Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process
المؤلفون المشاركون
Xu, Hao
Han, Jinglong
Yun, Haiwei
Chen, Xiaomao
المصدر
International Journal of Aerospace Engineering
العدد
المجلد 2019، العدد 2019 (31 ديسمبر/كانون الأول 2019)، ص ص. 1-11، 11ص.
الناشر
Hindawi Publishing Corporation
تاريخ النشر
2019-09-03
دولة النشر
مصر
عدد الصفحات
11
الملخص EN
A folding wing morphing aircraft should complete the folding and unfolding process of its wings while in flight.
Calculating the hinge moments during the morphing process is a critical aspect of a folding wing design.
Most previous studies on this problem have adopted steady-state or quasi-steady-state methods, which do not simulate the free-flying morphing process.
In this study, we construct an aeroelastic flight simulation platform based on the secondary development of ADAMS software to simulate the flight-folding process of a folding wing aircraft.
A flexible multibody dynamic model of the folding wing structure is established in ADAMS using modal neutral files, and the doublet lattice method is developed to generate aerodynamic influence coefficient matrices that are suitable for the flight-folding process.
The user subroutine is utilized, aerodynamic loading is realized in ADAMS, and an aeroelastic flight simulation platform of a folding wing aircraft is built.
On the basis of this platform, the flight-folding process of the aircraft is simulated, the hinge moments of the folding wings are calculated, and the influences of the folding rate and the aircraft’s center of gravity (c.g.) position on the results are investigated.
Results show that the steady-state method is applicable to the slow folding process.
For the fast folding process, the steady-state simulation errors of the hinge moments are substantially large, and a transient method is required to simulate the flight-folding process.
In addition, the c.g.
position considerably affects the hinge moments during the folding process.
Given that the c.g.
position moves aft, the maximum hinge moments of the inner and outer wings constantly increase.
نمط استشهاد جمعية علماء النفس الأمريكية (APA)
Xu, Hao& Han, Jinglong& Yun, Haiwei& Chen, Xiaomao. 2019. Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process. International Journal of Aerospace Engineering،Vol. 2019, no. 2019, pp.1-11.
https://search.emarefa.net/detail/BIM-1157136
نمط استشهاد الجمعية الأمريكية للغات الحديثة (MLA)
Xu, Hao…[et al.]. Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process. International Journal of Aerospace Engineering No. 2019 (2019), pp.1-11.
https://search.emarefa.net/detail/BIM-1157136
نمط استشهاد الجمعية الطبية الأمريكية (AMA)
Xu, Hao& Han, Jinglong& Yun, Haiwei& Chen, Xiaomao. Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process. International Journal of Aerospace Engineering. 2019. Vol. 2019, no. 2019, pp.1-11.
https://search.emarefa.net/detail/BIM-1157136
نوع البيانات
مقالات
لغة النص
الإنجليزية
الملاحظات
Includes bibliographical references
رقم السجل
BIM-1157136
قاعدة معامل التأثير والاستشهادات المرجعية العربي "ارسيف Arcif"
أضخم قاعدة بيانات عربية للاستشهادات المرجعية للمجلات العلمية المحكمة الصادرة في العالم العربي
تقوم هذه الخدمة بالتحقق من التشابه أو الانتحال في الأبحاث والمقالات العلمية والأطروحات الجامعية والكتب والأبحاث باللغة العربية، وتحديد درجة التشابه أو أصالة الأعمال البحثية وحماية ملكيتها الفكرية. تعرف اكثر