Propulsion system and aerospace equipment

Abstract

The invention discloses a propulsion system and spaceflight equipment, and relates to the technical field of spaceflight power systems, the propulsion system comprises a nuclear power source, a storage feeding device, an atomization device and an acceleration device, the nuclear power source can supply power to the atomization device and the acceleration device, the storage feeding device is used for storing a magnetic fluid propellant, and the atomization device is used for supplying power to the acceleration device. The storage feeding device communicates with the atomization device, the storage feeding device can convey the magnetic fluid propellant to the atomization device, and the atomization device can atomize the magnetic fluid propellant and convey the magnetic fluid propellant to the acceleration device; the accelerating device can generate a magnetic field and accelerate the magnetofluid propellant in the atomized state. The propelling system and the aerospace equipment are suitable for being used in the environment lacking solar energy, and power is more sufficient.

Description

Technical Field

[0001] This invention relates to the field of aerospace equipment power system technology, and in particular to a propulsion system and aerospace equipment. Background Technology

[0002] Currently, as researchers delve deeper into space exploration, the demands on spacecraft are increasing. Due to the extreme environment of space, especially for spacecraft operating in orbits far from or away from the sun, the stability of the propulsion system has become a crucial indicator of whether a mission can be successfully completed. However, many current spacecraft propulsion systems rely on solar power, which is unsuitable for use in extreme environments lacking solar energy, such as those far from or away from the sun. Furthermore, the power generated is insufficient to meet exploration needs. Therefore, there is an urgent need for a propulsion system and spacecraft that is suitable for use in environments lacking solar energy and offers more sufficient power. Summary of the Invention

[0003] The purpose of this invention is to provide a propulsion system and aerospace equipment that solves the problems existing in the prior art, is suitable for use in environments lacking solar energy, and has more sufficient power.

[0004] To achieve the above objectives, the present invention provides the following solution:

[0005] This invention provides a propulsion system, comprising: a nuclear power source, a storage and loading device, an atomizing device, and an acceleration device. The nuclear power source supplies power to the atomizing device and the acceleration device. The storage and loading device stores magnetohydrodynamic (MHD) propellant and is connected to the atomizing device. The storage and loading device delivers the MHD propellant to the atomizing device. The atomizing device atomizes the MHD propellant and delivers it to the acceleration device. The acceleration device generates a magnetic field and accelerates the atomized MHD propellant.

[0006] In some embodiments, the nuclear power source includes a fuel core and a thermoelectric transducer, an ablation-resistant cladding, a heat-insulating cladding, a shock-resistant cladding, and a sealing cladding, which are sequentially wrapped and fixedly connected from the outside to the inside. The fuel core is fixedly connected inside the sealing cladding. The thermoelectric transducer is connected to the atomizing device and the accelerating device. The fuel core is capable of releasing heat, and the thermoelectric transducer is capable of converting the heat energy generated by the fuel core into electrical energy.

[0007] In some embodiments, the fuel core is a plutonium dioxide (PuO2) fuel core.

[0008] In some embodiments, the nuclear power source further includes a venting assembly, with an installation gap between the sealed casing and the fuel core, and a venting channel communicating with the installation gap and the outside. The venting assembly is fixedly connected within the installation gap and covers one end of the venting channel near the installation gap. The venting assembly allows the gas generated by the decay of the fuel core to pass through and can block plutonium particles.

[0009] In some embodiments, the atomizing device includes an ultrasonic generator, an amplitude transformer, an emitting plate, and an atomizing tube. The two ends of the amplitude transformer are fixedly connected to the ultrasonic generator and the emitting plate, respectively. One end of the atomizing tube is connected to and communicates with the storage and feeding device, and the other end is connected to the acceleration device. The emitting plate has a first through hole, and the atomizing tube passes through the first through hole. The ultrasonic generator is connected to the nuclear power source and is capable of outputting ultrasonic waves.

[0010] In some embodiments, the nuclear power source has a central channel, the fuel core is arranged around the central channel, and the storage and feeding device, the atomizing device, and the acceleration device are all fixedly connected within the central channel.

[0011] In some embodiments, the storage and feeding device includes a storage bladder, a storage tank, a feeding pipe, and a throttle valve. The storage tank is fixedly connected within the central channel, and the outer wall of the storage tank is in contact with the inner wall of the central channel. The storage bladder is made of a soft material and is fixedly connected within the storage tank. The storage tank is used to store the magnetohydrodynamic propellant. There is a gap between the outer wall of the storage bladder and the inner wall of the storage tank. An inert gas is filled between the storage bladder and the storage tank, and the inert gas exerts pressure on the storage bladder. One end of the feeding pipe is connected to and communicates with the storage bladder, and the other end is connected to and communicates with the atomizing pipe. A throttle valve is provided on the feeding pipe.

[0012] In some embodiments, the acceleration device includes a protective shell, an acceleration coil, a magnetic shielding ring, and an attracting ring. The storage tank has an installation channel connecting both sides of the storage tank. The protective shell is fixedly connected within the installation channel. The protective shell has an acceleration channel connecting both sides of the protective shell. The acceleration coil is fixedly connected within the protective shell and surrounds the acceleration channel. One end of the acceleration channel is connected to the atomizing tube, and the other end is fixedly connected to the magnetic shielding ring. The attracting ring is fixedly connected to the magnetic shielding ring. The through holes on the attracting ring, the magnetic shielding ring, and the acceleration channel are connected. The emitting plate, the attracting ring, and the acceleration coil are all connected to the nuclear power source. The emitting plate and the attracting ring have a potential difference. The electric field generated by the emitting plate and the attracting ring and the magnetic field generated by the acceleration coil can both cause the magnetohydrodynamic propellant to move along the acceleration channel in a direction away from the atomizing device.

[0013] In some embodiments, a check valve is provided on the atomizing tube, and the forward flow direction of the check valve is from the feed tube to the atomizing tube.

[0014] The present invention also provides a spacecraft device, including a fuselage and the aforementioned propulsion system, wherein the propulsion system is disposed on the fuselage.

[0015] The present invention achieves the following technical effects compared to the prior art:

[0016] In this invention, the propulsion system utilizes a storage and loading device to deliver magnetohydrodynamic (MHD) propellant to an atomizing device. The atomizing device then atomizes the MHD propellant, which is ejected and enters an acceleration device with an initial velocity. The acceleration device further accelerates the MHD propellant, propelling the spacecraft. Since both the atomizing and acceleration devices are powered by nuclear energy, solar energy is not required. This allows the propulsion system to operate for extended periods in extreme environments lacking solar energy, such as those far from the sun or on the opposite side of the sun. Simultaneously, the acceleration device's secondary acceleration of the MHD propellant increases its output velocity, thereby increasing thrust and enabling the spacecraft to operate at higher speeds, meeting greater exploration needs.

[0017] Furthermore, the residual heat generated by the fuel core's heat dissipation is used to insulate the storage and loading device, atomizing device, acceleration device, and magnetohydrodynamic propellant, preventing damage to these devices or rendering the magnetohydrodynamic propellant unusable due to the low temperatures in space. At the same time, by fixing the storage and loading device, atomizing device, and acceleration device within the central channel, space utilization is improved, the overall size of the propulsion system is limited, and the size of aerospace equipment is reduced.

[0018] Furthermore, the accelerating coil can use the electrical energy output from the nuclear power source to generate a magnetic field and accelerate the magnetohydrodynamic propellant. The launch plate and the absorber ring can jointly generate an electric field and accelerate the magnetohydrodynamic propellant. By adjusting the magnitude of the magnetic field strength and the electric field strength, the acceleration of the magnetohydrodynamic propellant can be precisely controlled, thereby achieving precise control of the speed of aerospace equipment. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of the propulsion system in some embodiments of the present invention;

[0021] In the diagram: 1. Nuclear power source; 11. Fuel core; 12. Thermoelectric transducer; 13. Anti-ablation cladding; 14. Thermal insulation cladding; 15. Anti-collision cladding; 16. Sealed cladding; 17. Ventilation component; 2. Storage and feeding device; 21. Storage bladder; 22. Storage tank; 3. Atomizing device; 31. Ultrasonic generator; 32. Amplifier; 33. Emitting plate; 34. Atomizing tube; 4. Accelerating device; 41. Protective shell; 42. Accelerating coil; 43. Magnetic shielding ring; 44. Absorbing ring; 5. Feeding tube; 6. Throttling valve; 7. Check valve. Detailed Implementation

[0022] 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. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0023] The purpose of this invention is to provide a propulsion system and aerospace equipment that solves the problems existing in the prior art, is suitable for use in environments lacking solar energy, and has more sufficient power.

[0024] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0025] Example 1

[0026] This embodiment provides a propulsion system, such as Figure 1As shown, it includes: a nuclear power source 1, a storage and feeding device 2, an atomizing device 3, and an acceleration device 4. The nuclear power source 1 can supply power to the atomizing device 3 and the acceleration device 4. The storage and feeding device 2 is used to store magnetohydrodynamic propellant. The storage and feeding device 2 is connected to the atomizing device 3. The storage and feeding device 2 can transport the magnetohydrodynamic propellant to the atomizing device 3. The atomizing device 3 can atomize the magnetohydrodynamic propellant and transport it to the acceleration device 4. The acceleration device 4 can generate a magnetic field and accelerate the atomized magnetohydrodynamic propellant.

[0027] In this embodiment, the propulsion system operates by having the storage and loading device 2 deliver the magnetohydrodynamic (MHD) propellant to the atomizing device 3. The atomizing device 3 then atomizes the MHD propellant, which is ejected and enters the acceleration device 4 with a certain initial velocity. The acceleration device 4 then provides secondary acceleration to the MHD propellant, propelling the spacecraft. Since both the atomizing device 3 and the acceleration device 4 are powered by the nuclear power source 1, solar energy is not required. This allows the propulsion system to operate for extended periods in extreme environments lacking solar energy, such as those far from the sun or on the opposite side of the sun. Simultaneously, the acceleration device 4 provides secondary acceleration to the MHD propellant, increasing its output velocity and thus thrust, enabling the spacecraft to operate at higher speeds and meeting greater exploration needs.

[0028] In this embodiment, the nuclear power source 1 includes a fuel core 11 and a thermoelectric transducer 12, an ablation-resistant cladding 13, a heat-insulating cladding 14, a shock-absorbing cladding 15, and a sealing cladding 16, which are sequentially wrapped and fixedly connected from the outside to the inside. The fuel core 11 is fixedly connected inside the sealing cladding 16. The thermoelectric transducer 12 is connected to an atomizing device 3 and an accelerating device 4. The fuel core 11 can release heat, and the thermoelectric transducer 12 can convert the heat energy generated by the fuel core 11 into electrical energy. When the nuclear power source 1 is running, the fuel core 11 releases heat and transfers it to the thermoelectric transducer 12. The thermoelectric transducer 12 can convert heat into electrical energy using the Seebeck effect. At the same time, the ablation-resistant cladding 13 can resist high-temperature ablation and prevent the high temperature generated by the fuel core 11 from damaging the thermoelectric transducer. The heat insulation cladding 14 can prevent the high-temperature heat inside the heat insulation cladding 14 from being transferred in a short time. The impact-resistant cladding 15 can resist external impacts and protect the fuel core 11. The fuel sealing cladding 16 can seal and protect the fuel core 11.

[0029] In this first embodiment, the fuel core 11 is a plutonium dioxide (PuO2) fuel core 11. The plutonium dioxide (PuO2) fuel core 11 can release heat through decay, and the heat release time is long, generating high thermal energy.

[0030] In this embodiment, the nuclear power source 1 further includes a venting component 17. An installation gap exists between the sealed casing 16 and the fuel core 11. The nuclear power source 1 has a vent channel connecting the installation gap to the outside. The venting component 17 is fixedly connected within the installation gap and covers the end of the vent channel near the installation gap. The venting component 17 allows the gas generated by the decay of the fuel core 11 to pass through while blocking plutonium particles. During the decay of the plutonium dioxide (PuO2) fuel core 11, helium gas and plutonium-238 particles are generated. The venting component 17 allows the helium gas generated by the decay of the plutonium dioxide (PuO2) fuel core 11 to be discharged through the vent channel, while also preventing plutonium particle leakage.

[0031] In this embodiment, the atomizing device 3 includes an ultrasonic generator 31, an amplitude transformer 32, an emitting plate 33, and an atomizing tube 34. The ultrasonic generator 31 and the emitting plate 33 are fixedly connected to each other at both ends of the amplitude transformer 32. One end of the atomizing tube 34 is connected to and communicates with the storage and feeding device 2, and the other end is connected to the acceleration device 4. The emitting plate 33 has a first through hole through which the atomizing tube 34 passes. The ultrasonic generator 31 is connected to the nuclear power source 1 and can output ultrasonic waves. The nuclear power source 1 supplies electrical energy to the ultrasonic generator 31, causing it to generate ultrasonic waves. The amplitude transformer 32 amplifies the amplitude of the ultrasonic waves, and the emitting plate 33 transmits the amplified ultrasonic waves from the amplitude transformer 32 to the atomizing tube 34, causing the magnetohydrodynamic propellant inside the atomizing tube 34 to be atomized and ejected. Preferably, the ultrasonic transmitter is a piezoelectric ceramic assembly.

[0032] In this first embodiment, the nuclear power source 1 has a central channel, around which the fuel core 11 is arranged. The storage and loading device 2, the atomizing device 3, and the acceleration device 4 are all fixedly connected within the central channel. The storage and loading device 2 is located within the central channel and enclosed by the fuel core 11. The residual heat generated by the heat dissipation of the fuel core 11 is used to insulate the storage and loading device 2, the atomizing device 3, the acceleration device 4, and the magnetohydrodynamic propellant, preventing damage to the storage and loading device 2, the atomizing device 3, and the acceleration device 4, or the unusability of the magnetohydrodynamic propellant due to the low temperature in space. At the same time, fixing the storage and loading device 2, the atomizing device 3, and the acceleration device 4 within the central channel improves space utilization, limits the overall size of the propulsion system, and thus reduces the size of the aerospace equipment.

[0033] In this embodiment, the storage and feeding device 2 includes a storage bladder 21, a storage box 22, a feeding pipe 5, and a throttle valve 6. The storage box 22 is fixedly connected to the central channel, and the outer side wall of the storage box 22 is in contact with the inner side wall of the central channel. The storage bladder 21 is made of soft material and is fixedly connected to the storage box 22. The storage box 22 is used to store magnetohydrodynamic propellant. There is a gap between the outer side wall of the storage bladder 21 and the inner side wall of the storage box 22. The space between the storage bladder 21 and the storage box 22 is filled with inert gas, which exerts pressure on the storage bladder 21. One end of the feeding pipe 5 is connected to and communicates with the storage bladder 21, and the other end is connected to and communicates with the atomizing pipe 34. The feeding pipe 5 is equipped with a throttle valve 6. When the propulsion system is running, the throttle valve 6 is opened, and the storage bladder 21 can be compressed under the pressure of the inert gas, thereby pushing the magnetohydrodynamic propellant into the atomizing pipe 34 for atomization, thus conveniently realizing the supply of magnetohydrodynamic propellant. Preferably, there are two feeding pipes 5, and each feeding pipe 5 is equipped with a throttle valve 6.

[0034] In this embodiment, the acceleration device 4 includes a protective shell 41, an acceleration coil 42, a magnetic shielding ring 43, and an absorber ring 44. The storage tank 22 has an installation channel connecting both sides of the storage tank 22. The protective shell 41 is fixedly connected in the installation channel. The protective shell 41 has an acceleration channel connecting both sides of the protective shell 41. The acceleration coil 42 is fixedly connected in the protective shell 41 and surrounds the acceleration channel. One end of the acceleration channel is connected to the atomizing tube 34, and the other end is fixedly connected to the magnetic shielding ring 43. The absorber ring 44 is fixedly connected to the magnetic shielding ring 43. The through hole on the absorber ring 44, the through hole on the magnetic shielding ring 43, and the acceleration channel are connected. The emitter 33, the absorber ring 44, and the acceleration coil 42 are all connected to the nuclear power source 1. The emitter 33 and the absorber ring 44 have a potential difference. The electric field generated by the emitter 33 and the absorber ring 44 and the magnetic field generated by the acceleration coil 42 can both cause the magnetohydrodynamic propellant to move away from the atomizing device 3 along the acceleration channel. Acceleration coil 42 can use the electrical energy output by nuclear power source 1 to generate a magnetic field and accelerate the magnetohydrodynamic propellant. Launch plate 33 and absorber ring 44 can jointly generate an electric field and accelerate the magnetohydrodynamic propellant. By adjusting the magnitude of the magnetic field strength and the magnitude of the electric field strength, the acceleration of the magnetohydrodynamic propellant can be precisely controlled, thereby achieving precise control of the speed of aerospace equipment.

[0035] In this first embodiment, a check valve 7 is provided on the atomizing tube 34. The forward flow direction of the check valve 7 is from the feed tube 5 to the atomizing tube 34. The check valve 7 can prevent the backflow of the magnetohydrodynamic propellant.

[0036] Example 2

[0037] This embodiment provides a spacecraft device, including a fuselage and a propulsion system as described in Embodiment 1, with the propulsion system mounted on the fuselage.

[0038] The aerospace equipment in this embodiment, by using the propulsion system in Embodiment 1, can be used for a long time in extreme environments lacking solar energy, such as aphelion or doubly sun. At the same time, the acceleration device 4 can perform secondary acceleration on the magnetohydrodynamic propellant, increasing the output speed of the magnetohydrodynamic propellant and thus increasing the thrust, enabling the aerospace equipment to operate at a faster speed and meet more exploration needs.

[0039] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A propulsion system, characterized in that: include: The system includes a nuclear power source, a storage and feeding device, an atomizing device, and an acceleration device. The nuclear power source supplies power to the atomizing device and the acceleration device. The storage and feeding device stores magnetohydrodynamic (MHD) propellant and is connected to the atomizing device. The storage and feeding device delivers the MHD propellant to the atomizing device. The atomizing device atomizes the MHD propellant and delivers it to the acceleration device. The acceleration device generates a magnetic field and accelerates the atomized MHD propellant.

2. The propulsion system according to claim 1, characterized in that: The nuclear power source includes a fuel core and, from the outside to the inside, a thermoelectric transducer, an ablation-resistant cladding, a heat-insulating cladding, a shock-resistant cladding, and a sealing cladding that are sequentially wrapped and fixedly connected. The fuel core is fixedly connected inside the sealing cladding. The thermoelectric transducer is connected to the atomizing device and the accelerating device. The fuel core can release heat, and the thermoelectric transducer can convert the heat energy generated by the fuel core into electrical energy.

3. The propulsion system according to claim 2, characterized in that: The fuel core is a plutonium dioxide (PuO2) fuel core.

4. The propulsion system according to claim 3, characterized in that: The nuclear power source also includes a venting component. There is an installation gap between the sealed casing and the fuel core. The nuclear power source has a venting channel that connects the installation gap and the outside. The venting component is fixedly connected within the installation gap and covers one end of the venting channel near the installation gap. The venting component allows the gas generated by the decay of the fuel core to pass through and can block plutonium particles.

5. The propulsion system according to claim 2, characterized in that: The atomizing device includes an ultrasonic generator, an amplitude transformer, an emitting plate, and an atomizing tube. The ultrasonic generator and the emitting plate are fixedly connected to each end of the amplitude transformer, respectively. One end of the atomizing tube is connected to and communicates with the storage and feeding device, and the other end is connected to the acceleration device. The emitting plate has a first through hole, and the atomizing tube passes through the first through hole. The ultrasonic generator is connected to the nuclear power source and is capable of outputting ultrasonic waves.

6. The propulsion system according to claim 5, characterized in that: The nuclear power source has a central channel, the fuel core is arranged around the central channel, and the storage and feeding device, the atomizing device and the acceleration device are all fixedly connected inside the central channel.

7. The propulsion system according to claim 6, characterized in that: The storage and feeding device includes a storage bladder, a storage tank, a feeding pipe, and a throttle valve. The storage tank is fixedly connected within the central channel, and the outer wall of the storage tank is in contact with the inner wall of the central channel. The storage bladder is made of soft material and is fixedly connected within the storage tank. The storage tank is used to store the magnetohydrodynamic propellant. There is a gap between the outer wall of the storage bladder and the inner wall of the storage tank. The space between the storage bladder and the storage tank is filled with inert gas, which exerts pressure on the storage bladder. One end of the feeding pipe is connected to and communicates with the storage bladder, and the other end is connected to and communicates with the atomizing pipe. A throttle valve is installed on the feeding pipe.

8. The propulsion system according to claim 7, characterized in that: The acceleration device includes a protective shell, an acceleration coil, a magnetic shielding ring, and an attracting ring. The storage tank has an installation channel connecting both sides of the storage tank. The protective shell is fixedly connected to the installation channel. The protective shell has an acceleration channel connecting both sides of the protective shell. The acceleration coil is fixedly connected to the protective shell and surrounds the acceleration channel. One end of the acceleration channel is connected to the atomizing tube, and the other end is fixedly connected to the magnetic shielding ring. The attracting ring is fixedly connected to the magnetic shielding ring. The through holes on the attracting ring, the magnetic shielding ring, and the acceleration channel are connected. The launch plate, the attracting ring, and the acceleration coil are all connected to the nuclear power source. The launch plate and the attracting ring have a potential difference. The electric field generated by the launch plate and the attracting ring and the magnetic field generated by the acceleration coil can both cause the magnetohydrodynamic propellant to move along the acceleration channel in a direction away from the atomizing device.

9. The propulsion system according to claim 7, characterized in that: The atomizing tube is equipped with a check valve, and the forward flow direction of the check valve is from the feed tube to the atomizing tube.

10. An aerospace device, characterized in that: It includes a fuselage and a propulsion system as described in any one of claims 1-9, wherein the propulsion system is disposed on the fuselage.

Images