CN109823573B - Heat storage-power generation-propulsion integrated solar thermal propulsion system - Google Patents
Heat storage-power generation-propulsion integrated solar thermal propulsion system Download PDFInfo
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- CN109823573B CN109823573B CN201910059186.0A CN201910059186A CN109823573B CN 109823573 B CN109823573 B CN 109823573B CN 201910059186 A CN201910059186 A CN 201910059186A CN 109823573 B CN109823573 B CN 109823573B
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Abstract
The invention relates to a heat storage-power generation-propulsion integrated solar thermal propulsion system which comprises a secondary condenser, an energy extractor, a heat absorption cavity, a heat storage cavity, a porous heat absorption channel, a heat insulation layer, a spray pipe, a vacuum cavity and a thermal photovoltaic system, wherein the heat storage cavity is of a closed cavity structure, the heat absorption cavity is embedded in the heat storage cavity, the energy extractor is embedded in the heat absorption cavity, the energy extractor is connected with the front end face of the secondary condenser, the rear end face of the secondary condenser is positioned outside the heat insulation layer, the secondary condenser is of a circular truncated cone structure coaxially distributed with the heat storage cavity, the vacuum cavity is coated on the outer side of the rear end face of the side wall of the heat storage cavity, the porous heat absorption channel is coated outside the heat absorption cavity, the porous heat absorption through front end face is communicated with the spray pipe, and the thermal photovoltaic system comprises a heat dissipation channel and a heat pipe. The invention can generate 730s specific impulse and 0.9N thrust by using hydrogen as a working medium under the design working condition, has the generating capacity of 10W-40W, can continuously provide power supply in a solar erosion area, and has moderate specific impulse and thrust.
Description
Technical Field
The invention belongs to the technical field of special engines of aerospace propulsion systems, and particularly relates to a heat storage-power generation-propulsion integrated solar thermal propulsion system.
Background
The propulsion system is a power device for space navigation of the spacecraft and also is the heart of the spacecraft. The light, high-efficiency and low-cost propulsion technology is the premise and key for the rapid development of the miniature spacecraft. At present, the thrust generated by the conventional chemical propulsion technology which is widely applied is larger, but the specific impulse is smaller (about 300 s), the carried effective load is less, and the requirement of long-term on-orbit work is difficult to meet; the specific impulse of the electric propulsion technology is larger, but the thrust is too small (milli-Newton grade), the orbital transfer time is too long, and the requirement of a quick-response space mission is difficult to meet; at present, the thrust of the conventional solar thermal propulsion technology is about 1N, the specific impulse is more than 700s, the blank part of the performance of the conventional chemical propulsion and electric propulsion can be made up, but the problems of power supply interruption and thrust failure in a solar erosion area also exist, and the heat storage-power generation-propulsion integrated solar thermal propulsion system can effectively solve the technical problems, has the advantages of moderate specific impulse and thrust, stable power supply, wide working medium source and low cost, and is suitable for space missions such as rapid satellite orbit switching, long-term on-orbit work, attitude regulation and control, resistance compensation and the like.
Disclosure of Invention
In order to overcome the defects in the prior art, the invention provides a heat storage-power generation-propulsion integrated solar thermal propulsion system, on one hand, the heat energy of a heated working medium is converted into mechanical energy by utilizing the gathered solar radiation energy to heat fluid such as hydrogen, ammonia and the like, and the mechanical energy is discharged at a high speed after being expanded through an expansion nozzle to obtain thrust; on the other hand, the heat energy is stored by the high-temperature heat storage material; moreover, heat energy is converted into electric energy through a thermophotovoltaic technology, and electric power is provided for electronic devices in the spacecraft. The thermal propulsion system can make up for the blank space of conventional chemical propulsion and electric propulsion performance and can continuously provide power and thrust requirements in the solar eclipse region.
In order to achieve the purpose, the invention is realized by the following technical scheme:
a heat storage-power generation-propulsion integrated solar thermal propulsion system comprises a secondary condenser, an energy extractor, a heat absorption cavity, a heat storage cavity, a porous heat absorption channel, a heat insulation layer, a spray pipe, a vacuum cavity and a thermophotovoltaic system, wherein the heat storage cavity is of a closed cavity structure, the rear half section of the heat storage cavity is of a hollow cylinder structure, the top of the heat storage cavity is of a hemispherical structure, the heat absorption cavity is embedded in the heat storage cavity and is coaxially distributed with the heat storage cavity, the rear end face of the heat absorption cavity is connected with the bottom of the heat storage cavity to form a closed cavity structure, the distance between the outer surface of the heat absorption cavity and the inner surface of the heat storage cavity is 1/5-4/5 of the inner diameter of the heat storage cavity, the energy extractor is embedded in the heat absorption cavity and is coaxially distributed with the heat absorption cavity, the energy extractor and the front end face of the secondary condenser are mutually connected and are coaxially distributed, the energy extractor and the secondary condenser are connected and positioned in the heat absorption cavity, and the rear end face of the secondary condenser is positioned outside the heat insulation layer, the secondary condenser is a circular truncated cone structure coaxially distributed with the heat storage cavity, the length of the part outside the heat insulation layer is not less than 70% of the total length of the secondary condenser, the vacuum cavity is embedded between the heat storage cavity and the heat insulation layer and is a cavity structure coaxially distributed with the heat storage cavity, the vacuum cavity covers the outer side of the rear end surface of the side wall of the heat storage cavity, the front end surface of the vacuum cavity is connected with the rear end surface of the porous heat absorption channel, the rear end surface of the vacuum cavity is connected with the thermophotovoltaic system, the porous heat absorption channel is embedded in the heat storage cavity and is a closed annular structure coaxially distributed with the heat storage cavity, the distance between the inner surface of the porous heat absorption channel and the outer surface of the heat absorption cavity is 10% -90% of the distance between the outer surface of the heat absorption cavity and the inner surface of the heat storage cavity, the front end surface of the porous heat absorption channel is communicated with the spray pipe, the spray pipe is embedded in the heat insulation layer and coaxially distributed with the heat storage cavity, and the rear end surface of the spray pipe covers the front end surface of the heat storage cavity, terminal surface and insulating layer preceding terminal surface parallel and level distribute before the spray tube, thermophotovoltaic system includes heat dissipation channel and heat pipe, wherein heat dissipation channel inlays in the vacuum cavity, heat dissipation channel is the arc cavity structure with the coaxial distribution in heat accumulation chamber, working medium import is all established to its left end face and right-hand member face, and communicate each other through working medium import and vacuum cavity, the working medium export is established to heat dissipation channel rear end face, and communicate each other through working medium import and heat pipe preceding terminal surface, the heat pipe is a plurality of, each heat pipe all with heat accumulation chamber axis parallel distribution and encircle heat accumulation chamber axis equipartition, and the heat pipe rear end face all is located the insulating layer rear end outside and the cladding outside secondary spotlight ware, and the heat pipe rear end face does not surpass secondary spotlight ware rear end face.
Furthermore, the secondary condenser is of a circular truncated cone-shaped structure, the diameter of the rear end face of the secondary condenser is 1.5-5 times that of the front end face, the rear end face of the secondary condenser is of a spherical structure with a central angle of 50-70 degrees, the front end face of the secondary condenser is of a cylindrical structure which is coaxially distributed with the heat absorption cavity and is communicated with the energy extractor, and an included angle between a circular truncated cone bus of the circular truncated cone-shaped structure of the secondary condenser and an axis is 12-30 degrees.
Furthermore, the energy extractor comprises a connecting section and a heating section, wherein the connecting section is of a cylindrical structure and is communicated with the secondary condenser, the heating section is of a pyramid structure, and the connecting section and the heating section are of an integrated structure.
Furthermore, the secondary condenser and the energy extractor are made of single crystal Al 2O 3, can resist 2000K temperature and have refractive index of 1.76.
Furthermore, the heat absorption cavity, the heat storage cavity, the porous heat absorption channel and the vacuum cavity wall adopt intermetallic compounds which are high temperature resistant, good in stability and do not chemically react with the heat storage material boron, wherein the wall surface of the heat absorption cavity is coated with a high-temperature-resistant high-absorptivity coating; the heat insulation layer is made of a low-heat-conductivity material; the outer surface of the heat insulation layer is coated with a high emissivity material.
Furthermore, the heat absorption cavity, the heat storage cavity, the porous heat absorption channel and the vacuum cavity wall are made of BN/TiB 2; the wall surface coating material of the heat absorption cavity is any one of silicon carbide-based material, 2 MgO.2Al2O3.5SiO2 and zircon sand; the heat insulation layer is made of high-temperature resistant aerogel, and the high-emissivity material on the outer surface of the heat insulation layer is silicon carbide or silicon carbide-based material.
Furthermore, a heat storage filler based on high melting point and high energy density performance is filled between the heat absorption cavity and the heat storage cavity, and preferably, the heat storage filler is boron.
Furthermore, the porous heat absorption channel comprises a hollow cylindrical base body and two layers of airflow channels which are embedded in the side wall of the base body and are distributed at equal angular intervals in a rotating mode, and the airflow channels are distributed in parallel.
Furthermore, the heat pipe of the thermophotovoltaic system comprises a heat pipe shell, end covers, a liquid absorbing core and working liquid, wherein the heat pipe shell is of a hollow tubular structure, the end covers are arranged at two ends of the heat pipe shell, and the liquid absorbing core and the working liquid are embedded in the heat pipe shell.
Furthermore, a plurality of fins are uniformly distributed in the heat dissipation channel of the thermophotovoltaic system, the fins are respectively and vertically connected with the upper end face and the lower end face of the heat dissipation channel, the fins are distributed at intervals, at least one serpentine channel is formed in the heat dissipation channel, and two ends of the serpentine channel are respectively and mutually communicated with the working medium inlets of the left end face and the right end face of the heat dissipation channel.
The heat storage-power generation-propulsion integrated solar thermal propulsion system provided by the invention can generate 730s specific impulse and 0.9N thrust by taking hydrogen as a working medium under a design working condition (the flow is 0.125g/s), the generated energy is 10W-40W, the power supply can be continuously provided in a solar erosion area, the system has moderate specific impulse and thrust, can well make up the blank part of the conventional chemical propulsion and electric propulsion performances, and is suitable for aerospace tasks such as rapid orbit transfer from a microsatellite LEO orbit to a GEO orbit, long-term on-orbit work, resistance compensation, attitude regulation and the like.
Drawings
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic cross-sectional partial structure view of a porous heat absorption channel;
FIG. 3 is a schematic cross-sectional view of a heat dissipation channel of a thermophotovoltaic system;
FIG. 4 is a schematic cross-sectional view of a heat pipe of a thermophotovoltaic system;
FIG. 5 is a cloud of temperature profiles for the system of the present invention.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.
As shown in fig. 1-5, a heat accumulation-power generation-propulsion integrated solar thermal propulsion system comprises a secondary condenser 1, an energy extractor 2, a heat absorption cavity 3, a heat accumulation cavity 4, a porous heat absorption channel 5, a heat insulation layer 6, a spray pipe 7, a vacuum cavity 8 and a thermal photovoltaic system 9, wherein the heat accumulation cavity 4 is of a closed cavity structure, the rear half section of the heat accumulation cavity 4 is of a hollow cylinder structure, the top part of the heat accumulation cavity is of a hemispherical structure, the heat absorption cavity 3 is embedded in the heat accumulation cavity 4 and is coaxially distributed with the heat accumulation cavity 4, the rear end surface of the heat absorption cavity 3 is connected with the bottom of the heat accumulation cavity 4 to form a closed cavity structure, the distance between the outer surface of the heat absorption cavity 3 and the inner surface of the heat accumulation cavity 4 is 1/5-4/5 of the inner diameter of the heat accumulation cavity 3, the energy extractor 2 is embedded in the heat absorption cavity 3 and is coaxially distributed with the heat absorption cavity 3, the energy extractor 2 and the front end surface of the secondary condenser 1 are mutually connected and are coaxially distributed, the energy extractor 2 is connected with the secondary condenser 1 and positioned in the heat absorption cavity 3, the rear end face of the secondary condenser 1 is positioned outside the heat insulation layer 6, the secondary condenser 1 is in a circular table structure coaxially distributed with the heat storage cavity 4, the length of the outer part of the heat insulation layer 6 is not less than 70% of the total length of the secondary condenser 1, the vacuum cavity 8 is embedded between the heat storage cavity 4 and the heat insulation layer 6 and is in a cavity structure coaxially distributed with the heat storage cavity 4, the vacuum cavity 8 covers the outer side of the rear end face of the side wall of the heat storage cavity 4, the front end face of the vacuum cavity is connected with the rear end face of the porous heat absorption channel 5, the rear end face is connected with the thermal photovoltaic system 9, the porous heat absorption channel 5 is embedded in the heat storage cavity 4 and covers the heat absorption cavity 3 and is in a closed annular structure coaxially distributed with the heat storage cavity 4, and the distance between the inner surface of the porous heat absorption channel 5 and the outer surface of the heat absorption cavity 3 is 10% -90% of the distance between the outer surface of the heat absorption cavity 3 and the inner surface of the heat storage cavity 4, the terminal surface communicates each other with spray tube 7 before the porous endothermic passageway 5, and spray tube 7 inlays in insulating layer 6 and with heat accumulation chamber 4 coaxial distribution, and 7 rear end covers of spray tube 7 outside heat accumulation chamber 4 front end, terminal surface parallel and level distribution before 7 preceding terminal surfaces of spray tube and insulating layer 6.
In this embodiment, the thermophotovoltaic system 9 includes a heat dissipation channel 91 and heat pipes 92, wherein the heat dissipation channel 91 is embedded in the vacuum chamber 8, the heat dissipation channel 91 is an arc-shaped cavity structure coaxially distributed with the thermal storage chamber 4, working medium inlets 93 are respectively formed on the left end surface and the right end surface of the heat dissipation channel, the heat dissipation channel is communicated with the vacuum chamber 8 through the working medium inlets 93, a working medium outlet 94 is formed on the rear end surface of the heat dissipation channel 91, the heat pipes 92 are communicated with the front end surface of the heat pipes 92 through the working medium inlets 93, the heat pipes 92 are distributed in parallel with the axis of the thermal storage chamber 4 and uniformly distributed around the axis of the thermal storage chamber 4, the rear end surface of each heat pipe 92 is located outside the rear end surface of the thermal insulation layer 6 and covers the secondary condenser 1, and the rear end surface of each heat pipe 92 does not exceed the rear end surface of the secondary condenser 1.
The secondary condenser 1 is of a circular truncated cone-shaped structure, the diameter of the rear end face of the secondary condenser is 1.5-5 times of that of the front end face, the rear end face is of a spherical structure with a central angle of 50-70 degrees, the front end face is of a cylindrical structure which is coaxially distributed with the heat absorption cavity 3 and is communicated with the energy extractor 2, and an included angle between a circular truncated cone bus of the circular truncated cone structure of the secondary condenser and an axis is 12-30 degrees; the energy extractor 2 comprises a connecting section 21 and a heating section 22, wherein the connecting section 21 is of a cylindrical structure and is communicated with the secondary condenser 1, the heating section 22 is of a pyramid structure, the connecting section 21 and the heating section 22 are of an integrated structure, the secondary condenser 1 and the energy extractor 2 are made of single crystal Al 2O 3, can resist 2000K temperature, and have a refractive index of 1.76.
In addition, the walls of the heat absorption cavity 3, the heat storage cavity 4, the porous heat absorption channel 5 and the vacuum cavity 8 adopt intermetallic compounds which are high temperature resistant, good in stability and do not chemically react with boron which is a heat storage material, wherein the wall surface of the heat absorption cavity 3 is coated with a high-temperature-resistant high-absorptivity coating; the heat insulation layer 6 is made of a low-heat-conductivity material; the outer surface of the heat insulation layer 6 is coated with a high emissivity material, and the materials of the heat absorption cavity 3, the heat storage cavity 4, the porous heat absorption channel 5 and the cavity wall of the vacuum cavity 6 are BN/TiB 2; the wall surface coating material of the heat absorption cavity 3 is any one of silicon carbide-based material, 2 MgO.2Al2O3.5SiO2 and zircon sand; the heat-insulating layer 6 is made of high-temperature-resistant aerogel, and the high-emissivity material on the outer surface of the heat-insulating layer 6 is silicon carbide or silicon carbide-based material.
Meanwhile, a heat storage filler 10 based on high melting point and high energy density performance is filled between the heat absorption cavity 3 and the heat storage cavity 4, and preferably, the heat storage filler 10 is boron.
Preferably, the porous heat absorption channel 5 comprises a hollow cylindrical base body 51 and two layers of airflow channels 52 which are embedded in the side wall of the base body 51 and are distributed at equal angular intervals in a rotating manner, and the airflow channels 52 are distributed in parallel.
It should explain specially, thermophotovoltaic system 9's heat pipe 92 includes heat pipe housing 921, end cover 922, imbibition core 923 and working solution 924, heat pipe housing 921 is hollow tubular structure, and the end cover 922 is all established at both ends, imbibition core 923 and working solution 924 all inlay in the heat pipe housing, thermophotovoltaic system 9's heat dissipation channel 91 in a plurality of fins 911 of equipartition, fin 911 is connected with heat dissipation channel 91 up end and lower terminal surface mutually perpendicular respectively, mutual interval distribution between each fin 911 to constitute at least one serpentine channel 912 in heat dissipation channel 91, serpentine channel 912 both ends communicate with heat dissipation channel 91 way working medium import 93 of left end face and right-hand member face each other.
Preferably, the expansion section of the nozzle 7 is a conical structure, the material can be molybdenum, and the throat part is sprayed with tungsten to be used as a throat lining.
When the invention is implemented, the overall structure size of the invention is as follows: length 54cm, diameter 30 cm. The refractive index of the single crystal Al 2O 3 material of the secondary condenser is 1.76, the spherical radius is 9.56cm, the central angle is 55.4 degrees, the included angle between the generatrix of the circular truncated cone and the axis is 14.3 degrees, and the length is 11.6 cm. The diameter of the joint of the outlet of the secondary condenser and the inlet of the energy extractor is 3.3cm, the overall length of the energy extractor is 14.4cm, and the length of the cylindrical section is 1.5 cm. The radius of the heat absorption cavity is 2.25cm, the length of the cylindrical section is 14.4cm, and the rear part of the cylindrical section is connected with a hemispherical surface with the radius of 2.25 cm; the radius of the heat accumulation cavity is 4.43cm, the length of the cylindrical section is 14.4cm, and then the hemispherical surface with the radius of 4.43cm is connected. The inner diameter of the porous heat absorption channel is 4.43cm, the outer diameter of the porous heat absorption channel is 7cm, the length of the porous heat absorption channel is 10.3cm, the tail end of the porous heat absorption channel is connected with the tail end of the cylindrical surface of the heat storage cavity, and 80 micro pipelines (40 on the upper layer and 40 on the lower layer) with the diameter of 5mm are arranged in the porous heat absorption channel and are respectively arranged at equal angular intervals. In order to make the air flow entering the spray pipe uniform and reduce the turbulence degree, the front section of the contraction section of the spray pipe is 3.6cm, the contraction section is 3.6cm, the length of the expansion section is 2.5cm, and the expansion half angle is 15 degrees. The circumferential thickness of the heat insulation layer is 8cm, the axial thickness (the thickness of the heat pipe side) is 4cm, and the diameter of the heat insulation layer of the spray pipe section is 2.6 cm. The thermophotovoltaic is designed according to the maximum power 100W generated energy, the axial length is 1.43cm, the circumferential arc length is 6.9cm, the radial thickness is 0.8cm, and the radial distance between the thermophotovoltaic and the high-temperature radiation surface is 7 mm. The heat dissipation channel is composed of 9 fins which are symmetrically arranged in a staggered mode along the axis, the wall thickness of six faces around the heat dissipation channel is 1.5mm, the thickness of each fin is 1.5mm, the length of each fin is 8.5mm, the fin interval is 6mm, the heat dissipation channel is provided with two working medium inlets with the diameter of 3mm and arranged on two sides, and one working medium outlet with the diameter of 3mm is arranged on the rear side (heat pipe side). The heat pipe is composed of a heat pipe shell, an end cover, a liquid absorption core and working liquid, and is of a cylindrical structure with the length of 20cm and the diameter of 3mm, and 28 heat pipes are circumferentially arranged at equal angular intervals.
When the method is operated:
the propulsion system consists of a secondary condenser, an energy extractor, a heat absorption cavity, a heat storage cavity, a porous heat absorption channel, a heat insulation layer, a spray pipe, a vacuum cavity and a thermophotovoltaic system (comprising a heat dissipation channel). The curved surface at the front section of the secondary condenser is a spherical surface with the radius of R and is used for receiving the solar rays from the primary condenser; the rear section of the secondary condenser is of a circular truncated cone rotator structure and is coaxial with the heat absorption cavity, and light rays are totally reflected inside and then enter the energy extractor.
The front section of the energy extractor is of a cylindrical structure, and the rear section of the energy extractor is of a pyramid structure; the circular table surface at the tail end of the secondary condenser is coaxially connected with the cylindrical surface at the front section of the energy extractor; and condensed light from the secondary condenser enters the energy extractor and then is transmitted into the wall surface of the heat absorption cavity.
The heat absorption cavity is composed of a cylindrical surface and a hemispherical surface, the inner surface of the heat absorption cavity is provided with a high-absorptivity coating, and the heat absorption cavity receives light transmitted from the energy extractor, converts the light into heat after absorbing the light and stores the heat in the heat storage cavity.
The heat storage cavity is composed of a cylindrical surface and a hemispherical surface which are coaxial with the heat absorption cavity, and the cavity is filled with heat storage material boron to absorb heat transferred from the heat absorption cavity and store the heat through a phase change process.
The porous heat absorption channel overall structure is a hollow cylinder and is coaxially nested with the heat storage cavity, two layers of airflow channels are rotationally distributed at equal angular intervals inside the porous heat absorption channel, the total number of the airflow heat absorption channels is 80, and 40 airflow heat absorption channels are distributed at equal angular intervals on the upper layer and the lower layer and are distributed along the whole circumference. The total temperature of the working medium gas rises after passing through the porous heat absorption channel, and then the working medium gas passes through the spray pipe to obtain higher specific impulse.
The insulating layer is 8 cm's aerogel, and heat pipe side insulating layer thickness is 4cm, and the outer high emissivity coating that coats radiates heat dissipation to the outer space to avoid the insulating layer outer high temperature and with heat transfer to the heat pipe in order to reduce the heat dispersion of heat pipe to thermal photovoltaic.
The spray pipe is a contraction and expansion spray pipe, the expansion section is of a conical structure with an expansion angle of 15 degrees and an expansion ratio of 60, and the inlet of the contraction section of the spray pipe is connected with the outlet flow channel of the porous heat absorption channel; working medium flows out of the external storage tank and enters the porous heat absorption channel after heat photovoltaic heat exchange, the total temperature of the working medium is greatly improved, high-temperature subsonic airflow passes through the spray pipe and then is accelerated to supersonic velocity, and gas at the outlet of the spray pipe is in an underexpanded state.
The vacuum cavity is an annular cavity which is coaxially connected with the outer surface of the heat storage cavity, the circumferential radian of the vacuum cavity is 94 degrees, the arc length is 11cm, the axial length is 2cm, and the wall thickness is 1.5 mm; the thermophotovoltaic system is positioned in the vacuum cavity, the thermophotovoltaic is a coaxial annular structure with the heat storage cavity and the vacuum cavity, the radial distance of the surface of the bottom surface of the thermophotovoltaic, which is in connection contact with the vacuum cavity and the heat storage cavity, is 8mm, the radial thickness of the thermophotovoltaic is 1cm, the circumferential radian is 75 degrees, the arc length is 7cm, the axial length is 1cm, and the thermophotovoltaic can stretch and move in the vacuum cavity along the axial direction through an actuating mechanism so as to adjust the power generation power of the thermophotovoltaic; the outer surface part of the heat storage cavity in connection contact with the vacuum cavity is used as a high-temperature radiator of the thermophotovoltaic system, and the radiation energy emitted by the high-temperature radiator is converted into electric energy through thermophotovoltaic.
The thermal photovoltaic system consists of a heat dissipation channel and a heat pipe, and a thermal photovoltaic cell (GaAs cell) is of an annular structure and is 8mm away from the high-temperature radiation surface; the heat dissipation channel formed by the thermophotovoltaic cell is positioned at the upper part of the cell and consists of 9 fins which are arranged in a staggered way; the heat pipes are arranged on the rear surface of the thermophotovoltaic heat dissipation channel, the number of the heat pipes is 28, the heat pipes are respectively arranged along arc lines with the radiuses of 6cm and 5cm and the radians of 75 degrees at equal angular intervals, and 14 heat pipes are respectively distributed on the upper layer and the lower layer. When working medium gas passes through the thermophotovoltaic heat dissipation channel, a large amount of heat generated by thermophotovoltaic is taken away, and the thermophotovoltaic working temperature is ensured; when no working medium gas exists, heat generated by thermophotovoltaic is mainly conducted to the outside through a heat pipe and is transmitted to an outer space in a heat radiation mode, so that the thermophotovoltaic is guaranteed to work at a proper working temperature.
Example 1:
the specific implementation mode of the heat storage-power generation-propulsion integrated solar thermal propulsion system is as follows:
under the design condition, the working medium gas is hydrogen, the working medium flow is 0.125g/s, the working total pressure is 0.1MPa, the total working medium temperature is 2450K after passing through the porous heat exchange channel, the thrust of 1N, the specific impulse of 806s, the heat storage time (the mass of the heat storage material boron is 2kg) of 540s can be generated, and the maximum power generation power is 100W.
Example 2:
the working medium gas is hydrogen, the working medium flow is 0.614g/s, the working total pressure is 0.49MPa, the total working medium temperature is 2400K after passing through the porous heat exchange channel, the thrust 4.8N, the specific impulse 800s and the maximum power generation power 100W can be generated.
Example 3:
the working medium gas is ammonia gas, the working medium flow is 0.125g/s, the working total pressure is 0.03MPa, the thrust is 0.4N, the specific impulse is 295s, the heat storage time (the mass of the heat storage material boron is 2kg) is 540s, and the maximum power generation power is 22W.
The heat storage-power generation-propulsion integrated solar thermal propulsion system provided by the invention can generate 730s specific impulse and 0.9N thrust by taking hydrogen as a working medium under a design working condition (the flow is 0.125g/s), the generated energy is 10W-40W, the power supply can be continuously provided in a solar erosion area, the system has moderate specific impulse and thrust, can well make up the blank part of the conventional chemical propulsion and electric propulsion performances, and is suitable for aerospace tasks such as rapid orbit transfer from a microsatellite LEO orbit to a GEO orbit, long-term on-orbit work, resistance compensation, attitude regulation and the like.
It will be appreciated by persons skilled in the art that the present invention is not limited by the embodiments described above. The foregoing embodiments and description have been presented only to illustrate the principles of the invention. Various changes and modifications can be made without departing from the spirit and scope of the invention. Such variations and modifications are intended to be within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (10)
1. The heat storage-power generation-propulsion integrated solar thermal propulsion system is characterized in that: the heat storage-power generation-propulsion integrated solar thermal propulsion system comprises a secondary condenser, an energy extractor, a heat absorption cavity, a heat storage cavity, a porous heat absorption channel, a heat insulation layer, a spray pipe, a vacuum cavity and a thermophotovoltaic system, wherein the heat storage cavity is of a closed cavity structure, the rear half section of the heat storage cavity is of a hollow cylinder structure, the top of the heat storage cavity is of a hemispherical structure, the heat absorption cavity is embedded in the heat storage cavity and is coaxially distributed with the heat storage cavity, the rear end surface of the heat absorption cavity is connected with the bottom of the heat storage cavity to form a closed cavity structure, the distance between the outer surface of the heat absorption cavity and the inner surface of the heat storage cavity is 1/5-4/5 of the inner diameter of the heat storage cavity, the energy extractor is embedded in the heat absorption cavity, the energy extractor and the secondary condenser are connected with each other and are coaxially distributed, and the connection position of the energy extractor and the secondary condenser is positioned in the heat absorption cavity;
the rear end face of the secondary condenser is positioned outside the heat insulation layer, the secondary condenser is of a round table structure which is coaxially distributed with the heat storage cavity, the length of the outer portion of the heat insulation layer is not less than 70% of the total length of the secondary condenser, the vacuum cavity is embedded between the heat storage cavity and the heat insulation layer and is of a cavity structure which is coaxially distributed with the heat storage cavity, the vacuum cavity covers the outer side of the rear end face of the side wall of the heat storage cavity, the front end face of the vacuum cavity is connected with the rear end face of the porous heat absorption channel, the rear end face of the vacuum cavity is connected with the thermal photovoltaic system, the porous heat absorption channel is embedded in the heat storage cavity and covers the heat absorption cavity and is of a closed annular structure which is coaxially distributed with the heat storage cavity, and the distance between the inner surface of the porous heat absorption channel and the outer surface of the heat absorption cavity is 10% -90% of the distance between the outer surface of the heat absorption cavity and the inner surface of the heat storage cavity;
the front end surface of the porous heat absorption channel is communicated with the spray pipe, the spray pipe is embedded in the heat insulation layer and is coaxially distributed with the heat storage cavity, the rear end face of the spray pipe is coated outside the front end face of the heat storage cavity, the front end face of the spray pipe is distributed in parallel with the front end face of the heat insulation layer, the thermophotovoltaic system comprises a heat dissipation channel and a heat pipe, wherein the heat dissipation channel is embedded in the vacuum cavity, the heat dissipation channel is in an arc cavity structure which is coaxially distributed with the heat storage cavity, working medium inlets are arranged on the left end surface and the right end surface of the heat dissipation channel, the heat dissipation channel is communicated with the vacuum cavity through the working medium inlets, a working medium outlet is arranged on the rear end surface of the heat dissipation channel, and is communicated with the front end surface of the heat pipe through a working medium inlet, a plurality of heat pipes are arranged, each heat pipe is distributed in parallel with the axis of the heat storage cavity and is uniformly distributed around the axis of the heat storage cavity, and the rear end faces of the heat pipes are positioned outside the rear end face of the heat insulation layer and coated outside the secondary condenser, and the rear end faces of the heat pipes do not exceed the rear end face of the secondary condenser.
2. The integrated thermal storage-power generation-propulsion solar thermal propulsion system according to claim 1, characterized in that: the secondary condenser is of a circular truncated cone-shaped structure, the diameter of the rear end face of the secondary condenser is 1.5-5 times that of the front end face, the rear end face of the secondary condenser is of a spherical structure with a central angle of 50-70 degrees, the front end face of the secondary condenser is of a cylindrical structure which is coaxially distributed with the heat absorption cavity and is communicated with the energy extractor, and an included angle between a circular truncated cone bus of the circular truncated cone-shaped structure of the secondary condenser and the axis is 12-30 degrees.
3. The integrated thermal storage-power generation-propulsion solar thermal propulsion system according to claim 1, characterized in that: the energy extractor comprises a connecting section and a heating section, wherein the connecting section is of a cylindrical structure and is communicated with the secondary condenser, the heating section is of a pyramid structure, and the connecting section and the heating section are of an integrated structure.
4. The integrated thermal storage-power generation-propulsion solar thermal propulsion system as claimed in claim 1, 2 or 3, wherein: the secondary condenser and the energy extractor are made of single crystal Al 2O 3, can resist 2000K temperature, and have refractive index of 1.76.
5. The integrated thermal storage-power generation-propulsion solar thermal propulsion system according to claim 1, characterized in that: the heat absorption cavity, the heat storage cavity, the porous heat absorption channel and the vacuum cavity wall adopt intermetallic compounds which are high temperature resistant, good in stability and do not chemically react with boron serving as a heat storage material, wherein the wall surface of the heat absorption cavity is coated with a high-temperature-resistant high-absorptivity coating; the heat insulation layer is made of a low-heat-conductivity material; the outer surface of the heat insulation layer is coated with a high emissivity material.
6. The integrated thermal storage-power generation-propulsion solar thermal propulsion system according to claim 5, characterized in that: the heat absorption cavity, the heat storage cavity, the porous heat absorption channel and the vacuum cavity wall are made of BN/TiB 2; the wall surface coating material of the heat absorption cavity is any one of silicon carbide-based material, 2 MgO.2Al2O3.5SiO2 and zircon sand; the heat insulation layer is made of high-temperature resistant aerogel, and the high-emissivity material on the outer surface of the heat insulation layer is silicon carbide or silicon carbide-based material.
7. The integrated thermal storage-power generation-propulsion solar thermal propulsion system according to claim 1, characterized in that: and a heat storage filler based on high melting point and high energy density performance is filled between the heat absorption cavity and the heat storage cavity, and the heat storage filler is boron.
8. The integrated thermal storage-power generation-propulsion solar thermal propulsion system according to claim 1, characterized in that: the porous heat absorption channel comprises a hollow cylindrical base body and two layers of airflow channels which are embedded in the side wall of the base body and are distributed at equal angular intervals in a rotating mode, and the airflow channels are distributed in parallel.
9. The integrated thermal storage-power generation-propulsion solar thermal propulsion system according to claim 1, characterized in that: the heat pipe of the thermal photovoltaic system comprises a heat pipe shell, end covers, a liquid absorbing core and working liquid, wherein the heat pipe shell is of a hollow tubular structure, the end covers are arranged at two ends of the heat pipe shell, and the liquid absorbing core and the working liquid are embedded in the heat pipe shell.
10. Use of a thermal storage-power generation-propulsion integrated solar thermal propulsion system according to any one of claims 1 to 9, characterized in that: the heat dissipation channel of the thermophotovoltaic system is internally and uniformly provided with a plurality of fins, the fins are respectively and vertically connected with the upper end surface and the lower end surface of the heat dissipation channel, the fins are distributed at intervals, at least one serpentine channel is formed in the heat dissipation channel, and the two ends of the serpentine channel are respectively and mutually communicated with working medium inlets of the left end surface and the right end surface of the heat dissipation channel.
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| CN101907041A (en) * | 2010-07-23 | 2010-12-08 | 北京航空航天大学 | Propane liquid gas micro propulsion device suitable for micro-nano satellite |
| CN103921956A (en) * | 2014-04-16 | 2014-07-16 | 南京理工大学 | Solid cool air micro-propelling system |
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