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Author:   Steffen Haakon Schrader
Publisher:   Springer Fachmedien Wiesbaden
Imprint:   Springer Vieweg
Edition:   1st ed. 2023
Weight:   0.571kg
ISBN:  

9783662632178

ISBN 10:   3662632179
Pages:   266
Publication Date:   07 March 2023
Audience:   Professional and scholarly ,  Professional & Vocational
Format:   Paperback
Publisher's Status:   Active
Availability:   Manufactured on demand  
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Table of Contents

I.          Declaration                                                                                                    xxiiII.         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                                                                       49 4.4  Wing spar inspection                                                                                  51 4.5  Choice of relevant and investigated parameters                                       52 4.6  Flight envelope determination regarding masses and Centre of Gravity positions, limit of the tests and choice of the test points within the defined flight envelope                                                                               54 4.7  Legal basis for test flights                                                                           59 4.8  Flight trial procedures and conditions                                                        61 4.9  Conclusions                                                                                                64   5.     Spin description                                                                                             71 5.1  Introduction                                                                                                  71 5.2  Spin description on the basis of the measured flight test data                   72 5.3  Example of a spin entry                                                                               72 5.4  Example of a developed spin                                                                      81 5.4.1      Angle-of-Attack and Angle-of-Sideslip behaviour                            82 5.4.2      Acceleration behaviour around all three axes                                 85 5.4.3      Aeroplane’s attitude and turn rate behaviour (Φ with p, Θ with q, Ψ with r)                                                                             91 5.5  Example of a spin recovery                                                                         98 5.6  High frequency data fluctuation                                                                  99 5.7  Conclusion of the spin description                                                            101   6. Mathematical spin test data analysis                                                                   102        6.1 Introduction into the mathematical spin test data analysis             102        6.2 Evaluation and processing of the θ-Values                                                103        6.3 Pitch Angle data analysis                                                                            109        6.4 Observation 1: The second minimum value of the pitch down (ln_Theta)                         function always produces the highest negative value                      113 6.5 Observation 2: Independent of the aeroplane’s mass and CG position,                 the pitch angle (ln_Theta) approximates to a characteristic value   120        6.6 Observation 3: Maximum Yaw rate (ln_r) changes with CG position and                         mass                                                                                                  129        6.7 Observation 4: The yaw rate (ln_r) oscillation changes with CG                         position or mass                                                                                135        6.8 Observation 5: Maximum difference in angle of attack values between                         left and right wings lead to maximum in roll rates                         (alpha_le_c – alpha_ri_c; ln_p)                                                        147        6.9 Observation 6: Rate of roll (ln_p) changes with CG Position and                         aeroplane’s mass                                                                              154        6.10 Observation 7: Total Angular Velocity Ω changes with CG position           159        6.11 Observation 8: Recovery time becomes shorter with CG moving                         backwards                                                                                         165        6.12 Observation 9: The spin behaviour of the Fuji FA 200 – 160 can be                         generalised for single-engine low-wing aeroplanes                         167        6.13 Conclusion of the spin test data analysis                                                  173                6.13.1 Conclusion of the observations                                                      174   7. Flight test data comparison                                                                                  176 7.1 Introduction                                                                                           176        7.2 Comparison of Angle-of-Attack at Centre of Gravity                                  178        7.3 Comparison of Angle-of-Sideslip at Centre of Gravity                                179        7.4 Comparison of Pitch Rate                                                                           180        7.5 Comparison of Yaw Rate                                                                            182        7.6 Comparison of Roll Rate                                                                             182        7.7 Conclusion                                                                                                   187   8. Conclusion                                                                                                           188 8.1 Main conclusions, contributions and impact                                                189 8.1.1 Observation 1: The second minimum value of the pitch down (θ)                   function always produces the highest negative value                      189 8.1.2 Observation 2: Independent of the aeroplane’s mass and CG position,                   the pitch angle (θ) approximates to a characteristic value               190       8.1.3 Observation 3: Maximum Yaw rate (ln_r) changes with CG position                         and mass                                                                                           191       8.1.4 Observation 4: The yaw rate (ln_r) oscillation changes with CG                         position and mass                                                                             192       8.1.5 Observation 5: Maximum difference in angle of attack values                         between left and right wings leads to a maximum in roll rates                         (alpha_le_c – alpha_ri_c; ln_p)                                                        193       8.1.6 Observation 6: Rate of roll (ln_p) changes with CG Position and                         aeroplanes’s mass                                                                            194       8.1.7 Observation 7: Total Angular Velocity Ω changes with CG position                         and mass                                                                                           195       8.1.8 Observation 8: Recovery time becomes shorter with CG moving                         backwards                                                                                         196       8.1.9. Observation 9: The spin behaviour of the Fuji FA 200 – 160 can be                         generalised for single-engine low-wing aeroplanes                         197 8.2 Publications                                                                                                  198   9. Recommendations for further work                                                                      199   10. References and Bibliography                                                                             200        10.1 References                                                                                                200        10.2 Bibliography                                                                                               207

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Author Information

Steffen H. Schrader is Associate Professor for Flight Test and Polar Aviation at ‘The Arctic University of Norway’ in Tromsø, he teaches at the ‘Empire Test Pilots’ School’ (ETPS) in Boscombe Down (UK) and he is Leader of an Aerospace Technology Degree Programme at the Osnabrueck University of Applied Sciences in close collaboration with the University of the West of England (Bristol) where he completed his PhD. He studied Aerospace Technology at the Technical University of Braunschweig and the Coventry University (UK). He is Test Pilot according to EASA regulations since 2003, Airline Transport Pilot and Flying Instructor since more than 25 years.

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