Aerospace heat flow sensor and heat flow correction method based on double temperature difference compensation

• Main Authors: YAO JIE, ZHU YANDAN, GUO YIJUN, ZHANG HAOYUAN, QIU BO, SHI YOU'AN, JIANG BO, ZENG LEI
• Format: Patent
• Language: Chinese; English
• Published: 26.01.2024
• Subjects: MEASURING; MEASURING QUANTITY OF HEAT; MEASURING TEMPERATURE; PHYSICS; TESTING; TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES; TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR

The invention discloses a spaceflight heat flow sensor and a heat flow correction method based on double temperature difference compensation. The spaceflight heat flow sensor comprises a first heat sink, a second heat sink and a metal plate. The first heat sink and the second heat sink are arranged on the metal plate in an embedded mode, and the end faces of one sides of the first ends of the first heat sink and the second heat sink are flush with the plane where the metal plate is located. Wherein the first heat sink and the second heat sink are different in volume; a first thermocouple, a second thermocouple and a third thermocouple, the first thermocouple and the second thermocouple are respectively installed on the end portions of the second ends, far away from the metal plate, of the first heat sink and the second heat sink, and the third thermocouple is arranged on the side, where the incoming flow direction is located, of the metal plate; the second end of the first heat sink, the second end of the sec