Movable electromagnetic propulsion system and aerospace equipment

Abstract

The invention discloses a movable electromagnetic propelling system and aerospace equipment, and relates to the technical field of aerospace equipment power systems, the movable electromagnetic propelling system comprises a propelling device and a mechanical arm, the mechanical arm is rotatably connected to the propelling device, one end of the mechanical arm is used for being connected with the aerospace equipment, and the other end of the mechanical arm is used for being connected with the aerospace equipment. The mechanical arm can drive the propelling device to move relative to the spaceflight equipment, and the propelling device can drive the spaceflight equipment to move. The movable electromagnetic propulsion system and the aerospace equipment are higher in maneuverability, and the motion trail can be flexibly changed.

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] At present, as researchers' exploration of space gradually deepens, the requirements for aerospace equipment are getting higher and higher. In some exploration missions, aerospace equipment needs to be able to change direction flexibly to have strong maneuverability. However, the current propulsion systems on aerospace equipment mostly focus on the enhancement of power, and often ignore the importance of maneuverability. This leads to the poor maneuverability of current aerospace equipment and the inability to change the trajectory of motion more flexibly. Therefore, there is an urgent need for a mobile electromagnetic propulsion system and aerospace equipment with stronger maneuverability and the ability to flexibly change the trajectory of motion. 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 stronger 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 mechanical arm, wherein the mechanical arm is rotatably connected to the propulsion device, one end of the mechanical arm is used to connect with aerospace equipment, the mechanical 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 driving motor, wherein the driving motor is fixedly connected to the connecting member, and the magnetic foot is fixedly connected to an output shaft of the driving 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 magnetic fluid propellant to the atomizing device, the atomizing device can atomize the magnetic fluid propellant, the acceleration device can accelerate the atomized magnetic fluid propellant and spray it outside the propulsion device, and 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, and a first annular cavity is also arranged 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.

[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 magnetic fluid 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 an 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, 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 an 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, 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 an end of the outer sleeve away from the protective shell, and the other end is fixedly connected to the polarity absorption 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 mechanical arm that can be connected to aerospace equipment. The propulsion device can provide power for the movement of the aerospace equipment. The mechanical arm can be used to drive the propulsion device to move relative to the aerospace equipment, thereby changing the propulsion direction of the propulsion device, thereby 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, prevent the magnetic fluid propellant from shaking, leaking or unevenly flowing during movement or vibration, and improve the stability of the magnetic fluid propellant during transportation.

[0018] Furthermore, the magnetic field and electric field are used together to accelerate the magnetofluid propellant, which significantly speeds up the injection speed of the magnetofluid propellant and effectively improves the power; at the same time, by controlling the current of the first coil, the second coil and the polar absorption ring, the size of the magnetic field and the electric field can be accurately controlled, thereby improving the control accuracy of the magnetofluid 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 drawings required for use in the embodiments will be briefly introduced below. 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 creative work.

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

[0021] In the figure: 1. propulsion device; 2. mechanical arm; 3. electromagnetic suction foot; 4. connecting piece; 5. arm; 6. driving 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. pole suction ring; 18. power supply; 19. first magnetic shielding ring; 20. second magnetic shielding ring; 21. fixing ring; 22. thermal shielding layer; 23. replenishing pipe. DETAILED DESCRIPTION

[0022] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. 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 creative work 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] Embodiment 1

[0026] This embodiment provides a movable electromagnetic propulsion system, such as Figure 1 As shown, it includes: a propulsion device 1 and a mechanical arm 2, the mechanical arm 2 is rotatably connected to the propulsion device 1, one end of the mechanical arm 2 is used to connect with the aerospace equipment, the mechanical 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, and realizing flexible changes in the motion trajectory of the aerospace equipment, so that the aerospace equipment can adapt to more space exploration needs.

[0028] In one implementation of this embodiment, the mechanical arm 2 includes an electromagnetic suction foot 3, a connecting member 4 and an arm 5, one end of the arm 5 is hinged on the propulsion device 1, and the other end is hinged on the connecting member 4, the electromagnetic suction foot 3 is connected to the connecting member 4, and the electromagnetic suction foot 3 is used to be adsorbed on the fuselage of the aerospace equipment. When the electromagnetic suction foot 3 is powered on, it can be firmly fixed on the fuselage of the aerospace equipment, and when the electromagnetic suction foot 3 is powered off, it can be quickly separated from the fuselage of the aerospace equipment; when in use, taking two electromagnetic suction feet 3 as an example, one electromagnetic suction foot 3 can be powered on first and connected to the fuselage of the aerospace equipment, and then the arm 5 of the mechanical 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 suction foot 3 is powered on and connected to the fuselage of the aerospace equipment to achieve the movement and fixation of the movable electromagnetic propulsion system. Preferably, four mechanical arms 2 are provided; the arm 5 is fixedly connected to the propulsion device 1 via a fixing ring 21 , the fixing ring 21 is sleeved outside the propulsion device 1 , and one end of the arm 5 is hinged to the fixing ring 21 .

[0029] In one implementation of this embodiment, the robot arm 2 further includes a drive motor 6, the drive motor 6 is fixedly connected to the connecting member 4, and the magnetic foot is 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 implementation of this embodiment, the mechanical arm 2 further includes a steering gear 7 and a connecting seat 8, the connecting seat 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, the steering gear 7 has a free end, the free end can rotate, and the connecting member 4 is fixedly connected to the free end. When it is necessary to change the angle of the electromagnetic suction foot 3, the free end of the steering gear 7 can be rotated to control the angle between the connecting member 4 and the connecting seat 8; when it is necessary to fix the angle of the electromagnetic suction foot 3, the free end can also be stopped from rotating so that the connecting seat 8 and the connecting member 4 remain relatively fixed.

[0031] In one implementation of this embodiment, the propulsion device 1 includes a power supply 18 and a liquid supply device, an atomizing device and an accelerating device which are connected and communicated in sequence. The liquid supply device can deliver the magnetic fluid propellant to the atomizing device, the atomizing device can atomize the magnetic fluid propellant, the accelerating device can accelerate the atomized magnetic fluid propellant and spray it to the outside of the propulsion device 1, and the power supply 18 can supply power to the liquid supply device, the atomizing device, the accelerating device and the mechanical arm 2. During the operation of the propulsion device 1, the liquid supply device delivers the magnetic fluid propellant to the atomizing device, the atomizing device atomizes the magnetic fluid propellant and delivers it to the accelerating device, the accelerating device can accelerate the magnetic fluid propellant and spray it out, and the magnetic fluid propellant after spraying can generate a reaction force on the propulsion device 1 arranged on the fuselage of the aerospace equipment, thereby driving the aerospace equipment to move. The power source 18 is wrapped with a heat shielding layer 22, which can effectively reduce solar radiation and radiant heat flow in space, and keep the temperature of the power source 18 within a safe range; the magnetic fluid in the magnetic fluid propellant is preferably iron oxide magnetic particles, and poly-α-olefin is used as the magnetic fluid carrier. The iron oxide particles have excellent magnetic properties and high chemical stability, and are non-toxic, non-polluting and biodegradable, avoiding the environmental hazards of traditional magnetic materials. Poly-α-olefin is used as a magnetic fluid carrier, which overcomes the problem that conventional carriers are easy to volatilize and oxidize under high temperature, high pressure or vacuum environment. It has the characteristics of non-toxicity, chemical stability, anti-oxidation and high temperature resistance, and is suitable for long-term space missions.

[0032] In one embodiment of the present embodiment, 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, a mounting cavity is provided in the liquid storage tank 9, a liquid storage cavity is provided in the side wall of the mounting cavity, the liquid storage cavity is connected with the mounting 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 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 the buffer layer 11 is polyetherimide foam. The magnetic fluid propellant in the liquid storage tank 9 can enter the pores of the buffer layer 11 after entering the mounting cavity, and move toward the atomization device under the magnetic field generated by the first coil 10; the polyetherimide foam can effectively adsorb the magnetic fluid propellant, prevent the magnetic fluid propellant from shaking, leaking or unevenly flowing during movement or vibration, and improve the stability of the magnetic fluid propellant during transportation. The liquid storage tank 9 is also provided with a supplementary pipe 23 communicating with the installation cavity and the outside, and the magnetic fluid propellant can be supplemented into the liquid storage tank 9 through the supplementary pipe 23 .

[0033] In one embodiment of the present 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 arranged in the protective shell 12, one end of the connecting tube 14 is connected and connected to the installation cavity, and the other end is connected and connected to the acceleration device. The ultrasonic generator 13 is fixedly connected in the protective shell 12, and the ultrasonic generator 13 is connected to the power supply 18 and can emit ultrasonic waves to the magnetic fluid propellant in the connecting tube 14. After the magnetic fluid propellant enters the connecting tube 14, the ultrasonic generator 13 can emit ultrasonic waves to the connecting tube 14 and atomize the magnetic fluid propellant in the connecting tube 14. Among them, the ultrasonic generator 13 is preferably a piezoelectric ceramic group.

[0034] In one implementation of the present embodiment, the acceleration device includes an outer sleeve 15, a second coil 16 and an attractive pole 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. An acceleration channel is provided in the outer sleeve 15. One end of the acceleration channel is connected to the connecting pipe 14, and the other end is connected to the outside. A second annular cavity is provided in the side wall of the acceleration channel. The second coil 16 surrounds the acceleration channel and is fixedly connected in the second annular cavity. The attractive pole ring 17 and the second coil 16 are both connected to the power supply 18. The attractive pole 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 attractive pole 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 attractive pole ring and the connecting pipe 14 can both cause the magnetic fluid 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 polar attracting 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 together 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 polar attracting 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 polar attracting 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, and the conductor part is connected to the positive pole of the power supply 17. The electric field formed between the polar attracting ring 17 and the connecting tube 14 can accelerate the magnetic fluid propellant.

[0035] In one implementation of this embodiment, a first magnetic shielding ring 19 and a second magnetic shielding ring 20 are also 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 polarity attracting ring 17. The first magnetic shielding ring 19 can avoid mutual interference between the magnetic field of the first coil 10 and the magnetic field of the second coil 16; the second magnetic shielding ring 20 can avoid mutual interference between the magnetic field of the polarity attracting ring 17 and the magnetic field of the second coil 16.

[0036] Embodiment 2

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

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

[0039] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only used to help understand the method and core ideas of the present invention. At the same time, for those skilled in the art, according to the ideas of the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. A movable electromagnetic propulsion system, characterized in that: include: A propulsion device and a mechanical arm, wherein the mechanical arm is rotatably connected to the propulsion device, one end of the mechanical arm is used to connect to the aerospace equipment, the mechanical arm can drive the propulsion device to move relative to the aerospace equipment, and the propulsion device can drive the aerospace equipment to move.

2. The movable electromagnetic propulsion system according to claim 1, characterized in that: The robotic arm is provided with multiple ones, and the robotic arm 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.

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

4. The movable electromagnetic propulsion system according to claim 3, characterized in that: The mechanical arm also includes a steering gear and a connecting seat, wherein the connecting seat is fixedly connected to an end of the arm away from the propulsion device, the steering gear is fixedly connected to the arm, the steering gear has a free end, the free end can rotate, 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 propulsion device includes a power supply and a liquid supply device, an atomizing device and an acceleration device which 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 acceleration device can accelerate the atomized magnetic fluid propellant and spray it outside the propulsion device, and the power supply can supply power to the liquid supply device, the atomizing device, the acceleration device and the robotic arm.

6. The movable electromagnetic propulsion system according to claim 5, characterized in that: 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 arranged 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.

7. The movable electromagnetic propulsion system according to claim 6, 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 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 magnetic fluid propellant in the connecting pipe.

8. The movable electromagnetic propulsion system according to claim 7, characterized in that: The acceleration device includes an outer sleeve, a second coil and an attracting ring, one end of the outer sleeve is fixedly connected to an end of the protective shell away from the liquid storage tank, an acceleration channel is provided in the outer sleeve, one end of the acceleration channel is connected to the connecting pipe, and the other end is connected to the outside, a second annular cavity is provided in the side wall of the acceleration channel, the second coil surrounds the acceleration channel and is fixedly connected in the second annular cavity, the attracting ring and the second coil are both connected to the power supply, the attracting ring is fixedly connected to an end of the outer sleeve away from the protective shell, the connecting pipe is connected to the power supply, the attracting ring and the connecting pipe have a potential difference, the magnetic field generated by the second coil and the electric field generated by the attracting 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.

9. The movable electromagnetic propulsion system according to claim 8, 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 an end of the outer sleeve away from the protective shell, and the other end is fixedly connected to the pole-absorbing ring.

10. An aerospace device, characterized in that: The invention comprises a fuselage and a propulsion system according to any one of claims 1 to 9, wherein the propulsion system is arranged on the fuselage.

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