Design of a Low-Cost Fixed Wing UAV

Ariyanto, Mochammad; Setiawan, Joga Dharma; Prabowo, Teguh; Haryanto, Ismoyo

doi:10.1051/matecconf/201815902045

Cited by 7 publications

(7 citation statements)

References 2 publications

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“…Thus, field work was done to refine payload weight estimates for the missions that made the cut. The new and distinctive link between payload weight and total weight of BWB UAV is derived from the established relationship provided by Equation (1). The typical comprehensive representations of link between payload mass and overall UAV mass are shown in Figure 1.…”

Section: Conceptual Designmentioning

confidence: 99%

“…The authors additionally go over the advantages and disadvantages of each design, starting with the former. According to the literature [1], UAVs with a high wing are the most reliable option for use in life-or-death situations. Mediumrange long-endurance unmanned aerial vehicle (MALE UAV) concept design with blended wing-body architecture is the focus of this article.…”

Section: Introductionmentioning

confidence: 99%

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Design, Computational Aerodynamic, Aerostructural, and Control Stability Investigations of VTOL-Configured Hybrid Blended Wing Body-Based Unmanned Aerial Vehicle for Intruder Inspections

Raja¹,

Murugesan

Solaiappan³

et al. 2023

International Journal of Aerospace Engineering

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Unmanned aerial vehicles (UAVs) are gaining in popularity and sophistication in today’s modern world. UAVs are now available in a wide range of configurations. A UAV’s many applications include aerial photography and videography and target tracking. The upward-pointing propellers of some modern fixed-wing UAVs make it possible for them to take off and land vertically. Surveillance and intruder inspections are two areas where the blended wing body (BWB) configuration shines. This is because its weight is spread uniformly throughout the body, its radar signal is weaker than that of alternative configurations, and there is a relatively small amount of interference with its movement. With common design factors in mind, like vertical takeoff and landing, aerodynamic drag, and fundamental wing stability, the optimal BWB plan form for surveillance is designed. CATIA is used to finish the conceptual design of the BWB-based UAV. A fluid-structure interaction (FSI) study is carried out after the model has been examined in ANSYS Fluent. The UAV’s responsiveness is improved through simulation in the MATLAB environment after a proportional-integral-derivative-type altitude controller was developed. The results demonstrate that providing the UAV with an altitude instruction enhances its performance. Given the flexibility of the suggested BWB UAV’s design, we have decided to limit its maximum forward speed to 75 m/s and its maximum rate of vertical ascension to 50 m/s. Rapid BWB UAVs like the one seen here are quite helpful in dangerous situations.

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Section: Conceptual Designmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Design, Computational Aerodynamic, Aerostructural, and Control Stability Investigations of VTOL-Configured Hybrid Blended Wing Body-Based Unmanned Aerial Vehicle for Intruder Inspections

Raja¹,

Murugesan

Solaiappan³

et al. 2023

International Journal of Aerospace Engineering

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“…This paper discusses the three conventional types of UAV configurations by comparing the parameters such as ease of manufacturing process, stability, ease of hand launch, mass, and ground clearance and allotting the weightage between one and five. The conventional configuration with a high-wing UAV is efficient for basic applications [ 17 ].…”

Section: Related Workmentioning

confidence: 99%

Quality-of-Service-Centric Design and Analysis of Unmanned Aerial Vehicles

Jha

Prakash

Rathore

et al. 2022

Sensors

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Recent years have witnessed rapid development and great indignation burgeoning in the unmanned aerial vehicles (UAV) field. This growth of UAV-related research contributes to several challenges, including inter-communication from vehicle to vehicle, transportation coverage, network information gathering, network interworking effectiveness, etc. Due to ease of usage, UAVs have found novel applications in various areas such as agriculture, defence, security, medicine, and observation for traffic-monitoring applications. This paper presents an innovative drone system by designing and developing a blended-wing-body (BWB)-based configuration for next-generation drone use cases. The proposed method has several benefits, including a very low interference drag, evenly distributed load inside the body, and less radar signature compared to the state-of-the-art configurations. During the entire procedure, a standard design approach was followed to optimise the BWB framework for next-generation use cases by considering the typically associated parameters such as vertical take-off and landing and drag and stability of the BWB. Extensive simulation experiments were performed to carry out a performance analysis of the proposed model in a software-based environment. To further confirm that the model design of the BWB-UAV is fit to execute the targeted missions, the real-time working environments were tested through advanced numerical simulation and focused on avoiding cost and unwanted wastages. To enhance the trustworthiness of this said computational fluid dynamics (CFD) analysis, grid convergence test-based validation was also conducted. Two different grid convergence tests were conducted on the induced velocity of the Version I UAV and equivalent stress of the Version II UAV. Finite element analysis-based computations were involved in estimating structural outcomes. Finally, the mesh quality was obtained as 0.984 out of 1. The proposed model is very cost-effective for performing a different kind of manoeuvring activities with the help of its unique design at reasonable mobility speed and hence can be modelled for high-speed-based complex next-generation use cases.

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“…Aspect ratios between 3 and 6 are most frequently utilized for small, remote-controlled aircraft. Given that the UAV's wingspan is 1300 mm, and its mean chord length is 265 mm, the aspect ratio calculation yields a value of 4.91 as shown in Figure 2, still in the small UAV aspect ratio range [16] [17].…”

Section: Wingmentioning

confidence: 99%

Low-Cost of Fix-Wing Prototype Using Zimmerman Design

Mansor

Baki²,

Noor³

et al. 2022

ARASET

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This paper discussed the design and development of a fix-wing UAV that uses a Zimmerman parameter. To increase structural strength, a material made of expanded polypropylene and expanded polystyrene was used. Using a bagging vacuum technique for 24 hours, the structural strength procedure thoroughly combines the resin and fiber. The Zimmerman graph, generated at speeds between 50,000 and 200,000 using Reynolds Numbers (RE), was analyzed using three key variables: the coefficient of lift, drag, and the angle of attack (Alpha) of the airfoil. At 10o, the airfoil started to stall based on indicated coefficient used. The test flight is also comprised of pitch and roll flight with adequate force and little overshoot between the autopilot's requirement and the small aircraft's actual performance.

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Design of a Low-Cost Fixed Wing UAV

Cited by 7 publications

References 2 publications

Design, Computational Aerodynamic, Aerostructural, and Control Stability Investigations of VTOL-Configured Hybrid Blended Wing Body-Based Unmanned Aerial Vehicle for Intruder Inspections

Design, Computational Aerodynamic, Aerostructural, and Control Stability Investigations of VTOL-Configured Hybrid Blended Wing Body-Based Unmanned Aerial Vehicle for Intruder Inspections

Quality-of-Service-Centric Design and Analysis of Unmanned Aerial Vehicles

Low-Cost of Fix-Wing Prototype Using Zimmerman Design

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