The invention relates to a
vacuum chamber for a high-altitude
simulation test of a liquid
rocket engine, belongs to the technical field of
aerospace liquid
rocket engine tests, and solves the technical problems of single function, difficulty in operation and poor safety of a traditional
vacuum chamber. The cabin comprises a cabin body, a cabin door, a
heat sink system, a fire fighting
system, a gas replacement
system, an anti-arch blasting device, a blowdown system, a mounting platform, an operation platform, a
propellant supply pipeline and measurement and
control equipment. The cabin body is cubic, and the
working pressure in the cabin body is 0-0.1 MPa. The cabin door is used for entering and exiting of personnel, small ground equipment, an engine and a thrust measuring device. The
heat sink system, the fire fighting system, the gas replacement system, the
sewage discharge system, the mounting platform and the
propellant supply pipeline are mounted on the cabin body, and the measurement and
control equipment is a
transmission channel for engine control and measurement signals. The
vacuum chamber is used for a liquid
rocket engine high-altitude
simulation test.