Dual-redundancy compensation type empennage control plane fault state control method

Abstract

The invention discloses a dual-redundancy compensation type empennage control plane fault state control method. The method comprises the steps of building a fault state physical model; building a fault state parameterization universal model; calculating a control effect and a hinge moment limiting boundary; determining a residual maneuvering ability and a safe controllable flight envelope; binding an emergency disposal envelope; and performing online use. According to the method, the fault state analysis range is optimized and reduced, so that a maximum safe controllable flight envelope is obtained with a minimum calculation amount; a mathematic model is simplified; a floating yaw angle in a flight process is obtained by adopting a reduced order interpolation method in a control model, so that accurate calculation of the floating-state yaw angle is realized; and the emergency disposal envelope is bound in advance, so that a safe flight range is preset for online emergency. In addition, the influences of the hinge moment of the control plane and the efficiency on the residual maneuvering ability of an aircraft are comprehensively considered, and the height and speed ranges meeting safe flight requirements are preset for fault emergency disposal of the control plane, so that the survivability of the aircraft is improved.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a method for controlling the failure state of a double-redundancy compensation empennage rudder surface. Background technique [0002] Longitudinal maneuvering of aircraft is the most important maneuvering control to ensure basic flight safety. The tail rudder surface is the control surface that controls the longitudinal maneuver of the aircraft. In order to improve the survivability of the aircraft, the UAV often adopts a double-redundant tail rudder design. When one group fails, the remaining rudder surfaces can be recombined to make up for the faulty rudder surface. The resulting decrease in control efficiency is to meet certain longitudinal maneuvering requirements and basic flight safety. [0003] Public information generally only considers the impact of rudder effect reduction caused by rudder surface failure on flight safety, for example: the paper "Control Reconfigurati...

AI Technical Summary

Problems solved by technology

If only the influence of rudder effect on control reconfiguration and flight envelope is considered, the hinge moment of the rudder surface may have reached the limit of the strength of the steering gear system and structure before the rudder effect reaches the maximum value, resulting in damage to the steering gear or loss of the rudder surface, resulting in rudder failure. The loss of all control functions on the plane will endanger flight safety and reduce the survivability of the aircraft

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