Hypersonic speed propulsion wind tunnel control system based on PLC

Abstract

The invention discloses a hypersonic speed propulsion wind tunnel control system based on PLC. The hypersonic speed propulsion wind tunnel control system comprises the components of a master control unit (1), a server unit (2), a displaying and printing unit (3), a PLC master station unit (4), a PLC auxiliary station first unit (5), a PLC auxiliary station second unit (6), a PLC auxiliary station third unit (7), a PLC auxiliary station fourth unit (8), a PLC auxiliary station fifth unit (9), a PLC auxiliary station sixth unit (10), an air operated valve unit (51), a regulating valve unit (61), an electric valve unit (71), a water pump unit (81), a data acquisition unit (91) and a total-temperature and total-pressure measuring balance unit (101). According to the hypersonic speed propulsion wind tunnel control system, distributed control technology, industrial field bus technology, operation interlock technology, modular programming technology and manual / automatic integration technology are integrally utilized, centralized monitoring and control on controlled equipment and monitoring device which are distributed in a wind tunnel field is realized in a control room, and furthermore monitoring management level on the working condition of the wind tunnel system is further improved.

Description

Technical field [0001] The invention belongs to the technical field of hypersonic wind tunnels, and particularly relates to a hypersonic propulsion wind tunnel control system. Background technique [0002] Hypersonic wind tunnel refers to a wind tunnel with a test flow field above Mach 5, which is suitable for scramjet test. In this way, a test environment for a hypersonic vehicle model is formed on the ground. The experimental equipment must be able to provide hypersonic airflow, be able to simulate the increase in airflow value and pressure of the surrounding airflow and pressure when the hypersonic vehicle is flying at high Mach number, and simulate the high-altitude flight environment with thin air. When the above conditions are met at the same time, the experimental equipment system is very complicated, and the design and operation are very difficult. The hypersonic propulsion wind tunnel involved in this article adopts the method of burning hydrogen to supplement oxygen. ...

AI Technical Summary

Problems solved by technology

The structure of the wind tunnel is complex, the control parts are scattered, and the risk is high; during the test process, the number and types of detection signals are large, the amount of information is large in a short period of time, and the reliability and real-time performance of signal transmission are high.

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