A High-altitude Simulated Altitude And Mach Number Control System To Improve The Design Study

Units at inlet and exhaust pressure adjusting system on altitude simulation test cell includes the engine intake pressure adjusting system,exhaust pressure adjusting system. The result of its pressure control, the safety of its engine test and the validity of its performance measurement are closely related.When we do the testing of core engine, the testing to start the engine at high-altitude, the thrust transient state experiment of high-altitude aero-engine, such as excessive intake pressure and exhaust pressure on the environment will have bad control effect. As this have impaction on the safety of engine test and the performance rating, there is an urgent need for improving the design. On the other hand, the experiment of aero-engine simulation is high-risk, high energy consumption. Only reducing the intake and exhaust test debug control system are permitted, thus these increase the risk and difficulty of its development and improvement under the premise in order to ensure the safety of engine and test equipment.This article is to solve the above problems. It researches and develops the units at high inlet pressure regulator hard ware in the loop simulation platform, also takes the advantage of the platform to begin a design an exploratory research to system of intake and exhaust, system theory, control algorithms and so on. The main contents are as follows. This paper introduced a set air pressure at high altitudes units conditioning systems design, program analysis, control study and generic simulation platform. At the same time can be used for development of control system software, test of software integration, and full function check of controllers, and personnel training. Through simulation experiments and real comparison test proved that the set up of the mathematical model, real-time simulation system are more realistic to meet the engineering needs.In this paper, a detailed study of aero-engine high-altitude simulation test only gas pressure control system and the major sources of interference characteristics, proposed that we should increase air flow disturbance compensation and disturbance compensation by inputting , constituting a complex control system on the base of inlet pressure of conventional PID feedback control. By the air flow disturbance compensation control for high-altitude missile engine to start testing, aero-engine high-altitude thrust transient test, by the input disturbance compensation is mainly applied to the core engine test. By the hard ware in the loop simulation test, the design of complex system dynamics and implementation of the fast high-precision unity.We had a detailed analysis on the status and its major characteristic of China's aero-engine high-altitude simulation test's exhaust pressure on the environment control system, proposed the establishment of artificial intelligence like fuzzy PID parameters ,the system of online self-tuning exhaust pressure on the environment. Detailed introduction of fuzzy PID algorithm also showed how to realize some details when the control algorithm is at the exhaust pressure on the environment control system. After hard ware in the loop simulation test, its result proved that the designed fuzzy PID control system can achieve fast and high-precision. Furthermore, we studied in detail high-altitude Hydraulic Control Valve Units median P control.