Direct adaptive reconstruction control method for three-degree-of-freedom helicopter

Abstract

The invention relates to a direct adaptive reconstruction control method for a three-degree-of-freedom helicopter. A model structure of a direct adaptive reconstruction control law is improved, and a series of calculation steps for controlled variables of the three-degree-of-freedom helicopter are performed, so that the response of the three-degree-of-freedom helicopter to failure conditions is quickened, and the flight safety of the helicopter is ensured.

Description

technical field [0001] The invention relates to a direct adaptive reconfiguration control method for a three-degree-of-freedom helicopter. Background technique [0002] The helicopter flight control system is an important part of the helicopter, which plays a very critical role in the flight performance and safety of the helicopter. Since there are many components in the helicopter flight control system, the possibility of failure is high, so it is very important to study the fault-tolerant control technology of the flight control system. When a failure occurs, the helicopter can be restored to a stable flight within a short period of time by reconfiguring the control to improve flight safety. [0003] The purpose of the reconfiguration control of the flight control system is to make the helicopter have higher survivability in the event of actuator failure or other unknown failures during flight. Adaptive reconfiguration control is divided into two methods: direct adaptive...

AI Technical Summary

Problems solved by technology

In the existing adaptive reconfiguration control method, the control quantity of the helicopter adopts the model Obtained, where u is the control quantity of the three-degree-of-freedom helicopter, x is the state vector of the three-degree-of-freedom helicopter, and r is the input vector of the three-degree-of-freedom helicopter reference model, is the fault compensation vector, K x is the state vector feedback gain matrix, K r is a feed-forward gain matrix, but using this model system is not fast enough to deal with failure situations, which directly affects the self-regulation ability of the helicopter when dealing with failures, and the self-regulation ability of the helicopter when dealing with failures directly affects its own flight Safety issues, so the calculation speed of the control volume of the helicopter determines the flight safety of the helicopter

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