Movable electromagnetic propulsion system and aerospace equipment

Abstract

The present invention discloses a movable electromagnetic propulsion system and aerospace equipment, relating to the technical field of aerospace equipment power systems. The movable electromagnetic propulsion system comprises a propulsion device and a robotic arm, the robotic arm being rotatably connected to the propulsion device, one end of the robotic arm being connected to the aerospace equipment, the robotic arm being capable of driving the propulsion device to move relative to the aerospace equipment, and the propulsion device being capable of driving the aerospace equipment to move. The movable electromagnetic propulsion system and aerospace equipment have enhanced maneuverability and can flexibly change their motion trajectory.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace equipment power systems, and in particular to a movable electromagnetic propulsion system and aerospace equipment. Background Art

[0002] As researchers delve deeper into space exploration, the requirements for aerospace equipment are becoming increasingly stringent. Some exploration missions require aerospace equipment to be able to flexibly change direction and possess greater maneuverability. However, current propulsion systems for aerospace equipment mostly focus on enhancing power, often ignoring the importance of maneuverability. This results in poor maneuverability of current aerospace equipment and an inability to flexibly change its trajectory. Therefore, there is an urgent need for a mobile electromagnetic propulsion system and aerospace equipment with greater maneuverability and the ability to flexibly change its trajectory. Summary of the Invention

[0003] The purpose of the present invention is to provide a movable electromagnetic propulsion system and aerospace equipment to solve the problems existing in the above-mentioned prior art, with greater maneuverability and the ability to flexibly change the motion trajectory.

[0004] To achieve the above object, the present invention provides the following solutions:

[0005] The present invention provides a movable electromagnetic propulsion system, comprising: a propulsion device and a robotic arm, wherein the robotic arm is rotatably connected to the propulsion device, one end of the robotic arm is used to connect to aerospace equipment, the robotic arm can drive the propulsion device to move relative to the aerospace equipment, and the propulsion device can drive the aerospace equipment to move.

[0006] In some embodiments, there are multiple robotic arms, each of which includes an electromagnetic suction foot, a connecting piece, and an arm rod. One end of the arm rod is hinged to the propulsion device, and the other end is hinged to the connecting piece. The electromagnetic suction foot is connected to the connecting piece, and the electromagnetic suction foot is used to be adsorbed on the fuselage of the aerospace equipment.

[0007] In some embodiments, the robotic arm further includes a drive motor, the drive motor is fixedly connected to the connecting member, and the magnetic foot is fixedly connected to an output shaft of the drive motor.

[0008] In some embodiments, the robotic arm further includes a servo and a connecting seat, wherein the connecting seat is fixedly connected to an end of the arm away from the propulsion device, the servo is fixedly connected to the arm, the servo has a free end, the free end is capable of rotating, and the connecting member is fixedly connected to the free end.

[0009] In some embodiments, the propulsion device includes a power supply and a liquid supply device, an atomizing device and an acceleration device that are connected and communicated in sequence. The liquid supply device can transport the magnetofluid propellant to the atomizing device, the atomizing device can atomize the magnetofluid propellant, and the acceleration device can accelerate the atomized magnetofluid propellant and spray it out of the propulsion device. The power supply can power the liquid supply device, the atomizing device, the acceleration device and the robotic arm.

[0010] In some embodiments, the liquid supply device includes a liquid storage tank, a first coil and a buffer layer. The power supply is fixedly connected to the liquid storage tank. The liquid storage tank has an installation cavity. The side wall of the installation cavity has a liquid storage cavity. The liquid storage cavity is connected to the installation cavity. The liquid storage cavity is used to store magnetic fluid propellant. A first annular cavity is also provided in the side wall between the installation cavity and the liquid storage cavity. The first coil is fixedly connected in the first annular cavity and surrounds the installation cavity. The first coil is connected to the power supply. The buffer layer is fixedly connected in the installation cavity. The buffer layer is polyetherimide foam.

[0011] In some embodiments, the atomization device includes a protective shell, an ultrasonic generating device and a connecting tube, one end of the protective shell is fixedly connected to the liquid storage tank, and the other end is fixedly connected to the acceleration device, the connecting tube is arranged in the protective shell, one end of the connecting tube is connected to and communicated with the installation cavity, and the other end is connected to and communicated with the acceleration device, the ultrasonic generating device is fixedly connected in the protective shell, the ultrasonic generating device is connected to the power supply and can emit ultrasonic waves to the magnetofluid propellant in the connecting tube.

[0012] In some embodiments, the acceleration device includes an outer sleeve, a second coil and an absorption ring, one end of the outer sleeve is fixedly connected to the end of the protective shell away from the liquid storage tank, the outer sleeve has an acceleration channel, one end of the acceleration channel is connected to the connecting pipe, and the other end is connected to the outside world, the side wall of the acceleration channel has a second annular cavity, the second coil surrounds the acceleration channel and is fixedly connected in the second annular cavity, the absorption ring and the second coil are both connected to the power supply, the absorption ring is fixedly connected to the end of the outer sleeve away from the protective shell, the connecting pipe is connected to the power supply, the absorption ring and the connecting pipe have a potential difference, the magnetic field generated by the second coil and the electric field generated by the absorption ring and the connecting pipe can both cause the magnetic fluid propellant to move along the acceleration channel in a direction away from the atomization device.

[0013] In some embodiments, a first magnetic shielding ring and a second magnetic shielding ring are further included. The first magnetic shielding ring is sleeved outside the connecting tube and fixedly connected between the protective shell and the liquid storage tank. One end of the second magnetic shielding ring is fixedly connected to an end of the outer sleeve away from the protective shell, and the other end is fixedly connected to the pole-absorbing ring.

[0014] The present invention also provides a spaceflight device, comprising a fuselage and the above-mentioned propulsion system, wherein the propulsion system is arranged on the fuselage.

[0015] Compared with the prior art, the present invention has achieved the following technical effects:

[0016] The movable electromagnetic propulsion system provided by the present invention has a robotic arm that can be connected to aerospace equipment. The propulsion device can provide power for the movement of the aerospace equipment. The robotic arm can drive the propulsion device to move relative to the aerospace equipment, thereby changing the propulsion direction of the propulsion device, improving the maneuverability of the aerospace equipment, and realizing flexible changes in the motion trajectory of the aerospace equipment, so that the aerospace equipment can adapt to more space exploration needs.

[0017] Furthermore, the polyetherimide foam can effectively absorb the magnetic fluid propellant, preventing the magnetic fluid propellant from shaking, leaking or unevenly flowing during movement or vibration, thereby improving the stability of the magnetic fluid propellant during transportation.

[0018] Furthermore, the magnetic field and electric field are used together to accelerate the magnetohydrodynamic propellant, which significantly speeds up the injection speed of the magnetohydrodynamic propellant and effectively improves the power; at the same time, by controlling the current of the first coil, the second coil and the polarization ring, the size of the magnetic field and the electric field can be precisely controlled, thereby improving the control accuracy of the magnetohydrodynamic propellant speed. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0020] Figure 1 A schematic structural diagram of a movable electromagnetic propulsion system in some embodiments of the present invention;

[0021] In the figure: 1. Propulsion device; 2. Robotic arm; 3. Electromagnetic suction foot; 4. Connector; 5. Arm; 6. Drive motor; 7. Servo; 8. Connecting seat; 9. Liquid storage tank; 10. First coil; 11. Buffer layer; 12. Protective shell; 13. Ultrasonic generating device; 14. Connecting pipe; 15. Outer sleeve; 16. Second coil; 17. Electrode suction ring; 18. Power supply; 19. First magnetic shielding ring; 20. Second magnetic shielding ring; 21. Fixed ring; 22. Thermal shielding layer; 23. Supplementary pipe. DETAILED DESCRIPTION

[0022] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0023] The purpose of the present invention is to provide a movable electromagnetic propulsion system to solve the problems existing in the prior art, with greater maneuverability and the ability to flexibly change the motion trajectory.

[0024] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0025] Example 1

[0026] This embodiment provides a movable electromagnetic propulsion system, such as Figure 1 As shown, it includes: a propulsion device 1 and a robotic arm 2, the robotic arm 2 is rotatably connected to the propulsion device 1, one end of the robotic arm 2 is used to connect with the aerospace equipment, the robotic arm 2 can drive the propulsion device 1 to move relative to the aerospace equipment, and the propulsion device 1 can drive the aerospace equipment to move.

[0027] The movable electromagnetic propulsion system provided in this embodiment has a robotic arm 2 that can be connected to aerospace equipment, and the propulsion device 1 can provide power for the movement of the aerospace equipment. The robotic arm 2 can drive the propulsion device 1 to move relative to the aerospace equipment, thereby changing the propulsion direction of the propulsion device 1, thereby improving the maneuverability of the aerospace equipment, realizing flexible changes in the motion trajectory of the aerospace equipment, and enabling the aerospace equipment to adapt to more space exploration needs.

[0028] In one embodiment of the present invention, the robotic arm 2 includes an electromagnetic foot 3, a connector 4, and an arm 5. One end of the arm 5 is hinged to the propulsion device 1, and the other end is hinged to the connector 4. The electromagnetic foot 3 is connected to the connector 4. The electromagnetic foot 3 is used to be adsorbed on the fuselage of the aerospace equipment. When the electromagnetic foot 3 is energized, it can be firmly fixed to the fuselage of the aerospace equipment. When the electromagnetic foot 3 is de-energized, it can be quickly separated from the fuselage of the aerospace equipment. During use, taking two electromagnetic feet 3 as an example, one electromagnetic foot 3 can be energized and connected to the fuselage of the aerospace equipment. Then, the arm 5 of the robotic arm 2 can be rotated to move the entire movable electromagnetic propulsion system. When the entire movable electromagnetic propulsion system reaches the specified position, the other electromagnetic foot 3 is energized and connected to the fuselage of the aerospace equipment, thereby achieving the movement and fixation of the movable electromagnetic propulsion system. Among them, four robotic arms 2 are preferably provided; the arm 5 is fixedly connected to the propulsion device 1 through a fixing ring 21, the fixing ring 21 is sleeved outside the propulsion device 1, and one end of the arm 5 is hinged on the fixing ring 21.

[0029] In one embodiment of this invention, the robotic arm 2 further includes a drive motor 6, which is fixedly connected to the connector 4, and a magnetic foot fixedly connected to the output shaft of the drive motor 6. When the electromagnetic foot 3 is connected to the fuselage of the aerospace equipment, the position or angle of the electromagnetic propulsion system can be adjusted by rotating the motor output shaft, thereby further improving flexibility.

[0030] In one embodiment of this embodiment, the robotic arm 2 further includes a steering gear 7 and a connecting base 8. The connecting base 8 is fixedly connected to the end of the arm 5 away from the propulsion device 1. The steering gear 7 is fixedly connected to the arm 5 and has a free end that is capable of rotation. The connecting member 4 is fixedly connected to the free end. When the angle of the electromagnetic foot 3 needs to be changed, the free end of the steering gear 7 can be rotated to control the angle between the connecting member 4 and the connecting base 8. When the angle of the electromagnetic foot 3 needs to be fixed, the free end can be stopped from rotating, thereby maintaining the connecting base 8 and the connecting member 4 relative to each other.

[0031] In one embodiment of the present invention, the propulsion device 1 includes a power supply 18 and a liquid supply device, an atomizing device, and an accelerator that are sequentially connected and communicated. The liquid supply device can transport the magnetic fluid propellant to the atomizing device, the atomizing device can atomize the magnetic fluid propellant, and the accelerator can accelerate the atomized magnetic fluid propellant and spray it outside the propulsion device 1. The power supply 18 can power the liquid supply device, the atomizing device, the accelerator, and the robotic arm 2. During operation of the propulsion device 1, the liquid supply device transports the magnetic fluid propellant to the atomizing device, the atomizing device atomizes the magnetic fluid propellant and transports it to the accelerator, and the accelerator can accelerate the magnetic fluid propellant and spray it out. The sprayed magnetic fluid propellant can generate a reaction force on the propulsion device 1 disposed on the fuselage of the aerospace equipment, thereby driving the aerospace equipment to move. The power source 18 is wrapped with a thermal shield 22, which effectively reduces solar radiation and radiant heat flux from space, maintaining the power source 18 temperature within a safe range. The magnetic fluid in the magnetic fluid propellant is preferably iron oxide magnetic particles, and polyalphaolefin (PAO) is used as the magnetic fluid carrier. The iron oxide particles possess excellent magnetic properties and high chemical stability. They are also non-toxic, non-polluting, and biodegradable, avoiding the environmental hazards of traditional magnetic materials. PAO overcomes the volatilization and oxidation issues of conventional carrier fluids under high temperature, high pressure, or vacuum environments. Its non-toxic, chemically stable, antioxidant, and high-temperature resistance make it suitable for long-duration space missions.

[0032] In one embodiment of this invention, the liquid supply device includes a liquid storage tank 9, a first coil 10, and a buffer layer 11. A power supply 18 is fixedly connected to the liquid storage tank 9. The liquid storage tank 9 has a mounting cavity, and a liquid storage cavity is formed in the sidewall of the mounting cavity. The liquid storage cavity is connected to the mounting cavity and is used to store magnetic fluid propellant. A first annular cavity is also provided in the sidewall between the mounting cavity and the liquid storage cavity. The first coil 10 is fixedly connected in the first annular cavity and surrounds the mounting cavity. The first coil 10 is connected to the power supply 18. The buffer layer 11 is fixedly connected in the mounting cavity and is composed of polyetherimide foam. After entering the mounting cavity, the magnetic fluid propellant in the liquid storage tank 9 can enter the pores of the buffer layer 11 and move toward the atomization device under the magnetic field generated by the first coil 10. The polyetherimide foam can effectively absorb the magnetic fluid propellant, preventing the magnetic fluid propellant from shaking, leaking, or unevenly flowing during movement or vibration, thereby improving the stability of the magnetic fluid propellant during transportation. The liquid storage tank 9 is further provided with a replenishing pipe 23 communicating with the installation cavity and the outside, and the magnetic fluid propellant can be replenished into the liquid storage tank 9 through the replenishing pipe 23 .

[0033] In one embodiment of this embodiment, the atomizing device includes a protective shell 12, an ultrasonic generator 13, and a connecting tube 14. One end of the protective shell 12 is fixedly connected to the liquid storage tank 9, and the other end is fixedly connected to the acceleration device. The connecting tube 14 is disposed within the protective shell 12. One end of the connecting tube 14 is connected to and communicates with the mounting cavity, and the other end is connected to and communicates with the acceleration device. The ultrasonic generator 13 is fixedly connected within the protective shell 12. The ultrasonic generator 13 is connected to a power source 18 and is capable of emitting ultrasonic waves toward the magnetic fluid propellant within the connecting tube 14. After the magnetic fluid propellant enters the connecting tube 14, the ultrasonic generator 13 can emit ultrasonic waves toward the connecting tube 14 and atomize the magnetic fluid propellant within the connecting tube 14. The ultrasonic generator 13 is preferably a piezoelectric ceramic group.

[0034] In one embodiment of this embodiment, the acceleration device includes an outer sleeve 15, a second coil 16 and an absorption ring 17. One end of the outer sleeve 15 is fixedly connected to the end of the protective shell 12 away from the liquid storage tank 9. The outer sleeve 15 has an acceleration channel. One end of the acceleration channel is connected to the connecting pipe 14, and the other end is connected to the outside world. The side wall of the acceleration channel has a second annular cavity. The second coil 16 surrounds the acceleration channel and is fixedly connected in the second annular cavity. The absorption ring 17 and the second coil 16 are both connected to the power supply 18. The absorption ring 17 is fixedly connected to the end of the outer sleeve 15 away from the protective shell 12. The connecting pipe 14 is connected to the power supply 18. The absorption ring 17 and the connecting pipe 14 have a potential difference. The magnetic field generated by the second coil 16 and the electric field generated by the absorption ring and the connecting pipe 14 can cause the magnetofluid propellant to move along the acceleration channel in a direction away from the atomization device. During acceleration, the second coil 16 can generate a magnetic field that causes the magnetic fluid propellant to move along the acceleration channel box away from the atomizing device, and the potential difference between the polarization ring 17 and the connecting tube 14 can generate an electric field that causes the magnetic fluid propellant to move along the acceleration channel box away from the atomizing device. The magnetic field and the electric field are used to accelerate the magnetic fluid propellant, which significantly speeds up the injection speed of the magnetic fluid propellant and effectively improves the power. At the same time, by controlling the current intensity passing through the connecting tube 14, the second coil 16 and the polarization ring 17, the size of the magnetic field and the electric field can be accurately controlled, thereby improving the control accuracy of the speed of the magnetic fluid propellant. Among them, the polarization ring 17 is connected to the negative pole of the power supply 18, and the end of the connecting tube 14 away from the liquid storage tank 9 is set as a conductor part, which is connected to the positive pole of the power supply 17. The electric field formed between the polarization ring 17 and the connecting tube 14 can accelerate the magnetic fluid propellant.

[0035] In one embodiment of this embodiment, a first magnetic shielding ring 19 and a second magnetic shielding ring 20 are further included. The first magnetic shielding ring 19 is sleeved outside the connecting tube 14 and fixedly connected between the protective shell 12 and the liquid storage tank 9. One end of the second magnetic shielding ring 20 is fixedly connected to the end of the outer sleeve 15 away from the protective shell 12, and the other end is fixedly connected to the polarizing ring 17. The first magnetic shielding ring 19 can prevent mutual interference between the magnetic fields of the first coil 10 and the second coil 16; the second magnetic shielding ring 20 can prevent mutual interference between the magnetic fields of the polarizing ring 17 and the second coil 16.

[0036] Example 2

[0037] This embodiment provides a spaceflight device, including a fuselage and the propulsion system of the first embodiment, wherein the propulsion system is arranged on the fuselage.

[0038] The aerospace equipment in this embodiment has greater maneuverability and can flexibly change its motion trajectory by using the propulsion system in the first embodiment.

[0039] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only intended to help understand the method and core concept of the present invention. At the same time, those skilled in the art will find that the specific implementation methods and application scopes may vary based on the concept of the present invention. In summary, the contents of this specification should not be construed as limiting the present invention.

Claims

1. A movable electromagnetic propulsion system, characterized in that: include: A propulsion device and a robotic arm, wherein the robotic arm is rotatably connected to the propulsion device, one end of the robotic arm is used to connect to the aerospace equipment, the robotic arm can drive the propulsion device to move relative to the aerospace equipment, the propulsion device can drive the aerospace equipment to move, the propulsion device includes a power supply and a liquid supply device, an atomizing device and an accelerator that are connected and communicated in sequence, the liquid supply device can transport the magnetic fluid propellant to the atomizing device, the atomizing device can atomize the magnetic fluid propellant, the accelerator can accelerate the atomized magnetic fluid propellant and spray it outside the propulsion device, the power supply can supply the liquid supply device, and the atomizing device can atomize the magnetic fluid propellant. The device, the atomizing device, the acceleration device and the robotic arm are powered, the liquid supply device includes a liquid storage tank, a first coil and a buffer layer, the power supply is fixedly connected to the liquid storage tank, the liquid storage tank has an installation cavity, the side wall of the installation cavity has a liquid storage cavity, the liquid storage cavity is connected to the installation cavity, the liquid storage cavity is used to store magnetic fluid propellant, and a first annular cavity is also provided in the side wall between the installation cavity and the liquid storage cavity, the first coil is fixedly connected in the first annular cavity and surrounds the installation cavity, the first coil is connected to the power supply, the buffer layer is fixedly connected in the installation cavity, and the buffer layer is polyetherimide foam.

2. The movable electromagnetic propulsion system according to claim 1, characterized in that: There are multiple robotic arms, each including an electromagnetic suction foot, a connecting piece and an arm rod. One end of the arm rod is hinged to the propulsion device, and the other end is hinged to the connecting piece. The electromagnetic suction foot is connected to the connecting piece, and the electromagnetic suction foot is used to be adsorbed on the fuselage of the aerospace equipment.

3. The movable electromagnetic propulsion system according to claim 2, characterized in that: The robotic arm further includes a drive motor, which is fixedly connected to the connecting member, and the magnetic foot is fixedly connected to an output shaft of the drive motor.

4. The movable electromagnetic propulsion system according to claim 3, characterized in that: The robotic arm also includes a servo and a connecting seat, wherein the connecting seat is fixedly connected to an end of the arm away from the propulsion device, the servo is fixedly connected to the arm, the servo has a free end, the free end is capable of rotating, and the connecting piece is fixedly connected to the free end.

5. The movable electromagnetic propulsion system according to claim 1, characterized in that: The atomization device includes a protective shell, an ultrasonic generating device and a connecting pipe. One end of the protective shell is fixedly connected to the liquid storage tank, and the other end is fixedly connected to the acceleration device. The connecting pipe is arranged in the protective shell, one end of the connecting pipe is connected to and communicates with the installation cavity, and the other end is connected to and communicates with the acceleration device. The ultrasonic generating device is fixedly connected in the protective shell, the ultrasonic generating device is connected to the power supply and can emit ultrasonic waves to the magnetic fluid propellant in the connecting pipe.

6. The movable electromagnetic propulsion system according to claim 5, characterized in that: The acceleration device includes an outer sleeve, a second coil and an absorption ring, one end of the outer sleeve is fixedly connected to the end of the protective shell away from the liquid storage tank, the outer sleeve is provided with an acceleration channel, one end of the acceleration channel is connected to the connecting pipe, and the other end is connected to the outside world, the side wall of the acceleration channel is provided with a second annular cavity, the second coil surrounds the acceleration channel and is fixedly connected in the second annular cavity, the absorption ring and the second coil are both connected to the power supply, the absorption ring is fixedly connected to the end of the outer sleeve away from the protective shell, the connecting pipe is connected to the power supply, the absorption ring and the connecting pipe have a potential difference, the magnetic field generated by the second coil and the electric field generated by the absorption ring and the connecting pipe can both cause the magnetic fluid propellant to move along the acceleration channel in a direction away from the atomization device.

7. The movable electromagnetic propulsion system according to claim 6, characterized in that: It also includes a first magnetic shielding ring and a second magnetic shielding ring. The first magnetic shielding ring is sleeved outside the connecting tube and fixedly connected between the protective shell and the liquid storage tank. One end of the second magnetic shielding ring is fixedly connected to the end of the outer sleeve away from the protective shell, and the other end is fixedly connected to the pole-absorbing ring.

8. An aerospace device, characterized in that: The invention comprises a fuselage and a propulsion system according to any one of claims 1 to 7, wherein the propulsion system is arranged on the fuselage.

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