Variable cross-section shock wave induced ultralow-pressure self-ignition experimental device and method

Abstract

The invention discloses a variable cross-section shock wave induced ultralow-pressure self-ignition experimental device and method. The variable cross-section shock wave induced ultralow-pressure self-ignition experimental device comprises a high-pressure driving section, a dual-mode membrane breaking mechanism, a conical transition section and a low-pressure experimental section which are coaxially connected in sequence, wherein the high-pressure driving section is coaxially connected with the dual-mode membrane breaking mechanism; the high-pressure driving section and the double-membrane breaking mechanism are separated by a membrane; the double-membrane breaking mechanism is coaxially connected with a small-diameter port of the conical transition section, and the double-membrane breaking mechanism and the conical transition section are blocked by a membrane; the large-diameter port of the conical transition section is coaxially connected with the low-pressure experiment section, high-strength shock waves generated by a traditional shock tube can be matched, the defect that the traditional shock tube cannot stably block the high-pressure driving section and the low-pressure experiment section can be overcome, and accurate measurement of ultralow-pressure self-ignition delay of the near-space aircraft is effectively obtained.

Description

technical field [0001] The invention belongs to the technical field of ignition and combustion of near-space vehicles, and relates to an ultra-low pressure self-ignition experimental device and method induced by a variable-section shock wave. Background technique [0002] Near space has many flight advantages in both aviation space and outer space, and it is a must for future space combat strategists. The self-ignition delay characteristic is the key to the design of mainstream aircraft in near space, such as scramjet engine and turbine combined engine, and its accurate experimental characterization is directly related to the combustion stability and operational reliability of near space aircraft. [0003] The high-altitude atmosphere is thin, and the air density at conventional flight altitudes (32km) is only one percent of that on the ground. The air intake pressure during flight is extremely low, making accurate measurement of self-ignition difficult. The traditional sho...

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Problems solved by technology

[0004] In order to solve the problem of accurate characterization of self-ignition in the ultra-low pressure environment of near-space aircraft, the present invention proposes an experimental device and method for ultra-low pressure self-ignition induced by variable-section shock waves. This method can not only match the high-intensity shock waves generated by traditional shock tubes, but also It can overcome the defect that the traditional shock tube cannot stably block the high-voltage driving section and the low-pressure experimental section, and effectively obtain accurate measurements of the ultra-low pressure self-ignition delay of near-space vehicles

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