CN104158443B - Aircraft supply unit based on hypersonic speed flow Aerodynamic Heating and thermo-electric conversion - Google Patents
Aircraft supply unit based on hypersonic speed flow Aerodynamic Heating and thermo-electric conversion Download PDFInfo
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- CN104158443B CN104158443B CN201410324950.XA CN201410324950A CN104158443B CN 104158443 B CN104158443 B CN 104158443B CN 201410324950 A CN201410324950 A CN 201410324950A CN 104158443 B CN104158443 B CN 104158443B
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Abstract
The invention discloses a kind of aircraft supply unit based on hypersonic speed flow Aerodynamic Heating and thermo-electric conversion, including voltage stabilizing charging circuit, accumulator, transformation power supply circuits and thermo-electric conversion module, thermo-electric conversion module is connected with accumulator by voltage stabilizing charging circuit, and accumulator is powered by transformation power supply circuits；Thermo-electric conversion module includes multiple thermoelectric power generation unit, and thermoelectric power generation unit includes the P type thermo-electric converting material unit, N-type thermo-electric converting material unit and the conducting strip that are connected by conducting strip, and multiple thermoelectric power generation unit connect associating power supply as required.The heat transfer of the Aerodynamic Heating that aircraft work process high speed incoming flow produces and engine chamber can be carried out recycling by the present invention, realize aircraft carried out heat management effectively and realize the comprehensive utilization of energy to improve total energy utilization efficiency, it is advantageously implemented miniaturization and the lightweight of aircraft power, with the combination of aircraft thermal protection system, integration degree is high.
Description
Technical field
The present invention relates to a kind of high ultrasonic vehicle technology field, be specifically related to the aircraft supply unit based on hypersonic speed flow Aerodynamic Heating and thermo-electric conversion.
Background technology
Hypersonic aircraft is a Main way of 21 century Global Aerospace career development.For hypersonic aircraft, the total energy approach how to carry out heat management effectively, realizing whole aircraft is the major issue faced in hypersonic flight process.Bearing serious Aerodynamic Heating in aircraft flight process on the one hand, face serious thermal force in scramjet engine work process, the thermal protection of this skin-surface causing aircraft and scramjet engine combustor faces great difficulty.On the other hand, hypersonic aircraft flying for long time needs very big power consumption, and to realize the functions such as the navigation of aircraft, communication and flowing control, miniaturization and the lightweight of aircraft electrical origin system are had higher requirement by this.
Temperature-difference thermoelectric technology is a kind of to utilize thermoelectric material to realize heat energy and technology that electric energy is directly changed, since within 1821, being found by Sai Beike, just cause giving more sustained attention of research worker, research at that time shows that two different objects can produce electric potential difference when contact jaw temperature difference, here it is so-called Seebeck (Seebeck) effect.The fast-developing development of thermoelectric generation started from for 20 beginnings of the century, research at that time breaches the restriction of metal thermoelectric material, find that semi-conductor thermoelectric material has more excellent characteristic in thermoelectric conversion, this just determines semi-conducting material irreplaceable status in thermo-electric generation so that the development of thermoelectric generation steps has gone up a new step.Thermo-electric generation has without the plurality of advantages such as any additional mechanical moving component, temperature range wide, volume is little, lightweight, reliability is high, long service life, the safety non-pollution that can work compared with other electricity generation systems, thus shows good application prospect.
The heat transfer of Aerodynamic Heating and chamber wall is all processed by the design of current hypersonic aircraft overwhelming majority thermal protection system as used heat, solar heat protection, heat insulation mode is adopted to stop the transmission of heat, and by introducing thermoelectric generation in hypersonic aircraft, above-mentioned heat can be made full use of, more efficiently realize the total energy approach of aircraft.
Summary of the invention
The technical problem to be solved in the present invention is: for the above-mentioned technical problem of prior art, there is provided a kind of and the heat transfer of the Aerodynamic Heating that aircraft work process high speed incoming flow produces and engine chamber can be carried out recycling, realize aircraft carried out heat management effectively and realize the comprehensive utilization of energy to improve total energy utilization efficiency, it is advantageously implemented miniaturization and the lightweight of aircraft power, with the combination of aircraft thermal protection system, the aircraft supply unit based on hypersonic speed flow Aerodynamic Heating and thermo-electric conversion that integration degree is high.
In order to solve above-mentioned technical problem, the technical solution used in the present invention is:
A kind of aircraft supply unit based on hypersonic speed flow Aerodynamic Heating and thermo-electric conversion, including voltage stabilizing charging circuit, accumulator, transformation power supply circuits and at least one thermo-electric conversion module, described thermo-electric conversion module is plate-shaped and is installed in the surface of aircraft, described thermo-electric conversion module is connected with accumulator respectively through voltage stabilizing charging circuit, and described accumulator is carry-on load supplying by transformation power supply circuits.
Preferably, described thermo-electric conversion module includes multiple thermoelectric power generation unit, described thermoelectric power generation unit includes P type thermo-electric converting material unit, N-type thermo-electric converting material unit and conducting strip, described P type thermo-electric converting material unit, the thermal source of N-type thermo-electric converting material unit aircraft all relatively is arranged vertically, it is connected by conducting strip between described P type thermo-electric converting material unit and N-type thermo-electric converting material unit, and connected by conducting strip between the plurality of thermoelectric power generation unit, or it is in parallel, or the mode of series connection and mixing in parallel connects combination and constitutes thermo-electric conversion module.
Preferably, described thermo-electric conversion module also includes top panel, lower panel and support frame, described top panel is connected with lower panel by support frame, described lower panel is connected with the body of aircraft, the plurality of thermoelectric power generation unit is located between top panel, lower panel, and described P type thermo-electric converting material unit, N-type thermo-electric converting material unit are all close to top panel and are arranged.
Preferably, being filled with insulator between described top panel, lower panel, described P type thermo-electric converting material unit, N-type thermo-electric converting material unit are all inserted in insulator and arrange with lower panel gap.
Preferably, described top panel is honeycomb sandwich board.
Preferably, described lower panel is honeycomb sandwich board.
Preferably, the honeycomb sandwich board constituting described top panel adopts super Chlorimet to make.
Preferably, the honeycomb sandwich board constituting described lower panel adopts titanium alloy to make.
Preferably, described voltage stabilizing charging circuit includes comparison amplifier, pulse width modulator, driver, DC/DC transducer, reference voltage source and two control resistance, the outfan of described comparison amplifier passes sequentially through pulse width modulator, driver is connected with the control end of DC/DC transducer, the cathode output end of described thermo-electric conversion module is connected with the positive pole of accumulator by DC/DC transducer, the negative pole of described accumulator is connected with the cathode output end of thermo-electric conversion module, said two is connected between the cathode output end of thermo-electric conversion module and earth terminal after controlling resistant series, one input of described comparison amplifier is connected with reference voltage source, another input of described comparison amplifier is connected to said two and controls between resistance.
Preferably, described transformation power supply circuits include high-frequency inverter, high-frequency step-up transformer and rectifier filter, described high-frequency inverter, high-frequency step-up transformer and rectifier filter are sequentially connected in series, and described high-frequency inverter is connected with accumulator, and described rectifier filter is connected with carry-on load.
The present invention has an advantage that based on the aircraft supply unit of hypersonic speed flow Aerodynamic Heating and thermo-electric conversion
1, the present invention includes voltage stabilizing charging circuit 2, accumulator 3, transformation power supply circuits 4 and at least one thermo-electric conversion module 1, thermo-electric conversion module 1 is connected with accumulator 3 respectively through voltage stabilizing charging circuit 2, and accumulator 3 is carry-on load supplying by transformation power supply circuits 4, Aerodynamic Heating and the heat transfer of engine chamber that aircraft work process high speed incoming flow is produced based on thermoelectric generation technology by thermo-electric conversion module 1 carry out recycling, aircraft can be carried out heat management and the comprehensive utilization realizing energy effectively, improve total energy utilization efficiency, simultaneously that the miniaturization and lightweight realizing aircraft power is significant.
2, the thermo-electric conversion module 1 of the present invention is plate-shaped and be installed in the surface of aircraft, it is achieved that metal fever protection and thermo-electric conversion structure are carried out integrated design, the combination of thermo-electric converting material and aircraft thermal protection system can be achieved better, embody the thought of Highgrade integration, thermo-electric conversion module 1 has thermo-electric generation, anti-/ heat insulation and three functions of load simultaneously, can alleviating the thermo-lag pressure of aircraft to a certain extent, the design for hypersonic aircraft thermal protection system opens a new thinking.
Accompanying drawing explanation
Fig. 1 is the theory structure schematic diagram of the embodiment of the present invention.
Fig. 2 is the sectional structure schematic diagram of thermoelectric power generation unit in the embodiment of the present invention.
Fig. 3 is the connection perspective view of multiple thermoelectric power generation unit in the embodiment of the present invention.
Fig. 4 is the circuit theory schematic diagram of thermo-electric conversion module rear end in the embodiment of the present invention.
Marginal data: 1, thermo-electric conversion module；11, thermoelectric power generation unit；111, P type thermo-electric converting material unit；112, N-type thermo-electric converting material unit；113, conducting strip；12, top panel；13, lower panel；14, support frame；15, insulator；2, voltage stabilizing charging circuit；21, resistance is controlled；22, reference voltage source；23, comparison amplifier；24, pulse width modulator；25, driver；26, DC/DC transducer；3, accumulator；4, transformation power supply circuits；41, high-frequency inverter；42, high-frequency step-up transformer；43, rectifier filter.
Detailed description of the invention
As shown in Figure 1, the present embodiment includes voltage stabilizing charging circuit 2, accumulator 3, transformation power supply circuits 4 and at least one thermo-electric conversion module 1 based on the aircraft supply unit of hypersonic speed flow Aerodynamic Heating and thermo-electric conversion, thermo-electric conversion module 1 is plate-shaped and is installed in the surface of aircraft, thermo-electric conversion module 1 is connected with accumulator 3 respectively through voltage stabilizing charging circuit 2, and accumulator 3 is carry-on load supplying by transformation power supply circuits 4.The present embodiment is operationally, Aerodynamic Heating and the heat transfer of engine chamber that the high speed incoming flow of aircraft produces can be partially converted into electric energy after thermo-electric conversion module 1, the size of its output electromotive force can change with the size of external heat power, the unstable problem of electromotive force is exported for thermo-electric conversion module 1, it is adjusted by voltage stabilizing charging circuit 2, make the charge voltage range being sized to remain stable for and be positioned at accumulator 3 of output electromotive force, thus to accumulator 3 stable power-supplying, the existence of accumulator 3 can realize the management and control of energy better, the recovery of energy is carried out when outside heating power is bigger, export electric energy when aircraft needs electricity consumption and carry out the recycling of energy；And due to the rated voltage of each load differing in aircraft, it is thus desirable to increase transformation power supply circuits 4 after accumulator 3, it is adjusted being converted into high-quality electric energy to voltage swing by transformation power supply circuits 4, carry-on multiple loads can be carried out high-quality to power simultaneously, thought based on preservation of energy and conversion, the heat transfer of the Aerodynamic Heating of aircraft surface and engine combustion locular wall can be carried out recycling by thermoelectric generation technology, thus aircraft being carried out heat management and the comprehensive utilization realizing energy effectively；Simultaneously, thermo-electric conversion module 1 is plate-shaped and is installed in the surface of aircraft, specifically can be arranged in Vehicle nose, the leading edge of a wing, the place that the Aerodynamic Heatings such as empennage are serious, and engine chamber, the heat concentration places such as afterburning chamber wall, both Aerodynamic Heating and combustor heat transfer can have been utilized to carry out thermo-electric generation, but also aircraft can be played anti-/ heat insulation and load function, there is thermo-electric generation simultaneously, prevent/heat insulation and three functions of load, the comprehensive utilization of energy is achieved aircraft being carried out heat management effectively, the miniaturization and lightweight realizing aircraft electrical origin system is significant, and by metal fever protection and thermo-electric conversion structure are carried out integrated design, design for the hypersonic thermal protection system of aircraft opens new thinking.
As shown in Figure 2, thermo-electric conversion module 1 includes multiple thermoelectric power generation unit 11, thermoelectric power generation unit 11 includes P type thermo-electric converting material unit 111, N-type thermo-electric converting material unit 112 and conducting strip 113, the thermal source (surface of aircraft or combustor etc.) of P type thermo-electric converting material unit 111, N-type thermo-electric converting material unit 112 aircraft all relatively is arranged vertically, and is connected by conducting strip 113 between P type thermo-electric converting material unit 111 and N-type thermo-electric converting material unit 112.In P type thermo-electric converting material unit 111, how sub hole is, free electron is few son, and the carrier of conduction is mainly hole；In N-type thermo-electric converting material unit 112, hole is few son, and how sub free electron is, the carrier of conduction is mainly free electron.Two ends not yet being set up to the material of the temperature difference, its carrier is for being uniformly distributed.Owing to the thermal source of P type thermo-electric converting material unit 111, N-type thermo-electric converting material unit 112 aircraft all relatively is arranged vertically, therefore aircraft surface and combustor heating can be made during aircraft flight, thus the two ends formation temperature gradient (namely making to exist between two ends the temperature difference) of P type thermo-electric converting material unit 111, N-type thermo-electric converting material unit 112 can be made, once after thermograde foundation, the carrier being in hot junction just has bigger kinetic energy, tend to the diffusion of cold end and pile up at cold end so that the carrier number of cold end is more than hot junction.The accumulation of this electric charge will make the electric neutrality in material be destroyed, electric charge causes setting up a built-in field in material in the accumulation of cold end, to stop the further diffusion to cold end of the hot junction carrier, when the motion of carrier reaches to balance, without the displacement of net charge in material, the electric potential difference now formed at material two ends is exactly Seebeck electromotive force.For P type thermo-electric converting material unit 111, hole will be piled up at cold end as carrier so that cold end is with positive charge；For N-type thermo-electric converting material unit 112, free electron will be piled up at cold end as carrier, namely make cold end with negative charge, so that P type thermo-electric converting material unit 111, N-type thermo-electric converting material unit 112 may make up thermal generator output electric energy with conducting strip 113 after connecting.In the present embodiment, SiGe alloy that when thermo-electric converting material that P type thermo-electric converting material unit 111, N-type thermo-electric converting material unit 112 use can adopt high temperature as required, ZT value is bigger or NaCoO4 or gradient-structure thermoelectric material, simply respectively obtain P type thermo-electric converting material unit 111, the two distinct types of thermo-electric converting material unit of N-type thermo-electric converting material unit 112 by different preparation methoies during preparation；In addition it should be noted that other thermo-electric converting material can also be adopted as required.
As shown in Figure 2, thermo-electric conversion module 1 also includes top panel 12, lower panel 13 and support frame 14, top panel 12 is connected with lower panel 13 by support frame 14, lower panel 13 is connected with the body of aircraft, multiple thermoelectric power generation unit 11 are located between top panel 12, lower panel 13, and P type thermo-electric converting material unit 111, N-type thermo-electric converting material unit 112 are all close to top panel 12 and are arranged.The present embodiment is connected with lower panel 13 by support frame 14 due to top panel 12, lower panel 13 is connected with the body of aircraft, multiple thermoelectric power generation unit 11 are located between top panel 12, lower panel 13, multiple thermoelectric power generation unit 11, top panel 12, lower panel 13 are connected with support frame 14 4 and constitute the framework of whole thermo-electric conversion module 1 such that it is able to guarantee the load performance of structure；Owing to P type thermo-electric converting material unit 111, N-type thermo-electric converting material unit 112 are all close to top panel 12 and are arranged, when aircraft flight, top panel 12 absorbs the heat energy of outside and is in the condition of high temperature, it is thus possible to guarantee P type thermo-electric converting material unit 111, the two ends of N-type thermo-electric converting material unit 112 have the bigger temperature difference such that it is able to improve P type thermo-electric converting material unit 111, N-type thermo-electric converting material unit 112 power generation performance.
Consider that heat energy also has after thermo-electric conversion module 1 not absorbed greatly, therefore in the present embodiment, be filled with insulator 15, P type thermo-electric converting material unit 111 between top panel 12, lower panel 13, N-type thermo-electric converting material unit 112 is all inserted in insulator 15 and arranges with lower panel 13 gap.Bigger thermograde so both can have been set up at the two ends of P type thermo-electric converting material unit 111, N-type thermo-electric converting material unit 112; heat energy can be stoped again further incoming to the inside of aircraft; realize better the present embodiment to aircraft anti-/ heat-proof quality such that it is able to protect aircraft better.The heat-barrier material that insulator 15 uses can select the material that density is low, heat conductivity is little, specific heat capacity is bigger, such as currently used more silicon dioxide, aluminium oxide, Saffil heat-barrier material etc..In the present embodiment, top panel 12 is honeycomb sandwich board, it is possible to realize alleviating the architecture quality of top panel 12 under the premise keeping higher force performance；In like manner, lower panel 13 is capable of alleviating under the premise keeping higher force performance the architecture quality of lower panel 13 for honeycomb sandwich board.In the present embodiment, the honeycomb sandwich board constituting top panel 12 adopts super Chlorimet inconel617 to make, and this material can bear the high temperature of more than 1000 DEG C, and has the advantages such as the stability under high temperature, non-oxidizability and corrosion resistance；In addition other type of super Chlorimet can also be adopted as required；The honeycomb sandwich board constituting lower panel 13 adopts titanium alloy to make, similar to body thermal expansion character etc. such that it is able to realizes the connection with aircraft body well, and can bear the high temperature of 400 DEG C ~ 500 DEG C.Additionally, the support frame 14 of the present embodiment is the same with top panel 12, it is also adopted by super Chlorimet inconel617 and makes.
As shown in Figure 3, after adopting first series connection between multiple thermoelectric power generation unit 11 of the present embodiment, mode in parallel is attached improving voltage and the power of whole thermo-electric conversion module 1, referring to Fig. 3, Fig. 3 illustrates the structure of 9 thermoelectric power generation unit 11, wherein every 3 thermoelectric power generation unit 11 are by conducting strip 113 one group of thermoelectric power generation unit 11 in series, are then connected in parallel by conducting strip 113 between three groups of thermoelectric power generation unit 11.It should be noted that, the quantity of multiple thermoelectric power generation unit 11 can be configured as required, can connect as desired by conducting strip 113 between multiple thermoelectric power generation unit 11 or the mode of parallel connection or series connection and mixing in parallel connects combination composition thermo-electric conversion module 1, the structure that connected mode between quantity and the thermoelectric power generation unit 11 of thermoelectric power generation unit 11 and the power demands of aircraft load and the profile of aircraft are planar arrangement or curved surface arrangement is particularly relevant, therefore does not repeat them here.
As shown in Figure 4, voltage stabilizing charging circuit 2 includes comparison amplifier 23, pulse width modulator 24, driver 25, DC/DC transducer 26, reference voltage source 22 and two control resistance 21, the outfan of comparison amplifier 23 passes sequentially through pulse width modulator 24, driver 25 is connected with the control end of DC/DC transducer 26, the cathode output end of thermo-electric conversion module 1 is connected with the positive pole of accumulator 3 by DC/DC transducer 26, the negative pole of accumulator 3 is connected with the cathode output end of thermo-electric conversion module 1, it is connected between cathode output end and the earth terminal of thermo-electric conversion module 1 after two control resistance 21 series connection, one input of comparison amplifier 23 is connected with reference voltage source 22, another input of comparison amplifier 23 is connected to two and controls between resistance 21, comparison amplifier 23 is to output voltage, reference voltage 22 amplifies the change in voltage of output thermo-electric conversion module 1 after comparing, then through pulse width modulator 24, driver 25 changes the dutycycle of output voltage, reach to control the purpose of output voltage.
As shown in Figure 4, transformation power supply circuits 4 include high-frequency inverter 41, high-frequency step-up transformer 42 and rectifier filter 4, inverter 41, high-frequency step-up transformer 42 and rectifier filter 43 are sequentially connected in series, high-frequency inverter 41 is connected with accumulator 3, and rectifier filter 43 is connected with carry-on load (such as carry-on plasma synthesis jet-flow excitor).The present embodiment in working order time, the low-voltage DC of accumulator 3 output converts the high-frequency alternating current primary input voltage as high-frequency step-up transformer 42 to by high-frequency inverter 41, and this boosting mode can be greatly reduced volume and the quality of transformator and follow-up rectifier filter；Alternating voltage is increased to the high pressure needed for carry-on loaded work piece by high-frequency step-up transformer 42, it is rectified into the high direct voltage that ripple voltage is only small then through rectifier filter 43, for carry-on load supplying, make carry-on loaded work piece, carry-on plasma synthesis jet-flow excitor is such as made to work, to produce the plasma high energy synthesizing jet-flow for hypersonic aircraft active Flow Control.
The above is only the preferred embodiment of the present invention, and protection scope of the present invention is not limited merely to above-described embodiment, and all technical schemes belonged under thinking of the present invention belong to protection scope of the present invention.It should be pointed out that, for those skilled in the art, some improvements and modifications without departing from the principles of the present invention, these improvements and modifications also should be regarded as protection scope of the present invention.
Claims (7)
1. the aircraft supply unit based on hypersonic speed flow Aerodynamic Heating and thermo-electric conversion, it is characterized in that: include voltage stabilizing charging circuit (2), accumulator (3), transformation power supply circuits (4) and at least one thermo-electric conversion module (1), described thermo-electric conversion module (1) is plate-shaped and is installed in the surface of aircraft, described thermo-electric conversion module (1) is connected with accumulator (3) respectively through voltage stabilizing charging circuit (2), and described accumulator (3) is carry-on load supplying by transformation power supply circuits (4)；Described thermo-electric conversion module (1) includes multiple thermoelectric power generation unit (11), described thermoelectric power generation unit (11) includes P type thermo-electric converting material unit (111), N-type thermo-electric converting material unit (112) and conducting strip (113), described P type thermo-electric converting material unit (111), the thermal source of N-type thermo-electric converting material unit (112) aircraft all relatively is arranged vertically, it is connected by conducting strip (113) between described P type thermo-electric converting material unit (111) and N-type thermo-electric converting material unit (112), and by conducting strip (113) series connection between the plurality of thermoelectric power generation unit (11), or it is in parallel, or the mode of series connection and mixing in parallel connects combination and constitutes thermo-electric conversion module (1)；Described thermo-electric conversion module (1) also includes top panel (12), lower panel (13) and support frame (14), described top panel (12) is connected with lower panel (13) by support frame (14), described lower panel (13) is connected with the body of aircraft, the plurality of thermoelectric power generation unit (11) is located between top panel (12), lower panel (13), and described P type thermo-electric converting material unit (111), N-type thermo-electric converting material unit (112) are all close to top panel (12) and are arranged；Being filled with insulator (15) between described top panel (12), lower panel (13), described P type thermo-electric converting material unit (111), N-type thermo-electric converting material unit (112) are all inserted in insulator (15) and arrange with lower panel (13) gap.
2. the aircraft supply unit based on hypersonic speed flow Aerodynamic Heating and thermo-electric conversion according to claim 1, it is characterised in that: described top panel (12) is honeycomb sandwich board.
3. the aircraft supply unit based on hypersonic speed flow Aerodynamic Heating and thermo-electric conversion according to claim 2, it is characterised in that: described lower panel (13) is honeycomb sandwich board.
4. the aircraft supply unit based on hypersonic speed flow Aerodynamic Heating and thermo-electric conversion according to claim 3, it is characterised in that: the honeycomb sandwich board constituting described top panel (12) adopts super Chlorimet to make.
5. the aircraft supply unit based on hypersonic speed flow Aerodynamic Heating and thermo-electric conversion according to claim 4, it is characterised in that: the honeycomb sandwich board constituting described lower panel (13) adopts titanium alloy to make.
6. the aircraft supply unit based on hypersonic speed flow Aerodynamic Heating and thermo-electric conversion according to any one in Claims 1 to 5, it is characterized in that: described voltage stabilizing charging circuit (2) includes comparison amplifier (23), pulse width modulator (24), driver (25), DC/DC transducer (26), reference voltage source (22) and two controls resistance (21), the outfan of described comparison amplifier (23) passes sequentially through pulse width modulator (24), driver (25) is connected with the control end of DC/DC transducer (26), the cathode output end of described thermo-electric conversion module (1) is connected with the positive pole of accumulator (3) by DC/DC transducer (26), the negative pole of described accumulator (3) is connected with the cathode output end of thermo-electric conversion module (1), said two is connected between cathode output end and the earth terminal of thermo-electric conversion module (1) after controlling resistance (21) series connection, one input of described comparison amplifier (23) is connected with reference voltage source (22), another input of described comparison amplifier (23) is connected to said two and controls between resistance (21).
7. the aircraft supply unit based on hypersonic speed flow Aerodynamic Heating and thermo-electric conversion according to claim 6, it is characterized in that: described transformation power supply circuits (4) include high-frequency inverter (41), high-frequency step-up transformer (42) and rectifier filter (43), described high-frequency inverter (41), high-frequency step-up transformer (42) and rectifier filter (43) are sequentially connected in series, described high-frequency inverter (41) is connected with accumulator (3), and described rectifier filter (43) is connected with carry-on load.
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| CN107425754B (en) * | 2017-09-08 | 2023-07-04 | 中国民航大学 | Thermal power source device of aeroengine |
| CN110967369A (en) * | 2019-11-25 | 2020-04-07 | 中国航空工业集团公司沈阳飞机设计研究所 | Device and method for testing heat insulation capability of high-temperature thermoelectric material |
| CN112104264B (en) * | 2020-08-28 | 2021-10-26 | 电子科技大学 | Thermoelectric power generation device for aircraft engine |
| CN112671266A (en) * | 2020-12-25 | 2021-04-16 | 中国航天空气动力技术研究院 | Aircraft heat protection device and aircraft |
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| CN100555833C (en) * | 2005-08-08 | 2009-10-28 | 南京航空航天大学 | Thermoelectric type complex jet flow piezo-electric micro-drive device and control method |
| CN101409324B (en) * | 2008-07-24 | 2013-10-16 | 中国科学院上海硅酸盐研究所 | Manufacturing method of bismuth-telluride-based thermoelectric electrification device |
| US8933676B2 (en) * | 2012-04-10 | 2015-01-13 | Palo Alto Research Center Incorporated | Output power control circuit for a thermoelectric generator |
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