Development of a Wind Tunnel Apparatus for Aircraft Stability Augmentation System Testing Escola de Engenharia de São Carlos - Universidade de São Paulo

Format:

Conference/Event

Author/Creator:

de Carvalho Pereira, Natanael, author.

Conference Name:

SAE Brasil 2003 Congress and Exhibit (2003-11-18 : Sao Paulo, Brazil)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 2003

Summary:

Wind tunnel testing can be used, to some extent, to validate computational methods applied to aircraft analysis. The costs associated with those tests are usually much less than with flight testing and with more flexible instrumentation settings. Aircraft automatic flight control systems can be developed and simulated using computational methods. Very often, though, computer simulations fail to reproduce real flight characteristics. This paper describes the first phase of development and testing of an apparatus designed to experimentally verify, in a wind tunnel, the functionality of aircraft stability augmentation systems (SAS). The objective of such testing is to aid in validating the methodologies used in the development and tuning of automatic flight control systems

Notes:

Vendor supplied data

Publisher Number:

2003-01-3587

Access Restriction:

Restricted for use by site license