| 摘要 |
The proposed device for the ground testing of the operation of a static-pressure tube relay at the decending section of an aircraft flight path contains a measuring chamber, a vacuum manometer, an electric heating element, a resistive temperature transducer, a pressure difference transducer, a vacuum chamber, and facilities for supplying compressed air to the measuring chamber. The relay to be tested is installed in the measuring chamber. The measuring chamber is connected to the vacuum chamber by a tube with a vacuum check valve. The facilities for supplying compressed air include a receiver, a pressure reducer, an electropneumatic valve, a control valve, and a pressure indicator.
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