scholarly journals EXPERIMENTAL ANALYSIS OF DOUBLE BOX WING UAV.

2022 ◽  
pp. 14-19
Author(s):  
Sai Adithya Vanga ◽  
Moulshree Srivastava ◽  
Y. D. Dwivedi
Keyword(s):  
Wind Tunnel ◽  
Unmanned Aerial Vehicles ◽  
Preliminary Analysis ◽  
Computational Analysis ◽  
Computational Results ◽  
Wing Model ◽  
Induced Drag ◽  
Aerial Vehicles ◽  
Payload Capacity ◽  
Fuel Consumption And Emissions

In an attempt to reduce the induced drag on a wing, Prandtl found that induced drag reduced significantly by highly increasing the number of vertically offset wings. The same result could be obtained by joining the wingtips of two vertically offset wings. This helped increase payload capacity and also reduced fuel consumption and emissions. Such a wing configuration came to be known as Prandtl’s box wing. In this work, the design and analysis of a box wing aircraft model has been carried out. The preliminary analysis is performed using XFLR5, and the computational analysis is done with the help of ANSYS 18.2. The values of experiments are computed with the help of MATLab R2017. The box wing model has shown a nearly 53.74% reduction in drag as compared with conventional wing models. The computational results of drag have been compared and validated with the results of analytical and the experimental results from the wind tunnel and found to be within 10% of the computational result. Since the drag of the box wing is significantly lesser than the conventional wings the box wing is a feasible configuration which can be used to design various aircrafts including Unmanned Aerial Vehicles and Commercial Planes.

scholarly journals Box Wing: Aerodynamic experimental study for applications in MAVs

2020 ◽  
Author(s):  
Mohit SIngh ◽  
Jasmine Jerry Aloor ◽  
Annanya Singh ◽  
Sandeep Saha
Keyword(s):  
Wind Tunnel ◽  
Cfd Simulation ◽  
Lift Coefficient ◽  
Flow Visualisation ◽  
Scaled Model ◽  
Wing Model ◽  
Induced Drag ◽  
Aerial Vehicles ◽  
Stall Angle ◽  
Joined Wing

Advancements in the field of aerial robotics and micro aerial vehicles (MAVs) have increased the demand for high payload capabilities. Closed wing designs like the annular wing, the joined wing, the box wing and spiroid tip devices improve the aerodynamic performance by suppressing the wingtip vortices along with an enhanced lift coefficient. A box wing may be defined as a wing that effectively has two main planes which merge at their ends so that there are no conventional wingtips. We propose the implementation of box wings as the main lifting surface for such systems. Box wings have a potential of generating lift with considerably less induced drag and delayed stall angles than monoplane wings. We study the aerodynamic aspects of a box wing model using wind tunnel tests and numerical simulations. We conducted Computational Fluid Dynamics (CFD) simulation subjecting the model to a steady flow and later analysed the vortex core using CFD tools. Wind tunnel measurements of the forces were obtained using sting balance. Furthermore, polyester thread tufts and smoke flow visualisation were performed to understand the qualitative behaviour of the scaled model in the open to atmosphere, suction type tunnel. Our results reveal an increase in the lift to drag (L/D) ratio of the wing by 25 % and a delay in the model’s stall angle by +6° compared to a monoplane; implying a lower stalling speed for mini unmanned aerial vehicles (UAVs) and MAVs. These advancements if applied could revolutionize the capabilities of intelligent flying systems by enabling them to carry better sensors, computational units and other payloads as per the mission.

Design and manufacture of propellers for small unmanned aerial vehicles

2016 ◽  
Vol 4 (4) ◽  
pp. 228-245 ◽  
Author(s):  
Brian Rutkay ◽  
Jeremy Laliberté
Keyword(s):  
Additive Manufacturing ◽  
Wind Tunnel ◽  
Unmanned Aerial Vehicles ◽  
Wind Tunnel Testing ◽  
Performance Requirements ◽  
Propeller Design ◽  
Aerial Vehicles ◽  
Aircraft Performance ◽  
Design And Manufacture ◽  
Propeller Performance

The objective of this research was to develop a process for the design and manufacture of mission- and aircraft-specific propellers for small unmanned aerial vehicles. This objective was met by creating a computer program to design a propeller that meets user-defined aircraft performance requirements within the limitations of the electric motor, user-selected materials, and manufacturing methods. A comprehensive review of prior UAV propeller design and additive manufacturing for small propellers is also presented in this paper. The use of additive manufacturing (3D printing) in making flightworthy propellers was explored through material testing, manufacturing trials, and by testing the propellers under simulated flight conditions in a wind tunnel. It was found that the propeller performance generated nearly the predicted design thrust but the efficiency and power consumption could not be accurately measured with the present test setup. While flight testing was not completed at this time, ground and wind tunnel testing were sufficient to demonstrate the feasibility of producing flightworthy propellers using additive manufacturing.

Low Speed Aerodynamics of Drogue System Refueling of Unmanned Aerial Vehicles

2014 ◽  
Vol 1016 ◽  
pp. 349-353 ◽  
Author(s):  
Ian R. McAndrew ◽  
Elena Navarro ◽  
Orin Godsey
Keyword(s):  
Wind Tunnel ◽  
Unmanned Aerial Vehicles ◽  
Weather Conditions ◽  
Military Strategy ◽  
Wind Tunnel Experiments ◽  
Low Speed ◽  
Significant Aspect ◽  
Aerial Vehicles ◽  
Low Speeds

Refueling aircraft has become a significant aspect of military strategy for air forces to work at further distances from safe shores. This paper will address the aerodynamics of the drogue refueling system and in particular its characteristics at low speeds, including head and tail winds. Data from wind tunnel experiments are used to show how the docking when refueling is affected by the lower speeds, position behind the supply aircraft and weather conditions. Possibilities of design improvements and implications are related to the task of refueling Unmanned Aerial Vehicles in-flight

scholarly journals Analisis Flutter Pada Uji Model Separuh Sayap Pesawat N219 di Terowongan Angin Kecepatan Rendah

WARTA ARDHIA ◽  
2017 ◽  
Vol 42 (4) ◽  
pp. 165
Author(s):  
Sayuti Syamsuar ◽  
Muhamad Kusni ◽  
Adityo Suksmono ◽  
Muhamad Ivan Aji Saputro
Keyword(s):  
Wind Tunnel ◽  
Computational Analysis ◽  
Aerodynamic Force ◽  
Unstable Condition ◽  
Low Speed ◽  
Wing Flutter ◽  
Flutter Speed ◽  
Wing Model ◽  
Speed Range ◽  
Low Speed Wind Tunnel

Fenomena flutter akan terjadi apabila ada gaya dan momen aerodinamika yang berinteraksi berlebihan di permukaan sayap di dalam terowongan angin atau pesawat sesungguhnya. Sayap akan bergetar dan berosilasi bertambah besar menuju ke keadaan tidak stabil. Osilasi osilasi membuat osilasi yang lebih besar terjadi sehingga frekuensi dan damping pada daerah kecepatan tertentu dengan mudah terlihat apabila terjadi flutter pada model separuh sayap. Penelitian ini, digunakan model separuh sayap dari pesawat N219 yang di uji pada terowongan angin kecepatan rendah BBTA3, kawasan Puspiptek, Serpong. Kecepatan flutter terjadi pada 40,5 m/s pada hasil analisis komputasional dan hasil pengujian di terowongan angin sebesar 40,83 m/s. [The Analysis of Half Wing Flutter Test N219 Aircraft Model in The Low Speed Wind Tunnel] The flutter phenomenon will occur when the aerodynamic force and moment excessively interacted on the wing surface, whether it takes place in the wind tunnel or on the real aircraft. The wing will vibrate and oscillate towards an unstable condition. Each oscillation will subsequently build a greater one until the damping and frequency on a certain speed range can be seen easily when flutter occur on the half wing model. On this research, the half wing model of N219 aircraft was tested in the low speed wind tunnel of BBTA3, Puspitek Serpong. The flutter speed occurred at 40,5 m/s based on computational analysis while the wind tunnel result is at the speed of 40,83 m/s.

scholarly journals Unmanned Aerial Vehicles for Magnetic Surveys: A Review on Platform Selection and Interference Suppression

Drones ◽  
2021 ◽  
Vol 5 (3) ◽  
pp. 93
Author(s):  
Yaoxin Zheng ◽  
Shiyan Li ◽  
Kang Xing ◽  
Xiaojuan Zhang
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Hot Spot ◽  
Low Cost ◽  
Research Fields ◽  
Aerial Vehicles ◽  
Increased Risk ◽  
Payload Capacity ◽  
Pros And Cons ◽  
Low Altitude

In the past two decades, unmanned aerial vehicles (UAVs) have been used in many scientific research fields for various applications. In particular, the use of UAVs for magnetic surveys has become a hot spot and is expected to be actively applied in the future. A considerable amount of literature has been published on the use of UAVs for magnetic surveys, however, how to choose the platform and reduce the interference of UAV to the collected data have not been discussed systematically. There are two primary aims of this study: (1) To ascertain the basis of UAV platform selection and (2) to investigate the characteristics and suppression methods of UAV magnetic interference. Systematic reviews were performed to summarize the results of 70 academic studies (from 2005 to 2021) and outline the research tendencies for applying UAVs in magnetic surveys. This study found that multi-rotor UAVs have become the most widely used type of UAVs in recent years because of their advantages such as easiness to operate, low cost, and the ability of flying at a very low altitude, despite their late appearance. With the improvement of the payload capacity of UAVs, to use multiple magnetometers becomes popular since it can provide more abundant information. In addition, this study also found that the most commonly used method to reduce the effects of the UAV’s magnetic interference is to increase the distance between the sensors and the UAV, although this method will bring about other problems, e.g., the directional and positional errors of sensors caused by erratic movements, the increased risk of impact to the magnetometers. The pros and cons of different types of UAV, magnetic interference characteristics and suppression methods based on traditional aeromagnetic compensation and other methods are discussed in detail. This study contributes to the classification of current UAV applications as well as the data processing methods in magnetic surveys.

scholarly journals Computational Analysis and Optimization of Boxwing Aircraft for Reducing Induced Drag

2020 ◽  
Vol 9 (4) ◽  
pp. 1966-1972
Keyword(s):  
Computational Analysis ◽  
Computational Results ◽  
Military Aircraft ◽  
Commercial Aircraft ◽  
Tip Vortices ◽  
Aircraft Wings ◽  
Induced Drag ◽  
Front Wing ◽  
Commercial Aircrafts

The paper describes the importance of reducing induced drag built up due to tip vortices which is caused by the lift produced by the aircraft wings. In this paper the effectiveness of boxwing is improved by reducing the induced drag on the boxwing. With this the practicality of boxwing rises to new level.The airfoil impact on the boxwing is studied and different airfoils are selected accordingly. Supercritical airfoils are analyzed and its importance is applied to boxwing as their practicality is observed. Here the effect of different supercritical airfoils when used for the front wing, aft wing and winglet according to their functionality are analyzed in the paper using sophisticated software. Then by selecting a specified commercial aircraft we can check the normal conventional wing computational results comparing the same aircraft with boxwing configuration on it. By this comparison we can determine by what percentage we would decrease the induced drag with the usage of boxwing configuration. The following work is done to ensure that the boxwing is applied into practical aircrafts such commercial aircrafts hence we have used a commercial aircraft as the base to determine boxwing effectiveness in a commercial perspective also. With the results of this paper one can decrease the induced drag to an extent where the uses of the boxwing in commercial aircrafts will exceed that of the conventional winged aircrafts. In future, its application to military aircraft can also be deduced as supercritical airfoils are also being used in fighter jets.

Extractor X — Autonomous Tilt Rotor UAV

2013 ◽  
Vol 01 (02) ◽  
pp. 177-198 ◽  
Author(s):  
Joshua Jang En Chao
Keyword(s):  
Wind Tunnel ◽  
Unmanned Aerial Vehicles ◽  
Potential Role ◽  
Theoretical Calculations ◽  
Flight Mechanics ◽  
Tilt Rotor ◽  
Aerial Vehicles ◽  
Military Applications ◽  
Wind Tunnel Data ◽  
Near Future

This paper looks into conceptualization, implementation and validation of the potential role that hybrid quad tilt rotor unmanned aerial vehicles (UAV) may undertake in the near future, especially so in military applications. A tilt rotor is designed, built and analyzed with wind tunnel data, theoretical calculations and flight log data. In addition, the paper will discuss the flight mechanics involved during its transition from hover to forward flight. As the tandem wing tilt rotor encompasses two unconventional designs, numerous mathematical models were developed in the design of the UAV.

scholarly journals Reduction of the head-up pitching moment of small quad-rotor unmanned aerial vehicles in uniform flow

2017 ◽  
Vol 10 (1) ◽  
pp. 85-105 ◽  
Author(s):  
Hikaru Otsuka ◽  
Daisuke Sasaki ◽  
Keiji Nagatani
Keyword(s):  
Wind Tunnel ◽  
Unmanned Aerial Vehicles ◽  
Uniform Flow ◽  
The Body ◽  
Pitching Moment ◽  
Aerial Vehicles ◽  
Flow Interactions ◽  
Wire Method ◽  
The Moment ◽  
Cruise Flight

Multi-rotor unmanned aerial vehicles are unstable in headwind because of nose-up pitching moment generation and thrust degradation. Reducing the pitching moment generation could enhance the tolerance of the unmanned aerial vehicles to wind and improve cruise flight speed. In this study, a canted rotor configuration was proposed to reduce the moment in uniform flow and examined. The objective of the study is to evaluate the effect of moment reduction by canted rotors. First, flow interactions between rotors of the quad-rotor were visualized using a smoke wire method. Second, the moment reduction by canted rotors was estimated based on isolated rotor performance. Third, the moment of the quad-rotor varying the body pitching angle was examined using a wind tunnel. At an 8 m/s wind, when the body pitching angle is horizontal, slanting the rotor by 20° to outside the body degraded the moment by 26% compared with the parallel rotor configuration.

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