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Purpose This study aims to simultaneously and stochastically maximize autonomous flight performance of a variable wing incidence angle having an unmanned aerial vehicle (UAV) and its flight control system (FCS) design. Design/methodology/approach A small UAV is produced in Iskenderun Technical University Drone Laboratory. Its wing incidence angle is able to change before UAV flight. FCS parameters and wing incidence angle are simultaneously and stochastically designed to maximize autonomous flight performance using an optimization method named simultaneous perturbation stochastic approximation. Obtained results are also benefitted during UAV flight simulations. Findings Applying simultaneous and stochastic design approach for a UAV having passively morphing wing incidence angle and its flight control system, autonomous flight performance is maximized. Research limitations/implications Permission of the Directorate General of Civil Aviation in Turkish Republic is necessary for real-time flights. Practical implications Simultaneous stochastic variable wing incidence angle having UAV and its flight control system design approach is so useful for maximizing UAV autonomous flight performance. Social implications Simultaneous stochastic variable wing incidence angle having UAV and its flight control system design methodology succeeds confidence, excellent autonomous performance index and practical service interests of UAV users. Originality/value Creating an innovative method to recover autonomous flight performance of a UAV and generating an innovative procedure carrying out simultaneous stochastic variable wing incidence angle having UAV and its flight control system design idea.

Purpose This research study aims to minimize autonomous flight cost and maximize autonomous flight performance of a slung load carrying rotary wing mini unmanned aerial vehicle (i.e. UAV) by stochastically optimizing autonomous flight control system (AFCS) parameters. For minimizing autonomous flight cost and maximizing autonomous flight performance, a stochastic design approach is benefitted over certain parameters (i.e. gains of longitudinal PID controller of a hierarchical autopilot system) meanwhile lower and upper constraints exist on these design parameters. Design/methodology/approach A rotary wing mini UAV is produced in drone Laboratory of Iskenderun Technical University. This rotary wing UAV has three blades main rotor, fuselage, landing gear and tail rotor. It is also able to carry slung loads. AFCS variables (i.e. gains of longitudinal PID controller of hierarchical autopilot system) are stochastically optimized to minimize autonomous flight cost capturing rise time, settling time and overshoot during longitudinal flight and to maximize autonomous flight performance. Found outcomes are applied during composing rotary wing mini UAV autonomous flight simulations. Findings By using stochastic optimization of AFCS for rotary wing mini UAVs carrying slung loads over previously mentioned gains longitudinal PID controller when there are lower and upper constraints on these variables, a high autonomous performance having rotary wing mini UAV is obtained. Research limitations/implications Approval of Directorate General of Civil Aviation in Republic of Türkiye is essential for real-time rotary wing mini UAV autonomous flights. Practical implications Stochastic optimization of AFCS for rotary wing mini UAVs carrying slung loads is properly valuable for recovering autonomous flight performance cost of any rotary wing mini UAV. Originality/value Establishing a novel procedure for improving autonomous flight performance cost of a rotary wing mini UAV carrying slung loads and introducing a new process performing stochastic optimization of AFCS for rotary wing mini UAVs carrying slung loads meanwhile there exists upper and lower bounds on design variables.

Purpose The purpose of this paper is to improve autonomous flight performance of an unmanned aerial vehicle (UAV) having actively sweep angle morphing wing using simultaneous UAV and flight control system (FCS) design. Design/methodology/approach An UAV is remanufactured in the ISTE Unmanned Aerial Vehicle Laboratory. Its wing sweep angle can vary actively during flight. FCS parameters and wing sweep angle are simultaneously designed to optimize autonomous flight performance index using a stochastic optimization method called as simultaneous perturbation stochastic approximation (SPSA). Results obtained are applied for flight simulations. Findings Using simultaneous design process of an UAV having actively sweep angle morphing wing and FCS design, autonomous flight performance index is maximized. Research limitations/implications Authorization of Directorate General of Civil Aviation in Turkey is crucial for real-time UAV flights. Practical implications Simultaneous UAV having actively sweep angle morphing wing and FCS design process is so beneficial for recovering UAV autonomous flight performance index. Social implications Simultaneous UAV having actively sweep angle morphing wing and FCS design process achieves confidence, high autonomous performance index and simple service demands of UAV operators. Originality/value Composing a novel approach to improve autonomous flight performance index (e.g. less settling and rise time, less overshoot meanwhile trajectory tracking) of an UAV and creating an original procedure carrying out simultaneous UAV having actively sweep angle morphing wing and FCS design idea.

[LANGUAGE= \"English\"] BACKGROUND: The surgical treatment of fifth metacarpal fractures, especially using Kirschner (K) wire techniques, has recently become popular because it provides for early hand movement. Successful anatomical reduction of the fracture is often achieved with surgery; however, an anatomical reduction cannot always be achieved and, according to 30° oblique radiography, the fracture is fixed with an apex dorsal angulation below 40°. The aim of this study was to evaluate the stability of such fractures postoperatively and compare the two different angulation options that provide early movement of the hand and wrist.METHODS: Thirty consecutive cases of neck fractures of the fifth metacarpal were treated intramedullarly with one K wire. Cases were divided into two groups: One fixed with anatomical reduction (Group 1) and the other (Group 2) fixed in apex dorsal angulation below 40°, according to 30° oblique radiography. Angulation, shortening, and functional outcome as Quick DASH scores and grip strengths were evaluated at 6 months.RESULTS: The mean correction angle was 56.6° (between 30° and 110°) for Group 1 and the residual angle was 0°. The mean cor-rection angle was 42.4° (between 20° and 75°) for group 2 (Figs. 4 and 5) and the residual angle was 23.6° (between 10° and 45°). The mean Quick DASH scores were 1.9 (SD: 1.7) for Group 1 and 5.67 (SD: 2.93) for Group 2 (p<0.05). Grip strength values were similar for both groups. All the patients returned to their previous occupations without any limitations in an average of 4 weeks (SD: 1.4) (range 2–6 weeks). No complications such as correction loosening or shortening were detected. Rotation was not detected during physical examination.CONCLUSION: Our investigation revealed no risk of shortening or rotation of the fracture; the patients were able to return quickly to their everyday activities.[LANGUAGE= \"Turkish\"] AMAÇ: Beşinci metakarpal kırıkların, özellikle Kirschner teli teknikleri kullanılarak cerrahi tedavisi, erken el hareketini sağladığı için son zamanlarda popüler hale gelmiştir. Kırığın başarılı anatomik redüksiyonu genellikle cerrahi ile sağlanmakla birlikte; anatomik bir redüksiyon her zaman elde edilemez ve 30° oblik grafilerde, kırık 40°’nin altındaki dorsal açılanma ile sabitlenir. Bu çalışmanın amacı, ameliyat sonrası bu tür kırıkların stabilitesini değerlendirmek ve el ve bileğin erken hareket etmesini sağlayan iki farklı açılanma seçeneğini karşılaştırmaktı.GEREÇ VE YÖNTEM: Beşinci metakarpal boyun kırığının 30 ardışık olgusu bir Kirschner teli ile intramedüller olarak tedavi edildi. Olgular iki gruba ayrıldı: Biri anatomik redüksiyonla sabitlendi (grup 1) ve diğeri (grup 2) 30° oblik radyografiye göre apeks dorsal açılanmada 40°’nin altında sabitlen-di. Quick DASH skorları ve kavrama kuvvetleri olarak açılanma, kısalma ve fonksiyonel sonuç altıncı ayda değerlendirildi.BULGULAR: Grup 1 için ortalama düzeltme açısı 56.6° (30° ile 110° arasında) ve rezidüel açı 0° idi. Grup 2 için ortalama düzeltme açısı 42.4° (20° ile 75° arasında) ve rezidüel açı 23.6° (10° ile 45° arasında) idi. Ortalama Quick DASH skorları grup 1 için 1.9 (SS: 1.7) ve grup 2 için 5.67 (SS: 2.93) idi (p<0.05). Kavrama gücü değerleri her iki grup için benzerdi. Ortalama 4. haftada (SS: 1.4) (dağılım, 2–6 hafta) tüm hastalar herhangi bir sınırlama olmaksızın önceki mesleklerine döndüler. Redüksiyon kaybı veya kısalma gibi komplikasyonlar tespit edilmedi. Fizik muayenede rotasyon tespit edilmedi.TARTIŞMA: Araştırmamız, kırığın kısalması veya rotasyon riski olmadığını ortaya koydu; hastalar günlük aktivitelerine hızla geri dönebildi.

Purpose. We evaluated whether intramedullary nail fixation for tibial diaphysis fractures with concomitant fibula fractures (except at the distal one-third level) managed conservatively with an associated fibula fracture resulted in ankle deformity and assessed the impact of the ankle deformity on lower extremity function. Methods. Sixty middle one-third tibial shaft fractures with associated fibular fractures, except the distal one-third level, were included in this study. All tibial shaft fractures were anatomically reduced and fixed with interlocking intramedullary nails. Fibular fractures were managed conservatively. Hindfoot alignment was assessed clinically. Tibia and fibular lengths were compared to contralateral measurements using radiographs. Functional results were evaluated using the Knee Injury and Osteoarthritis Outcome Score (KOOS) and the Foot and Ankle Disability Index Score (FADI). Results. Anatomic union, defined as equal length in operative and contralateral tibias, was achieved in 60 fractures (100%). Fibular shortening was identified in 42 fractures (68%). Mean fibular shortening was 1.2 cm (range, 0.5–2 cm). Clinical exams showed increased hindfoot valgus in 42 fractures (68%). The mean KOOS was 88.4, and the mean FADI score was 90. Conclusion. Fibular fractures in the middle or proximal one-third may need to be stabilized at the time of tibial intramedullary nail fixation to prevent development of hindfoot valgus due to fibular shortening.

Purpose The aim of this paper is to redesign of morphing unmanned aerial vehicle (UAV) using neural network for simultaneous improvement of roll stability coefficient and maximum lift/drag ratio. Design/methodology/approach Redesign of a morphing our UAV manufactured in Faculty of Aeronautics and Astronautics, Erciyes University is performed with using artificial intelligence techniques. For this purpose, an objective function based on artificial neural network (ANN) is obtained to get optimum values of roll stability coefficient (Clβ) and maximum lift/drag ratio (Emax). The aim here is to save time and obtain satisfactory errors in the optimization process in which the ANN trained with the selected data is used as the objective function. First, dihedral angle (φ) and taper ratio (λ) are selected as input parameters, C*lβ and Emax are selected as output parameters for ANN. Then, ANN is trained with selected input and output data sets. Training of the ANN is possible by adjusting ANN weights. Here, ANN weights are adjusted with artificial bee colony (ABC) algorithm. After adjusting process, the objective function based on ANN is optimized with ABC algorithm to get better Clβ and Emax, i.e. the ABC algorithm is used for two different purposes. Findings By using artificial intelligence methods for redesigning of morphing UAV, the objective function consisting of C*lβ and Emax is maximized. Research limitations/implications It takes quite a long time for Emax data to be obtained realistically by using the computational fluid dynamics approach. Practical implications Neural network incorporation with the optimization method idea is beneficial for improving Clβ and Emax. By using this approach, low cost, time saving and practicality in applications are achieved. Social implications This method based on artificial intelligence methods can be useful for better aircraft design and production. Originality/value It is creating a novel method in order to redesign of morphing UAV and improving UAV performance.

Purpose The purpose of this study is to increase maximum lift/drag ratio (Emax) of tactical unmanned aerial vehicles (TUAVs) via applying novel small aerodynamic modifications. Design methodology/approach A TUAV is manufactured in Erciyes University, Faculty of Aeronautics and Astronautics, Model Aircraft Laboratory. It has both passive and active morphing capabilities. Its nosecone and tailcone shapes are redesigned to improve Emax. Moreover, active flow control is also built on its wing for improving Emax. Findings Using these novel small aerodynamic modifications, considerable improvement on Emax is obtained. Research limitations/implications Permission of Directorate General of Civil Aviation in Turkey is required for testing TUAVs in real-time applications. Practical implications Small aerodynamic modifications such as nosecone-tailcone shape modifications and building active flow control on wing are very beneficial for improving Emax of TUAVs. Social implications Small aerodynamic modifications satisfy confidence, high performance and easy utility demands of TUAV users. Originality/value The study will enable the creation of novel approaches to improve Emax value and therefore aerodynamic performance of TUAVs.