deployed, and forces of equal magnitude and opposite direction are used to precisely accelerate the momentum conversion medium, counteracting the reaction force as much as possible. After reaching a certain speed, the dual tracks synchronously deflect towards the target direction to a preset angle, decelerating the momentum conversion medium to relative rest. During this process, the reaction force on the tracks serves as the propulsion power.

[0011] Furthermore, to overcome the limitations of the working fluid, the electromagnetic drive coil, electromagnetic stabilization array, and synchronous deflection unit are all driven by pure electrical energy. The dual-momentum running track has no material exchange with the outside world, and can provide propulsion without losing mass.

[0012] Furthermore, in order to make the most of the momentum to run the track length, the electromagnetic drive coils are mainly distributed at both ends of the track, which increases the acceleration before the track deflects and enhances the deceleration capability after the track deflects.

[0013] Furthermore, in order to convert the acquired internal energy into external kinetic energy, a synchronous deflection unit is used to deflect the orbit and modify the motion direction of the momentum conversion medium. When the starting point of the medium is at the centrifugal end, although the medium's kinetic energy will be lost due to centrifugal force, the stability of the system is ensured, and the remaining momentum of the medium can be used for propulsion.

[0014] A reaction-coupled momentum transfer propulsion method, characterized by the following steps:

[0015] Step 1: The synchronous deflection unit unfolds the dual-momentum running track to 180°, forming a 90° angle with the propulsion direction;

[0016] Step 2: The momentum conversion medium is placed at the distal or proximal end of the dual-track symmetry to ensure that it is constrained by the electromagnetic stabilization array.

[0017] Step 3: The electromagnetic drive coil accelerates the momentum conversion medium along the track direction, with equal magnitude but opposite direction of acceleration.

[0018] Step 4: After reaching a certain speed, if the initial placement position is at the distal end and the acceleration direction is at the proximal end, the synchronous deflection unit deflects the double track in the opposite direction of the propulsion direction; if the initial placement position is at the proximal end and the acceleration direction is at the distal end, the synchronous deflection unit deflects the double track in the propulsion direction. During the process, the electromagnetic stabilization array ensures that the momentum conversion medium is correctly constrained.

[0019] Step 5: After the dual tracks deflect to the preset angle, they stop. The remaining velocity of the momentum conversion medium is continuously decelerated by the electromagnetic drive coil until it is in a relatively stationary state.

[0020] Step 6: The electromagnetic drive coil locks the position of the momentum conversion medium within the track. After the synchronous deflection unit unfolds the dual-momentum running track again, the momentum conversion medium is synchronously advanced to the initial position to stand by.

[0021] The present invention has the following beneficial effects:

[0022] ① This invention cleverly utilizes reverse synchronous acceleration and reverse synchronous deflection to achieve coupling cancellation of system reaction forces, converting internal energy into external kinetic energy while ensuring system stability, thus achieving propulsion without working fluid loss.

[0023] ②This invention enables repeated propulsion in the space environment, has a high acceleration limit in long-distance missions, and can perform more distant deep space exploration missions.

[0024] ③ This invention uses electromagnetic drive and electromagnetic constraint, with no direct contact during momentum conversion, resulting in low wear rate and long service life.

[0025] ④ The mechanical structure of this invention is simple, and it does not require carrying a large amount of propellant and related storage tanks and pipeline systems, resulting in a high effective payload.

[0026] ⑤ This invention uses pure electric propulsion, which can achieve energy self-circulation by relying on solar energy, and the propulsion cost is low. Attached Figure Description

[0027] Figure 1 is a schematic diagram of the overall simulation of the reaction-coupled momentum transfer propulsion system provided by the present invention;

[0028] Figure 2 is a flowchart of the reaction-coupled momentum transfer propulsion system provided by the present invention operating from the distal end as the starting position.

[0029] Figure 3 is a flowchart of the reaction-coupled momentum transfer propulsion system provided by the present invention operating from the proximal end as the starting position. Detailed Implementation

[0030] The present application will now be described in further detail with reference to the accompanying drawings and embodiments.

[0031] This application discloses a reaction-coupled momentum transfer propulsion system and method. (Refer to...) Figure 1 A reaction-coupled momentum transfer propulsion system includes a dual-momentum running track 1, electromagnetic drive coils 2 arranged at both ends of the track, an electromagnetic stabilizing array 3 surrounding the track, and a synchronous deflection unit 4 connected to the end of the track. (Refer to...) Figure 2 5, the momentum conversion medium located within the orbit.

[0032] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, 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 some embodiments of the present invention, and not all embodiments. Specific implementation can reduce the difficulty of implementation by decreasing the propulsion speed and efficiency, and the specific implementation scheme will be determined based on objective factors such as material limitations.

[0033] Example 1: Structural Implementation of a Reaction-Coupled Momentum Transfer Propulsion System

[0034] Track layout: The system uses two straight circular tracks 1, each 20m long, connected by a carbon fiber frame. The overall weight of a single track does not exceed 5 tons.

[0035] Carbon fiber frame: The circular thin-walled tube is made of T1000 grade carbon fiber wound into shape, with 35% of the circumferential fiber, 55% of the axial fiber, and 10% of the ±45° oblique fiber.

[0036] Electromagnetic drive coil: The electromagnetic drive coil 2 is mainly composed of segmented copper winding coils set at both ends of the track. Each end is 5m long and uses an independent frequency conversion power supply. The response time is ≤10ms. The reaction force cancellation error during acceleration is controlled within ±5%. The speed data is fed back in real time through distributed Hall sensors.

[0037] Electromagnetic stabilization array: The electromagnetic stabilization array consists of 12 groups of neodymium iron boron permanent magnets distributed circumferentially. The magnetic flux density of a single group is 0.5T and the spacing between adjacent units is 2m, which generates radial magnetic force constraint.

[0038] Synchronous deflection unit: At the end of the orbit, synchronous deflection unit 4 is connected to the spacecraft. It is driven by a 5kW servo motor and a planetary gearbox with a rated output torque of 70,000 N·m.

[0039] The two momentum conversion media 5 are made of aerospace-grade aluminum alloy Al-7075 (3mm wall thickness) and filled with copper. The surface is embedded with a Hellbeck permanent magnet array, with a pole spacing of 0.2m and a peak magnetic field of 0.3T. The overall mass is 200kg.

[0040] Example 2: Specific Operation Procedures of the Propulsion Method

[0041] The synchronous deflection unit 4 unfolds the dual-momentum running track 1 to 180°, forming a 90° angle with the propulsion direction;

[0042] The momentum conversion medium 5 is placed at the distal or proximal end of the symmetrical double track 1 to ensure that it is constrained by the electromagnetic stabilization array 3.

[0043] The electromagnetic drive coil 2 accelerates the momentum conversion medium 5 along the track direction, with equal magnitude but opposite direction of acceleration.

[0044] After reaching a certain speed, see Figure 2 If the initial placement position is at the distal end and the acceleration direction is at the proximal end, then the synchronous deflection unit deflects the dual tracks in the opposite direction of the propulsion direction in four directions; see Figure 3If the initial placement position is at the proximal end and the acceleration direction is at the distal end, the synchronous deflection unit 4 deflects the dual tracks in the propulsion direction. During the process, the electromagnetic stabilization array 3 ensures that the momentum conversion medium 5 is correctly constrained.

[0045] After the dual track 1 deflects to a preset angle and stops, the remaining velocity of the momentum conversion medium 5 is continuously decelerated by the electromagnetic drive coil 2 until it is in a relatively stationary state.

[0046] The electromagnetic drive coil 2 locks the position of the momentum conversion medium 5 within the track 1. After the synchronous deflection unit 4 re-deploys the dual-momentum running track 1, the momentum conversion medium 5 is synchronously advanced to the initial position to stand by.

Claims

1. A reaction-coupled momentum transfer propulsion system, characterized in that, Includes a dual-momentum orbit, a synchronous deflection unit, and a momentum conversion medium; The dual-momentum running track consists of two straight tracks, with their ends connected by the synchronous deflection unit. The tracks maintain the same specifications and lie on the same straight line, and include an electromagnetic drive coil and a circumferentially distributed electromagnetic stabilization array. The synchronous deflection unit includes two high-precision servo motors, which control the deflection angle of the track respectively; The momentum conversion medium consists of two conductors or magnets of the same size, mass, and density, located within the dual orbits, and capable of electromagnetic interaction. During propulsion, the dual tracks are deployed, and forces of equal magnitude and opposite direction are used to precisely accelerate the momentum conversion medium, counteracting the reaction force as much as possible. After reaching a certain speed, the dual tracks synchronously deflect towards the target direction to a preset angle, decelerating the momentum conversion medium to relative rest. During this process, the reaction force on the tracks serves as the propulsion power.

2. The reaction-coupled momentum transfer propulsion system according to claim 1, characterized in that: The dual-momentum orbit is a closed system with no exchange of matter with the outside world, and its interior is in a vacuum state.

3. The reaction-coupled momentum transfer propulsion system according to claim 1, characterized in that: The electromagnetic drive coils are mainly distributed at both ends of the track, and can accelerate or decelerate the momentum conversion medium according to the settings.

4. The reaction-coupled momentum transfer propulsion system according to claim 1, characterized in that: When the electromagnetic stabilizing array interacts with the momentum conversion medium, it generates a constraint force pointing towards the center of the track. When the track deflects as a whole, the magnitude of the constraint force can be adjusted to maintain stability.

5. The reaction-coupled momentum transfer propulsion system according to claim 1, characterized in that: The synchronous deflection unit deflects the two tracks in opposite directions at the same speed and angle during operation, ensuring that the anti-torque is canceled out.

6. The reaction-coupled momentum transfer propulsion system according to claim 1, characterized in that: The momentum conversion medium must be able to withstand high overload, strong electromagnetic environment and vacuum state in space for a long time.

7. A reaction-coupled momentum transfer propulsion method, characterized in that: Includes the following steps: Step 1: The synchronous deflection unit unfolds the dual-momentum running track to 180°, forming a 90° angle with the propulsion direction; Step 2: The momentum conversion medium is placed at the distal or proximal end of the dual-track symmetry to ensure that it is constrained by the electromagnetic stabilization array. Step 3: The electromagnetic drive coil accelerates the momentum conversion medium along the track direction, with equal magnitude but opposite direction of acceleration. Step 4: After reaching a certain speed, if the initial placement position is at the distal end and the acceleration direction is at the proximal end, the synchronous deflection unit deflects the double track in the opposite direction of the propulsion direction; if the initial placement position is at the proximal end and the acceleration direction is at the distal end, the synchronous deflection unit deflects the double track in the propulsion direction. During the process, the electromagnetic stabilization array ensures that the momentum conversion medium is correctly constrained. Step 5: After the dual tracks deflect to the preset angle, they stop. The remaining velocity of the momentum conversion medium is continuously decelerated by the electromagnetic drive coil until it is in a relatively stationary state. Step 6: The electromagnetic drive coil locks the position of the momentum conversion medium within the track. After the synchronous deflection unit unfolds the dual-momentum running track again, the momentum conversion medium is synchronously advanced to the initial position to stand by.

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