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scientific edition of Bauman MSTU
SCIENCE & EDUCATION
Bauman Moscow State Technical University. El № FS 77 - 48211. ISSN 1994-0408
Technique for Assessing the Stability and Controllability Characteristics of Naval Aircraft Systems Based on the Rational Combination of Modeling, Identification and Flight Experiments
# 10, October 2015
DOI: 10.7463/1015.0813316
Article file:
SE-BMSTU...o193.pdf
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SE-BMSTU...o193.pdf
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1 Chkalov State Flight Test Center of the Ministry of Defence, Akhtyubinsk, Russia  |
The aim of this work is to improve test quality and reliability of modern naval aircraft for assessment of stability and controllability characteristics and test shortening. To achieve this goal it is necessary to develop an algorithmic, mathematical and methodological support of the flight trials and the mathematical modeling of controlled flight modes to determine the stability and controllability characteristics of the naval aircraft.
The article analyses the problems related to determining the stability and controllability characteristics under flight tests, describes the technique to correct a mathematical model of aerodynamic characteristics and engine thrust forces of modern naval aircraft. It shows the importance of using algorithm to control the correctness of onboard measurements of flight parameters. The article presents new results of identification of the aircraft aerodynamic coefficients and proves that in identifying characteristics of the longitudinal control channel it is necessary to take into account the engine thrust forces. In the article the aerodynamic coefficients, obtained by identification methods, are compared with those in the original aerodynamic data Bank.
An important and new component of the work described in the fourth part of the article, is a set of computer programmes, integrated into a common interface. The development of this software has greatly improved a processing technology of the flight experiment materials and identification of the aerodynamic characteristics of the aircraft.
When applying the work results in the testing phase, the required characteristics of stability and controllability are determined by simulation, and identification provides the model refinement according to the flight data.
The created technology of practical identification is used to verify and refine the mathematical models according to the flight experiment data. Thus, the result is a proven and refined model of the aircraft motion in the range of main flight operating conditions. This model is aimed at using to not only to support testing, but at subsequent stages of the aviation system life cycle as well. These models are necessary when training the pilots to fly to the ship, when developing the simulators, at the stage of modernization, in examination of aircraft accidents, etc. As a result of the work, have been created a new technique for evaluating the stability and controllability characteristics of the naval aircraft system, including a new procedure for the identification and also the new algorithmic techniques that can be used to visualize the dependence of aerodynamic coefficients as a function of the angle of attack and a new approach to identify longitudinal channel according to lateral test flight modes. All the results are confirmed by processing of flight experiment materials.
The work is fulfilled with the support of the Russian Foundation for Basic Research (RFBR), project 15-08-06237.
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Publications with keywords: identification, methods, flight tests, aerodynamic coefficients, naval aircraft system
Publications with words: identification, methods, flight tests, aerodynamic coefficients, naval aircraft system
See also:
- Identification of Nonlinear Dynamic Systems Possessing Some Non-linearities
- Conversion Method of the Balance Test Results in Open Jet Tunnel on the Free Flow Conditions
- Project Analysis of Aerodynamics Configuration of Re-entry Сapsule-shaped Body Based on Numerical Methods for Newtonian Flow Theory
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