A Self-tuning Method for Pressure Feedback Control Parameters of Variable Thrust Engine

Abstract

The present invention is a pressure feedback control parameter self-tuning method of a variable thrust engine. After real-time collection of the pressure of the combustion chamber of the solid rocket motor by the pressure sensor, the appropriate control is given according to the deviation between the measured pressure and the target pressure through the feedback comparison link. Output, so that the working pressure of the engine combustion chamber can be stabilized near the target pressure or follow the change of the target pressure, and the combustion state of the solid propellant can be controlled by controlling the working pressure of the engine, so as to realize engine thrust regulation and system energy management. The pressure change of the solid engine is affected by the coupling of multiple factors such as throat area, charge burning rate, and charge burning surface. The pressure feedback control system is a complex nonlinear time-varying system, and the pressure control parameters are related to the system state in real time. The patent of the present invention proposes a variable thrust engine feedback control parameter self-adjustment method, which can effectively realize the pressure stability control of the solid engine, and it has been verified that the pressure control deviation is less than 2%.

Description

technical field [0001] The invention relates to a method for setting pressure control parameters of a combustion chamber of a variable thrust engine, belonging to the technical field of variable thrust solid rocket motors. Background technique [0002] Solid rocket motor has many advantages such as simple structure and reliable operation, and has become an important power device of weapon system. The variable thrust engine is a solid engine that can adjust the thrust according to the flight state and work requirements of the missile. The thrust of the engine cannot be directly obtained when the missile is flying, and the thrust is not controlled during the thrust adjustment process, which belongs to open-loop adjustment. Assuming that the adjustment amount cannot be accurately corresponded to the actual output thrust, according to the correlation of the thrust pressure of the solid engine, the thrust is adjusted after the pressure feedback control is introduced, and the pre...

AI Technical Summary

Problems solved by technology

[0005] 2. The adjustment performance varies greatly with the working state of the engine

During the working process of the engine, the propellant is gradually consumed, and the free volume gradually increases, resulting in a gradual increase in the thrust pressure response time. Different initial throat openings correspond to different initial working pressures, and the thrust and pressure dynamically oscillate under the same control parameters. Quantity and steady-state control errors vary greatly

[0006] 3. Reduced structural integrity and reliability

When the throat is adjusted, the pressure changes dynamically. Under the influence of various disturbances, it is easy to cause the pressure of the combustion chamber to be too high, which will damage the structural integrity of the ring, and it is difficult to meet the safe and reliable working requirements of the weapon system.

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