Light Aircraft Instrumentation to Determine Performance, Stability and Control Characteristics in Flight Tests 2004-01-3474
This paper present the instrumentation procedure used in order to determine the performance, stability and control characteristics of the light aircraft CEA-205 CB-9 Curumim.
The instrumentation used is: i) autonomous acquisition system using micro controllers; ii) solid state inertial platform; iii) pitot probe; iv) attack and sideslip angle indicators; v) potentiometer on control system; vi) load cell on control system; vii) propeller tachometer; viii) barometer; ix) thermometer and x) GPS.
Assembly and calibration detail procedures are presented with some results obtained on typical maneuvers. This work, in development on the Center for Aeronautical Studies of Federal University of Minas Gerais (CEA/UFMG) and on the Department of Aeronautical Engineering of Naples University (DPA), intend to assembly a system in order to perform low cost flight tests on light aircrafts.
Citation: de Oliveira, P., Ribeiro, R., de Freitas Pinto, R., Resende, L. et al., "Light Aircraft Instrumentation to Determine Performance, Stability and Control Characteristics in Flight Tests," SAE Technical Paper 2004-01-3474, 2004, https://doi.org/10.4271/2004-01-3474. Download Citation
Author(s):
Paulo Henriques Iscold Andrade de Oliveira, Rogério Pinto Ribeiro, Ricardo Luiz Utsch de Freitas Pinto, Luciano Saraiva Resende, Fabrizio Nicolosi, Domenico Pietro Coiro, Nicola Genito
Affiliated:
Federal University of Minas Gerais, Naples University
Pages: 8
Event:
2004 SAE Brasil Congress and Exhibit
ISSN:
0148-7191
e-ISSN:
2688-3627
Related Topics:
Business and general aviation aircraft
Control systems
Aircraft instruments
Flight tests
Assembling
Education and training
Global positioning systems (GPS)
Slip
Propellers and rotors
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