Anti-disturbance steady speed control system of micro turbojet engine based on sliding mode variable structure

By using a sliding mode variable structure control system, combined with a band-stop filter and a second-order superspiral algorithm, the problem of the superposition of combustion delay and bearing thermal inertia phase antiphase under the fuel split configuration of a micro turbojet engine was solved, thereby improving the steady-state control accuracy and the long-term operational reliability of the engine.

CN122407375APending Publication Date: 2026-07-17CIVIL AVIATION UNIV OF CHINA
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Patent Information

Authority / Receiving Office
CN Β· China
Patent Type
Applications(China)
Current Assignee / Owner
CIVIL AVIATION UNIV OF CHINA
Filing Date
2026-05-29
Publication Date
2026-07-17

AI Technical Summary

Technical Problem

Existing speed control methods for micro turbojet engines fail to effectively compensate for the superposition effect of combustion delay caused by fuel splitting configuration and bearing thermal inertia phase antiphase, resulting in attenuation of control gain and affecting steady-state control accuracy and long-term engine reliability.

Method used

A sliding mode variable structure-based control system is adopted. The combustion branch time delay and bearing lubrication branch thermal inertia parameters are obtained through the parameter calculation unit. The disturbance energy of the notch frequency is eliminated by the band-stop filter, and the final fuel command is calculated and generated by the continuous second-order superspiral algorithm to avoid the speed response.

Benefits of technology

It effectively avoids the mis-injection of control energy into the bearing thermal state or combustion thermoacoustic field, improves the long-term operational stability and anti-disturbance capability of the micro turbojet engine at the steady-state operating point, and solves the problem of steady-state implicit excitation and component life loss that are easily generated under the fuel split configuration.

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Abstract

The present application relates to the technical field of aero-engine control, and discloses a disturbance-resistant steady-state rotating speed control system for a micro turbojet engine based on a sliding mode variable structure, which comprises: a parameter solving unit that calculates a notch frequency based on the phase-reversed superposition relationship between a combustion branch and a bearing lubrication branch; a pre-filtering unit that processes a rotating speed deviation signal by using a band-stop filter with a center frequency of the notch frequency to generate an avoidance deviation signal; a sliding mode controller that determines a gain adjustment coefficient based on the amplitude attenuation ratio at the notch frequency, and generates a primary fuel instruction by using a continuous second-order hyper-spiral algorithm; and a post-filtering unit that performs notch filtering on the primary fuel instruction again to generate a final fuel instruction. The present application can effectively avoid the gain collapse frequency band caused by fuel shunting configuration, prevent the misinjection of control energy into a non-rotating speed channel, and improve the steady-state control precision and operation reliability of the engine.
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