Influence of flight control laws on structural sizing of commercial aircraft / Rahmetalla Nazzeri.

Format:

Book

Author/Creator:

Nazzeri, Rahmetalla, author.

Language:

English

Subjects (All):

Aircraft industry.

Physical Description:

1 online resource (181 pages)

Edition:

1st ed.

Place of Publication:

Göttingen : Cuvillier Verlag, [2021]

Summary:

The increasing demand for new civil aircraft pushes aircraft manufacturers to develop innovative solutions that lead in particular to mass reductions. One way to achieve these kinds of improvements is the use of multidisciplinary analysis and optimization. In this sense the intention of this PhD thesis is to develop a multidisciplinary framework in order to quantify the impact of load alleviation function parameter changes on structural components like the wing and fuselage in terms of resulting mass changes. The developed iterative process chain covers the loads calculation including an active load alleviation system, a structural assessment of the wing and fuselage components and a dedicated feedback loop in order to update mass and stiffness properties of the loads calculation model. The study shows that significant mass reductions are achievable while on the other hand estimated mass penalties are irrelevant.Die stetig wachsende Nachfrage an zivilen Verkehrsflugzeugen drängt Flugzeughersteller dazu, innovative Lösungen zu entwickeln. Diese Lösungen zielen speziell auf Kostenträger ab, wie z.B. eine Reduzierung der Flugzeuggesamtmasse. Ein Ansatz, um diese Art von Verbesserungen zu erreichen, ist die Nutzung von multidisziplinärer Analyse und Optimierung. In diesem Sinne besteht die Intention dieser Dissertation darin, eine multidisziplinäre Analyseumgebung zu entwickeln, um den Einfluss von Parametervariationen des Lastabminderungssystems auf Strukturkomponenten wie den Flügel und Rumpf mit Bezug auf resultierende Änderungen der Massen zu quantifizieren. Die hierbei entstehende iterative Prozesskette deckt Disziplinen ab, wie z.B. die Lastenberechnung samt Lastabminderungssystem sowie die strukturmechanische Auswertung der Flügel- sowie Rumpfkomponenten. Zudem ist eine Rückkopplung zur Berücksichtigung von Massen- und Steifigkeitsänderungen im Lastenberechnungsmodell implementiert. Die Studie zeigt, dass eine signifikante Reduzierung der Flügelmasse möglich ist, wobei die geschätzte Massenzunahme am Rumpf vernachlässigbar gering ist.

Contents:

Intro

List of Figures

List of Tables

List of symbols

1 Introduction

1.1 The need for a new simulation framework

1.2 State of the art

1.3 Objectives and thesis overview

2 Multidisciplinary analysis andoptimization framework

2.1 Developed process and mixture of competences

2.2 General process overview

3 Loads calculation process

3.1 Scope of computed load conditions

3.2 Loads calculation model

3.3 Electronic Flight Control System

4 Structural property optimization andmass penalty estimation

4.1 Modeling aspects of global FEM representation

4.2 Global FEM external loading

4.3 Linear static analysis and results management

4.4 Wing structural property optimization

4.5 Fuselage mass penalty estimation

5 Feedback loop

5.1 Starting approach

5.2 Main process steps of the feedback loop

5.3 Update of stiffness values - equivalent beamapproach

5.4 Update of mass values - grid point weight generator

5.5 Global convergence criteria

5.6 Impact of wing stiffness changes on the jig and flightshape

6 Design studies

6.1 Influence of the load alleviation function on thecalculated flight loads

6.2 First design study with reduced load case set

6.3 Design study with complete load case set

7 Summary, discussion of methods andresults, outlook

7.1 Summary

7.2 Discussion of methods

7.3 Discussion of results

7.4 Outlook

Bibliography

A Loads calculation and structuralassessment

B Feedback loop - main process steps

C Equivalent beam approach -validation

D Equivalent beam approach -influence of skin and stringer

E Grid Point Weight Generator - basics

F Influence of the load alleviationfunction on the calculated flightloads

G Structural baseline generation

H Influence of load alleviation functionon structural components.

Notes:

Includes bibliographical references.

Description based on print version record.

Other Format:

Print version: Nazzeri, Rahmetalla Influence of flight control laws on structural sizing of commercial aircraft

ISBN:

9783736965164

OCLC:

1285783061