The objectives of this paper are the study and the implementation of both aerodynamic and propulsion models, as linear interpolations using look-up tables in a database. The aerodynamic and propulsion dependencies on state and control variable have been described by analytic polynomial models. Some simplifying hypotheses were made in the development of the nonlinear aircraft simulations. The choice of a certain technique to use depends on the desired accuracy of the solution and the computational effort to be expended. Each nonlinear simulation includes the full nonlinear dynamics of the bare airframe, with a scaled direct connection from pilot inputs to control surface deflections to provide adequate pilot control. The engine power dynamic response was modeled with an additional state equation as first order lag in the actual power level response to commanded power level was computed as a function of throttle position. The number of control inputs and engine power states varied depending on the number of control surfaces and aircraft engines. The set of coupled, nonlinear, first-order ordinary differential equations that comprise the simulation model can be represented by the vector differential equation. A linear time-invariant (LTI) system representing aircraft dynamics for small perturbations about a reference trim condition is given by the state and output equations present. The gradients are obtained numerically by perturbing each state and control input independently and recording the changes in the trimmed state and output equations. This is done using the numerical technique of central finite differences, including the perturbations of the state and control variables. For a reference trim condition of straight and level flight, linearization results in two decoupled sets of linear, constant-coefficient differential equations for longitudinal and lateral / directional motion. The linearization is valid for small perturbations about the reference trim condition. Experimental aerodynamic and thrust data are used to model the applied aerodynamic and propulsion forces and moments for arbitrary states and controls. There is no closed form solution to such problems, so the equations must be solved using numerical integration. Techniques for solving this initial value problem for ordinary differential equations are employed to obtain approximate solutions at discrete points along the aircraft state trajectory.
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27 January 2017
ICNPAA 2016 WORLD CONGRESS: 11th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences
4–8 July 2016
La Rochelle, France
Research Article|
January 27 2017
Analysis of control system responses for aircraft stability and efficient numerical techniques for real-time simulations Available to Purchase
Gabriela Stroe;
Gabriela Stroe
b)
1“POLITEHNICA”
University of Bucharest, Faculty of Aerospace Engineering
, Str. Gh. Polizu 1-7, Sector 1, Bucharest, 011061, Romania
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Irina-Carmen Andrei;
Irina-Carmen Andrei
a)
2
INCAS - The National Institute for Aerospace Research
“Elie Carafoli” B-dul Iuliu Maniu 220, Sector 6, Bucharest, 061126, Romania
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Florin Frunzulica
Florin Frunzulica
c)
1“POLITEHNICA”
University of Bucharest, Faculty of Aerospace Engineering
, Str. Gh. Polizu 1-7, Sector 1, Bucharest, 011061, Romania
Search for other works by this author on:
Gabriela Stroe
1,b)
Irina-Carmen Andrei
2,a)
Florin Frunzulica
1,c)
1“POLITEHNICA”
University of Bucharest, Faculty of Aerospace Engineering
, Str. Gh. Polizu 1-7, Sector 1, Bucharest, 011061, Romania
2
INCAS - The National Institute for Aerospace Research
“Elie Carafoli” B-dul Iuliu Maniu 220, Sector 6, Bucharest, 061126, Romania
AIP Conf. Proc. 1798, 020156 (2017)
Citation
Gabriela Stroe, Irina-Carmen Andrei, Florin Frunzulica; Analysis of control system responses for aircraft stability and efficient numerical techniques for real-time simulations. AIP Conf. Proc. 27 January 2017; 1798 (1): 020156. https://doi.org/10.1063/1.4972748
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