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Improvement of Micro UAV Performance using Tandem-Wing Design

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Abstract

The main objective for the present work is related with design of MAV to get high performance and long endurance used for surveillance and monitoring in military and civilian. The most important problem that faced the MAV is flying with low Reynolds numbers (Mach number is too law) and high lift with avoid high drag, the tandem-wing design is sucseceful and more reliable for this purpose because it reduced the drag to a half and gives good aerodynamic chractrastices when it’s compared with the conventional wing design. The dimensions of a MAV are 120mm length, wing span 130mm ( from tip to tip) and 12g in weight (the standard weight of MAV about 5- 20 g) with rang 50m (is the distance that the aircraft cut from point to another). The softwares that used in the present work are (Java foil, Soled works, ANSYS, J2) to prove the results.For the aerodynamic coefficients (CL, CD) were checked for two models (Tandem wing and conventional wing) by using ANSYS. To ensure that the design is successful we made a Simulation for the design by using (The J2 Universal Tool-Kit for Aircraft Dynamics) software and used to testing the aerodynamic characteristic and performers, stability and control. The major benefits of the tandem wings are to reduce drag to half and increase the lift rather than conventional wing by separating the two wings. Java foil was used to calculate the aerodynamics coefficients for the airfoil.


Article
Design and Study of Unmanned Aerial Vehicle Powered by Solar Cells by Using Advance Aircrafts Simulation Softwares
تصميم ودراسة طائرة مسيرة تعمل بالخلايا الشمسية باستخدام برامجيات متطورة في محاكاة الطائرات

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Abstract

The objective of this work is to design the Unmanned Aerial Vehicle (UAV) powered by solar cells, to provide maximum power which consumes by the electrical motor of the aircraft during takeoff at its maximum weight 11(kg). UAV was designed to use for multi-purposes tasks civil and military missions, such as surveillance, communication, intelligence and monitoring. Solar cells power magnitude was checked and selected their types as Ga0.5In0.5P/Ga0.99In0.01As/Ga triple junction which has got practical average efficiency limit of 30%, that placed on the upper surface of wing as a matrix consist of 14 raw .Each raw contains 62 cells (0.04m×0.08m). Several advance software programs were used (Java foil, Advanced Aircraft Analysis version 2.5 (AAA2.5) and the j2 Universal Tool-Kit for Aircraft Dynamics).All of them, give the perfect aircraft design that is suitable operation of solar cells to get maximum power which is sufficient to produce maximum thrust for aircraft motor, and able to complete its mission during steady flight .The residual of solar cells power can be stored in batteries to use it as a power at night flight. The results were obtained from the present work which is nearest to the fact have more reliability and accurate by using these cells which install on the wing surface for producing the requirement power and by using the mentioned softwares specially J2 software which gives the authority to produce the aircraft due its theoretical simulation was applied on aircraft configuration with its real dimensions to predict suitable performance during its flight as a steep before for manufacture to avoid any manufacture cost loses for the model during test because of the cost of the cells and its position on the wing.

يتضمن البحث تصميم طائرة مسيرة تدار بقدرة الخلايا الشمسية لتوفير أعلى طاقة ممكنة لمحرك الطائرة للاقلاع والتي وزنها الاجمالي 11كغم. صممت هذه الطائرة لعدة استخدامات ومهام مدنية وعسكرية مثل المسح الجوي, الاتصالات, العمل الاستخباراتي والمراقبة. حسب مقدار قدرة الخلايا الشمسية اللازمة لرفع الطائرة واختيرت الخلية نوع (Ga0.5In0.5P/Ga0.99In0.01As/Ge)ثلاثية الارتباطوبكفاءة 30% اذ فرض تثبيتها على سطح الجناح بشكل مصفوفة تتكون من 14صف و 62 خلية بأبعاد (0.04م*0.08م) لكل خلية. استخدمت عدة برامجيات متطورة وهي Java Foil، Advanced Aircraft Analysis version 2.5 (AAA2.5)و J2 والتي جميعها كانت تصب في اعطاء التصميم الامثل للطائرة بما يلائم وعمل تلك الخلايا الشمسية لغرض الحصول على اعلى قدرة تكون كافية لتجهيز محرك الطائرة لاعطاء اعلى دفع Thrust))بالاضافة الى الحصول على اطول وقت ممكن لتحليق الطائرة في الجو لتنفيذ مهامها والمتبقي من الطاقة الفائضة يمكن خزنها في البطاريات لغرض استخدامها ليلاً. تم الحصول على نتائج حقيقية من العمل الحالي وهي اقرب ما تكون للواقع عبر الاستخدام الامثل لتلك الخلايا عبر البرامجيات المذكورة اعلاه وبالاخص برنامج (J2) للسماح ببناء وتصنيع الطائرة الشمسية لانه يجري محاكاة للطائرة نظرياً وبابعادها الحقيقية للتنبؤ عن اداءها اثناء الطيران كخطوة تسبق عملية التصنيع لتلافي اي خسائر مادية للنموذج المصنع بسبب كلفة تلك الخلايا ووضعيتها على سطح الجناح

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