Cessna Citation X Aircraft Global Model Identification from Flight Tests

New Methodology for Optimal Flight Control Using Differential Evolution Algorithms Applied on the Cessna Citation X Business Aircraft – Part 1. Design and Optimization

“…The linearization routines developed by Ghazi and Botez in [31] were used to linearized , the aircraft longitudinal and lateral equations of motions for different aircraft configurations in terms of mass and center of gravity positions, and for different flight conditions in terms of altitudes and speeds, several comparisons of these models with the linear model obtained by use of identification techniques as proposed in [32] were performed.…”

“…The Cessna Citation X linear model is obtained for 72 flight conditions based on the Aircraft Flight Research Simulator tests performed at the LARCASE laboratory [32]. The linearized model is interpolated using the bilinear method [34] as represented in Figure 3.…”

New Methodology for Optimal Flight Control using Differential Evolution Algorithms applied on the Cessna Citation X Business Aircraft – Part 2. Validation on Aircraft Research Flight Level D Simulator

“…By using a Cessna Citation X Level D Research Aircraft Flight Simulator designed and manufactured by CAE Inc the benchmark was developed at Laboratory of Active Controls, Avionics and AeroServoElasticity LARCASE in [10]- [11]. This benchmark programmed in Matlab/Simulink was already used for new identification methods designed and developed in [12]- [13], for advanced flight control design and clearance [14]- [15], and for robust control analysis in [4]- [6]. This paper is organized as follows: First a description of the controller optimized using the differential evolution algorithm, the aircraft flight envelope is detailed, and then a brief description of the clearance criteria.…”

Cessna Citation X Business Aircraft Eigenvalue Stability– Part 1: a New GUI for the LFRs Generation

“…In order to validate these different models obtained by this linearization, several comparisons of them with the linear model obtained using the identification techniques proposed in ( [31], [32]) were performed for different flight conditions and aircraft configurations.…”