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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: 9)
Academia Revista Latinoamericana de Administraci√≥n     Open Access   (Followers: 2, SJR: 0.144, h-index: 4)
Accounting Auditing & Accountability J.     Hybrid Journal   (Followers: 30)
Accounting Research J.     Hybrid Journal   (Followers: 25, SJR: 0.26, h-index: 7)
Accounting, Auditing and Accountability J.     Hybrid Journal   (Followers: 19, SJR: 0.88, h-index: 40)
Advances in Accounting Education     Hybrid Journal   (Followers: 14, SJR: 0.514, h-index: 5)
Advances in Appreciative Inquiry     Hybrid Journal   (SJR: 0.124, h-index: 5)
Advances in Autism     Hybrid Journal   (Followers: 7)
Advances in Dual Diagnosis     Hybrid Journal   (Followers: 47, 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: 11, SJR: 0.125, h-index: 2)
Agricultural Finance Review     Hybrid Journal  
Aircraft Engineering and Aerospace Technology     Hybrid Journal   (Followers: 181, SJR: 0.391, h-index: 18)
American J. of Business     Hybrid Journal   (Followers: 16)
Annals in Social Responsibility     Full-text available via subscription  
Anti-Corrosion Methods and Materials     Hybrid Journal   (Followers: 10, SJR: 0.215, h-index: 25)
Arts and the Market     Hybrid Journal   (Followers: 9)
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: 3, SJR: 0.182, h-index: 7)
Asian Association of Open Universities J.     Open Access  
Asian Education and Development Studies     Hybrid Journal   (Followers: 5)
Asian J. on Quality     Hybrid Journal   (Followers: 2)
Asian Review of Accounting     Hybrid Journal   (Followers: 2, SJR: 0.29, h-index: 7)
Aslib J. of Information Management     Hybrid Journal   (Followers: 24, SJR: 0.65, h-index: 29)
Aslib Proceedings     Hybrid Journal   (Followers: 257)
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: 11, SJR: 0.556, h-index: 38)
British Food J.     Hybrid Journal   (Followers: 15, SJR: 0.329, h-index: 35)
Built Environment Project and Asset Management     Hybrid Journal   (Followers: 15, 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: 16, 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: 6)
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   (Followers: 1, 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: 18)
Direct Marketing An Intl. J.     Hybrid Journal   (Followers: 6)
Disaster Prevention and Management     Hybrid Journal   (Followers: 22, 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: 21, SJR: 0.532, h-index: 30)
Education, Business and Society : Contemporary Middle Eastern Issues     Hybrid Journal   (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: 4, SJR: 0.387, h-index: 39)
Engineering, Construction and Architectural Management     Hybrid Journal   (Followers: 14, SJR: 0.541, h-index: 28)
Equal Opportunities Intl.     Hybrid Journal   (Followers: 3)
Equality, Diversity and Inclusion : An Intl. J.     Hybrid Journal   (Followers: 14, 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: 7, 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: 20, 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: 6)
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: 17, SJR: 0.359, h-index: 22)
Grey Systems : Theory and Application     Hybrid Journal   (Followers: 1)
Health Education     Hybrid Journal   (Followers: 3, SJR: 0.383, h-index: 17)
Higher Education, Skills and Work-based Learning     Hybrid Journal   (Followers: 44, SJR: 0.172, h-index: 4)
History of Education Review     Hybrid Journal   (Followers: 13, SJR: 0.141, h-index: 2)
Housing, Care and Support     Hybrid Journal   (Followers: 9, 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: 6, SJR: 0.322, h-index: 19)
Industrial Management & Data Systems     Hybrid Journal   (Followers: 6, SJR: 0.63, h-index: 69)
Industrial Robot An Intl. J.     Hybrid Journal   (Followers: 3, 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: 45, SJR: 0.576, h-index: 28)
Interactive Technology and Smart Education     Hybrid Journal   (Followers: 14, SJR: 0.112, h-index: 1)
Interlending & Document Supply     Hybrid Journal   (Followers: 62, SJR: 0.48, h-index: 13)
Internet Research     Hybrid Journal   (Followers: 42, 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: 8, 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: 5, 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: 12, SJR: 1.329, h-index: 35)
Intl. J. of Culture Tourism and Hospitality Research     Hybrid Journal   (Followers: 16, SJR: 0.399, h-index: 5)
Intl. J. of Development Issues     Hybrid Journal   (Followers: 10)
Intl. J. of Disaster Resilience in the Built Environment     Hybrid Journal   (Followers: 8, 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: 5, SJR: 0.179, h-index: 1)
Intl. J. of Emerging Markets     Hybrid Journal   (Followers: 4, SJR: 0.199, h-index: 5)
Intl. J. of Energy Sector Management     Hybrid Journal   (Followers: 3, SJR: 0.25, h-index: 12)
Intl. J. of Entrepreneurial Behaviour & Research     Hybrid Journal   (Followers: 5, SJR: 0.694, h-index: 28)
Intl. J. of Event and Festival Management     Hybrid Journal   (Followers: 6, SJR: 0.32, h-index: 8)
Intl. J. of Gender and Entrepreneurship     Hybrid Journal   (Followers: 5, SJR: 0.638, h-index: 6)
Intl. J. of Health Care Quality Assurance     Hybrid Journal   (Followers: 9, 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: 9, 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: 9, 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: 8)
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: 4, SJR: 0.111, h-index: 2)
Intl. J. of Leadership in Public Services     Hybrid Journal   (Followers: 15)
Intl. J. of Lean Six Sigma     Hybrid Journal   (Followers: 7, SJR: 0.562, h-index: 15)
Intl. J. of Logistics Management     Hybrid Journal   (Followers: 12, SJR: 0.998, h-index: 15)
Intl. J. of Managerial Finance     Hybrid Journal   (Followers: 6, 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: 10, 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: 17, 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: 10, SJR: 0.254, h-index: 10)
Intl. J. of Productivity and Performance Management     Hybrid Journal   (Followers: 6, SJR: 0.785, h-index: 31)
Intl. J. of Public Sector Management     Hybrid Journal   (Followers: 23, SJR: 0.272, h-index: 37)
Intl. J. of Quality & Reliability Management     Hybrid Journal   (Followers: 8, 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: 9, SJR: 0.227, h-index: 25)
Intl. J. of Sociology and Social Policy     Hybrid Journal   (Followers: 47, 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: 12, SJR: 0.616, h-index: 29)
Intl. J. of Tourism Cities     Hybrid Journal   (Followers: 2)
Intl. J. of Web Information Systems     Hybrid Journal   (Followers: 6, SJR: 0.208, h-index: 13)
Intl. J. of Wine Business Research     Hybrid Journal   (Followers: 6, 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: 3, 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: 7)
J. of Adult Protection, The     Hybrid Journal   (Followers: 15, SJR: 0.291, h-index: 7)
J. of Advances in Management Research     Hybrid Journal   (Followers: 3)
J. of Aggression, Conflict and Peace Research     Hybrid Journal   (Followers: 49, SJR: 0.177, h-index: 9)
J. of Agribusiness in Developing and Emerging Economies     Hybrid Journal   (Followers: 1)
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: 51)
J. of Asia Business Studies     Hybrid Journal   (Followers: 3, SJR: 0.115, h-index: 1)
J. of Assistive Technologies     Hybrid Journal   (Followers: 19, 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: 12, 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: 3)
J. of Chinese Human Resource Management     Hybrid Journal   (Followers: 7, SJR: 0.112, h-index: 3)
J. of Communication Management     Hybrid Journal   (Followers: 7, 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: 116, SJR: 0.13, h-index: 1)
J. of Criminological Research, Policy and Practice     Hybrid Journal   (Followers: 54)
J. of Cultural Heritage Management and Sustainable Development     Hybrid Journal   (Followers: 11, SJR: 0.109, h-index: 5)
J. of Documentation     Hybrid Journal   (Followers: 186, SJR: 0.936, h-index: 50)
J. of Economic and Administrative Sciences     Hybrid Journal   (Followers: 3)
J. of Economic Studies     Hybrid Journal   (Followers: 10, 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: 17, SJR: 0.173, h-index: 10)
J. of Enterprise Information Management     Hybrid Journal   (Followers: 5, 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: 9)
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: 6)
J. of Fashion Marketing and Management     Hybrid Journal   (Followers: 13, SJR: 0.529, h-index: 30)
J. of Financial Crime     Hybrid Journal   (Followers: 343, SJR: 0.158, h-index: 5)
J. of Financial Economic Policy     Hybrid Journal  
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: 9)
J. of Financial Reporting and Accounting     Hybrid Journal   (Followers: 12)
J. of Forensic Practice     Hybrid Journal   (Followers: 49, SJR: 0.225, h-index: 8)
J. of Global Mobility     Hybrid Journal   (Followers: 1)
J. of Global Responsibility     Hybrid Journal   (Followers: 4)
J. of Health Organisation and Management     Hybrid Journal   (Followers: 23, SJR: 0.67, h-index: 27)
J. of Historical Research in Marketing     Hybrid Journal   (Followers: 3, 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: 5)
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]   [181 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 practice in the translation traditional and glass cockpit based on
           General Aviation I-31T aircraft
    • Pages: 749 - 756
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 749-756, October 2017.
      Purpose The aim of this paper is to present the results preparation of a new glass cockpit for a general aviation category airplane with a TP100 turboprop 180 kW engine. All the works were carried out within the framework of the European programme: “Efficient Systems and Propulsion for Small Aircraft” – ESPOSA. Design/methodology/approach As a part of the ongoing work, the avionics equipment available on the market were thoroughly analysed. Optimization of choice was defined at the level of costs, ergonomics and development requirements of the engine manufacturer. The paper presents the issues of the realized project and discusses its specific characteristics, such as advantages and disadvantages in comparison to the conventional analogue cockpit and the possibility of adaptation for the plane. Findings New avionics, ground and in-flight tests were carried out. The data were collected, which, together with an ergonomics assessment done by the pilot and the observer, confirmed the previously established technical and operational objectives. Practical implications Most airplanes, when being modernized, encounter minor or major problems. A new approach to upgrading the avionics, involving the exchange of a piston engine with a turbine engine, which is supported by 3D software, has allowed a significant reduction of working time and costs. Originality/value The achieved results allow specifying a plan of changes, necessary to adapt the aircraft to a new avionic system. However, an important value is to show a new development direction of the turbine engine implementation in general aviation aircrafts.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:54Z
      DOI: 10.1108/AEAT-04-2016-0058
       
  • An innovative method for exhaust gases toxicity evaluation in the
           miniature turbojet engine
    • Pages: 757 - 763
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 757-763, October 2017.
      Purpose The purpose of this paper is to present an assessment method of the toxicity emission evaluation during combustion in the miniature turbojet engine. Design/methodology/approach A small-scale turbojet engine was used for the research because measurements on real aircraft turbines are complex and expensive. The experiment was performed in accordance with innovative BAT – CELL Bio – Ambient Cell method which consists of determination of virtual toxic impact of the gas mixture on the living cells; it is therefore a direct method. The most significant innovation of this method is that, during the test, which consists of exposing the cells to the gas mixture, the cells are deprived of culture fluid. Findings The preliminary analysis shows that the method used here allows to determine the virtual impact of the gases on the human respiratory system and skin. It could be useful in defining the arduousness of an airport. The obtained results show that both of exhaust gases represent similar toxicity. Practical implications The new in vitro method allows to determine the virtual impact of the gases on the human respiratory system and skin. Significant potential for further research not only on the miniaturised engines, but also in the case of real objects, as this method does not have to be performed in a laboratory. Originality/value The work presents potential application of the innovatory method for exhaust gases toxicity evaluation in jet engines, which could be useful in defining the arduousness of an airport.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:56Z
      DOI: 10.1108/AEAT-06-2016-0091
       
  • Take-off and landing control for a coaxial ducted fan unmanned helicopter
    • Pages: 764 - 776
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 764-776, October 2017.
      Purpose This paper aims to present a control strategy that eliminates the longitudinal and lateral drifting movements of the coaxial ducted fan unmanned helicopter (UH) during autonomous take-off and landing and reduce the coupling characteristics between channels of the coaxial UH for its special model structure. Design/methodology/approach Unidirectional auxiliary surfaces (UAS) for terminal sliding mode controller (TSMC) are designed for the flight control system of the coaxial UH, and a hierarchical flight control strategy is proposed to improve the decoupling ability of the coaxial UH. Findings It is demonstrated that the proposed height control strategy can solve the longitudinal and lateral movements during autonomous take-off and landing phase. The proposed hierarchical controller can decouple vertical and heading coupling problem which exists in coaxial UH. Furthermore, the confronted UAS-TSMC method can guarantee finite-time convergence and meet the quick flight trim requirements during take-off and landing. Research limitations/implications The designed flight control strategy has not implemented in real flight test yet, as all the tests are conducted in the numerical simulation and simulation with a hardware-in-the-loop (HIL) platform. Social implications The designed flight control strategy can solve the common problem of coupling characteristics between channels for coaxial UH, and it has important theoretical basis and reference value for engineering application; the control strategy can meet the demands of engineering practice. Originality/value In consideration of the TSMC approach, which can increase the convergence speed of the system state effectively, and the high level of response speed requirements to UH flight trim, the UAS-TSMC method is first applied to the coaxial ducted fan UH flight control. The proposed control strategy is implemented on the UH flight control system, and the HIL simulation clearly demonstrates that a much better performance could be achieved.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:17Z
      DOI: 10.1108/AEAT-01-2016-0017
       
  • Fast image matching via multi-scale Gaussian mutation pigeon-inspired
           optimization for low cost quadrotor
    • Pages: 777 - 790
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 777-790, October 2017.
      Purpose The purpose of this paper is to propose an improved optimization method for image matching problem, which is based on multi-scale Gaussian mutation pigeon-inspired optimization (MGMPIO) algorithm, with the objective of accomplishing the complicated image matching quickly. Design/methodology/approach The hybrid model of multi-scale Gaussian mutation (MGM) mechanism and pigeon-inspired optimization (PIO) algorithm is established for image matching problem. The MGM mechanism is a nonlinear model, which can adjust the position of pigeons by mutation operation. In addition, the variable parameter (VP) mechanism is exploited to adjust the map and compass factor of the original PIO. Low-cost quadrotor, a type of electric multiple rotorcraft, is used as a carrier of binocular camera to obtain the images. Findings This work improved the PIO algorithm by modifying the search strategy and adding some limits, so that it can have better performance when applied to the image matching problem. Experimental results show that the proposed method demonstrates satisfying performance in convergence speed, robustness and stability. Practical implications The proposed MGMPIO algorithm can be easily applied to solve practical problems and accelerate convergence speed of the original PIO, and thus enhancing the speed of matching process, which will considerably increase the effectiveness of algorithm. Originality/value A hybrid model of the MGM mechanism and PIO algorithm is proposed for image matching problem. The VP mechanism and low-cost quadrotor is also utilized in image matching problem.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:49Z
      DOI: 10.1108/AEAT-01-2015-0020
       
  • Real-time modeling of retractable self-launching glider using spreadsheets
    • Pages: 791 - 796
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 791-796, October 2017.
      Purpose This paper aims to propose a spreadsheet method for modeling and simulation of a retraction system mechanism for the retractable self-launching system for a high-performance glider. Design/methodology/approach More precisely, the method is based on parametric link design using Excel spreadsheets. Findings This method can be used for kinematic and dynamic analysis, graphical plotting and allows simulation of control kinematics with the ability to make quick and easy parametric changes to a design. It also has the ability to calculate the loads imposed on each component in the control system as a function of input loads and position. Practical implications This paper shows that it is possible to model complex control systems quickly and easily using spreadsheet programs already owned by most small companies. The spreadsheet model is a parametric model, and it gives a simple visual presentation of the control system with interactive movement and control by the user. Originality/value This spreadsheet model in conjunction with a simple CAD program enables the rapid and cost-effective development of control system components.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:53Z
      DOI: 10.1108/AEAT-05-2014-0076
       
  • Design and analysis osculating general curved cone waverider
    • Pages: 797 - 803
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 797-803, October 2017.
      Purpose Waverider has high lift to drag ratio and will be an idea aerodynamic configuration for hypersonic vehicles. But a structure permitting aerodynamic like waverider is still difficult to generate under airframe’s geometric constrains using traditional waverider design methods. And furthermore, traditional waverider’s aerodynamic compression ability cannot be easily adjusted to satisfy the inlet entrance requirements for hypersonic air-breathing vehicles. The purpose of this paper is to present a new method named osculating general curved cone (OCC) method aimed to improve the shortcomings of traditional waveriders. Design/methodology/approach A basic curved cone is, first, designed by the method of characteristics. Then the waverider’s inlet captured curve and front captured tube are defined in the waverider’s exit plane. Osculating planes are generated along the inlet captured curve and the designed curved cone is transformed to the osculating planes. Streamlines are traced in the transformed curved cone flow field. Combining all streamlines which have been obtained, OCC waverider’s compression surface is generated. Waverider’s upper surface uses the free stream surface. Findings It is found that OCC waverider has good volumetric characteristics and good flow compression abilities compared with the traditional osculating cone (OC) waverider. The volume of OCC waverider is 25 per cent larger than OC waverider at the same design condition. Furthermore, OCC waverider can compress incoming flow to required flow conditions with high total pressure recovery in the waverider’s exit plane. The flow uniformity in the waverider exit plane is quite well. Practical implications The analyzed results show that the OCC waverider can be a practical high performance airframe/forebody for hypersonic vehicles. Furthermore, this novel waverider design method can be used to design a structure permitting aerodynamic like waverider for a practical hypersonic vehicle. Originality/value The paper puts forward a novel waverider design method which can improve the waverider’s volumetric characteristics and compression abilities compared with the traditional waverider design methods. This novel design approach can extend the waverider’s applications for designing hypersonic vehicles.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:32Z
      DOI: 10.1108/AEAT-12-2014-0214
       
  • Sequence planning for human and robot cooperative assembly of large space
           truss structures
    • Pages: 804 - 808
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 804-808, October 2017.
      Purpose In the future, large space truss structures will be likely to require on-orbit assembly. One of the several proposed methods includes cooperative assembly performed by pressure-suited astronauts during extravehicular activity (EVA) and space robots. An intelligent planning method was presented to generate optimal assembly tasks. Design/methodology/approach Firstly, the inherent hierarchical nature of truss structures allows assembly sequences to be considered from strut level and structural volume element (SVE) level. Then, a serial assembly strategy in human-robot environment was applied. Furthermore, a two-level planning algorithm was presented. At the first-level planning, one ant colony algorithm for assembly sequence planning was improved to adopt assembly direction and time as heuristic information and did not consider assembly tasks. And, at the second-level planning, another novel colony algorithm for assembly task planning mainly considered results of the first-level planning, human-robot interactive information, serial assembly strategy and assembly task distributions. Findings The proposed two-level planning algorithm is very effective for solving the human and robot cooperative assembly of large space truss structures. Research limitations/implications In this paper, the case study is based on the following assumptions: each tetrahedron is assembled by two astronauts; each pentahedron is assembled by three astronauts. Practical implications A case illustrates the results of the two-level planning. From this case study, because of geometrical symmetry nature of large space truss structures, the optimal assembly sequences are not only one. Originality/value The improved ant colony algorithm can deal with the assembly sequence and task planning in human-robot environment more effectively.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:36Z
      DOI: 10.1108/AEAT-06-2014-0093
       
  • Hybrid BTT/STT missile autopilot design
    • Pages: 809 - 814
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 809-814, October 2017.
      Purpose Traditional skid-to-turn (STT) missile control mode is adopted mostly, but with the improvement of requirements for mobility and the emergence of new aerodynamic layout, a bank-to-turn (BTT) control mode gradually shows a greater advantage. However, the BTT missile also has certain defects, for example, when attacking against a maneuvering target and at the last section of guidance, the maximum lifting surface position of the missile needs to be adjusted frequently, thereby increasing the difficulty of control as well as introducing high-frequency noise. Design/methodology/approach Based on respective characteristics of the two control modes, this paper puts forward a hybrid autopilot design method based on nonlinear dynamic inversion. Firstly, the method converts overload instructions into corresponding angle instructions through the design of hybrid control guidance logic; secondly, based on the nonlinear dynamic inversion algorithm and combined with the fast-changing circuit/slowly changing circuit, a hybrid controller is designed; finally, combined with the missile mathematical model and actuator, it forms a autopilot design closed loop. Findings The simulation result shows that the non-linear dynamic inverse-based BTT/STT hybrid controller can input a track command well, normal overload and roll angle tracking performance have more advantages than the hybrid controller designed on the basis of classical control method in terms of overshooting and hysteretic characteristics. Originality/value The paper puts forward a new BTT/STT hybrid control method which has both the high mobile ability of the BTT missile and the precise control ability of the STT missile, which can adapt to the more complicated fighting environment. And, the method can effectively weaken the impact of the transformation of the control mode on the system.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:20Z
      DOI: 10.1108/AEAT-05-2015-0134
       
  • Rotational and relative translational control for satellite
           electromagnetic formation flying in low earth orbit
    • Pages: 815 - 825
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 815-825, October 2017.
      Purpose The purpose of this paper is to develop a theoretical design for the attitude control of electromagnetic formation flying (EMFF) satellites, present a nonlinear controller for the relative translational control of EMFF satellites and propose a novel method for the allocation of electromagnetic dipoles. Design/methodology/approach The feedback attitude control law, magnetic unloading algorithm and large angle manoeuvre algorithm are presented. Then, a terminal sliding mode controller for the relative translation control is put forward and the convergence is proved. Finally, the control allocation problem of electromagnetic dipoles is formulated as an optimization issue, and a hybrid particle swarm optimization (PSO) – sequential quadratic programming (SQP) algorithm to optimize the free dipoles. Three numerical simulations are carried out and results are compared. Findings The proposed attitude controller is effective for the sun-tracking process of EMFF satellites, and the magnetic unloading algorithm is valid. The formation-keeping scenario simulation demonstrates the effectiveness of the terminal sliding model controller and electromagnetic dipole calculation method. Practical implications The proposed method can be applied to solve the attitude and relative translation control problem of EMFF satellites in low earth orbits. Originality/value The paper analyses the attitude control problem of EMFF satellites systematically and proposes an innovative way for relative translational control and electromagnetic dipole allocation.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:40Z
      DOI: 10.1108/AEAT-01-2016-0007
       
  • System identification of flexible aircraft in frequency domain
    • Pages: 826 - 834
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 826-834, October 2017.
      Purpose The purpose of this paper is to identify the flexible aircraft model accurately from the frequency responses. Design/methodology/approach The frequency domain output error method is used to estimate the aerodynamic (rigid body and elastic body) derivatives, and mode shape parameters in the process of identification of flexible aircraft model. The accurate identification of lightly damped low frequency rigid-body response modes requires a careful selection of the frequency sweep length and the fast Fourier transform (FFT) window size, as the FFT window length cannot be longer than any individual sweep records. To address this issue, an effort is made to derive the FFT window length for the application of frequency domain estimation approach. Findings The investigations are initially made to select a suitable FFT window size for the accurate identification of the lightly damped low frequency rigid-body response modes of the flexible aircraft. Subsequently, frequency domain estimation approach is applied to simulated data of flexible aircraft. Besides the stability and control derivatives, the structural modes of the flexible aircraft are also estimated as part of state space model identification, and it is shown that all the model parameter estimates are accurate. Identification of such flexible aircraft aerodynamic (rigid body and elastic body) derivatives and structural mode shape parameters will lead to mathematical models of flexible aircraft that are accurate over a wide frequency range. The identified models are validated using the time response of frequency sweep data. Research limitations/implications Aircraft system identification is an integral part of aerospace system design and life cycle process. This becomes a complex process when the aircraft has significant effects of flexibility on the flight dynamics, especially as the frequencies of the elastic modes become lower and approach those of the rigid body modes. Thus, an integrated mathematical model of flexible aircraft is required to develop, and it should be valid for a wide frequency range and relevant for the design of flight control system. Originality/value This paper focuses on the application of frequency domain approach to identify the valid model of flexible aircraft by estimating the aerodynamic (rigid body and elastic body) derivatives and structural mode shape parameters of flexible aircraft. The unknown frequencies of structural modes are also able to identify accurately in frequency domain. This gives more value addition to analyze the flight data of flexible aircraft, as it is challenging problem in parameter estimation of flexible aircraft.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:34Z
      DOI: 10.1108/AEAT-09-2015-0214
       
  • Deployment and control of cable-driven flexible solar arrays
    • Pages: 835 - 844
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 835-844, October 2017.
      Purpose The purpose of this study is to investigate the deployment and control of cable-driven flexible solar arrays. Design/methodology/approach First, dynamic model of the system is established by using the Jourdain’s velocity variation principle and the single direction recursive construction method, including the dynamic equation of a single flexible body, the kinematical recursive relation of two adjacent flexible bodies and the dynamic equation of the solar array system. Then, the contribution of joint friction to the dynamic equation of the system is derived based on the virtual power principle. A three-dimensional revolute joint model is introduced and discussed in detail. Finally, a proportion-differentiation (PD) controller is designed to control the drift of the system caused by the deployment. Findings Simulation results show that the proposed model is effective to describe the deployment of flexible solar arrays, joint friction may affect the dynamic behavior of the system and the PD controller can effectively eliminate the spacecraft drift. Practical implications This model is useful to indicate the dynamics behavior of the solar array system with friction. Originality/value The relationship between ideal constraint force and Lagrange multipliers is derived. The contribution of joint friction to the dynamic equation of the system is derived based on the virtual power principle. A PD controller is designed to control the drift of the system caused by the deployment of solar arrays.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:22Z
      DOI: 10.1108/AEAT-05-2015-0133
       
  • On the maximal and minimal distances of flying-around satellite formation
    • Pages: 845 - 852
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 845-852, October 2017.
      Purpose The purpose of this paper is to present the obtained analytic solutions of maximal and minimal inter-satellite distances for flying-around satellite formation. Design/methodology/approach The relative motion equation is used to express the inter-satellite distance as the function of the orbital elements of two participating satellites for the flying-around satellite formation. Then by taking the derivative of the distance function with respect to the true anomaly, some possible extreme value points are obtained. According to the detailed analysis, the maximal and minimal distance solutions are found. By a reverse process, the expected initial differential orbital elements that generate the required extreme inter-satellite distances are also obtained. Findings The maximal and minimal distances of the flying-around formation can be analytically written as the functions of three initial orbital elements differences, i.e. the differential orbital inclination, the differential eccentricity and the differential right ascension. For the given maximal and minimal distances, there are lots of solutions of the initial differential orbital elements, which can produce the expected relative motions. Research limitations/implications The solutions of the maximal and minimal inter-satellite distances are only accurate for the circular or near circular reference orbit. For the elliptic reference orbit, there is a need to develop new methods to find the analytic solutions. Practical implications The results here can be applied to design the factual flying-around formation with dimension requirements in mission analysis stage. Originality/value By using the solutions presented in this paper, the engineers can design the expected flying-around formation with required maximal and minimal inter-satellite distances in a very easy way.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:14Z
      DOI: 10.1108/AEAT-08-2015-0192
       
  • Effect of TRIZ on enhancing employees’ creativity and innovation
    • Pages: 853 - 861
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 853-861, October 2017.
      Purpose Regarding the important roles of creativity and innovation for accomplishing innovative missions in aerospace industries, this study aims to explore the impact of a three-month TRIZ (an engineering problem-solving toolkit) training workshop on enhancing three important creativity- and innovation-related characteristics of employees in Iran aerospace industries. Design/methodology/approach A three-month TRIZ educational program was run. Three standard questionnaires were used for assessing creative thinking (CT), need for cognition (NFC) and interest in work innovation (IWI). From different scientific sectors of aerospace industries, 290 participants took part in completing pre- and post-test questionnaires. The collected data were analyzed by the related statistical methods (the sign test, correlation analysis and descriptive statistics). Findings The results indicate that the TRIZ training workshop directly enhanced CT, NFC and IWI scores, and that there is a statistically significant positive correlation between these characteristics. Also, the results of the correlation analysis of these variables and the demographic features of the participants shed light on interesting facts that can be used for decision makers and researchers of aerospace industries. Research limitations/implications This study opens a new way for further research in the analysis of the impact of problem-solving techniques on improving creativity and innovation in aerospace and other high-tech industries. Originality/value This paper may be of high value to researchers in creativity and innovation fields in the high-tech industries, including the aerospace industry. This study further facilitates decision-making by enhancing inventive problem solving in these industries. It gives valuable information and guidelines that hopefully will help managers to consider the important issues during TRIZ toolkit establishment in their organizations.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:44Z
      DOI: 10.1108/AEAT-01-2016-0004
       
  • Double surrogate modeling usage in PSO
    • Pages: 862 - 870
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 862-870, October 2017.
      Purpose The purpose of this paper is to improve the efficiency of particle optimization method by using direct and indirect surrogate modeling in inverse design problems. Design/methodology/approach The new algorithm emphasizes the use of a direct and an indirect design prediction based on local surrogate models in particle swarm optimization (PSO) algorithm. Local response surface approximations are constructed by using radial basis neural networks. The principal role of surrogate models is to answer the question of which individuals should be placed into the next swarm. Therefore, the main purpose of surrogate models is to predict new design points instead of estimating the objective function values. To demonstrate its merits, the new approach and six comparative algorithms were applied to two different test cases including surface fitting of a geographical terrain and an inverse design of a wing, the averaged best-individual fitness values of the algorithms were recorded for a fair comparison. Findings The new algorithm provides more than 60 per cent reduction in the required generations as compared with comparative algorithms. Research limitations/implications The comparative study was carried out only for two different test cases. It is possible to extend test cases for different problems. Practical implications The proposed algorithm can be applied to different inverse design problems. Originality/value The study presents extra ordinary application of double surrogate modeling usage in PSO for inverse design problems.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:35Z
      DOI: 10.1108/AEAT-02-2015-0035
       
  • Aerodynamic performance improvement of a canard control missile
    • Pages: 871 - 878
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 871-878, October 2017.
      Purpose This paper aims to analyze the influence of the changings in geometrical parameters on the aerodynamic performance of the control canard projectiles. Design/methodology/approach Because of the mentioned point, the range of projectiles increment has a considerable importance, and the design algorithm of a control canard projectile was first written. Then, were studied the effects of canard geometric parameters such as aspect ratio, taper ratio and deflectable nose on lift to drag coefficient ratio, static margin based on the slender body theory and cross section flow. Findings The code results show that aspect ratio increment, results in an increase in lift-to-drag ratio of the missile, but increase in canard taper ratio results in increasing of lift-to-drag ratio at 1° angle of attack, while during increasing the canard taper ratio up to 0.67 at 4° angle of attack, lift to drag first reaches to maximum and then decreases. Also, static margin decreases with canard taper ratio and aspect ratio increment. The developed results for this type of missile were compared with same experimental and computational fluid dynamic (CFD) results and appreciated agreement with other results at angles of attack between 0° and 6°. Practical implications To design a control canard missile, the effect of each geometric parameter of canard needs to be estimated. For this purpose, the suitable algorithm is used. In this paper, the effects of canard geometric parameters, such as aspect ratio, taper ratio and deflectable nose on lift-to-drag coefficient ratio and static margin, were studied with help of the slender body theory and cross-section flow. Originality/value The contribution of this paper is to predict the aerodynamic characteristics for the control canard missile. In this study, the effect of the design parameter on aerodynamic characteristics can be estimated, and the effect of geometrical characteristics has been analyzed with a suitable algorithm. Also, the best lift-to-drag coefficient for the NASA Tandem Control Missile at Mach 1.75 was selected at various angles of attack. The developed results for this type of missile were compared with same experimental and CFD results.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:29Z
      DOI: 10.1108/AEAT-01-2016-0019
       
  • Aircraft maintenance checks using critical chain project path
    • Pages: 879 - 892
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 879-892, October 2017.
      Purpose Aircraft operators incur significant costs when an aircraft is taken out of service for maintenance. The purpose of this paper is to present a method for reducing time duration of aircraft maintenance checks using critical chain project management (CCPM) principle. Design/methodology/approach A case study of a typical heavy maintenance check performed on an Airbus 320 aircraft is undertaken for the analysis. The critical chain method is applied to develop a plan with a reduced duration and a survey and field observations to validate the findings have also been carried out as a part of this paper. Findings The paper compares the traditional project management method with CCPM in view of reducing the aircraft down time duration for maintenance. This paper repositions buffers and other techniques to shorten the chain path and a reduction in the total duration of the project by five days is achieved. Research limitations/implications It is argued that the application of CCPM principle can reduce the duration of an aircraft maintenance check, but this paper is done in a single project situation focusing on project planning and execution. Therefore, additional study may be required to examine other issues. Originality/value Cost of the maintenance is second highest expenditure factor for an airline operator. Therefore, it is necessary to drive the maintenance cost down. The paper demonstrates that the duration of a maintenance check can be reduced by 8.9 per cent using the method suggested in this paper.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:37Z
      DOI: 10.1108/AEAT-10-2013-0186
       
  • Design of MPCs for a fixed wing UAV
    • Pages: 893 - 901
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 893-901, October 2017.
      Purpose The purpose of the paper is to examine a fixed wing unmanned aerial vehicle (UAV) as it undergoes five flight scenarios under straight and level, level climb, level turn, climbing turn and level steady heading sideslip conditions in a desired and controlled manner using constrained multi input multi output (MIMO) model predictive controllers (MPCs). Design/methodology/approach An MPC strategy based on the lateral and longitudinal linear models is proposed for the flight control design. Simulations are carried out for the nonlinear closed-loop aircraft Simulink model available from the University of Minnesota UAV research group with the implemented MIMO MPCs designed in this paper. Findings The results of the simulations show that the MIMO MPCs can achieve satisfactory performance and flying qualities under three different test conditions in terms of existing unmeasured outputs and unmeasured output disturbances. Practical Implications The MPCs designed in this paper can be implemented to UAVs. Therefore, the implementation is considered as an advanced research. Originality/value The proposed MPC design in this paper provides more flexibility in terms of tracking complex trajectories comparing with the classical controllers in the literature. Besides they provide to change more than one reference of the states at any time.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:51Z
      DOI: 10.1108/AEAT-08-2015-0198
       
  • Robust launch vehicle’s generalized dynamic inversion attitude
           control
    • Pages: 902 - 910
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 902-910, October 2017.
      Purpose To design a robust attitude control system for the ascent flight phase of satellite launch vehicles (SLVs). Design/methodology/approach The autopilot is based on generalized dynamic inversion (GDI). Dynamic constraints are prescribed in the form of differential equations that encapsulate the control objectives, and are generalized inverted using the Moore-Penrose Generalized Inverse (MPGI) based Greville formula to obtain the control law. The MPGI is modified via a dynamic scaling factor for assuring generalized inversion singularity-robust tracking control. An additional sliding mode control (SMC) loop is augmented to robustify the GDI closed-loop system against model uncertainties and external disturbances. Findings The robust GDI control law allows for two cooperating controllers that act on two orthogonally complement control spaces: one is the particular controller that realizes the dynamic constraints, and the other is the auxiliary controller that is affined in the null control vector, and is used to enforce global closed-loop stability. Practical implications Orthogonality of the particular and the auxiliary control subspaces ensures noninterference of the two control actions, and thus, it ensures that both actions work toward a unified goal. The robust control loop increases practicality of the GDI control design. Originality/value The first successful implementation of GDI to the SLV control problem.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:13Z
      DOI: 10.1108/AEAT-06-2015-0149
       
  • Longitudinal stability characteristics of the LASTA airplane
    • Pages: 911 - 919
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 911-919, October 2017.
      Purpose This paper presents the longitudinal stability analysis of a single tractor propeller airplane LASTA at high engine power settings. This analysis is part of the ongoing process of certifying the airplane for civil use according to the civil regulations CS-23. Design/methodology/approach The design methodology that is presented in the paper consists of comparing flight test aerodynamic and calculation results. The methods used here are standard and routinely used in flight testing. Findings Flight testing results indicate that at low airspeeds the cumulative destabilizing effects because of high values of the angle of attack and high power settings are about 6 per cent of MAC. This value is in a very good agreement with published data. Practical implications The information presented in this paper are new, and are very specific to this one aircraft configuration. The methods used here are standard and widely used in flight testing. Originality/value The information in this paper presents flight test results. There are not many publications in this area.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:26Z
      DOI: 10.1108/AEAT-02-2016-0026
       
  • Towards structural health monitoring of space vehicles
    • Pages: 920 - 927
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 920-927, October 2017.
      Purpose The purpose of this paper is to report the results of a recent project of complex tests on the survival of structural health monitoring (SHM) technology with piezo wafer active sensors (PWAS) and electromechanical impedance spectroscopy (EMIS) at simulating the concomitant action of harsh conditions of outer space: extreme temperatures, radiations, vacuum. Design/methodology/approach The tests were conducted on PWAS, consists in adhesive and aluminium discs as structural specimens, with PWAS bonded on them. The substantiating of PWAS-EMIS-based SHM technique consists the fact that real part of the PWAS electromechanical impedance spectrum follows with fidelity the resonance behaviour of the structure vibrating under the PWAS excitation. This EMIS signature is very sensitive to any structural changes and, on this basis, can be monitored the onset and progress of structural damages such as fatigue, cracks, corrosion, etc. Findings The conclusion of the tests is that the cumulative impact of severe conditions of temperature, radiation and vacuum has not generated decommissioning of sensors or adhesive, which would have meant the compromise of the methodology. A second important outcome is linked to the capability of this methodology to distinguish between the damages of mechanical origin and the false ones, caused by environmental conditions, which are, basically, harmless. Originality/value The question of transfer of PWAS-EMIS-based SHM technology to space vehicles and applications received, as a novelty, a first and encouraging response.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:31Z
      DOI: 10.1108/AEAT-07-2015-0173
       
  • Identification of mechanical properties of adhesive joints using ANN
    • Pages: 928 - 935
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 928-935, October 2017.
      Purpose This paper aims to present a new approach to the fast determination of the effective, dynamic, mechanical properties of an adhesive for linear and nonlinear regions of the adhesive response, for both healthy and damaged states of the bond. Design/methodology/approach The proposed approach is based on the measurement of the linear and nonlinear frequency response function (FRF) of adhesive-bonded structure and using artificial neural network identification technique. For this purpose, linear and nonlinear FRFs are measured for several single-lap joint specimens that are fabricated in healthy and damaged configurations of the bond. The measured FRFs of healthy and damaged specimens are then used to identify the natural frequencies of the specimens. The experimental natural frequencies, in turn, would be used to train artificial neural network (ANN) which would be able to predict the effective Young’s and shear moduli and damping of adhesive in healthy and damaged specimens, for any given excitation level and frequency, within the training domain. Findings Simultaneous identification of the effective mechanical properties of adhesive for linear and nonlinear response regions, as well as healthy and damages states of the adhesive bond. Practical implications The introduced method is effective to model the assembled structures with the viscoelastic adhesive joints, for linear and nonlinear regions. Originality/value A fast methodology, using ANN, for identification the effective mechanical properties of adhesives, compared to other methods for both linear and nonlinear regions.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:24Z
      DOI: 10.1108/AEAT-06-2015-0163
       
  • Numerical simulation of ignition transient in solid rocket motor: a
           revisit
    • Pages: 936 - 945
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 936-945, October 2017.
      Purpose The capability to predict and evaluate the motor pressure during each phase by means of a numerical analysis can significantly increase the efficiency of the preliminary design process with a reduction of both the motor development and operational costs. This paper aims to perform numerical simulation to analyze the ignition transient in solid rocket motor by solving Euler equation coupled with some semi-empirical correlations. These relations take into account the main phenomena affecting the ignition transient. Coupling relationships include the heat transfer of the gas to the propellant and erosive burning rate relationship. Design/methodology/approach The current research effort divides motor into series of control volumes along the port axis, and the variation of port area, burning surface and burning rate along the port are taken into account. A set of governing equations are then solved using explicit, time-dependent, predictor-corrector finite difference method. The numerical model helps to capture and embed shock wave associated with igniter flow within the solution. Second-order artificial viscosity dampens out the numerical oscillations due to sharp gradient within the flow field. The developed computer code predicts the start-up characteristics of motor. The study also provides comparison of simulation results with in-house experimental motor. Findings Simulations are performed with and without erosive burning to demonstrate that the flow model is a good physical approximation of motor. Numerical results calculated by this model without erosive burning are not in good agreement with experimental results. This minor discrepancy has motivated the inclusion of erosive burning in numerical model. The simulated results are then compared with the experimental data for head-end and rear-end pressure. The agreement between simulation and experiment is remarkable. In summary, major finding of this study is that unsteady quasi-one-dimensional gas dynamic model can capture the flow field in the motor during ignition transient effectively. Research limitations/implications Unsteady quasi-one-dimensional gas dynamic model can capture the flow field in the motor during ignition transient effectively. However, in systems where two- and three-dimensional effects are pre-dominant, one would require to develop a more elaborate, multi-dimensional model which will allow for further understanding of the flow behavior and eventually lead to modeling of rocket motors with more complex geometries. Practical implications The close agreement between experimental and simulation results can be considered as forced to some degree, because the general mathematical model of erosive burning contains a free variable erosive burning exponent. However, in future, this variable can be established a priori by erosive burning tests. Originality/value The solid propellant ignition process consists of series of rapid events and must be completed in a fraction of a second. An understanding of the dynamics of ignition has become increasingly vital with the development of larger and more sophisticated solid propellant rocket motors. This research effort provides the simulation framework to predict and evaluate the motor pressure during each phase by means of a numerical analysis, thus significantly increasing the efficiency of the preliminary design process with a reduction of both the motor development and operational costs.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:25Z
      DOI: 10.1108/AEAT-04-2015-0109
       
  • Active disturbance rejection control for small unmanned helicopters via
           Levy flight-based pigeon-inspired optimization
    • Pages: 946 - 952
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 946-952, October 2017.
      Purpose The purpose of this paper is to propose a control approach for small unmanned helicopters, and a novel swarm intelligence algorithm is used to optimize the parameters of the proposed controller. Design/methodology/approach Small unmanned helicopters have many advantages over other unmanned aerial vehicles. However, the manual operation process is difficult because the model is always instable and coupling. In this paper, a novel optimized active disturbance rejection control (ADRC) approach is presented for small unmanned helicopters. First, a linear attitude model is built in hovering condition according to small perturbation linearization. To realize decoupling, this model is divided into two parts, and each part is equipped with an ADRC controller. Finally, a novel Levy flight-based pigeon-inspired optimization (LFPIO) algorithm is developed to find the optimal ADRC parameters and enhance the performance of controller. Findings This paper applies ADRC method to the attitude control of small unmanned helicopters so that it can be implemented in practical flight under complex environments. Besides, a novel LFPIO algorithm is proposed to optimize the parameters of ADRC and is proved to be more efficient than other homogenous methods. Research limitations/implications The model of proposed controller is built in the hovering action, whereas it cannot be used in other flight modes. Practical implications The optimized ADRC method can be implemented in actual flight, and the proposed LFPIO algorithm can be developed in other practical optimization problems. Originality/value ADRC method can enhance the response and robustness of unmanned helicopters which make it valuable in actual environments. The proposed LFPIO algorithm is proved to be an effective swarm intelligence optimizer, and it is convenient and valuable to apply it in other optimized systems.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:06Z
      DOI: 10.1108/AEAT-05-2016-0065
       
  • The influence of a number of points on results of measurements of a
           turbine blade
    • Pages: 953 - 959
      Abstract: Aircraft Engineering and Aerospace Technology, Volume 89, Issue 6, Page 953-959, October 2017.
      Purpose The purpose of this paper was to determine the influence of a number of measured points on results of measurements of turbine blades, which are the parts of aircraft engines. The selection of a number of points is the part of a measurement strategy in the coordinate measuring technique and determines the accuracy of measurements. Design/methodology/approach Numerical and experimental investigations were conducted. The measurements were simulated using different numbers of measured points. The simulated measurements were performed for the selected dispersion of measured points. The dispersion reflected the inaccuracy of a manufacturing process of the considered product and the uncertainty of measurements of curvilinear surfaces. To verify the accuracy of the numerical studies, experimental research was conducted. The real measurements were conducted using the selected coordinate measuring machine. Findings The gained results following the simulations can be very useful when selecting the appropriate number of measured points. The chosen number of points may be used during real measurements of turbine blades conducted on coordinate measuring machines. The results of numerical research indicate that there should be used the average radii of leading and trailing edges to increase the accuracy of measurements. The results of real coordinate measurements confirmed the results of simulation studies. Originality/value The main novelty of the paper is the presented methodology for determining the influence of measured points on results of measurements. The presented methodology helps the user of a coordinate measuring system select the appropriate measurement strategy of free-form surfaces applied in the aerospace industry.
      Citation: Aircraft Engineering and Aerospace Technology
      PubDate: 2017-11-09T01:58:18Z
      DOI: 10.1108/AEAT-03-2016-0044
       
 
 
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