Electromagnetic propulsion device and propulsion control method for polar orbiting satellites

Abstract

The present application relates to the technical field of spacecraft electromagnetic propulsion, and particularly relates to an electromagnetic propulsion device for polar orbit satellite and a propulsion control method, aiming at solving the technical problem of short service life of artificial satellite in the prior art. The electromagnetic propulsion device comprises a power supply assembly and a propulsion assembly; the power supply assembly is electrically connected with the propulsion assembly, and the two form a circuit loop; the propulsion assembly is used for shielding current passing through itself and is used for connecting with a spacecraft. The electromagnetic propulsion device does not need to use working medium such as liquid, gas and plasma, and obtains propulsive force through cooperation of the earth space magnetic field and the current, thereby reducing the cost of the propulsion device and greatly improving the service life of the on-orbit satellite.

Description

Technical Field

[0001] This invention relates to the field of electromagnetic propulsion technology for spacecraft, and in particular to an electromagnetic propulsion device and propulsion control method for polar orbit satellites. Background Technology

[0002] Polar orbit refers to the orbit of an artificial Earth satellite with an orbital plane at an angle of 90° to the equatorial plane. Artificial satellites using polar orbit can fly over the entire globe and have wide applications in meteorological observation, navigation, and Earth resource reconnaissance.

[0003] Artificial satellites in orbit are affected by factors such as celestial gravity, solar radiation pressure, and near-Earth atmospheric drag, which frequently cause changes in attitude or deviations from their target orbits, thus affecting their normal operation and safe functioning. Therefore, artificial satellites in orbit typically require propulsion systems to correct their flight attitude and orbit.

[0004] Currently, the propulsion systems of on-orbit satellites primarily use liquid, gas, and plasma propellants. However, due to the high cost of space launches, the amount of propellant a satellite can carry is extremely limited. Therefore, once the propellant is depleted, the satellite cannot continue operating normally, severely limiting its operational lifespan. Summary of the Invention

[0005] The purpose of this invention is to provide an electromagnetic propulsion device and propulsion control method for polar orbit satellites, so as to alleviate the technical problem of short operational life of artificial satellites in related technologies.

[0006] To solve the above-mentioned technical problems, the technical solution provided by the present invention is as follows:

[0007] An electromagnetic propulsion device for a polar orbit satellite includes: a power supply assembly and a propulsion assembly; the power supply assembly is electrically connected to the propulsion assembly, and the two form a circuit loop; the propulsion assembly is used to shield current passing through it from external sources and is used to connect to a spacecraft.

[0008] Furthermore, the propulsion assembly includes an electromagnetic propulsion cylinder; the power supply assembly is disposed inside the electromagnetic propulsion cylinder and electrically connected to the two metal ends of the electromagnetic propulsion cylinder; the electromagnetic propulsion cylinder is used to shield the current passing through the power supply assembly.

[0009] Furthermore, the body of the electromagnetic propulsion cylinder comprises, from the inside out, a high magnetic permeability layer, an insulating layer, and a high electrical conductivity non-magnetic layer; the high magnetic permeability layer, the insulating layer, and the high electrical conductivity non-magnetic layer are connected as a whole.

[0010] Furthermore, the propulsion assembly also includes an insulating connector; the insulating connector is used to connect the electromagnetic propulsion cylinder to the spacecraft.

[0011] Furthermore, the insulating connector includes an insulating connecting rod; one end of the insulating connecting rod is perpendicularly connected to the body of the electromagnetic propulsion cylinder, and the other end is used to connect to the spacecraft.

[0012] Furthermore, the power supply assembly includes a power supply component; the power supply component has a positive terminal and a negative terminal, the positive terminal and the negative terminal being electrically connected to the two metal terminals respectively.

[0013] Furthermore, the power supply includes a driving power supply; two metal conductors are provided between the driving power supply and the two metal ends, one end of the metal conductors is connected to the metal ends, and the other end is connected to the electrodes of the driving power supply.

[0014] Furthermore, the metal guide bar is insulated from the inner circumferential surface of the electromagnetic propulsion cylinder.

[0015] A propulsion control method employing an electromagnetic propulsion device for polar orbit satellites includes the following steps: connecting an electromagnetic propulsion cylinder to a spacecraft via an insulated connecting rod, and ensuring that the length direction of the electromagnetic propulsion cylinder is perpendicular to the orbital direction of the spacecraft; adjusting the magnitude of the output current of the drive power supply when the spacecraft flies over the Earth's South Pole or North Pole.

[0016] Furthermore, when the spacecraft flies over the Earth's South Pole or North Pole, the direction of current flow of the drive power supply is changed.

[0017] In summary, the technical effects achieved by this invention are as follows:

[0018] The electromagnetic propulsion device for polar orbit satellites provided by the present invention includes a power supply component and a propulsion component; the power supply component and the propulsion component are electrically connected to form a circuit loop; the propulsion component is used to shield currents passing through it from external sources and is used to connect to the spacecraft.

[0019] In this application, the power supply component and the propulsion component are electrically connected. When the power supply component is started, current flows from the positive terminal of the power supply component to the propulsion component, and then flows back from the propulsion component to the negative terminal of the power supply component, forming a closed loop, i.e., a circuit loop. When magnetic field lines act on this circuit loop, since the propulsion component shields the current flowing through it, the resultant force generated between the magnetic field lines and the circuit loop is the force generated by the magnetic field lines and the current flowing through the propulsion component.

[0020] In practical applications, the electromagnetic propulsion device is connected to the spacecraft, and the direction of the current flowing through the propulsion components is perpendicular to the spacecraft's orbital direction. When the spacecraft flies over the Earth's South or North Pole, the magnetic field lines of the Earth's magnetic field will generate a force with the current, and the direction of this force is consistent with the spacecraft's direction of motion. In this way, the spacecraft can be propelled, achieving the purpose of correcting its flight attitude and trajectory.

[0021] It can be seen that, compared with existing technologies, this electromagnetic propulsion device does not require the use of working fluids such as liquids, gases, or plasmas. It obtains propulsion force through the combination of the Earth's space magnetic field and electric current, which reduces the cost of propulsion devices and significantly improves the operational life of satellites in orbit. Attached Figure Description

[0022] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0023] Figure 1 This is a cross-sectional view of an electromagnetic propulsion device for a polar orbit satellite provided in an embodiment of the present invention;

[0024] Figure 2 This is a schematic diagram illustrating the application of an electromagnetic propulsion device for a polar orbit satellite, as provided in an embodiment of the present invention.

[0025] Icons: 100-Power assembly; 110-Power component; 120-Metal guide bar; 200-Propulsion assembly; 210-Electromagnetic propulsion tube; 220-Insulating connector; 211-Metal end; 221-Insulating connecting rod; 300-Spacecraft. Detailed Implementation

[0026] 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. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0027] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.

[0028] The following detailed description of some embodiments of the present invention is provided in conjunction with the accompanying drawings. Unless otherwise specified, the following embodiments and features can be combined with each other.

[0029] Existing satellites can only carry a very limited amount of propellant. Once the propellant is depleted, the satellite cannot continue to operate normally, severely limiting its operational lifespan.

[0030] In view of this, the present invention provides an electromagnetic propulsion device for a polar orbit satellite, including a power supply assembly 100 and a propulsion assembly 200; the power supply assembly 100 and the propulsion assembly 200 are electrically connected to form a circuit loop; the propulsion assembly 200 is used to shield currents passing through it from other currents and is used to connect to a spacecraft 300.

[0031] refer to Figure 1 and Figure 2 The power supply component 100 is electrically connected to the propulsion component 200. When the power supply component 100 is started, current flows from the positive terminal of the power supply component 100 to the propulsion component 200, and then flows back from the propulsion component 200 to the negative terminal of the power supply component 100, forming a closed loop, i.e., a circuit loop. When magnetic field lines act on this circuit loop, since the propulsion component 200 shields the current flowing through it, the resultant force generated between the magnetic field lines and the circuit loop is the force generated by the magnetic field lines and the current flowing through the propulsion component 200.

[0032] For specific applications, refer to Figure 2 The electromagnetic propulsion device is connected to the spacecraft 300, and the direction of the current flowing through the propulsion assembly 200 is perpendicular to the orbital direction of the spacecraft 300. When the spacecraft 300 flies over the Earth's South or North Pole, the magnetic field lines of the Earth's magnetic field will generate a force with the current, and the direction of this force is consistent with the direction of motion of the spacecraft 300. In this way, the spacecraft 300 can be propelled, thereby achieving the purpose of correcting its flight attitude and trajectory.

[0033] It can be seen that, compared with existing technologies, this electromagnetic propulsion device does not require the use of working fluids such as liquids, gases, or plasmas. It obtains propulsion force through the combination of the Earth's space magnetic field and electric current, reducing the cost of propulsion devices and significantly improving the operational life of satellites in orbit.

[0034] The following combination Figures 1 to 2 The structure and shape of the electromagnetic propulsion device for polar orbit satellites provided in this embodiment will be described in detail below:

[0035] Further reference Figure 1 and Figure 2The propulsion assembly 200 includes an electromagnetic propulsion cylinder 210; a power supply assembly 100 is disposed inside the electromagnetic propulsion cylinder 210 and electrically connected to the two metal ends 211 of the electromagnetic propulsion cylinder 210; the electromagnetic propulsion cylinder 210 is used to shield the current passing through the power supply assembly 100.

[0036] Continue to refer to Figure 1 and Figure 2 The two metal ends 211 are electrically connected to the positive and negative terminals of the power supply component 100, respectively, so that the current of the power supply component 100 can be output to the propulsion component 200 and flow back from the propulsion component 200 to the power supply component 100; the electromagnetic propulsion cylinder 210 shields the current flowing through it, so as to avoid the current from interacting with the electromagnetic field and affecting the propulsion effect.

[0037] To form a circuit loop with the power supply assembly 100, a straight conductor fixed to the electromagnetic propulsion cylinder 210 can be provided. The two ends of the straight conductor are respectively connected to two metal ends 211. In application, the current flow direction in the straight conductor is perpendicular to the orbital direction of the spacecraft 300. In one embodiment of this application, the electromagnetic propulsion cylinder 210 and the power supply assembly 100 form a circuit loop; that is, the electromagnetic propulsion cylinder 210 serves both as a shield for the current passing through the power supply assembly 100 and as a conductor. Specifically, the cylinder body of the electromagnetic propulsion cylinder 210, from the inside out, includes a high permeability layer, an insulating layer, and a high conductivity non-magnetic layer; the high permeability layer, the insulating layer, and the high conductivity non-magnetic layer are connected as a whole, and the two metal ends 211 are respectively connected to the two ends of the high conductivity non-magnetic layer.

[0038] In the above design, the high permeability layer and the insulating layer shield the internal current of the electromagnetic propulsion cylinder 210. The highly conductive but non-magnetic layer, together with the power supply component 100 and the two metal terminals 211, forms a complete circuit. When the power supply component 100 is started, it is assumed that the current passing through the power supply component 100 is the internal current and the current passing through the electromagnetic propulsion cylinder 210 is the external current. (Refer to...) Figure 2 It can be seen that the internal and external currents flow in opposite directions. (Reference) Figure 2 The length direction of the electromagnetic propulsion tube 210 is perpendicular to the orbit of the spacecraft 300 and also perpendicular to the line connecting the spacecraft 300 and the Earth's center. When the electromagnetic propulsion device travels with the spacecraft 300 to the airspace above the Earth's South Pole or North Pole, the magnetic field lines of the Earth's magnetic field are perpendicular to the length direction of the electromagnetic propulsion tube 210. The magnetic field lines and the current passing through the electromagnetic propulsion tube 210 generate a force, thereby propelling the spacecraft 300.

[0039] Further reference Figure 1 and Figure 2 The propulsion assembly 200 also includes an insulating connector 220; the insulating connector 220 is used to connect the electromagnetic propulsion cylinder 210 and the spacecraft 300.

[0040] refer to Figure 2 An insulating connector 220 connects the electromagnetic propulsion cylinder 210 and the spacecraft 300. When the magnetic field lines interact with the current flowing through the electromagnetic propulsion cylinder 210, the insulating connector 220 transmits this force to the spacecraft 300, thereby propelling the spacecraft 300. Furthermore, the insulating connector 220 provides insulation, preventing current from flowing into the spacecraft 300, ensuring the uniqueness of the circuit loop, and maximizing the force generated by the magnetic field lines and the current.

[0041] In one embodiment of this application, reference continues to be made to... Figure 1 and Figure 2 The insulating connector 220 includes an insulating connecting rod 221; one end of the insulating connecting rod 221 is perpendicularly connected to the body of the electromagnetic propulsion cylinder 210, and the other end is used to connect to the spacecraft 300. The insulating connecting rod 221 is fixed to the middle of the body of the electromagnetic propulsion cylinder 210, connecting the electromagnetic propulsion cylinder 210 to the spacecraft 300, thus enabling the transmission of force. Alternatively, the insulating connector 220 can also be selected from other structural forms, such as an insulating support or insulating bracket, or other insulating components capable of transmitting force.

[0042] Further reference Figure 1 The power supply assembly 100 includes a power supply component 110; the power supply component 110 has a positive terminal and a negative terminal, which are electrically connected to two metal terminals 211 respectively. Assuming the positive terminal is located at the left end of the power supply component 110, when the power supply component 110 is turned on, the current flows from the positive terminal through the left metal terminal 211, the electromagnetic propulsion cylinder 210, and the right metal terminal 211 back to the negative terminal, forming a closed loop. The magnetic field lines can exert a force on the current passing through the electromagnetic propulsion cylinder 210.

[0043] It should also be noted that the metal guide bar 120 is insulated from the inner circumferential surface of the electromagnetic propulsion cylinder 210. This prevents short circuits and ensures the normal flow of current in the highly conductive but non-magnetic layer.

[0044] In one embodiment of this application, reference is made to Figure 1 The power supply unit 110 includes a driving power supply; two metal conductors 120 are provided between the driving power supply and the two metal ends 211, one end of the metal conductors 120 is connected to the metal ends 211, and the other end is connected to the electrodes of the driving power supply.

[0045] Continue to refer to Figure 1The drive power supply has two output terminals, and two metal conductors 120 are respectively disposed on both sides of the drive power supply. The two ends of the metal conductor 120 on the left are connected to the output terminal on the left and the metal end 211 on the left, respectively. The two ends of the metal conductor 120 on the right are connected to the output terminal on the right and the metal end 211 on the right, respectively. In this way, the drive power supply, the metal conductors 120 and the electromagnetic propulsion cylinder 210 constitute a complete circuit.

[0046] refer to Figure 2 When spacecraft 300 flies over the Earth's South Pole or North Pole, the magnetic field lines of the Earth's magnetic field are perpendicular to the length direction of the electromagnetic propulsion cylinder 210. The magnetic field lines and the current passing through the electromagnetic propulsion cylinder 210 generate a force. At this time, changing the direction of the output current of the drive power supply can correspondingly change the direction of the force, so that spacecraft 300 can obtain electromagnetic thrust or drag. Adjusting the magnitude of the output current of the drive power supply can correspondingly adjust the magnitude of the force, thereby meeting the acceleration or deceleration requirements of spacecraft 300.

[0047] The working process of the electromagnetic propulsion device for polar orbit satellites provided in this embodiment is as follows:

[0048] The electromagnetic propulsion tube 210 is connected to the spacecraft 300 via an insulating connecting rod 221. The length direction of the electromagnetic propulsion tube 210 is perpendicular to the orbit of the spacecraft 300 and also perpendicular to the line connecting the spacecraft 300 and the Earth's center. When the spacecraft 300 flies over the Earth's South or North Pole, the magnetic field lines of the Earth's magnetic field are perpendicular to the length direction of the electromagnetic propulsion tube 210. By adjusting the direction and magnitude of the output current of the drive power supply in the electromagnetic propulsion tube 210, the spacecraft 300 can obtain an adjustable electromagnetic thrust or drag, thereby meeting the acceleration or deceleration requirements of the spacecraft 300. Compared to existing technologies, this invention eliminates the need for any propellant propulsion, significantly extending the operational lifespan of satellites in orbit.

[0049] The present invention also provides a propulsion control method, which is based on the electromagnetic propulsion device for polar orbit satellites described above, and includes the following steps: connecting the electromagnetic propulsion cylinder 210 to the spacecraft 300 through an insulating connecting rod 221, and making the length direction of the electromagnetic propulsion cylinder 210 perpendicular to the orbital direction of the spacecraft 300; when the spacecraft 300 flies over the Earth's South Pole or North Pole, adjusting the magnitude of the output current of the drive power supply, and changing the current flow direction of the drive power supply as needed.

[0050] Using this method, when spacecraft 300 flies over the Earth's South Pole or North Pole, the direction of the output current of the drive power supply is adjusted. The magnetic field lines and the current will generate a force that is the same as or opposite to the flight direction of spacecraft 300, so that spacecraft 300 can obtain electromagnetic thrust or drag, thereby meeting the acceleration or deceleration requirements of spacecraft 300. By adjusting the magnitude of the output current of the drive power supply, the magnitude of electromagnetic thrust or drag can be changed accordingly, thereby realizing the regulation of the flight speed of spacecraft 300.

[0051] Furthermore, experiments show that the magnetic field strength of the Earth's surface ranges from 25 to 65 μT, with the strongest magnetic field strength near the North and South Poles. Since polar orbit satellites generally do not exceed 1000 km in altitude, the geomagnetic field in orbit is not significantly different from that on the Earth's surface. Assuming the magnetic field strength near the poles in a polar orbit is 50 μT, the electromagnetic propulsion tube 210 in this invention is 60 m long, and the drive power supply output current is 200 A, according to the formula F = BIL, where F is the electromagnetic thrust, B is the magnitude of the Earth's magnetic field, I is the magnitude of the drive power supply output current, and L is the length of the propulsion device, and the direction of the electromagnetic thrust F is determined by the left-hand rule, substituting the values, we get: F = 50 μT × 200 A × 60 m = 0.6 N, meaning the satellite can obtain an electromagnetic thrust of 600 mN. Simultaneously, assuming the satellite's flight speed is 8 km / s, the motional electromotive force generated by the electromagnetic propulsion tube 210 is 24 V, meaning the output power of the drive power supply is approximately 4.8 kW. According to public reports, the Hall electromagnetic thruster developed in the United States requires as much as 10kW of electrical power to generate 600mN of thrust. This demonstrates that the propulsion efficiency of this invention is far superior to existing Hall thruster technologies, and it requires no propellant and has a long service life.

[0052] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. An electromagnetic propulsion device for a polar orbiting satellite, characterized in that, include: Power supply assembly (100) and propulsion assembly (200); The power supply component (100) is electrically connected to the propulsion component (200), and the two form a circuit loop; The propulsion assembly (200) is used to shield currents passing through it from other sources and to connect to the spacecraft (300); The propulsion assembly (200) includes an electromagnetic propulsion cylinder (210); The power supply assembly (100) is disposed inside the electromagnetic propulsion cylinder (210) and is electrically connected to the two metal ends (211) of the electromagnetic propulsion cylinder (210); The electromagnetic propulsion cylinder (210) is used to shield the current passing through the power supply assembly (100); The body of the electromagnetic propulsion cylinder (210) consists of a high magnetic permeability layer, an insulating layer, and a high electrical conductivity but non-magnetic layer from the inside out. The high permeability layer, the insulating layer, and the high conductivity but non-magnetic layer are connected as a whole.

2. The electromagnetic propulsion device for a polar orbiting satellite of claim 1, wherein, The propulsion assembly (200) also includes an insulating connector (220); The insulating connector (220) is used to connect the electromagnetic propulsion cylinder (210) to the spacecraft (300).

3. The electromagnetic propulsion device for a polar orbiting satellite of claim 2, wherein, The insulating connector (220) includes an insulating connecting rod (221); One end of the insulating connecting rod (221) is vertically connected to the body of the electromagnetic propulsion cylinder (210), and the other end is used to connect to the spacecraft (300).

4. The electromagnetic propulsion device for polar orbit satellites according to claim 2 or 3, characterized in that, The power supply assembly (100) includes a power supply component (110); The power supply unit (110) has a positive terminal and a negative terminal, which are electrically connected to the two metal terminals (211) respectively.

5. The electromagnetic propulsion device for a polar orbit satellite according to claim 4, characterized in that, The power supply unit (110) includes a drive power supply; Two metal conductors (120) are provided between the driving power supply and the two metal ends (211). One end of the metal conductor (120) is connected to the metal end (211), and the other end is connected to the electrode of the driving power supply.

6. The electromagnetic propulsion device for a polar orbit satellite according to claim 5, characterized in that, The metal guide bar (120) is insulated from the inner circumferential surface of the electromagnetic propulsion cylinder (210).

7. A propulsion control method, characterized in that, The electromagnetic propulsion device for polar orbit satellites as described in any one of claims 1 to 6 includes the following steps: The electromagnetic propulsion cylinder (210) is connected to the spacecraft (300) via an insulating connecting rod (221), and the length direction of the electromagnetic propulsion cylinder (210) is perpendicular to the orbital direction of the spacecraft (300). When the spacecraft (300) flies over the Earth's South Pole or North Pole, adjust the magnitude of the output current of the drive power supply.

8. The propulsion control method according to claim 7, characterized in that, When the spacecraft (300) flies over the Earth's South Pole or North Pole, the current flow direction of the drive power supply is changed.

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