Flight control method for large civil aircrafts on basis of direct adaptive control reconfiguration

Abstract

The invention discloses a flight control method for large civil aircrafts on the basis of direct adaptive control reconfiguration, and relates to the field of control technology for aircrafts. The flight control method has the advantages that a direct adaptive process and a model following process are combined with each other and are applied to B747-200 aircrafts, control reconfiguration flight simulation for the large civil aircrafts in an actuator failure mode is implemented, reference is provided for control reconfiguration for the large civil aircrafts in the actuator failure mode, and accordingly the flight control method has an important significance in improving the safety of the aircrafts, reducing the accident rate of the aircrafts and improving the survival ability of the aircrafts under failure conditions.

Description

technical field [0001] The invention relates to a method in the technical field of aircraft control, in particular to a model-following-based direct adaptive control reconstruction algorithm and its application in flight control of large civil aircraft. Background technique [0002] A reconfigurable flight control system (Reconfigurable Flight Control System, RFCS) can redesign the controller structure or calculate the controller gain when the aircraft fails, and use the aircraft's control redundancy function to ensure flight safety autonomously and in a timely manner. [0003] Classical control reconfiguration methods can be divided into active reconfiguration and passive reconfiguration. Passive reconfiguration is based on the design method of robust control, which can tolerate certain types and certain degrees of faults through the inherent fault tolerance of the control law, but it lacks adaptive capabilities for unknown and sudden faults. Different from the controlled ...

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Problems solved by technology

However, this technology uses a unified reference model to replace the actual flight conditions. When the flight conditions deviate greatly from the reference model, the reconstruction control will bring a large deviation; secondly, when considering the stability of multi-model switching, the author uses the desalination link to This method can suppress high-frequency noise, but the stability of the system is also related to the stability margin of the switching system. If the switching system is extremely unstable, it is difficult to ensure switching stability even if there is a desalination link.

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