High-temperature thermal radiation testing device and method capable of synchronously and continuously adjusting large-volume temperature and pressure

The invention relates to a high-temperature thermal radiation testing device and method capable of synchronously and continuously adjusting the large-volume temperature and pressure, and belongs to the technical field of thermal vacuum testing. The device and method are used for vacuum pneumatic the...

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Main Authors CAO ZHIHONG, WANG LEI, XIA LINSHI, NA WEI, TIAN NING, CAO YUQING, ZHANG LISONG, QI BIN, ZHAO LING, YUE HUI, ZHANG KAI, ZOU YANGHUI, YANG CHI
Format Patent
LanguageEnglish
Published 23.12.2015
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Summary:The invention relates to a high-temperature thermal radiation testing device and method capable of synchronously and continuously adjusting the large-volume temperature and pressure, and belongs to the technical field of thermal vacuum testing. The device and method are used for vacuum pneumatic thermal loads stressed by an outer layer heat prevention/isolation material and structure of a ground-based simulation aircraft in the flight process from the space environment to the atmospheric layer, and the vacuum environment. Through linkage control over an electromagnetic valve A, an electromagnetic valve B and an electromagnetic valve C capable of being opened and closed quickly on three exhaust pipelines of the exhaust pipeline a, the exhaust pipeline b and the exhaust pipeline c which are connected on the downstream of an exhaust system vacuum pipeline A in parallel and have different calibers and an air supply ball valve on an air supply system vacuum pipeline, the real-time dynamic adjusting function on the cabin pressure of a vacuum testing cabin is achieved successfully, the problem of continuously and dynamically adjusting the pressure environment during orbit change of different heights in the in-orbit and orbit-transfer maneuvering flight process of the aircraft is solved, the vacuum degree of the testing cabin can be adjusted continuously and precisely within a certain vacuum degree range, and the flight environment of an aircraft of a new generation in the process of entering the atmospheric layer again can be simulated more realistically.
Bibliography:Application Number: CN20151604654