Sensors of a Beechcraft C90 Aircraft for Extension of Data Acquisition System

Abstract

In-flight data acquisition is a key point in the aircraft design process. For the control of a simulated prototype using the control surfaces, state variables such as acceleration, pitch rate for longitudinal motion, and roll rate or slideslip angle for lateral-directional motion are commonly defined as control variables. The purpose of this paper is to evaluate the risk of in -flight laboratory modification through extension of data acquisition system for collection of additional data related to pilot command input and the reaction of the system.

Keywords

• ARINC 429
• Data Acquisition
• α angle
• β angle