Fault-Tolerant Flight Control Based on Two-Stage Approach and Interior Point Method
| Autor: | Alexandre C. B. Ramos, Felix Mora-Camino, Lunlong Zhong |
|---|---|
| Přispěvatelé: | Ecole Nationale de l'Aviation Civile (ENAC), Instituto de Recursos Naturais [Itajubá], Universidade Federal de Itajubá |
| Jazyk: | angličtina |
| Rok vydání: | 2018 |
| Předmět: |
0209 industrial biotechnology
Computer science Flight control ComputerApplications_COMPUTERSINOTHERSYSTEMS 010103 numerical & computational mathematics 02 engineering and technology 01 natural sciences Field (computer science) Actuator reassignment [SPI.AUTO]Engineering Sciences [physics]/Automatic Computer Science::Robotics 020901 industrial engineering & automation Control theory Interior point method Quadratic programming 0101 mathematics Electrical and Electronic Engineering Computer simulation Fault tolerance Computer Science Applications Nonlinear system Fault tolerant control Two-stage approach Inverse control Affine transformation Actuator |
| Zdroj: | Wireless Personal Communications Wireless Personal Communications, Springer Verlag, 2018, 102 (2), pp 1809-1825. ⟨10.1007/s11277-017-5238-4⟩ |
| ISSN: | 0929-6212 1572-834X |
| DOI: | 10.1007/s11277-017-5238-4⟩ |
| Popis: | International audience; The main objective of this paper is how to make the best use of remaining available actuators when an aircraft with an aerodynamic actuator failure tries to perform a guidance maneuver. Considering the flight dynamics of a transportation aircraft can be expressed as an input affine nonlinear system, a two-stage control approach is adopted here. At the first stage, nonlinear inverse control technique is used to generate virtual inputs related to the intended maneuver. At the second stage, an actuator reassignment problem how to achieve necessary virtual inputs by remaining available actuators is considered. Taking into account the physical limits of the remaining actuators and of the aircraft structure, the problem is formulated as a quadratic programming problem to get the corresponding control signals sent to the remaining actuators. The proposed solution method for this quadratic mathematical programming problem is based on a primal-dual path following interior point method. Numerical simulation studies based on the nonlinear aircraft models show that the proposed solution approach appears to provide acceptable response times to perform accurately the guidance maneuver. |
| Databáze: | OpenAIRE |
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