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Session 2502

Section 2502

Dynamic Analysis of Aircraft Designs Using Archangel 98

Mr. Dushan B. Bilbija, Dr. Daniel J. Biezad California Polytechnic State University

Abstract

A user friendly software program called Archangel98 has been developed that provides rapid visual analysis of aircraft dynamics given aircraft stability derivatives and flight conditions. Its purpose is to provide a quick yet accurate look at the effects of design changes on the dynamics and handling qualities of aircraft. Using an intuitive "drag and drop" interface allows the user to look at aircraft data, root locus plots and a new graphical tool called Response Locus Maps. Re- sponse Locus Maps use traditional graphical residue computations and Eigenspace analysis to show the controllability of aircraft at a given operating point. Archangel98 also links to MAT- LAB for use of its resources in further design analysis. Archangel98 uses the latest software de- sign concepts allowing a very open design process, working with virtually all other applications.

Introduction

Archangel98 is the latest in a series of programs built around the idea of providing a rapid analy- sis tool for students to use in aircraft stability and control design. There are two versions devel- oped: a Student Edition as well as a Full Edition. The Student Edition does not have any of the more advanced tools such as Root Locus and Response Locus Maps, but is fully capable of ex- porting any analysis data to other programs for its reuse.

Arcgangel98 begins with the Standard Aircraft Data (SAD) file. The aircraft data can include non-dimensional or dimensional stability derivatives and flight condition parameters. The file is built around the aircraft input files from Appendix C of Airplane Flight Dynamics1. The input has been expanded to accommodate the Archangel98 equation engine. From here, the user has several tools to use in analysis.

Equation Engine

The equations of motion which comprise the Archangel98 engine are an expanded version of standard textbook equations, which allow the aircraft to have certain initial flight condition val- ues such as pitch rate and flight path angle. The object is to allow for the least restrictive steady state flight condition. The user can also select the equations of motion used by eliminating un- necessary force expansions. In addition, Archangel98 uses two modes of longitudinal system equations, which are assembled from two sets of perturbed axis and steady state axis rotations. The first rotation follows traditional assumptions and has a steady state Euler pitch angle equal to the body axis pitch angle. The second rotation has a steady state Euler angle equal to the flight

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Bilbija, D. B., & Biezad, D. J. (1998, June), Dynamic Analysis Of Aircraft Designs Using Archangel 98 Paper presented at 1998 Annual Conference, Seattle, Washington. 10.18260/1-2--7061