Abstract
In order to accurately control the gas temperature of a supersonic heat-airflow simulated test system, this paper introduces the working principle of the system, including the fuel supply subsystem and the air supply subsystem, establishes the mathematical model of the system, including the fuel supply subsystem, the air supply subsystem and the gas temperature, and analyses the characteristics of the system. Based on characteristics such as non-linearity, parameter time variations, disturbance and pure time delay exist in the system; a new cascade control scheme that can control both the fuel supply subsystem and the air supply subsystem is proposed to achieve an accurate control of the gas temperature. On this basis, the simulation and experimental studies are carried out by the proposed control algorithm. The results show that the proposed gas temperature cascade control algorithm can achieve a fast, stable and no overshoot control of the gas temperature in a wide operating range, and the control accuracy can reach at ±5°C.
Highlights
Supersonic heat-airflow simulated test system (SHSTS) is an important ground test support equipment in the field of aerospace
It is mainly used to simulate the high temperature and high heat flux density environment encountered by high-end aviation equipment such as high-speed aircraft and aero engine, so as to provide thermal performance test conditions for high-end equipment in the field of aerospace and ensure that the performance of the equipment meets the design requirements [1], [2]
It is of great significance to study its temperature control performance characteristics and improve its overall performance test level for improving the manufacturing level of important equipment in the national aerospace field
Summary
Supersonic heat-airflow simulated test system (SHSTS) is an important ground test support equipment in the field of aerospace. The associate editor coordinating the review of this manuscript and approving it for publication was Bin Xu. centralized parameter modeling of the combustion process, fuel flow rate control, air flow rate control and gas temperature control, which are closely related to promote the temperature control performance of the test system, are not thorough and systematic. Centralized parameter modeling of the combustion process, fuel flow rate control, air flow rate control and gas temperature control, which are closely related to promote the temperature control performance of the test system, are not thorough and systematic This situation leads to the performance of the test system cannot meet the current development requirements of aero engine and high-speed aircraft in China. The disturbance of fuel flow rate and air flow rate will affect the performance of the gas temperature control during the experiment. The mathematical model of the air supply subsystem is established, and according to the characteristics of the subsystem, a new sliding mode predictive control strategy is proposed
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