Disclosed are thermal protection and drag reduction method and system for an ultra high-speed aircraft. A cold source (200) is and a cold source driving device (100) are arranged inside a cavity of the ultra high-speed aircraft. A plurality of micropores (300) are arranged on a wall surface (310) of the cavity. The cold source driving device (100) comprises an air pump (110), a cold source reservoir (210) and a buffer (150). The air pump (110) supplies compressed air to a cold source reservoir (210) during operating. The cold source (200) enters the buffer (150) and is vaporized under the action of air pressure. High-pressure gas is ejected from the micropores (300) to form a gas film on the outer surface of the cavity. The gas film not only can perform thermal protection on the ultra high-speed aircraft, but also can effectively reduce viscous drag between the aircraft and the external gas, by virtue of which the thermal barrier phenomenon is alleviated or eliminated. Therefore, security of the ultra high-speed aircraft is improved and service life is prolonged.
THERMAL PROTECTION AND DRAG REDUCTION METHOD AND SYSTEM FOR ULTRA HIGH-SPEED AIRCRAFT
VERFAHREN UND SYSTEM FÜR WÄRMESCHUTZ UND WIDERSTANDSVERRINGERUNG FÜR HOCHGESCHWINDIGKEITSFLUGZEUG
PROCÉDÉ ET SYSTÈME DE PROTECTION THERMIQUE ET DE RÉDUCTION DE TRAÎNÉE POUR AÉRONEF ULTRA-RAPIDE
2022-10-26
Patent
Electronic Resource
English
IPC: | B64G Raumfahrt , COSMONAUTICS / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F15D FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS , Strömungsdynamik, d.h. Verfahren oder Vorrichtungen zum Beeinflussen der Strömung von Gasen oder Flüssigkeiten / F42B EXPLOSIVE CHARGES, e.g. FOR BLASTING , Explosive Ladungen, z.B. für Sprengungen |
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