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Publisher: Emerald   (Total: 335 journals)

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Showing 1 - 200 of 335 Journals sorted alphabetically
A Life in the Day     Hybrid Journal   (Followers: 12)
Academia Revista Latinoamericana de Administraci√≥n     Open Access   (Followers: 2, SJR: 0.144, h-index: 4)
Accounting Auditing & Accountability J.     Hybrid Journal   (Followers: 31)
Accounting Research J.     Hybrid Journal   (Followers: 25, SJR: 0.26, h-index: 7)
Accounting, Auditing and Accountability J.     Hybrid Journal   (Followers: 21, SJR: 0.88, h-index: 40)
Advances in Accounting Education     Hybrid Journal   (Followers: 15, SJR: 0.514, h-index: 5)
Advances in Appreciative Inquiry     Hybrid Journal   (SJR: 0.124, h-index: 5)
Advances in Autism     Hybrid Journal   (Followers: 14)
Advances in Dual Diagnosis     Hybrid Journal   (Followers: 46, SJR: 0.228, h-index: 2)
Advances in Gender Research     Full-text available via subscription   (Followers: 3, SJR: 0.229, h-index: 7)
Advances in Intl. Marketing     Full-text available via subscription   (Followers: 5, SJR: 0.123, h-index: 11)
Advances in Mental Health and Intellectual Disabilities     Hybrid Journal   (Followers: 60, SJR: 0.29, h-index: 5)
Advances in Mental Health and Learning Disabilities     Hybrid Journal   (Followers: 29)
African J. of Economic and Management Studies     Hybrid Journal   (Followers: 10, SJR: 0.125, h-index: 2)
Agricultural Finance Review     Hybrid Journal  
Aircraft Engineering and Aerospace Technology     Hybrid Journal   (Followers: 194, SJR: 0.391, h-index: 18)
American J. of Business     Hybrid Journal   (Followers: 17)
Annals in Social Responsibility     Full-text available via subscription  
Anti-Corrosion Methods and Materials     Hybrid Journal   (Followers: 11, SJR: 0.215, h-index: 25)
Arts and the Market     Hybrid Journal   (Followers: 8)
Asia Pacific J. of Marketing and Logistics     Hybrid Journal   (Followers: 8, SJR: 0.244, h-index: 15)
Asia-Pacific J. of Business Administration     Hybrid Journal   (Followers: 5, SJR: 0.182, h-index: 7)
Asian Association of Open Universities J.     Open Access   (Followers: 1)
Asian Education and Development Studies     Hybrid Journal   (Followers: 5)
Asian J. on Quality     Hybrid Journal   (Followers: 3)
Asian Review of Accounting     Hybrid Journal   (Followers: 2, SJR: 0.29, h-index: 7)
Aslib J. of Information Management     Hybrid Journal   (Followers: 25, SJR: 0.65, h-index: 29)
Aslib Proceedings     Hybrid Journal   (Followers: 288)
Assembly Automation     Hybrid Journal   (Followers: 2, SJR: 0.657, h-index: 26)
Baltic J. of Management     Hybrid Journal   (Followers: 3, SJR: 0.354, h-index: 14)
Benchmarking : An Intl. J.     Hybrid Journal   (Followers: 10, SJR: 0.556, h-index: 38)
British Food J.     Hybrid Journal   (Followers: 16, SJR: 0.329, h-index: 35)
Built Environment Project and Asset Management     Hybrid Journal   (Followers: 14, SJR: 0.232, h-index: 4)
Business Process Re-engineering & Management J.     Hybrid Journal   (Followers: 8, SJR: 0.614, h-index: 42)
Business Strategy Series     Hybrid Journal   (Followers: 6, SJR: 0.201, h-index: 6)
Career Development Intl.     Hybrid Journal   (Followers: 17, SJR: 0.686, h-index: 32)
China Agricultural Economic Review     Hybrid Journal   (Followers: 2, SJR: 0.238, h-index: 10)
China Finance Review Intl.     Hybrid Journal   (Followers: 5)
Chinese Management Studies     Hybrid Journal   (Followers: 4, SJR: 0.216, h-index: 12)
Circuit World     Hybrid Journal   (Followers: 15, SJR: 0.346, h-index: 17)
Collection Building     Hybrid Journal   (Followers: 11, SJR: 0.829, h-index: 10)
COMPEL: The Intl. J. for Computation and Mathematics in Electrical and Electronic Engineering     Hybrid Journal   (Followers: 3, SJR: 0.269, h-index: 22)
Competitiveness Review : An Intl. Business J. incorporating J. of Global Competitiveness     Hybrid Journal   (Followers: 5)
Construction Innovation: Information, Process, Management     Hybrid Journal   (Followers: 14, SJR: 0.508, h-index: 8)
Corporate Communications An Intl. J.     Hybrid Journal   (Followers: 7, SJR: 0.703, h-index: 26)
Corporate Governance Intl. J. of Business in Society     Hybrid Journal   (Followers: 7, SJR: 0.309, h-index: 29)
Critical Perspectives on Intl. Business     Hybrid Journal   (SJR: 0.32, h-index: 15)
Cross Cultural & Strategic Management     Hybrid Journal   (Followers: 8, SJR: 0.356, h-index: 13)
Development and Learning in Organizations     Hybrid Journal   (Followers: 7, SJR: 0.138, h-index: 8)
Digital Library Perspectives     Hybrid Journal   (Followers: 23)
Direct Marketing An Intl. J.     Hybrid Journal   (Followers: 6)
Disaster Prevention and Management     Hybrid Journal   (Followers: 21, SJR: 0.533, h-index: 32)
Drugs and Alcohol Today     Hybrid Journal   (Followers: 129, SJR: 0.241, h-index: 4)
Education + Training     Hybrid Journal   (Followers: 22, SJR: 0.532, h-index: 30)
Education, Business and Society : Contemporary Middle Eastern Issues     Hybrid Journal   (Followers: 1, SJR: 0.141, h-index: 10)
Emerald Emerging Markets Case Studies     Hybrid Journal   (Followers: 1)
Employee Relations     Hybrid Journal   (Followers: 6, SJR: 0.435, h-index: 22)
Engineering Computations     Hybrid Journal   (Followers: 3, SJR: 0.387, h-index: 39)
Engineering, Construction and Architectural Management     Hybrid Journal   (Followers: 10, SJR: 0.541, h-index: 28)
Equal Opportunities Intl.     Hybrid Journal   (Followers: 3)
Equality, Diversity and Inclusion : An Intl. J.     Hybrid Journal   (Followers: 13, SJR: 0.239, h-index: 9)
EuroMed J. of Business     Hybrid Journal   (Followers: 1, SJR: 0.145, h-index: 9)
European Business Review     Hybrid Journal   (Followers: 8, SJR: 0.481, h-index: 21)
European J. of Innovation Management     Hybrid Journal   (Followers: 23, SJR: 0.596, h-index: 30)
European J. of Marketing     Hybrid Journal   (Followers: 21, SJR: 0.933, h-index: 55)
European J. of Training and Development     Hybrid Journal   (Followers: 9, SJR: 0.489, h-index: 23)
Evidence-based HRM     Hybrid Journal   (Followers: 5)
Facilities     Hybrid Journal   (Followers: 2, SJR: 0.371, h-index: 18)
Foresight     Hybrid Journal   (Followers: 7, SJR: 0.486, h-index: 20)
Gender in Management : An Intl. J.     Hybrid Journal   (Followers: 18, SJR: 0.359, h-index: 22)
Grey Systems : Theory and Application     Hybrid Journal   (Followers: 1)
Health Education     Hybrid Journal   (Followers: 2, SJR: 0.383, h-index: 17)
Higher Education, Skills and Work-based Learning     Hybrid Journal   (Followers: 45, SJR: 0.172, h-index: 4)
History of Education Review     Hybrid Journal   (Followers: 12, SJR: 0.141, h-index: 2)
Housing, Care and Support     Hybrid Journal   (Followers: 8, SJR: 0.174, h-index: 4)
Human Resource Management Intl. Digest     Hybrid Journal   (Followers: 17, SJR: 0.121, h-index: 6)
Humanomics     Hybrid Journal   (Followers: 2, SJR: 0.14, h-index: 4)
IMP J.     Hybrid Journal  
Indian Growth and Development Review     Hybrid Journal   (SJR: 0.163, h-index: 4)
Industrial and Commercial Training     Hybrid Journal   (Followers: 5, SJR: 0.217, h-index: 14)
Industrial Lubrication and Tribology     Hybrid Journal   (Followers: 5, SJR: 0.322, h-index: 19)
Industrial Management & Data Systems     Hybrid Journal   (Followers: 7, SJR: 0.63, h-index: 69)
Industrial Robot An Intl. J.     Hybrid Journal   (Followers: 2, SJR: 0.375, h-index: 32)
Info     Hybrid Journal   (Followers: 1, SJR: 0.25, h-index: 21)
Information and Computer Security     Hybrid Journal   (Followers: 22)
Information Technology & People     Hybrid Journal   (Followers: 43, SJR: 0.576, h-index: 28)
Interactive Technology and Smart Education     Hybrid Journal   (Followers: 11, SJR: 0.112, h-index: 1)
Interlending & Document Supply     Hybrid Journal   (Followers: 60, SJR: 0.48, h-index: 13)
Internet Research     Hybrid Journal   (Followers: 37, SJR: 1.746, h-index: 57)
Intl. J. for Lesson and Learning Studies     Hybrid Journal   (Followers: 4)
Intl. J. for Researcher Development     Hybrid Journal   (Followers: 9)
Intl. J. of Accounting and Information Management     Hybrid Journal   (Followers: 9, SJR: 0.304, h-index: 7)
Intl. J. of Bank Marketing     Hybrid Journal   (Followers: 8, SJR: 0.515, h-index: 38)
Intl. J. of Climate Change Strategies and Management     Hybrid Journal   (Followers: 14, SJR: 0.416, h-index: 7)
Intl. J. of Clothing Science and Technology     Hybrid Journal   (Followers: 7, SJR: 0.279, h-index: 25)
Intl. J. of Commerce and Management     Hybrid Journal   (Followers: 1)
Intl. J. of Conflict Management     Hybrid Journal   (Followers: 15, SJR: 0.763, h-index: 38)
Intl. J. of Contemporary Hospitality Management     Hybrid Journal   (Followers: 13, SJR: 1.329, h-index: 35)
Intl. J. of Culture Tourism and Hospitality Research     Hybrid Journal   (Followers: 18, SJR: 0.399, h-index: 5)
Intl. J. of Development Issues     Hybrid Journal   (Followers: 9)
Intl. J. of Disaster Resilience in the Built Environment     Hybrid Journal   (Followers: 6, SJR: 0.225, h-index: 7)
Intl. J. of Educational Management     Hybrid Journal   (Followers: 5, SJR: 0.424, h-index: 32)
Intl. J. of Emergency Services     Hybrid Journal   (Followers: 6, SJR: 0.179, h-index: 1)
Intl. J. of Emerging Markets     Hybrid Journal   (Followers: 3, SJR: 0.199, h-index: 5)
Intl. J. of Energy Sector Management     Hybrid Journal   (Followers: 2, SJR: 0.25, h-index: 12)
Intl. J. of Entrepreneurial Behaviour & Research     Hybrid Journal   (Followers: 4, SJR: 0.694, h-index: 28)
Intl. J. of Event and Festival Management     Hybrid Journal   (Followers: 5, SJR: 0.32, h-index: 8)
Intl. J. of Gender and Entrepreneurship     Hybrid Journal   (Followers: 6, SJR: 0.638, h-index: 6)
Intl. J. of Health Care Quality Assurance     Hybrid Journal   (Followers: 11, SJR: 0.352, h-index: 32)
Intl. J. of Health Governance     Hybrid Journal   (Followers: 26, SJR: 0.277, h-index: 15)
Intl. J. of Housing Markets and Analysis     Hybrid Journal   (Followers: 9, SJR: 0.201, h-index: 5)
Intl. J. of Human Rights in Healthcare     Hybrid Journal   (Followers: 6, SJR: 0.13, h-index: 2)
Intl. J. of Information and Learning Technology     Hybrid Journal   (Followers: 7)
Intl. J. of Innovation Science     Hybrid Journal   (Followers: 10, SJR: 0.173, h-index: 5)
Intl. J. of Intelligent Computing and Cybernetics     Hybrid Journal   (Followers: 3, SJR: 0.258, h-index: 10)
Intl. J. of Intelligent Unmanned Systems     Hybrid Journal   (Followers: 4, SJR: 0.145, h-index: 2)
Intl. J. of Islamic and Middle Eastern Finance and Management     Hybrid Journal   (Followers: 9)
Intl. J. of Law and Management     Hybrid Journal   (Followers: 2, SJR: 0.107, h-index: 2)
Intl. J. of Law in the Built Environment     Hybrid Journal   (Followers: 3, SJR: 0.111, h-index: 2)
Intl. J. of Leadership in Public Services     Hybrid Journal   (Followers: 19)
Intl. J. of Lean Six Sigma     Hybrid Journal   (Followers: 5, SJR: 0.562, h-index: 15)
Intl. J. of Logistics Management     Hybrid Journal   (Followers: 10, SJR: 0.998, h-index: 15)
Intl. J. of Managerial Finance     Hybrid Journal   (Followers: 5, SJR: 0.212, h-index: 11)
Intl. J. of Managing Projects in Business     Hybrid Journal   (Followers: 2)
Intl. J. of Manpower     Hybrid Journal   (Followers: 2, SJR: 0.354, h-index: 37)
Intl. J. of Mentoring and Coaching in Education     Hybrid Journal   (Followers: 24)
Intl. J. of Migration, Health and Social Care     Hybrid Journal   (Followers: 11, SJR: 0.261, h-index: 5)
Intl. J. of Numerical Methods for Heat & Fluid Flow     Hybrid Journal   (Followers: 11, SJR: 0.594, h-index: 32)
Intl. J. of Operations & Production Management     Hybrid Journal   (Followers: 18, SJR: 2.198, h-index: 94)
Intl. J. of Organizational Analysis     Hybrid Journal   (Followers: 3, SJR: 0.222, h-index: 11)
Intl. J. of Pervasive Computing and Communications     Hybrid Journal   (Followers: 3, SJR: 0.165, h-index: 9)
Intl. J. of Pharmaceutical and Healthcare Marketing     Hybrid Journal   (Followers: 4, SJR: 0.304, h-index: 12)
Intl. J. of Physical Distribution & Logistics Management     Hybrid Journal   (Followers: 11, SJR: 1.694, h-index: 66)
Intl. J. of Prisoner Health     Hybrid Journal   (Followers: 8, SJR: 0.254, h-index: 10)
Intl. J. of Productivity and Performance Management     Hybrid Journal   (Followers: 7, SJR: 0.785, h-index: 31)
Intl. J. of Public Sector Management     Hybrid Journal   (Followers: 24, SJR: 0.272, h-index: 37)
Intl. J. of Quality & Reliability Management     Hybrid Journal   (Followers: 7, SJR: 0.544, h-index: 63)
Intl. J. of Quality and Service Sciences     Hybrid Journal   (Followers: 2, SJR: 0.133, h-index: 1)
Intl. J. of Retail & Distribution Management     Hybrid Journal   (Followers: 6, SJR: 0.543, h-index: 36)
Intl. J. of Service Industry Management     Hybrid Journal   (Followers: 2)
Intl. J. of Social Economics     Hybrid Journal   (Followers: 5, SJR: 0.227, h-index: 25)
Intl. J. of Sociology and Social Policy     Hybrid Journal   (Followers: 48, SJR: 0.361, h-index: 5)
Intl. J. of Sports Marketing and Sponsorship     Hybrid Journal   (Followers: 1)
Intl. J. of Structural Integrity     Hybrid Journal   (Followers: 2, SJR: 0.325, h-index: 8)
Intl. J. of Sustainability in Higher Education     Hybrid Journal   (Followers: 13, SJR: 0.616, h-index: 29)
Intl. J. of Tourism Cities     Hybrid Journal   (Followers: 2)
Intl. J. of Web Information Systems     Hybrid Journal   (Followers: 4, SJR: 0.208, h-index: 13)
Intl. J. of Wine Business Research     Hybrid Journal   (Followers: 7, SJR: 0.196, h-index: 12)
Intl. J. of Workplace Health Management     Hybrid Journal   (Followers: 11, SJR: 0.358, h-index: 8)
Intl. Marketing Review     Hybrid Journal   (Followers: 16, SJR: 1.076, h-index: 57)
J. for Multicultural Education     Hybrid Journal   (Followers: 1, SJR: 0.124, h-index: 11)
J. of Accounting & Organizational Change     Hybrid Journal   (Followers: 5, SJR: 0.346, h-index: 7)
J. of Accounting in Emerging Economies     Hybrid Journal   (Followers: 8)
J. of Adult Protection, The     Hybrid Journal   (Followers: 15, SJR: 0.291, h-index: 7)
J. of Advances in Management Research     Hybrid Journal   (Followers: 2)
J. of Aggression, Conflict and Peace Research     Hybrid Journal   (Followers: 44, SJR: 0.177, h-index: 9)
J. of Agribusiness in Developing and Emerging Economies     Hybrid Journal  
J. of Applied Accounting Research     Hybrid Journal   (Followers: 16, SJR: 0.22, h-index: 5)
J. of Applied Research in Higher Education     Hybrid Journal   (Followers: 49)
J. of Asia Business Studies     Hybrid Journal   (Followers: 2, SJR: 0.115, h-index: 1)
J. of Assistive Technologies     Hybrid Journal   (Followers: 20, SJR: 0.215, h-index: 6)
J. of Business & Industrial Marketing     Hybrid Journal   (Followers: 8, SJR: 0.664, h-index: 48)
J. of Business Strategy     Hybrid Journal   (Followers: 11, SJR: 0.381, h-index: 17)
J. of Centrum Cathedra     Open Access  
J. of Children's Services     Hybrid Journal   (Followers: 5, SJR: 0.167, h-index: 9)
J. of Chinese Economic and Foreign Trade Studies     Hybrid Journal   (Followers: 1, SJR: 0.188, h-index: 4)
J. of Chinese Entrepreneurship     Hybrid Journal   (Followers: 4)
J. of Chinese Human Resource Management     Hybrid Journal   (Followers: 6, SJR: 0.112, h-index: 3)
J. of Communication Management     Hybrid Journal   (Followers: 6, SJR: 0.735, h-index: 6)
J. of Consumer Marketing     Hybrid Journal   (Followers: 18, SJR: 0.613, h-index: 62)
J. of Corporate Real Estate     Hybrid Journal   (Followers: 3, SJR: 0.633, h-index: 5)
J. of Criminal Psychology     Hybrid Journal   (Followers: 118, SJR: 0.13, h-index: 1)
J. of Criminological Research, Policy and Practice     Hybrid Journal   (Followers: 46)
J. of Cultural Heritage Management and Sustainable Development     Hybrid Journal   (Followers: 10, SJR: 0.109, h-index: 5)
J. of Documentation     Hybrid Journal   (Followers: 174, SJR: 0.936, h-index: 50)
J. of Economic and Administrative Sciences     Hybrid Journal   (Followers: 2)
J. of Economic Studies     Hybrid Journal   (Followers: 5, SJR: 0.498, h-index: 26)
J. of Educational Administration     Hybrid Journal   (Followers: 6, SJR: 0.848, h-index: 36)
J. of Engineering, Design and Technology     Hybrid Journal   (Followers: 16, SJR: 0.173, h-index: 10)
J. of Enterprise Information Management     Hybrid Journal   (Followers: 4, SJR: 0.433, h-index: 38)
J. of Enterprising Communities People and Places in the Global Economy     Hybrid Journal   (Followers: 1, SJR: 0.212, h-index: 8)
J. of Entrepreneurship and Public Policy     Hybrid Journal   (Followers: 8)
J. of European Industrial Training     Hybrid Journal   (Followers: 2)
J. of European Real Estate Research     Hybrid Journal   (Followers: 3, SJR: 0.52, h-index: 7)
J. of Facilities Management     Hybrid Journal   (Followers: 3)
J. of Family Business Management     Hybrid Journal   (Followers: 7)
J. of Fashion Marketing and Management     Hybrid Journal   (Followers: 12, SJR: 0.529, h-index: 30)
J. of Financial Crime     Hybrid Journal   (Followers: 373, SJR: 0.158, h-index: 5)
J. of Financial Economic Policy     Hybrid Journal   (Followers: 1)
J. of Financial Management of Property and Construction     Hybrid Journal   (Followers: 8, SJR: 0.234, h-index: 1)
J. of Financial Regulation and Compliance     Hybrid Journal   (Followers: 8)
J. of Financial Reporting and Accounting     Hybrid Journal   (Followers: 12)
J. of Forensic Practice     Hybrid Journal   (Followers: 54, SJR: 0.225, h-index: 8)
J. of Global Mobility     Hybrid Journal   (Followers: 2)
J. of Global Responsibility     Hybrid Journal   (Followers: 4)
J. of Health Organisation and Management     Hybrid Journal   (Followers: 21, SJR: 0.67, h-index: 27)
J. of Historical Research in Marketing     Hybrid Journal   (Followers: 4, SJR: 0.376, h-index: 8)
J. of Hospitality and Tourism Technology     Hybrid Journal   (Followers: 4, SJR: 0.672, h-index: 10)
J. of Human Resource Costing & Accounting     Hybrid Journal   (Followers: 4)
J. of Humanitarian Logistics and Supply Chain Management     Hybrid Journal   (Followers: 13)

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Journal Cover Aircraft Engineering and Aerospace Technology
  [SJR: 0.391]   [H-I: 18]   [194 followers]  Follow
    
   Hybrid Journal Hybrid journal (It can contain Open Access articles)
   ISSN (Print) 0002-2667 - ISSN (Online) 1748-8842
   Published by Emerald Homepage  [335 journals]
  • Design parameters improvement of helicopter ducted tail rotor
    • Pages: 237 - 245
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 237-245, March 2018.
      Purpose The purpose of this paper is to reduce the acoustic noise of helicopter ducted tail rotor. Design/methodology/approach To predict the noise accurately, a thin-body boundary element method (BEM)/Ffowcs Williams–Hawkings method is developed in this paper. It is a hybrid method combining the BEM with computational aeroacoustics and can be used efficiently to predict the propagation of sound wave in the duct. Findings Compared with the experimental results, the proposed method of acoustic noise is rather desirable. Practical implications Then several geometry parameters are modified to investigate the noise reduction of ducted tail rotor by using the numerical prediction method. Originality/value The aerodynamic and acoustic performance of different modification tasks is discussed. These results demonstrate the validity of design parameters modification of ducted tail rotor in acoustic noise reduction.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:05Z
      DOI: 10.1108/AEAT-01-2017-0033
       
  • Indian and Chinese aviation industry: the EASA framework option
    • Pages: 246 - 250
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 246-250, March 2018.
      Purpose This viewpoint aims to increase the awareness on the demand faced by the technical sector of the Indian and Chinese aviation industry and how this can be met by the adoption of the European Aviation Safety Agency (EASA) regulatory framework. Design/methodology/approach A brief overview of the challenges that the Indian and the Chinese aviation industry is facing is provided, in terms of meeting the demand for sustainable growth. A description of the structure of the EASA framework and its main characteristics is presented, along with a focussed discussion on the framework’s applicability to the Indian and the Chinese aviation maintenance and broader continuing airworthiness sector. Findings The EASA regulatory framework can offer a safe and business-effective solution for the Indian and the Chinese aviation industry, aligning with world’s best practice. Practical implications A discussion in adopting the EASA framework in India and China can be helpful in increasing awareness and assisting decision makers realise that this is a possible option. Originality/value This viewpoint can be useful in provoking discussion, by summarising the key issues and points surrounding aviation regulation standardisation in India and China, along the lines of the EASA framework. Moreover, some possible ways to increase awareness around EASA in India and China are discussed from the point of view of influencing tomorrow’s decision makers.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:43Z
      DOI: 10.1108/AEAT-03-2017-0083
       
  • Optimising the multiplicative AF model parameters for AA7075 cyclic
           plasticity and fatigue simulation
    • Pages: 251 - 260
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 251-260, March 2018.
      Purpose This study presents the improvements of the multicomponent Armstrong–Frederick model with multiplier (MAFM) performance through a numerical optimisation methodology available in a commercial software. Moreover, this study explores the application of a multiobjective optimisation technique for the determination of the parameters of the constitutive models using uniaxial experimental data gathered from aluminium alloy 7075-T6 specimens. This approach aims to improve the overall accuracy of stress–strain response, for not only symmetric strain-controlled loading but also asymmetrically strain- and stress-controlled loading. Design/methodology/approach Experimental data from stress- and strain-controlled symmetric and asymmetric cyclic loadings have been used for this purpose. The analysis of the influence of the parameters on simulation accuracy has led to an adjustment scheme that can be used for focused optimisation of the MAFM model performance. The method was successfully used to provide a better understanding of the influence of each model parameter on the overall simulation accuracy. Findings The optimisation identified an important issue associated with competing ratcheting and mean stress relaxation objectives, highlighting the issues with arriving at a parameter set that can simulate ratcheting and mean stress relaxation for load cases not reaching at complete relaxation. Practical implications The study uses a strain-life fatigue application to demonstrate the importance of incorporating a technique such as the presented multiobjective optimisation method to arrive at robust parameters capable of accurately simulating a variety of transient cyclic phenomena. Originality/value The proposed methodology improves the accuracy of cyclic plasticity phenomena and strain-life fatigue simulations for engineering applications. This study is considered a valuable contribution for the engineering community, as it can act as starting point for further exploration of the benefits that can be obtained through material parameter optimisation methodologies for models of the MAFM class.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:45Z
      DOI: 10.1108/AEAT-05-2017-0119
       
  • System identification-based aeroelastic modelling for wing flutter
    • Pages: 261 - 269
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 261-269, March 2018.
      Purpose Ground vibration testing (GVT) results can be used as system parameters for predicting flutter, which is essential for aeroelastic clearance. This paper aims to compute GVT-based flutter in time domain, using unsteady air loads by matrix polynomial approximations. Design/methodology/approach The experimental parameters, namely, frequencies and mode shapes are interpolated to build an equivalent finite element model. The unsteady aerodynamic forces extracted from MSC NASTRAN are approximated using matrix polynomial approximations. The system matrices are condensed to the required shaker location points to build an aeroelastic reduced order state space model in SIMULINK. Findings The computed aerodynamic forces are successfully reduced to few input locations (optimal) for flutter simulation on unknown structural system (where stiffness and mass are not known) through a case study. It is demonstrated that GVT data and the computed unsteady aerodynamic forces of a system are adequate to represent its aeroelastic behaviour. Practical implications Airforce of every nation continuously upgrades its fleet with advanced weapon systems (stores), which demands aeroelastic flutter clearance. As the original equipment manufacturers does not provide the design data (stiffness and mass) to its customers, a new methodology to build an aeroelastic system of unknown aircraft is devised. Originality/value A hybrid approach is proposed, involving GVT data to build an aeroelastic state space system, using rationally approximated air loads (matrix polynomial approximations) computed on a virtual FE model for ground flutter simulation.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:26Z
      DOI: 10.1108/AEAT-08-2016-0122
       
  • Evaluation of ozone risk under different air-supply mode in aircraft
           cabins
    • Pages: 270 - 279
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 270-279, March 2018.
      Purpose The purpose of this paper is to evaluate the ozone risk introduced by the mixing air-supply mode, displacement air-supply mode and personalized air-supply mode, respectively, in commercial aircraft cabins. Design/methodology/approach In this study, a computational fluid dynamics (CFD) model of aircraft cabin has been built to study the distribution of ozone mass fraction and the ozone surface deposition rate on passenger’s face and clothes under the three different air-supply modes, respectively. The distribution of ozone mass fraction has been obtained by calculating the mass concentration of ozone in different location. The ozone surface deposition rate on passenger’s face and clothes has been calculated according to the mechanism of the reactions between ozone and squalene, which is the primary reactant in human sebum. Findings By comparing the three air-supply modes, it was considered that the mixing air-supply mode made lower ozone concentration and ozone surface deposition risk in most area, but this was because of the thin air distribution in cabin. The displacement air-supply mode made an uneven distribution of ozone concentration and increased absorbing ozone risk in the breathing zone. The personalized air-supply mode was proper for avoiding ozone harm and making a comfortable air environment. The air supply from the inlet on seat back could not increase the ozone surface deposition risk on passenger’s face. Originality/value This paper provides the qualitative and quantitative analysis for ozone risk to the passengers under the different air-supply modes. Findings can provide some suggestions for the designers to optimize the air-supply mode of air distribution system for reducing passengers’ discomfort caused by high-altitude ozone introduction, such as breathing in too much ozone.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:37:51Z
      DOI: 10.1108/AEAT-07-2016-0106
       
  • Overview of thermal arcjet thruster development
    • Pages: 280 - 301
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 280-301, March 2018.
      Purpose This paper aims to provide an overview of current and historical arcjet development. The reviewed arcjets are considered with respect to both design and thruster relevant parameters. Correspondingly, the paper enables the identification of adequate design criteria and of the probable thruster parameters. Design/methodology/approach The approach consists of a database for thruster relevant parameters in conjunction with relevant operational requirements (such as type of propellant) and specific design criteria (such as e.g. propellant injection systems). Findings The synopsis of both operational parameter and respectively assigned design allows for the derivation of development approaches for arcjets under given high level requirements such as power regime. Research limitations/implications The paper is a general review. However, its strength is in the synthesis of the arcjet classification, the functional evidence of design criteria and the application scenario. Practical implications Not only basic but also specific design criteria are analyzed and evaluated leading to a recommendation feature of the paper with respect to the overall design of adequate arcjets. Social implications Within the scope of the Clean Space initiative, new applications and scenarios from the operation of arcjets arise enabling EOL phases of spacecraft that fulfill respective levels of debris mitigation and, in addition, the requirements concerning the adequately adapted re-entry of spacecrafts that are at end of life. Originality/value The paper is a general review. However, its strength is in the synthesis of the arcjet classification, the functional evidence of design criteria and the application scenario.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:32Z
      DOI: 10.1108/AEAT-08-2016-0124
       
  • Parameter estimation of UAV from flight data using neural network
    • Pages: 302 - 311
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 302-311, March 2018.
      Purpose The purpose of this paper is to present the application of the neural-based estimation method, Neural-Gauss-Newton (NGN), using the real flight data of a small unmanned aerial vehicle (UAV). Design/methodology/approach The UAVs in general are lighter in weight and their flight is usually influenced by the atmospheric winds because of their relatively lower cruise speeds. During the presence of the atmospheric winds, the aerodynamic forces and moments get modified significantly and the accurate mathematical modelling of the same is highly challenging. This modelling inaccuracy during parameter estimation is routinely treated as the process noise. Furthermore, because of the limited dimensions of the small UAVs, the measurements are usually influenced by the disturbances caused by other subsystems. To handle these measurement and process noises, the estimation methods based on neural networks have been found reliable in the manned aircrafts. Findings Six sets of compatible longitudinal flight data of the designed UAV have been chosen to estimate the parameters using the NGN method. The consistency in the estimates is verified from the obtained mean and the standard deviation and the same has been validated by the proof-of-match exercise. It is evident from the results that the NGN method was able to perform on a par with the conventional maximum likelihood method. Originality/value This is a partial outcome of the research carried out in estimating parameters from the UAVs.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:36Z
      DOI: 10.1108/AEAT-03-2016-0050
       
  • Bayesian filtering based on solving the Fokker-Planck equation
    • Pages: 312 - 319
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 312-319, March 2018.
      Purpose This paper aims to propose Bayesian filtering based on solving the Fokker–Planck equation, to improve the accuracy of filtering in non-Gauss case. Nonlinear filtering plays an important role in many science and engineering fields for estimating the state of dynamic system, but the existing filtering algorithms are mainly used for solving the problem of Gauss system. Design/methodology/approach Under the Bayesian framework, the time update of this filtering is based on solving Fokker–Planck equation, while the measurement update uses the Bayes formula directly. Therefore, this novel algorithm can be applied to nonlinear, non-Gaussian estimation. To reduce the computational complexity due to standard meshing, an adaptive meshing algorithm proposed which includes the coarse meshing, significant domain determination that is generated using extended Kalman filtering and Chebyshev’s inequality theorem, and value assignment for significant domain. Simulations are conducted on a reentry body tracking problem to demonstrate the effectiveness of this novel algorithm. Findings In this way, finer grid points can be placed in the regions with high conditional probability density, while the grid points with low conditional probability density can be neglected. The simulation results indicate that the novel algorithm can reduce the computational burden significantly compared to the standard meshing, while achieving similar accuracy. Practical implications A novel Bayesian filtering based on solving the Fokker–Planck equation using adaptive meshing is proposed, and the simulations show that algorithm can reduce the computational burden significantly compared to the standard meshing, while achieving similar accuracy. Originality/value A novel nonlinear filtering based on solving the Fokker–Planck equation is proposed. The novel algorithm is suitable for non-Gauss system, and can achieve similar accuracy compared to the standard meshing with the significant reduction of computational burden.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:37:53Z
      DOI: 10.1108/AEAT-09-2016-0161
       
  • Application of reverse processing in SINS initial alignment and SINS/GPS
           integrated navigation
    • Pages: 320 - 327
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 320-327, March 2018.
      Purpose The study aims to propose reverse processing solution to improve the performance of strapdown inertial navigation system (SINS) initial alignment and SINS-/global positioning system- (GPS) integrated navigation. The proposed scheme can be well applied in the fields of aircraft and aerospace navigation. Design/methodology/approach For the SINS alignment phase, a fast initial alignment scheme is proposed: the initial value of reverse filter is determined by the final result of forward filter, and then, the reverse filter is carried out using the stored data. Multiple iterations are performed until the accuracy is satisfied. For the SINS-/GPS-integrated phase, a forward–reverse navigation algorithm is proposed: first, the standard forward filter is used, and then, the reverse filter is carried out using the initial value determined by the forward filter, and the final fusion results are achieved by the weighted smoothing of the forward and reverse filtering results. Findings The simulation and the actual test results show that in the initial alignment stage, the proposed reverse processing method can obviously shorten the SINS alignment time and improve the alignment accuracy. In the SINS-/GPS-integrated navigation data fusion stage, the proposed forward–reverse data fusion processing can, obviously, improve the performance of the navigation solution. Practical implications The proposed reverse processing technology has an important application in improving the accuracy of navigation and evaluating the performance of real-time navigation. The proposed scheme can be not only used for SINS-/GPS-integrated system but also applied to other integrated systems for general aviation aircraft. Originality/value Compared with the common forward filtering algorithm, the proposed reverse scheme can not only shorten alignment time and improve alignment accuracy but also improve the performance of the integrated navigation.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:30Z
      DOI: 10.1108/AEAT-11-2016-0191
       
  • An optimization approach for DAL assignments
    • Pages: 328 - 335
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 328-335, March 2018.
      Purpose Development assurance level (DAL) is the measurement of the rigor of development assurance tasks performed to functions or items. The DAL assignment is an important process of aircraft system development that can make the reliability and safety of the system stay at acceptable levels. This paper aims to propose an optimization approach for the DAL assignments to minimize the development cost of aircraft systems. Design/methodology/approach The mathematical model for the DAL assignment optimization has been developed on the basis of the given expressions of objective function and constraints. In addition, a hybrid algorithm model synthesizing the advantages of genetic algorithm (GA) and Tabu search (TS) has been proposed to solve the optimization problem of the DAL assignment. Findings The results of the case study show that the proposed hybrid algorithm is more efficient and effective than the exhaustive method as well as the pure GA. Practical implications The proposed approach can be applied in the development of aircraft systems, and it has great significance in minimizing the development cost as well as keeping the system reliability and safety at an acceptable level. Originality/value The constrained optimization method has been applied in the DAL assignments, the corresponding mathematical model has been built and a hybrid evolutionary algorithm has been proposed to solve the optimization problem.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:14Z
      DOI: 10.1108/AEAT-10-2016-0167
       
  • Coatings characterization of Ni-based alloy applied by HVOF
    • Pages: 336 - 343
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 336-343, March 2018.
      Purpose The thermal spraying technique of High-Velocity Oxygen Fuel (HVOF) coating was used to deposit coatings of an alloy composed of Ni-based substrates on stainless steel AISI 304. The aim of this study was to determine the mechanical properties such as hardness and bond strength that these coatings have when the spray distance is varied, as well as the microstructure and phases formed during the thermal spray process. Design/methodology/approach The coatings were applied by HVOF and characterized by scanning electron microscopy, image analysis, X-ray diffraction, microhardness and bond strength to analyze the mechanical properties. Findings The microstructure of the coatings showed low porosity, oxide content and interface contamination in the substrate–coating interface, without the presence of unmolten particles. The microhardness values reached 600 HV for the three spray distances used and the bond strength values reached over 55 MPa. Practical implications The use of coatings on aircraft components is growing dramatically owing to the high costs of advanced materials and the growing lifecycle requirements for high-performance systems, which are taken into account because of the variety of coatings and complexity of environmental factors. Originality/value The originality of this study lies in the development of new coating materials for the manufacture and protection of various turbine components. The value is based on the development of materials and processes to be used to manufacture them.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:03Z
      DOI: 10.1108/AEAT-09-2016-0146
       
  • Exergy indicators of a low-emission aero-engine combustor
    • Pages: 344 - 350
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 344-350, March 2018.
      Purpose It is essential to develop more environment-friendly energy systems to prevent climate change and minimize environmental impact. Within this scope, many studies are performed on performance and environmental assessments of many types of energy systems. This paper, different from previous studies, aims to prove exergy performance of a low-emission combustor of an aero-engine. Design/methodology/approach It is a well-known fact that, with respect to previous exergy analysis, highest exergy destruction occurs in the combustor component of the engine. For this reason, it is required to evaluate a low-emission aero-engine combustor thermodynamically to understand the state of the art according to the authors’ best of knowledge. In this framework, combustor has been operated at numerous conditions (variable engine load) and evaluated. Findings As a conclusion of the study, the impact of emission reduction on performance improvement of the aero-engine combustors exergetically is presented. It is stated that exergy efficiency of the low-emission aero-engine combustor is found to be 64.69, 61.95 and 71.97 per cent under various operating conditions. Practical implications Results obtained in this paper may be beneficial for researchers who are interested in combustion and propulsion technology and thermal sciences. Originality/value Different from former studies, the impact of operating conditions on performance of a combustor is examined from the viewpoint of thermodynamics.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:37:45Z
      DOI: 10.1108/AEAT-03-2016-0045
       
  • Simulation-based dynamic model and speed controller design of a
           small-scale turbojet engine
    • Pages: 351 - 358
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 351-358, March 2018.
      Purpose This paper aims to present a nonlinear mathematical model of a small-scale turbojet aeroengine and also a speed controller design that is conducted for the constructed nonlinear mathematical model. Design/methodology/approach In the nonlinear mathematical model of the turbojet engine, temperature, rotational speed, mass flow, pressure and other parameters are generated using thermodynamic equations (e.g. mass, energy and momentum conservation laws) and some algebraic equations. In calculation of the performance parameters, adaptive neuro fuzzy inference system (ANFIS) method is preferred in related components. All calculated values from the mathematical model are then compared with the cycle data of the turbojet engine. Because of the single variable control need and effect of noise factor, modified proportional–integral–derivative (PID) controller is treated for speed control. For whole operation envelope, various PID structures are designed individually, according to the operating points. These controller structures are then combined via gain-scheduling approach and integrated to the nonlinear engine model. Simulations are performed on MATLAB/Simulink environment for design and off-design operating points between idle to maximum thrust levels. Findings The cascade structure (proposed nonlinear engine aero-thermal model and speed controller) is simulated and tested at various operating points of the engine and for different transient conditions. Simulation results show that the transitions between the operating points are found successfully. Furthermore, the controller is effective for steady-state load changes. It is suggested to be used in real-time engine applications. Research limitations/implications Because of limited data, only speed control is treated and simulated. Practical implications It can be used as an application in the industry easily. Originality/value First point of novelty in the paper is in calculation of the performance parameters of compressor and turbine components. ANFIS method is preferred to predict performance parameters in related components. Second novelty in the paper can be seen in speed controller design part. Because of the single variable control need and effect of noise factor, modified PID is treated.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:39Z
      DOI: 10.1108/AEAT-09-2016-0150
       
  • Comparative analysis of numerical methods for the determination of contact
           pattern of spiral bevel gears
    • Pages: 359 - 367
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 359-367, March 2018.
      Purpose This paper aims to present a comparison of numerical methods for determining the contact pattern of Gleason-type bevel gears. The mathematical model of tooth contact analysis and the finite element method were taken into consideration. Conclusions have been drawn regarding the usefulness of the considered methods and the compatibility of results. The object of the analysis was a bevel gear characterised by an 18:43 gear ratio and arc tooth line, and manufactured according to the spiral generated modified-roll method. Design/methodology/approach The mathematical model of tooth contact analysis consists of both the mathematical model of tooth generating and the mathematical model of operating gear set. The first model is used to generate tooth flanks of the pinion and the ring gear in the form of grids of points. Then, such tooth surfaces are used for the tooth contact analysis performed with the other model. It corresponds to the no-load gear meshing condition. The finite element method model was built on the basis of the same tooth flanks obtained with the former model. The commercial finite element method software Abaqus was used to perform two instances of the contact analysis: a very light load, corresponding to the former no-load condition, and the operating load condition. The results obtained using the two models, in the form of the contact pattern for no-load condition, were compared. The effect of heavy load on contact pattern position, shape and size was shown and discussed. Findings The mathematical models correctly reproduce the shape, position and size of the contact pattern; thus, they can be reliably used to assess the quality of the bevel gear at the early stage of its design. Practical implications Determination of the correct geometry of the flank surfaces of the gear and pinion teeth through the observation of contact pattern is a fundamental step in designing of a new aircraft bevel gear. Originality/value A possibility of the independent use of the mathematical analysis of the contact pattern has been shown, which, thanks to the compatibility of the results, does not have to be verified experimentally.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:37:40Z
      DOI: 10.1108/AEAT-08-2016-0133
       
  • An alternative neural airspeed computation method for aircrafts
    • Pages: 368 - 378
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 368-378, March 2018.
      Purpose This paper aims to present an alternative airspeed computation method based on artificial neural networks (ANN) without requiring pitot-static system measurements. Design/methodology/approach The data set used to train proposed neural model is obtained from the Digital Flight Data Acquisition Unit records of a Boeing 737 type commercial aircraft for real flight routes. The proposed method uses the flight parameters as inputs of the ANN. The Levenberg–Marquardt training algorithm was used to train the neural model. Findings The predicted airspeed values obtained with ANN are in good agreement with the measured airspeed values. The proposed neural model can be used as an alternative airspeed computation method. Practical implications The proposed alternative airspeed computation method can be used when the air data computer or pitot-static system has failed. Originality/value The proposed method uses flight parameters as inputs for the ANN. As such, airspeed is calculated using flight parameters instead of the pitot-static system measurements.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:37:32Z
      DOI: 10.1108/AEAT-10-2015-0228
       
  • Swarm system for CubeSats
    • Pages: 379 - 389
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 379-389, March 2018.
      Purpose This paper aims to present an innovative system able to establish an inter-satellite communication crosslink and to determine the mutual physical positioning for CubeSats belonging to a swarm. Design/methodology/approach Through a system involving a smart antenna array managed by a beamforming control strategy, every CubeSat of the swarm can measure the direction of arrival (DOA) and the distance (range) to estimate the physical position of the received signal. Moreover, during the transmission phase, the smart antenna shapes the beam to establish a reliable and directive communication link with the other spacecraft and/or with the ground station. Furthermore, the authors introduce a deployable structure fully developed at Politecnico di Torino that is able to increase the external surface of CubeSats: this surface allows to gain the interspace between elements of the smart antenna. Findings As a consequence, the communication crosslink, the directivity and the detection performance of the DOA system in terms of directivity and accuracy are improved. Practical implications Moreover, the deployable structure offers a greater usable surface, so a larger number of solar panels can be used. This guarantees up to 25 W of average power supply for the on-board systems and for transmission on a one-unit (1U) CubeSat (10 × 10 × 10 cm). Originality/value This paper describes the physical implementation of the antenna array system on a 1U CubeSat by using the deployable structure developed. Depending on actuators and ability that every CubeSat disposes, various interaction levels between elements can be achieved, thus making the CubeSat constellation an efficient and valid solution for space missions.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:34Z
      DOI: 10.1108/AEAT-07-2016-0119
       
  • Aerodynamic performance of flying discs
    • Pages: 390 - 397
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 390-397, March 2018.
      Purpose The purpose of this paper is to examine geometrical design influence of various types of flying discs on their flight performance from the aerodynamics perspective. Design/methodology/approach The lift, drag and moment coefficients of the discs were measured experimentally using a wind tunnel. Three types of golf discs and four sets of simpler parametric discs were studied to analyze and isolate the effect of design factors on these aerodynamic characteristics. Full six degree-of-freedom simulations of the discs were performed to visualize their flight trajectories and attitudes. These simulations, combined with the experimental data, provide details on the well-known “S-shaped” ground-path traced by a flying disc. Findings This paper reveals two key parameters to evaluate the flight performance of a disc: its coefficient of lift-to-drag ratio (CL/CD) and, more importantly, its coefficient of pitching moment (CM). The latter influences the tendency of the disc to yaw from its intended path, and the former influences its throwing distance. Practical implications The work suggests that to optimize the flight performance of a disc, the magnitudes and gradient of its CM should be minimized and its trim-point shifted from origin, while its CL/CD should be maximized with a flatter peak. Originality/value In this paper, the design parameters and the aerodynamic characteristics of various types of flying discs are analysed, compared and discussed in depth. Recommendations of design improvements to enhance the performance of any flying disc are offered as well.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:00Z
      DOI: 10.1108/AEAT-09-2016-0143
       
  • Stability analysis of aircraft’s sudden damage process with ROA
           overlapping
    • Pages: 398 - 411
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 398-411, March 2018.
      Purpose The paper aims to propose a stability analysis method based on region-of-attraction (ROA) overlapping to evaluate the flight stability of the possible sudden damage process and guarantee flight safety in extreme cases. Design/methodology/approach First, according to the two flight conditions before and after damage which the aircraft may encounter, flight dynamical models are built and fitted by polynomial equation for subsequent ROA analysis. And then, the ROA overlapping estimation method based on V-s iteration is presented to complete the stability analysis of such airplane sudden damage process. Findings Finally, in the presence of control surface damage, case aircraft flight stability is analyzed and simulated to verify the effectiveness of the proposed method. Practical implications The proposed method can be used for stability check during the aircraft control law design, or for further completing the design of the emergency stable controller design. Originality/value Compared with previous studies on sudden damage process of aircraft, to the best of the authors’ knowledge, this is one of the pioneer studies in which the ROA and ROA overlapping concept has been introduced. This study on stability analysis of aircraft sudden damage process could further develop the theory of emergency stable control.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:21Z
      DOI: 10.1108/AEAT-08-2016-0127
       
  • Bevel gears tooth contact pattern verification
    • Pages: 412 - 417
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 412-417, March 2018.
      Purpose This paper aims to create an application to support spiral bevel gear contact pattern verification in the computer aided design (CAD) system to speed up the selection of technological setups for the cutting machine by finding these in the virtual environment at the design level. Design/methodology/approach This paper presents an application which has been created to simulate a pattern check on spiral bevel gears in the virtual environment. The pattern check is conducted on the CAD models obtained from the cutting simulation in the CAD system using technological settings calculated by the KONTEPS system. Check of the contact pattern in the virtual environment works in the same way as in the real production process. The application has been written in C# programming language and run in the NX open environment in the UG NX. Findings This paper shows the possibilities of how the CAD system can be used at the design level of spiral bevel gears to verify an unloaded tooth contact pattern position for applied technological setups for dedicated cutting machine. Practical implications This paper describes an application that has the possibility to be implemented in small companies which produce small lots of gear sets and help to decrease the time for setting a cutting machine. Originality/value This paper addresses the needs to find new technologies to improve the design process of the spiral bevel gears.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:37:35Z
      DOI: 10.1108/AEAT-10-2016-0176
       
  • An approach to configuration management in the aero-engine overhaul
           process
    • Pages: 418 - 426
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 418-426, March 2018.
      Purpose The functionality and reliability of an overhauled aero-engine is determined by all configuration changes in the overhaul process. Identifying, recording, auditing, tracking and tracing of configuration modifications are significant and meaningful. Considering the barriers to these goals, this paper aims to put forward an approach to configuration management in the aero-engine overhaul process. Design/methodology/approach The overhaul configuration management model is proposed to describe an aero-engine’s configuration evolution trajectory in the overhaul process. The controlling and auditing procedures are put forward to control and audit parts’ return-to-zero statuses and overproof statuses. And some searching algorithms are also designed to enable tracking and tracing of the configuration status along the time coordinate, or get a snapshot of an aero-engine’s configuration at a certain time. The above model, procedures and algorithms have been implemented and adopted to fulfill the configuration management requirements in the aero-engine overhaul process. Findings The approach is effective in identifying, recording, controlling, auditing, tracking and tracing configuration changes in the overhaul process. Practical implications The approach’s implementation and adoption present a practical example for aero-engines’ configuration management issue in the overhaul process. Originality/value The work proposes an original aero-engine configuration management solution for the overhaul process and enables a reliable and accurate configuration management mode.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:23Z
      DOI: 10.1108/AEAT-11-2016-0198
       
  • Mixed fault diagnosis scheme for satellite formation
    • Pages: 427 - 434
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 427-434, March 2018.
      Purpose The purpose of this paper is to present a solution for the uncertain fault with the propulsion subsystem of satellite formation, using the Lur’e differential inclusion linear state observers (DILSOs) and fuzzy wavelet neural network (FWNN) to perform fault detection and diagnosis. Design/methodology/approach The uncertain fault system cannot be described based on the accurate differential equations. The set-value mapping is introduced into the state equations to solve the problem of uncertainty, but it will cause output uncertainty. The problem can be solved by linearization of Lur’e differential inclusion state observers. The Lur’e DILSOs can be used to detect uncertain fault. The fault isolation and estimation can be performed using the FWNN. Findings The mixed approach from fault detection and diagnosis has featured fast and correct to found the uncertain fault. The simulation results to indicate that the methods of design are not only effective but also have the advantages of good approximation effect, fast detection speed, relatively simple structure and prior knowledge and realization of adaptive learning. Research limitations/implications The hybrid algorithm can be extensively applied to engineering practice and find uncertain faults of the propulsion subsystem of satellite formation promptly. Originality/value This paper provides a fast, effective and simple mixed fault detection and diagnosis scheme for satellite formation.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:57Z
      DOI: 10.1108/AEAT-11-2016-0206
       
  • A data-driven method of health monitoring for spacecraft
    • Pages: 435 - 451
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 435-451, March 2018.
      Purpose The purpose of this paper is to detect the occurrence of anomaly and fault in a spacecraft, investigate various tendencies of telemetry parameters and evaluate the operation state of the spacecraft to monitor the health of the spacecraft. Design/methodology/approach This paper proposes a data-driven method (empirical mode decomposition-sample entropy-principal component analysis [EMD-SE-PCA]) for monitoring the health of the spacecraft, where EMD is used to decompose telemetry data and obtain the trend items, SE is utilised to calculate the sample entropies of trend items and extract the characteristic data and squared prediction error and statistic contribution rate are analysed using PCA to monitor the health of the spacecraft. Findings Experimental results indicate that the EMD-SE-PCA method could detect characteristic parameters that appear abnormally before the anomaly or fault occurring, could provide an abnormal early warning time before anomaly or fault appearing and summarise the contribution of each parameter more accurately than other fault detection methods. Practical implications The proposed EMD-SE-PCA method has high level of accuracy and efficiency. It can be used in monitoring the health of a spacecraft, detecting the anomaly and fault, avoiding them timely and efficiently. Also, the EMD-SE-PCA method could be further applied for monitoring the health of other equipment (e.g. attitude control and orbit control system) in spacecraft and satellites. Originality/value The paper provides a data-driven method EMD-SE-PCA to be applied in the field of practical health monitoring, which could discover the occurrence of anomaly or fault timely and efficiently and is very useful for spacecraft health diagnosis.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:37:48Z
      DOI: 10.1108/AEAT-08-2016-0130
       
  • Effect of momentum flux distribution on multiple round jets
    • Pages: 452 - 460
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 452-460, March 2018.
      Purpose This study aims to investigate the effects of nozzle momentum flux distribution on the flow field characteristics. Design/methodology/approach The nozzle configuration consists of a central nozzle surrounded by four nozzles. All nozzles have the same diameter and constant separation between nozzles. OpenFOAM® is used for simulating the jet flow. Reynolds-averaged Navier-Stokes (RANS) equations are solved iteratively with a first-order closure for turbulence. Pitot-static tube with differential pressure transducer is used for mean velocity measurements. The comparison of computed results with experimental data shows similar trend and acceptable validation. Findings According to the results, the momentum flux distribution significantly alters the near field of multiple turbulent round jets. Highly non-linear decay region in the near field is found for the cases having higher momentum in the outer jets. As a result of merging, increased positive pressure is found in the mixing region. Higher secondary flows and wider mixing region are reported as a result of momentum transfer from axial to lateral directions by Reynolds stresses. Research limitations/implications The present study is limited to isothermal flow of air jet in air medium. Social implications Optimum momentum flux distribution in multijet injector of a combustor can reap better mixing leading to better efficiency and lesser environmental pollution. Originality/value As summary, the contributions of this paper in the field of turbulent jets are following: simulations for various momentum distribution cases have been performed. In all the cases, the flow at the nozzle exit is subsonic along with constant velocity profile. To simulate proper flow field, a large cylinder-type domain with structured grid is used with refinements toward the nozzle exit and jet axis. The results show that the non-linearity increases with increase in momentum of outer jets. Longer merging zones are reported for cases with higher momentum in outer nozzles using area-averaged turbulent kinetic energy. Similarly, wider mixing regions are reported using secondary flow parameter and visualizations.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:09Z
      DOI: 10.1108/AEAT-11-2016-0233
       
  • PIL simulations of an FWUAV under windy conditions
    • Pages: 461 - 470
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 461-470, March 2018.
      Purpose A fixed wing unmanned aerial vehicle (FWUAV) is targeted to perform processor in the loop (PIL) simulations for the flight scenarios such as straight and level, level climb, level turn, climbing turn and level steady heading sideslip under windy conditions such as steady wind (SW) and wind gust (WG) in a desired and controlled manner. Design/methodology/approach The constrained multi-input–multi-output (MIMO) lateral and longitudinal linear models-based model predictive controllers (MPCs) which are proposed in a previous study (Ulker et al., 2017) are tested in the PIL simulations under specified windy conditions. BeagleBone Black Rev C is used as a target hardware or processor in the PIL simulations. Findings The results of the PIL simulations show that the MPCs proposed in the previous study can achieve satisfactory performance and flying qualities for the all flight scenarios handled in this paper under windy conditions. Practical implications The MPCs proposed in the previous study can be easily implemented in the real world to a low-cost and small-sized board like BeagleBone Black Rev C which is used in this paper. Originality/value The proposed MPCs in the previous study which are capable of providing more flexibility in terms of tracking complex trajectories are showed to be able to be implemented to real system by means of PIL simulations under the changeable windy conditions which are difficult for performance tests.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:38:47Z
      DOI: 10.1108/AEAT-06-2016-0096
       
  • Aerothermodynamic study of a small hypersonic plane
    • Pages: 471 - 480
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 90, Issue 2, Page 471-480, March 2018.
      Purpose This paper aims to present an aerothermodynamic analysis of a new concept of a small hypersonic airplane. Aerodynamics characteristics for different flow conditions encountered during the missions are analyzed. The effects of elevons deflection for pitch control and of the presence of engines on aerodynamic performances are also investigated for different flight conditions. The effects of boundary layer laminar–turbulent transition on aerodynamic heating are studied to preliminarily identify proper materials that can sustain the hypersonic phase. Design/methodology/approach Aerodynamic characteristics are predicted by means of the semi-empirical aerodynamic prediction code Missile DATCOM and computational fluid dynamics simulations. Computational fluid dynamics analysis is also performed to investigate aerodynamic heating phenomenon. Findings Major discrepancies between the results offered by the two methods have been registered in transonic regime, whereas in subsonic and super-hypersonic conditions, Missile DATCOM confirms to be a suitable tool for preliminary design steps. The results of the analysis show that for the identification of the materials that can sustain the hypersonic phase, the turbulent solution must be taken into account. Carbon fiber reinforced ceramics composite materials seem particularly well suited for the nose, wing and vertical tail leasing edges and control surfaces, while titanium alloys could be used for the rest of the vehicle surface. Originality/value This new concept of vehicle is designed both for point-to-point medium range hypersonic transportation and long duration suborbital space tourism missions, by integrating available technologies developed for aeronautical and space systems.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2018-03-12T01:37:56Z
      DOI: 10.1108/AEAT-06-2015-0151
       
 
 
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