CN112158343A - Unmanned aerial vehicle power device for terrain aerial survey of long and large railway - Google Patents
Unmanned aerial vehicle power device for terrain aerial survey of long and large railway Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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Abstract
The invention relates to the technical field of unmanned aerial vehicle power sources, in particular to an unmanned aerial vehicle power device for terrain aerial survey of long and large railway lines, which is characterized in that: the system comprises a nuclear power system, a superconducting power generation system and a power propulsion system, wherein the nuclear power system and the superconducting power generation system are both connected with the power propulsion system so that the power propulsion system can provide power required by the flight of the unmanned aerial vehicle, and the power propulsion system is a propeller; and a nuclear heat exchanger is arranged between the nuclear power system and the superconducting discovery system, and transfers the heat energy of the nuclear power system to a superconducting generator of the superconducting power generation system so as to realize the high-speed rotation of the superconducting generator. The invention has the advantages that: the method has the advantages of voyage and ultra-long dead time, and has very important significance for acquiring large data of surface topography along the newly-built railway.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle power sources, in particular to an unmanned aerial vehicle power device for terrain aerial survey of long and large railway lines, and particularly relates to a superconductive and nuclear power interactive unmanned aerial vehicle power device.
Background
Along with unmanned aerial vehicle science and technology development is more and more rapid, unmanned aerial vehicle also uses in the operation of railway aerial survey with continuous innovation, and it often has degree of automation height, aerial survey is fast, and effective operating personnel working strength's advantage.
However, the conventional unmanned aerial vehicle includes a solar unmanned aerial vehicle or a hydrocarbon fuel unmanned aerial vehicle, which has limited load, low flying speed and limited power generation capability of a fuselage, cannot provide sufficient power for an airborne radar and a communication system, and is very difficult to detect if the aerial vehicle is long-time and remote and does not land on the premise of energy supplement; especially when unmanned aerial vehicle uses long and large railway navigation time measurement, long and large railway route's mileage is extremely long, and unmanned aerial vehicle often need carry out the energy supply through landing many times in order to guarantee its flight power, can so, the analysis of the resource topography information that obtains when surveying unmanned aerial vehicle by plane has further proposed the processing requirement again, and the resource topography information that needs to guarantee to break off many times can effectively and accurately be fit together to guarantee that the actual conditions is identical.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle power device for long-reach railway terrain aerial survey according to the defects of the prior art, the power of the unmanned aerial vehicle is provided by combining a superconducting and nuclear power interaction method, and meanwhile, a flight means is improved by matching with a propeller, so that the long-time uninterrupted flight of the unmanned aerial vehicle is realized, and the aerial survey requirement of the long-reach railway terrain is met.
The purpose of the invention is realized by the following technical scheme:
the utility model provides an unmanned aerial vehicle power device for long and large line railway topography aerial survey which characterized in that: the system comprises a nuclear power system, a superconducting power generation system and a power propulsion system, wherein the nuclear power system and the superconducting power generation system are both connected with the power propulsion system so that the power propulsion system can provide power required by the flight of the unmanned aerial vehicle, and the power propulsion system is a propeller; and a nuclear heat exchanger is arranged between the nuclear power system and the superconducting discovery system, and transfers the heat energy of the nuclear power system to a superconducting generator of the superconducting power generation system so as to realize the high-speed rotation of the superconducting generator.
The thruster is a Hall electric thruster, and the Hall electric thruster is connected with the nuclear power system and the superconducting power generation system.
The nuclear power system comprises a nuclear safety emergency refitting device, wherein the nuclear safety emergency refitting device is composed of a lead shielding plate and lead sand, the lead shielding plate is attached to the outer surface of a cabin of a nuclear reactor of the nuclear power system, and the lead sand is arranged between the lead shielding plate and the outer surface of the cabin.
The nuclear heat exchanger is arranged in an annular combustion chamber of the nuclear power system, and adopts a multi-ring structure coupled with the annular combustion chamber.
The superconducting power generation system comprises a superconducting generator and a thermal energy storage, the thermal energy storage is connected with the nuclear power system to convert the thermal energy of the nuclear power system into high-pressure steam, and a motor rotor of the superconducting generator is arranged in the thermal energy storage.
The power propulsion system comprises a propellant, a propeller, magnetic poles, a hollow cathode, electrons, a thermal energy storage and a discharge chamber, wherein the propellant is connected with a power transmission device of the superconducting power generation system, the magnetic poles provide a magnetic field environment for the propeller, the hollow cathode is connected with the propeller, the electrons provide the propellant and electric energy for the propeller, the thermal energy storage is used for recycling a heat source generated by the propeller, and the discharge chamber is connected with the thermal energy storage to convert the thermal energy into the electric energy.
The invention has the advantages that:
1) the unmanned aerial vehicle nuclear power breaks away from the defect of insufficient cruising ability of the traditional unmanned aerial vehicle, realizes remote detection without landing supplementary energy, and greatly improves the operation efficiency of the unmanned aerial vehicle.
2) The unmanned aerial vehicle load of solving traditional unmanned aerial vehicle solar energy unmanned aerial vehicle or hydrocarbon fuel is limited, and flying speed is lower, and fuselage generating capacity is limited, realizes long-time empty carrying out relevant data acquisition operation.
3) The high-temperature superconducting technology is used for realizing the energy lossless transmission of the unmanned aerial vehicle, the superconducting magnetic energy storage can independently perform active and reactive power compensation on a power system in four quadrants, and the power supply of the unmanned aerial vehicle is effectively improved.
4) The aim of safe nuclear use is achieved by emergency modification of nuclear safety and shielding nuclear pollution by using different materials for many times.
5) Based on relevant regulations of nuclear safety regulations, the unmanned aerial vehicle is cracked to acquire and analyze the resource topographic information under the conditions of long time, long distance and no landing energy supply in a newly-built high-speed rail (or a long-line railway with the same grade); the propeller is used for replacing a traditional unmanned aerial vehicle rotor wing and a fixed wing to improve a flight means, and meanwhile, a method combining superconductivity and nuclear power interaction force breaks through a traditional unmanned aerial vehicle endurance mode to provide a power device, long-line railway survey design is completed in a very short time, and good conditions are created for lowering labor and lowering the target.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a diagram of the design system architecture of the present invention;
FIG. 3 is a schematic diagram of the enhanced heat transfer of the air and nuclear heat exchanger of the present invention;
fig. 4 shows the radiation dose field design limits of the present invention.
Detailed Description
The features of the present invention and other related features are described in further detail below by way of example in conjunction with the following drawings to facilitate understanding by those skilled in the art:
as shown in fig. 1-4, the labels 1-23 and a-C are respectively shown as: the system comprises a nuclear reactor 1, a nuclear safety emergency modifying device 2, a nuclear heat exchanger 3, a thermal effect box body 4, a liquid nitrogen vacuum container 5, a superconducting winding 6, a motor rotor 7, a power transmission device 8, an electric insulation filling 9, a thermal energy storage 10, a normally conductive winding 11, a vacuum container wall 12, an induction plate 13, a stator superconducting winding 14, a pressure hole 15, a current lead 16, a propellant 17, a propeller 18, a magnetic pole 19, a hollow cathode 20, an electron 21, a thermal energy storage 22, a discharge chamber 23, a nuclear power system A, a superconducting power generation system B and a power propulsion system C.
Example (b): the unmanned aerial vehicle power device who is used for long and large line railway topography aerial survey in this embodiment includes, nuclear power unmanned aerial vehicle uses nuclear power source and safety protection thereof as the core in principle. The nuclear power unmanned plane has the characteristics of nuclear radiation, high power, high voltage and large current, so that corresponding solutions must be made in the fields of nuclear power sources, nuclear safety systems, mechanical design, thermal energy utilization, high-temperature superconductivity and the like. Meanwhile, the embodiment is based on: the nuclear safety needs to be designed according to the standards of GB 15146 + 2008 series nuclear critical safety of fissile materials outside the reactor, GB 18871 + 2002 basic standards for the safety of ionizing radiation protection and radiation sources, GB-11806 + 2004 + safe transport regulations for radioactive substances, GB 11806 + 2004 + safe transport regulations for radioactive substances, and the like, and the related requirements specified by the spacecraft.
1) Nuclear power source
The nuclear power source firstly determines a scheme of selecting a nuclear reactor or an isotope power source according to system requirements of the unmanned aerial vehicle on the nuclear power source, including power generation power, conversion efficiency, radiation dose, mass, volume, service life and the like, so as to ensure that the unmanned aerial vehicle can complete tasks and functions as required.
The nuclear power source designed by the invention is an ultra-high power space nuclear reactor power source, the thermal power of the reactor is designed to be 4.0MW, the outlet temperature is 1800K, Xe is selected as a power generation working medium, the output electric power of the system is 2.80MWe, and the system efficiency is 55.2%. The space nuclear reactor (especially the space nuclear reactor applied to the short-life orbit) preferably selects the high-enrichment U-235 as the fuel. The nuclear power source parameters ensure that the unmanned aerial vehicle can fly without stopping to acquire data in the flying process.
2) Thermally controlled interaction
In conventional reactor design, the design of unmanned aerial vehicle mini-reactor is limited by the thermal aspects of the reactor core. If the heat of the reactor core can be effectively and rapidly output, the volume of the reactor core is smaller, and the weight of the reactor core is greatly reduced, which has great significance for the small and light reactor core.
Since the starting process of the nuclear power system is subjected to an initial boiling stage, bubbles are generated rapidly and flow is violent in the heating process, and the maintenance of the potential flow instability phenomenon influences the wall surface coupling heat transfer. The invention designs a nuclear heat exchanger which is a coupling component of a phase change heat transfer channel and a propulsion system engine and mainly used for heating compressed air by utilizing heat from a reactor core. For nuclear powered engines, air is the primary source of thrust. The nuclear heat exchanger with the multi-ring structure is placed inside an annular combustion chamber of the engine to form an integrated propulsion system, the prototype of the turbojet engine is a TRI60 turbojet engine, and the propulsion performance is effectively improved by the aid of the integrated coupling structure formed by the annular combustion chamber space, so that the nuclear heat exchanger achieves the same propulsion performance as that of a conventional fuel engine by means of the original combustion chamber space to achieve heat transfer inside the heat exchanger.
The problem of the high-power heat emission of nuclear power unmanned aerial vehicle is solved in the thermal control interaction, on the other hand can provide energy conversion for the later stage with heat energy transfer superconductive generator.
3) Superconducting motor
In the embodiment, the superconducting winding is adopted for the motor end to replace the copper winding to be used as the armature winding of the motor, so that the power density of the motor can be further improved, and the volume of the motor is hardly increased. At present, the high-temperature superconducting armature winding motor can only work at low rotating speed. The invention breaks through the high-speed application of the low-speed and high-temperature superconducting armature winding motor, and is beneficial to further improving the power density of the unmanned aerial vehicle motor.
The invention provides a high-temperature superconducting concept, which realizes the high-speed superconducting motor in a nuclear reaction high-temperature environment. The specific parameters of the invention are 25kW, 6 poles, 1800r/min, the high-temperature full-superconducting motor with the stator outer diameter of 230mm, the stator rated current of 70A and the current frequency of 50 HZ. The armature winding of the motor adopts YBCO strips (boundary current is 100A) produced by AMSC company, after the armature winding is wound into a superconducting coil, the critical current of the coil is about 50A, and the rotor of the motor adopts a YBCO superconducting block permanent magnet for excitation.
In this kind of motor, high temperature superconducting winding transmits direct current or low frequency alternating current, has effectively controlled the alternating current loss, guarantees simultaneously that the motor has higher power density, ensures the unmanned aerial vehicle power supply.
4) Propulsion device
The propellant is ionized by the Hall current effect generated by the closed drift motion of electrons in an orthogonal electromagnetic field to generate plasma, and ions are accelerated mainly through an electrostatic field to generate thrust to drive the unmanned aerial vehicle to fly directionally.
The Hall electric thruster is used as a driving device, has the advantages of high thrust density, high thrust-power ratio, reliable system and the like, and has the functions of maintaining the position of the unmanned aerial vehicle, transferring a flight path, adjusting the flight path and the like. The invention adopts a Hall electric propulsion method, and the main parameters are as follows: the atmosphere is adopted as a propellant, and the 5KW Hall electric propulsion system is simple and reliable and has good safety; the comprehensive performance is good, and both thrust and specific impulse are considered. The thrust power ratio is maintained at 40-66Mn/kW, and the thrust density is 1-2mN/cm2, and the configuration can shorten the flight mission.
The Hall electric propulsion of above-mentioned configuration is used on unmanned aerial vehicle, can bring following advantage:
1. the propellant is greatly saved, the effective load is increased or the surveying operation period of the unmanned aerial vehicle is prolonged;
2. the impulse is little, the uniformity is good and easily control, improves unmanned aerial vehicle gesture stability.
3. The flexibility of landing place selection reduces the gravitational acceleration dependence of the high-speed incremental unmanned aerial vehicle on the unmanned aerial vehicle.
5) Nuclear safety emergency retrofit
The nuclear safety emergency modification mainly comprises an integral radiation-proof shielding structure consisting of lead shielding plates, lead sand and a transition connection structure. The lead shielding layer is composed of a lead plate with the thickness of 10 mm, the lead shielding plate has the main radiation shielding effect when the lead plate with the size of 10 mm is adopted in radiation shielding. Therefore, the integral shielding has no dead angle, the integral structure can be attached to the outer surface of the cabin, and the lead sand forms an effective radiation-proof shielding layer, so that the safe use of the nuclear energy of the unmanned aerial vehicle is protected.
On the premise of meeting the radiation safety requirement, the primary shielding and the secondary shielding of the reactor are comprehensively considered so as to achieve the purposes of reducing the size of the shielding body as much as possible and reducing the weight of the shielding body. The radiation shield design for a nuclear reactor or isotope power supply should meet the radiation dose field design limits specified in the table below, as shown in fig. 4.
The structure in the embodiment is divided into three systems, namely a nuclear power system A, a superconducting power generation system B and a power propulsion system C. The nuclear power obtains energy by using controllable nuclear reaction so as to obtain power, heat and electric energy, wherein the nuclear reaction is a process of changing the state of atomic nucleus or forming a new nucleus caused by collision of incident particles (or atomic nucleus) and the atomic nucleus (called target nucleus) and provides a main power source. Secondly, nuclear heat is interacted to promote superconducting lossless power generation through thermal control, the power is a secondary power supply, the energy loss is reduced to the minimum in the purpose, finally, a propeller is used as a terminal, electric energy is converted into kinetic energy, the unmanned aerial vehicle flies, and the capacity conversion mode is as follows in sequence: nuclear energy, thermal energy, electrical energy, mechanical energy. The design system architecture is shown in fig. 2.
The working principle of the power device is as follows:
1. nuclear and heat energy generation principle
The nuclear reactor designed by the embodiment is an ultra-high power space nuclear reactor power supply, the thermal power of the reactor is designed to be 4.0MW, the outlet temperature is 1800K, Xe is selected as a power generation working medium, the system output electric power is 2.80MWe, and the system efficiency is 55.2%. The nuclear reactor 1 preferably uses high enrichment U-235 as fuel. The nuclear safety emergency refitting device 2 mainly comprises an integral radiation-proof shielding structure and a transition connection structure, wherein the integral radiation-proof shielding structure comprises a lead shielding plate, lead sand and the transition connection structure. The nuclear heat exchanger 3 has the overall dimension parameter of ∅ 93.4.4- ∅ 280mm, a multi-layer annular channel is arranged in a combustion chamber annular space to form a nuclear heat exchanger structure, the outer side is strong steam for phase change heat exchange, the inner side is compressed air for engine air inlet, and two working media realize heat transfer in the heat exchanger through inner wall surface heat exchange. The thermal effect box body 4 is a thermal energy conversion space device and comprises two layers of materials, wherein the first layer is austenitic stainless steel, namely stainless steel with an austenitic structure at normal temperature. The steel contains about 18 percent of Cr, 8 to 25 percent of Ni and about 0.1 percent of C, has stable austenite structure, good strength and corrosion resistance at high temperature and low price, and is also used as cladding of the heat-effect box body 4 and other structural materials. The second layer is an absorbent, the main material is boron, and the second layer is used for adsorbing neutrons and gamma rays with high residual penetrating power and carrying out secondary protection treatment on nuclear pollution.
Specific ways of generating nuclear energy: the energy released in the process of the change of the atomic nucleus is mainly released in the nuclear power system at the stage by a fission mode, and the atomic nucleus with larger mass is split into 2 new atomic nuclei under the bombardment of neutrons and releases the energy. The capability is focused on the effective control of the nuclear reactor 1, and the nuclear safety emergency reformer 2 is a containment vessel to prevent the nuclear leakage. The nuclear heat exchanger 3 receives a large amount of heat energy released by the nuclear reactor 1 for storage, and the austenitic stainless steel of the thermal effect box body 4 cannot deform at the high temperature of the nuclear reactor 1, so that the space structure stability of the nuclear energy generation stage is maintained.
2. Design principle of nuclear heat exchanger
Design principle of the nuclear heat exchanger 3: the nuclear heat exchanger with the multi-ring structure is designed and placed inside an annular combustion chamber of an engine to form an integrated propulsion system, the prototype of the turbojet engine is a TRI60 turbojet engine, and the nuclear heat exchanger is arranged by utilizing an integrated coupling structure formed by the annular combustion chamber space of the turbojet engine.
For a turbojet engine, air enters the inside of a propulsion system engine from an engine air inlet channel, enters a nuclear heat exchanger after being pressurized by a compressor, a main heat exchange area of the nuclear heat exchanger is in direct contact with high-temperature strong steam to form a condensation section of a heat transfer pipeline, compressed air forms an adherence heat exchanger in an inner cavity and Li steam forms an adherence heat exchanger in an outer cavity, the air realizes the increase of the self baking value in a wall surface heat transfer mode, and the heated air enters a turbine to do work to generate thrust. The general arrangement of the nuclear heat exchanger in heat exchange relationship with air is shown in figure 4.
The nuclear heat exchanger 3 is arranged in an annular space of a combustion chamber of 93.4mm-280mm, a turbine shaft of a turbojet engine is arranged on the inner side of a wall surface of 93.4mm, an outer wall surface of an aircraft engine is arranged on the outer side of the wall surface of 280mm, all the wall surfaces are designed to be heat insulation wall surfaces, a plurality of layers of annular channels are arranged in an annular cavity to form a nuclear heat exchanger structure, Li steam of phase change heat exchange is led out on the outer side, compressed air of engine air inlet is led out on the inner side, and two working media realize heat transfer in the heat exchanger through.
3. Principle of electric energy design
In the superconducting power generation system B, the present embodiment proposes a high-temperature superconducting concept, which realizes a high-speed superconducting motor in nuclear and thermal energy conduction. The concrete form is as follows:
1) nuclear, thermal energy pretreatment
The previous part of nuclear and thermal energy is mainly removed, and the loss-free effect in energy transfer is controlled as much as possible. The specific form is that a two-layer system space is provided by arranging a liquid nitrogen and vacuum container 5, and the liquid nitrogen layer and the vacuum layer are contained for heat insulation. The specific parameters of the superconducting power generation system are set to be 25kW, 6 poles, 1800r/min, a high-temperature full-superconducting motor with the stator outer diameter of 230mm, the rated current of the stator is 70A, and the current frequency is 50 HZ. A superconducting winding 6 of the motor adopts a YBCO strip (boundary current is 100A) produced by AMSC company, after the superconducting winding is wound into a superconducting coil, the critical current of the coil is about 50A, and a rotor 7 of the motor adopts a YBCO superconducting block permanent magnet to provide a stator power supply.
2) Forming a superconducting winding
The motor is cooled by the liquid nitrogen layer, and is simultaneously depressurized through the pressure hole 15, so that the system is prevented from being damaged due to overlarge space high-temperature pressure. The liquid nitrogen layer is externally provided with a vacuum container, and the liquid nitrogen and vacuum container 5 belongs to a cooling area. The whole motor stator is arranged in the space and comprises a stator superconducting winding 14, a normal conducting winding 11, a superconducting winding 6, a current lead 16 and the like. The superconducting tape has mechanical properties similar to ceramics, and excessive twisting or bending stress affects the current carrying capacity, and superconducting coils are wound in advance, arranged in a stator superconducting winding 14 of a motor, and connected with joints of each coil, and the steps are performed for forming the superconducting winding.
In order to reduce the influence of the magnetic field generated by other windings on the current carrying capacity of the superconducting winding. The normal conducting winding 11 and the superconducting winding 6 can enable the high-temperature superconducting coil to bear alternating current with the frequency of 200 HZ. The mixed electromagnetic windings are uniformly and symmetrically distributed along the circumferential direction of the rotor, the high-temperature superconducting part of the mixed windings provides stable and adjustable bearing capacity for the rotor, and the control of the interference on the rotor in working is realized through the induction plate detection 13 and the normal conductive winding 11 so as to realize the stability of a magnetic suspension system. The superconducting winding 14 of the stator adopts a 2-pole 12-slot structure, the normal-conducting winding 11 adopts a 4-pole 12-slot double-layer winding structure, and ∅ 1.0.0 mm copper wires are adopted for winding.
3) Conversion of nuclear, thermal energy into electrical energy
The heat energy storage 10 absorbs the transferred heat to be changed into high-pressure steam, and then the high-pressure steam pushes the motor rotor 7 to drive the superconducting power generation system to generate power. The motor rotor 7 is arranged in a vacuum heat energy storage 10, and the vacuum area of the rotor is connected with the liquid nitrogen and the vacuum container 5. The vacuum container wall 12 not only plays a role in heat insulation, but also reduces the air resistance of the rotor, and is beneficial to increasing the rotating speed of the motor. The stator and the rotor of the motor are separated by a sealed container, the container wall of the air gap part is made of glass fiber reinforced plastics and is adhered with the metal bearing seats of the upper part and the lower part, and eddy current loss generated by an alternating air gap magnetic field in the container wall is avoided.
The superconducting power generation system is terminated by a power transmission device 8, and power transmission is performed through a current lead 16, and in order to prevent leakage, the superconducting power generation system is mainly configured by carbon dioxide using an electrical insulation filler 9 as an insulator, and thus, components such as a generator, a rotor, a stator and the like can be cleaned without damage.
4. Principle of mechanical energy propulsion
The terminal of the superconducting power generation system is used for ionizing the propellant 17 and generating plasma by the Hall current effect generated by the closed drift motion of the power transmission device 8 in an orthogonal electromagnetic field, and the ions are accelerated by an electrostatic field to generate thrust.
In an ignition state, the mechanical kinetic energy is directly provided by the propeller 18, the power processing unit of the propeller 18 comprises a magnetic pole 19, a hollow cathode 20, an electron 21 and the like, the magnetic pole 19 provides a magnetic field environment for the propeller 18, the hollow cathode 20 of the electric propeller needs to be heated for several minutes before being started to ignite, the purpose of improving the reliability of the hollow cathode and the Hall propeller is achieved, the electron 21 supplies propellant and electric energy to the Hall propeller, the heat energy storage 22 and the discharge chamber 23 are included, the mechanical energy is recycled to generate a heat source to convert the secondary mechanical energy into the electric energy, and therefore the operation of the power propulsion system is controlled.
In the embodiment, in specific implementation: the whole power transmission path is as follows: in the nuclear power system A, a nuclear power source in a nuclear reactor 1 is a power source of a super-high power space nuclear reactor, and incident particles (or atomic nuclei) collide with atomic nuclei (called target nuclei) to cause the state of the atomic nuclei to change or form new nuclei to generate heat energy and electric energy. Wherein, the electric energy is directly transmitted to a propeller 18 in the power propulsion system C, and the flight power is obtained by the work of the propeller 18. Secondly, heat energy is transmitted to a heat energy storage 10 of the superconducting power generation system B through the nuclear heat exchanger 3 for storing heat energy, the heat energy storage 10 converts the heat energy into high-temperature steam to drive a motor rotor 7 to work, the motor rotor 7 drives a stator superconducting winding 14 to work, the superconducting power generation system terminal is a power transmission device 8, power transmission is completed through a current lead 16, a propellant 17 is ionized by utilizing a Hall current effect generated by the closed drift motion of the power transmission device 8 in an orthogonal electromagnetic field to generate plasma, and ions are accelerated through an electrostatic field to generate thrust. Meanwhile, the power propulsion system C recovers mechanical energy to generate a heat source to convert secondary mechanical energy into electric energy at the terminal of the superconducting power generation system B, and the energy is fully utilized in advance.
Although the conception and the embodiments of the present invention have been described in detail with reference to the drawings, those skilled in the art will recognize that various changes and modifications can be made therein without departing from the scope of the appended claims, and therefore, they are not to be considered repeated herein.
Claims (6)
1. The utility model provides an unmanned aerial vehicle power device for long and large line railway topography aerial survey which characterized in that: the system comprises a nuclear power system, a superconducting power generation system and a power propulsion system, wherein the nuclear power system and the superconducting power generation system are both connected with the power propulsion system so that the power propulsion system can provide power required by the flight of the unmanned aerial vehicle, and the power propulsion system is a propeller; and a nuclear heat exchanger is arranged between the nuclear power system and the superconducting discovery system, and transfers the heat energy of the nuclear power system to a superconducting generator of the superconducting power generation system so as to realize the high-speed rotation of the superconducting generator.
2. The drone power plant for long haul railway terrain aerial surveying of claim 1, wherein: the thruster is a Hall electric thruster, and the Hall electric thruster is connected with the nuclear power system and the superconducting power generation system.
3. The drone power plant for long haul railway terrain aerial surveying of claim 1, wherein: the nuclear power system comprises a nuclear safety emergency refitting device, wherein the nuclear safety emergency refitting device is composed of a lead shielding plate and lead sand, the lead shielding plate is attached to the outer surface of a cabin of a nuclear reactor of the nuclear power system, and the lead sand is arranged between the lead shielding plate and the outer surface of the cabin.
4. The drone power plant for long haul railway terrain aerial surveying of claim 1, wherein: the nuclear heat exchanger is arranged in an annular combustion chamber of the nuclear power system, and adopts a multi-ring structure coupled with the annular combustion chamber.
5. The drone power plant for long haul railway terrain aerial surveying of claim 1, wherein: the superconducting power generation system comprises a superconducting generator and a thermal energy storage, the thermal energy storage is connected with the nuclear power system to convert the thermal energy of the nuclear power system into high-pressure steam, and a motor rotor of the superconducting generator is arranged in the thermal energy storage.
6. The drone power plant for long haul railway terrain aerial surveying of claim 1, wherein: the power propulsion system comprises a propellant, a propeller, magnetic poles, a hollow cathode, electrons, a thermal energy storage and a discharge chamber, wherein the propellant is connected with a power transmission device of the superconducting power generation system, the magnetic poles provide a magnetic field environment for the propeller, the hollow cathode is connected with the propeller, the electrons provide the propellant and electric energy for the propeller, the thermal energy storage is used for recycling a heat source generated by the propeller, and the discharge chamber is connected with the thermal energy storage to convert the thermal energy into the electric energy.
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1215499A (en) * | 1967-09-18 | 1970-12-09 | Gen Electric | Improvements in aircraft nuclear propulsion system having an alternative power source |
| US20050012397A1 (en) * | 2003-07-14 | 2005-01-20 | Weeber Konrad Roman | Methods and system for power generation |
| US20050166574A1 (en) * | 1999-01-27 | 2005-08-04 | Agence Spatiale Europeenne | Propulsion device, in particular for a rocket |
| RU2533672C1 (en) * | 2013-07-18 | 2014-11-20 | Государственный научный центр Российской Федерации-федеральное государственное унитарное предприятие "Исследовательский Центр имени М.В. Келдыша" | Spacecraft nuclear propulsion system |
| US9964073B1 (en) * | 2014-11-06 | 2018-05-08 | Florida Turbine Technologies, Inc. | Liquid rocket engine with hybrid electric motor driven pump |
| CN109677639A (en) * | 2018-12-30 | 2019-04-26 | 上海空间推进研究所 | The high-power Nuclear Power System in space based on Closed Brayton Power Cycle |
-
2020
- 2020-10-16 CN CN202011108637.4A patent/CN112158343B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1215499A (en) * | 1967-09-18 | 1970-12-09 | Gen Electric | Improvements in aircraft nuclear propulsion system having an alternative power source |
| US20050166574A1 (en) * | 1999-01-27 | 2005-08-04 | Agence Spatiale Europeenne | Propulsion device, in particular for a rocket |
| US20050012397A1 (en) * | 2003-07-14 | 2005-01-20 | Weeber Konrad Roman | Methods and system for power generation |
| RU2533672C1 (en) * | 2013-07-18 | 2014-11-20 | Государственный научный центр Российской Федерации-федеральное государственное унитарное предприятие "Исследовательский Центр имени М.В. Келдыша" | Spacecraft nuclear propulsion system |
| US9964073B1 (en) * | 2014-11-06 | 2018-05-08 | Florida Turbine Technologies, Inc. | Liquid rocket engine with hybrid electric motor driven pump |
| CN109677639A (en) * | 2018-12-30 | 2019-04-26 | 上海空间推进研究所 | The high-power Nuclear Power System in space based on Closed Brayton Power Cycle |
Non-Patent Citations (3)
| Title |
|---|
| （苏）科马罗夫斯基: "《核装置辐射屏蔽建筑材料》", 30 September 1965, 上海科学技术出版社 * |
| 李琳等: "电力推进之优势", 《船电技术》 * |
| 苏光辉等: "核能在未来载人航天中的应用", 《载人航天》 * |
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