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As spinning is involved in around 60% of all aircraft accidents, this aerodynamic phenomenon is still not fully understood.

This book contributes to a better understanding of the spin through investigating the spin regime for normal, utility and aerobatic aircraft, and to explain what happens to the aircraft in terms of the aerodynamics, flight mechanics and the aircraft stability.

The approach used is to vary the main geometric parameters such as the center of gravity position and the aeroplane's mass across the flight envelope, and to investigate the subsequent effect on the main spin characteristic parameters.

A conventional-geometry, single-engine low-wing aeroplane, has been instrumented with a proven digital flight measurement system and 27 spins have been systematically conducted inside and outside the certified flight envelope.

The data collected include left and right wing a and ß-angles, roll-pitch-yaw angles and corresponding rates, all control surface deflections, vertical speeds, altitude losses and the aeroplane's accelerations in all three directions. Such data have been statistically analysed and the pitch behaviour has been mathematically modelled.

These results can be used to improve flight test programmes, aircraft design processes, flight training materials and hence contribute strongly to better flight safety.



Autorentext

Steffen H. Schrader became flying instructor in 1991 and he was at that time the youngest flying instructor in Germany. Shortly after that he became Airline Transport Pilot and in 2003 he graduated as Test Pilot. As a Programme Leader of the academic course of studies 'Aircraft and Flight Engineering' at the Osnabrueck University of Applied Science he gathered a huge experience in teaching and research in the discipline of flight testing.



Klappentext

As spinning is still involved in around 60% of all aircraft accidents (BFU, 1985 and Belcastro, 2009), this aerodynamic phenomenon is still not fully understood. As U.S. and European Certification Specifications do not require recoveries from fully developed spins of Normal Category aeroplanes, certification test flights will not discover aeroplane mass and centre of gravity combinations which may result in unrecoverable spins.

This book aims to contribute to a better understanding of the spin phenomenon through investigating the spin regime for normal, utility and aerobatic aircraft, and to explain what happens to the aircraft in terms of the aerodynamics, flight mechanics and the aircraft stability. The approach used is to vary the main geometric parameters such as the centre of gravity position and the aeroplane's mass across the flight envelope, and to investigate the subsequent effect on the main spin characteristic parameters such as the angle of attack, pitch angle, sideslip angle, rotational rates, and recovery time.
First of all, a literature review sums up the range of technical aspects that affect the problem of spinning. It reviews the experimental measurement techniques used, theoretical methods developed and flight test results obtained by previous researchers. The published results have been studied to extract the effect on spinning of aircraft geometry, control surface effectiveness, flight operational parameters and atmospheric effects. Consideration is also made of the influence on human performance of spinning, the current spin regulations and the available training material for pilots.
A conventional-geometry, single-engine low-wing aeroplane, the basic trainer Fuji FA-200-160, has been instrumented with a proven digital flight measurement system and 27 spins have been systematically conducted inside and outside the certified flight envelope. The accuracy of the flight measurements is ensured through effective calibration, and the choice of sensors has varied through the study, with earlier sensors suffering from more drift than the current sensors (Belcastro, 2009 and Schrader, 2013).
In-flight parameter data collected includes left and right wing a and ß-angles, roll-pitch-yaw angles and corresponding rates, all control surface deflections, vertical speeds, altitude losses and the aeroplane's accelerations in all three directions.
Such data have been statistically analysed. The pitch behaviour has been mathematically modelled on the basis of the gathered flight test data.
Nine observations have been proposed. These mainly cover the effects of centre of gravity and aircraft mass variations on spin characteristic behaviour. They have all been proven as true through the results of this thesis. The final observation concerns the generalisation of the Fuji results, to the spin behaviour of other aircraft in the same category.
These observations can be used to improve flight test programmes, aircraft design processes, flight training materials and hence contribute strongly to better flight safety.



Inhalt

I. Declaration xxii

II. Abstract xxiii

III. Acknowledgements xxv

1. Introduction

1.1 The problem with spinning 1

1.2 Scope of the research 5

1.3 Reasoning for the research and its relevance 5

1.4 Aim of the study 6

1.5 Research questions and subsequent observations 7

1.6 Preparation for the Flight Testing 8

1.7 Structure of the Thesis 8

1.8 Contribution to state of the art / research 11

2. Literature review 13

2.1 Introduction into the literature review 13

2.2 Civil and military spin training material 14

2.3 The phases of a spin 15

2.4 Measurement techniques for spinning 15

2.4.1 Experimental measurements 15

2.4.2 Theoretical models 18

2.4.2.1 Forces and moment models 18

2.4.2.2 Area models for spin safety 19

2.4.2.3 Computational programmes for modelling high

angle of attack cases 20

2.4.3 Flight Tests 20

2.4.3.1 Low wing aircraft 21

2.4.3.2 High wing aircraft 23

2.5 Effect of Aeroplane shape on spin behaviour 24

2.5.1 Wing leading edge changes 24

2.5.2 Control surface effectiveness 24

2.5.3 Tail effects 25

2.6 Spin parameters 25

2.7 Spin Accident statistics / Safety 27

2.8 Spin related regulations 28

2.9 Sources of human factors during spinning 29

2.10 Conclusions of the literature review 30

3. Measurement system for spin test data acquisition 31

3.1 Introduction 31

3.2 System Requirements 31

3.2.1 What needs to be measured? 31

3.2.2 What precision is needed for the parameters of interest? 32

3.2.3 What ranges are needed for the parameters of interest? 33

3.2.4 What resolution is needed for the parameters of interest? 33

3.3 The Measurement System 34

3.4 Data acquisition 39

3.5 Installation of the measurement system in the research aeroplane 40

3.5.1 Installation of displacement sensor systems 41

3.5.2 Installation of the Inertial Measurement Unit (IMU) 41

3.5.3 Installation of the wing booms and wind vanes 42

3.5.4 Installation of the data acquisition computer, pressure

sensors and Uninterrupted Power Supply (UPS) 42

3.5.5 Wiring of the measurement system 42

3.6 Calibration and data validation of the sensor systems   44

3.6.1 IMU data calibration 44

3.6.2 Wind vane sensor calibration 44

3.6.3 Static pressure sensor calibration 46

3.6.4 Calibration of fuel gauges 47

3.7 Conclusions 48

4. Preparation of the aeroplane and the spin trials 49

4.1 Introduction 49

4.2 Modification and inspection of the utilized aeroplane 49

4.3 Suction system modification 4…

Titel
Flight Testing
Untertitel
Analysis of the Spin Dynamics of a Single-Engine Low-Wing Aeroplane
Autor
Steffen Haakon Schrader
EAN
9783662632185
Format
E-Book (pdf)
Hersteller
Springer Berlin Heidelberg
Genre
Luft- und Raumfahrttechnik
Veröffentlichung
06.03.2023
Digitaler Kopierschutz
Wasserzeichen
Dateigrösse
14.2 MB
Anzahl Seiten
266