Power supply device for aircraft based on hypersonic flow aerodynamic heating and thermoelectric conversion
A thermoelectric conversion and pneumatic heating technology, applied in battery circuit devices, circuit devices, current collectors, etc., can solve the problems of difficult thermal protection of skin surface and scramjet combustion chamber, large power consumption, etc., to improve energy utilization Efficiency, relieve the pressure of thermal protection, realize the effect of miniaturization
Active Publication Date: 2016-06-29
NAT UNIV OF DEFENSE TECH
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Problems solved by technology
On the one hand, the aircraft is subjected to severe aerodynamic heat during flight, and the scramjet engine faces severe thermal loads during its operation, which leads to great difficulties in the thermal protection of the skin surface of the aircraft and the scramjet engine combustion chamber
On the other hand, the long-term flight of hypersonic aircraft requires a lot of power consumption to realize the functions of navigation, communication and flow control of the aircraft, which puts forward higher requirements for the miniaturization and light weight of the aircraft power system
Method used
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[0025] Such as figure 1 As shown, the aircraft power supply device based on hypersonic flow aerodynamic heating and thermoelectric conversion in this embodiment includes a voltage-stabilizing charging circuit 2, a storage battery 3, a voltage-transforming power supply circuit 4, and at least one thermoelectric conversion module 1. The thermoelectric conversion module 1 is in the shape of a plate And installed on the surface of the aircraft, the thermoelectric conversion modules 1 are respectively connected to the storage battery 3 through the voltage stabilizing charging circuit 2, and the storage battery 3 supplies power to the load on the aircraft through the voltage transformation power supply circuit 4. When this embodiment is running, the aerodynamic heat generated by the high-speed incoming flow of the aircraft and the heat transfer of the engine combustion chamber can be partially converted into electrical energy after passing through the thermoelectric conversion module...
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The invention discloses an aircraft power supply device based on hypersonic flow aerodynamic heating and thermoelectric conversion, which includes a voltage-stabilizing charging circuit, a storage battery, a voltage-transforming power supply circuit and a thermoelectric conversion module. The thermoelectric conversion module is connected to the storage battery through a voltage-stabilizing charging circuit. The storage battery is powered by a variable voltage power supply circuit; the thermoelectric conversion module includes multiple thermoelectric power generation units, and the thermoelectric power generation units include P-type thermoelectric conversion material units, N-type thermoelectric conversion material units and conductive plates connected through conductive sheets. Requires connection to combined power supply. The invention can recycle and reuse the aerodynamic heat generated by the high-speed incoming flow during the working process of the aircraft and the heat transfer of the engine combustion chamber, realize effective thermal management of the aircraft and comprehensive utilization of energy to improve the overall energy utilization efficiency, which is beneficial Realize the miniaturization and light weight of the aircraft power supply, organically combine with the aircraft thermal protection system, and have a high degree of integration.
Description
technical field [0001] The invention relates to the technical field of hypersonic aircraft, in particular to an aircraft power supply device based on hypersonic flow aerodynamic heating and thermoelectric conversion. Background technique [0002] Hypersonic vehicles are a major development direction of the world's aerospace industry in the 21st century. For hypersonic aircraft, how to effectively manage heat and realize the comprehensive utilization of energy of the entire aircraft is an important issue in the process of hypersonic flight. On the one hand, the aircraft is subjected to severe aerodynamic heat during flight, and the scramjet engine faces severe thermal loads during its operation, which leads to great difficulties in the thermal protection of the skin surface of the aircraft and the scramjet combustion chamber. On the other hand, the long-term flight of a hypersonic vehicle requires a lot of power consumption to realize the navigation, communication and flow c...
Claims
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IPC IPC(8): H02N11/00H02J7/00
Inventor 周岩刘冰罗振兵夏智勋刘沛林
Owner NAT UNIV OF DEFENSE TECH