Longitudinal automatic control system for a light weight aircraft
Journal Title: INCAS BULLETIN - Year 2016, Vol 8, Issue 4
Abstract
This paper presents the design of an automatic control system for longitudinal axis of a light weight aircraft. To achieve this goal it is important to start from the mathematical model in longitudinal plane and then to determine the steady-state parameters for a given velocity and altitude. Using MATLAB Software the mathematical model in longitudinal plane was linearized and the system transfer functions were obtained. To determine the automatic control design we analyzed the stability of the linearized model for each input. After the stability problem was solved, using MATLAB-Simulink Software we designed the control system architecture and we considered that the objective for a stable flight was to continuously adjust the pitch angle θ through control of elevator and velocity through control of the throttle. Finally, we analyzed the performance of the designed longitudinal control system and the results highlighted in graphs outline that the purpose for which it was designed was fulfilled.
Authors and Affiliations
Cristian VIDAN, Silviu Ionut BADEA
Keywords
Related Articles
- EP ID EP249405
- DOI 10.13111/2066-8201.2016.8.4.13
- Views 90
- Downloads 0
[b]Homage to Henri Coanda[/b]
Small power wind turbine (Type DARRIEUS)
This presentation focuses on the calculation for small vertical axis wind turbines (VAWT) for an urban application. The fixed-pitch straight – bladed vertical axis wind turbine (SB-VAWT) is one of the simplest types of w...
Optimization of the flueric actuators testing system
A supplying system for air with precisely controlled temperature, pressure, flow and speed has been designed in order to test the flueric actuator. All these parameters are monitored and the acquired data are stored on a...
Dynamic study of the virtual prototype of the IAR-99 SOIM Aircraft
This paper contains a dynamic study of the IAR-99 SOIM aircraft using ADAMS, multibody dynamic solutions. First, the analysis of the whole airplane is envisaged and then the analysis of the flight control system and the...
Static and Dynamic Design Methods for Hybrid Bolted Joints in a Satellite Structure
A detailed analytical design for hybrid (metal-composite) bolted joints in static and dynamic (random vibrations) analysis is presented in this paper. Due to the fact that a space structure must be lighter and stiffened,...