Development and simulations of aircraft guidance system using a 3-degree-of-freedom point mass model

Numerical simulations play an essential role in the development and testing of navigation and guidance algorithms, especially when developer must keep the development costs as low as possible. Low budget development focuses mainly on utilization of numerical flight mechanics simulators including opt...

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Vydané v:Aviation (Vilnius, Lithuania) Ročník 13; číslo 2; s. 35 - 43
Hlavný autor: Sudars, Martins
Médium: Journal Article
Jazyk:English
Vydavateľské údaje: Taylor & Francis Group 01.01.2009
Vilnius Gediminas Technical University
Predmet:
aerodinmaniai kampai
aerodynamic angles
Aerodynamics
Aircraft
Algorithms
Attitude control
BSA skrydžio modeliavimas
Computer simulation
Flight simulators
guidance
Laws
Mathematical models
modelio materialus taškas
navigacija
navigation
Numerical simulations
point mass model
skaitinis modeliavimas
trajectory
trajektorija
UAV flight simulations
valdymas
Numerical simulations
navigation
aerodynamic angles
guidance
UAV flight simulations
trajectory
point mass model
ISSN:1648-7788, 1822-4180
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Popis
Shrnutí:Numerical simulations play an essential role in the development and testing of navigation and guidance algorithms, especially when developer must keep the development costs as low as possible. Low budget development focuses mainly on utilization of numerical flight mechanics simulators including optimization and hardware in loop tests. Reliable, high fidelity results can be easily obtained by numerical simulations of flight dynamics utilizing computing power provided by a normal off-the-shelf home PC. However, it still requires a simple, but good and valid model of the aircraft and environment. This paper describes an approach to a numerical simulation of aircraft motion that respects the requirement for a full environment high fidelity model and keeps a good interface for further development of attitude control. The goal is achieved by directly specifying the aerodynamic angles of the vehicle in the simulation environment by the guidance system, which can later be used as input for attitude control algorithms. It is proved how an appropriate selection of reference frames and formulation of laws of motion gives very quick and reliable results by employing large integration time steps that would be difficult to achieve in 6-degree-of-freedom simulations. This paper also investigates the range of applicability, advantages, and drawbacks of this method. An example of an aerodynamic angle-based guidance law for a UAV is explained and demonstrated by figures.
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ISSN:1648-7788
1822-4180
DOI:10.3846/1648-7788.2009.13.35-43