ANALYSIS OF UAVs FLIGHT CHARACTERISTICS

Prisacariu, Vasile

doi:10.19062/1842-9238.2018.16.3.4

Cited by 7 publications

(5 citation statements)

References 4 publications

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“…XFLRv5 gives three option for analysis purposes, which are LLT (Lifting Line Theory), panel methods and VLM(Vortex Lattice Method). LLT does not give accurate results for low aspect ratio wings with large amount of sweep and dihedral angles [43]. Since FWMAV has all these geometrical features, LLT option was therefore not selected in XFLRv5 for analysis of FWMAV with varying elevon deflections.…”

Section: Elevon Control Derivativesmentioning

confidence: 99%

Airfoil Selection Procedure, Wind Tunnel Experimentation and Implementation of 6DOF Modeling on a Flying Wing Micro Aerial Vehicle

et al. 2020

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Airfoil selection procedure, wind tunnel testing and an implementation of 6-DOF model on flying wing micro aerial vehicle (FWMAV) has been proposed in this research. The selection procedure of airfoil has been developed by considering parameters related to aerodynamic efficiency and flight stability. Airfoil aerodynamic parameters have been calculated using a potential flow solver for ten candidate airfoils. Eppler-387 proved to be the most efficient reflexed airfoil and therefore was selected for fabrication and further flight testing of vehicle. Elevon control surfaces have been designed and evaluated for longitudinal and lateral control. The vehicle was fabricated using hot wire machine with EPP styrofoam of density 50 Kg/ m 3 . Static aerodynamic coefficients were evaluated using wind tunnel tests conducted at cruise velocity of 20 m/s for varying angles of attack. Rate derivatives and elevon control derivatives have also been calculated. Equations of motion for FWMAV have been written in a body axis system yielding a 6-DOF model. It was found during flight tests that vehicle conducted coordinated turns with no appreciable adverse yaw. Since FWMAV was not designed with a vertical stabilizer and rudder control surface, directional stability was therefore augmented through winglets and high wing leading edge sweep. Major problems encountered during flight tests were related to left rolling tendency. The left roll tendency was found inherent to clockwise rotating propeller as ‘P’ factor, gyroscopic precession, torque effect and spiraling slipstream. To achieve successful flights, many actions were required including removal of excessive play from elevon control rods, active actuation of control surfaces, enhanced launch speed during take off, and increased throttle control during initial phase of flight. FWMAV flew many successful stable flights in which intended mission profile was accomplished, thereby validating the proposed airfoil selection procedure, modeling technique and proposed design.

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Section: Elevon Control Derivativesmentioning

confidence: 99%

Airfoil Selection Procedure, Wind Tunnel Experimentation and Implementation of 6DOF Modeling on a Flying Wing Micro Aerial Vehicle

et al. 2020

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“…Although an airfoil profile is provided by Azuma and Okuno (1987) , difficulties in designing a self-stabilizing airfoil based on it (from early tests with XFLR5) were encountered. Thus, our design starting point utilized a self-stabilizing Fauvel airfoil Prisacariu (2018) , which was then geometrically modified to match the Javan cucumber seed’s shape, as seen in Figure 3A . In this manner, the camber of the flying seed is also accounted for.…”

Section: Methodsmentioning

confidence: 99%

Transient bio-inspired gliders with embodied humidity responsive actuators for environmental sensing

Wiesemüller

Meng

et al. 2022

Front. Robot. AI

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Collecting temporal and spatial high-resolution environmental data can guide studies in environmental sciences to gain insights in ecological processes. The utilization of automated robotic systems to collect these types of data can maximize accuracy, resilience, and deployment rate. Furthermore, it reduces the risk to researchers deploying sensors in inaccessible environments and can significantly increase the cost-effectiveness of such studies. The introduction of transient robotic systems featuring embodied environmental sensors pushes towards building a digital ecology, while introducing only minimal disturbance to the environment. Transient robots made from fully biodegradable and non-fossil based materials, do not develop into hazardous e-waste at the end of their lifetime and can thus enable a broader adoption for environmental sensing in the real world. In this work, our approach towards the design of transient robots includes the integration of humidity-responsive materials in a glider, which is inspired by the Alsomitra macrocarpa seed. The design space of these gliders is explored and their behavior studied numerically, which allows us to make predictions on their flight characteristics. Results are validated against experiments, which show two different gliding behaviors, that can help improve the spread of the sensors. By tailoring the Cellulose-Gelatin composition of the humidity actuator, self-folding systems for selective rainwater exposure can be designed. The pH sensing layer, protected by the actuator, provides visual feedback on the pH of the rainwater. The presented methods can guide further concepts developing transient aerial robotic systems for sustainable, environmental monitoring.

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“…Peneltian yang berkaitan dengan analisis aerodinamika dengan menggunakan perangkat lunak XFLR5 telah dilakukan oleh [1], [2] dan [3]. Pada penelitian yang dilakukan menunjukkan hasil simulasi XFLR5 dapat dijadikan untuk menganalisis karakteristik aerodinamika.…”

Section: Pendahuluanunclassified

“…Oleh karena itu berdasarkan nilai parameter yang didapat dan nilai M yang diperoleh dari referensi dapat dilakukan perhitungan pada Persamaan (11). Hasil perhitungan disajikan pada Tabel (2) Berdasarkan Tabel (2)dan Gambar (3c), diperoleh nilai sebesar 8.143, gradien C Lα yang baru sebesar 0.068 dan kofisien gaya hambat pada saat α = 0 sebesar 0.01698. Kedua nilai ini digunakan untuk menghitung koefisien gaya angkat yang baru dengan menggunakan rumus dibawah ini Memperhatikan Gambar (4c), ada perbandingan yang cukup signifikan yaitu pada grafik lama tidak diperoleh gaya angkat maksimal dan sudut stall.…”

Section: Metodologi Penelitianunclassified

Terapan Fungsi Sigmoid Untuk Menentukan Nilai Maksimal Koefisien Gaya Angkat Dan Sudut Stall Pada Kurva Linear Cl Terhadap Α

Septiyana

et al. 2022

puc

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Karya tulis ilmiah ini membahas tentang terapan fungsi sigmoid untuk menentukan nilai maksimal gaya angkat dan sudut stall pada pesawat berdasarkan hasil simulasi dengan menggunakan perangkat lunak XFLR5.Nilai maksimal gaya angkat dan sudut stall pada sebuahpesawatmerupakankomponenyangharusdiketahuiagarpesawattidakmengalamistall. Dimana pada saat pesawat sudah mencapai sudut stall pesawat akan kehilangan gaya angkat dan menyebabkan pesawat jatuh. Perangkat lunak XFLR5 digunakan untuk mensimulasikan sertauntukmendapatkankurvakoefisiengayaangkat CLterhadapsudutserang α. Hasilsimulasi dengan menggunakan perangkat lunak XFLR5 menunjukkan grafik CL terhadap α bersifat linear yang artinya tidak dapat diketahui dimana koefisien gaya angkat maksimal dan sudut serang dimana pesawat mengalami stall. Hasil penelitian ini fungsi sigmoid ini dapat diterapkan untuk menentukan nilai maksimal koefisien gaya angkat dan sudut stall dari pesawat. Penelitian yang dilakukan dengan memilih nilai transition rate M sebesar 0.8 diperoleh hasilnilai koefisien gaya angkat maksimal 1.2648 dan sudut stall sebesar 13◦

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ANALYSIS OF UAVs FLIGHT CHARACTERISTICS

Cited by 7 publications

References 4 publications

Airfoil Selection Procedure, Wind Tunnel Experimentation and Implementation of 6DOF Modeling on a Flying Wing Micro Aerial Vehicle

Airfoil Selection Procedure, Wind Tunnel Experimentation and Implementation of 6DOF Modeling on a Flying Wing Micro Aerial Vehicle

Transient bio-inspired gliders with embodied humidity responsive actuators for environmental sensing

Terapan Fungsi Sigmoid Untuk Menentukan Nilai Maksimal Koefisien Gaya Angkat Dan Sudut Stall Pada Kurva Linear Cl Terhadap Α

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