Manufacturing Process and Flight Testing of an Unmanned Aerial Vehicle (UAV) with Composite Material

2016 ◽  
Vol 842 ◽  
pp. 311-318
Author(s):  
Gesang Nugroho ◽  
Ali Ashar Rafsan Jani ◽  
Ridho Ramadhan Trio Sadewo ◽  
Muhammad Satrio
Keyword(s):  
Composite Material ◽  
Unmanned Aerial Vehicle ◽  
Manufacturing Process ◽  
Flight Testing ◽  
Aircraft Flight ◽  
Good Surface ◽  
High Durability ◽  
Monitoring Process ◽  
Strong Material ◽  
Aerial Vehicle

The manufacturing process of lightweight and strong (Unmanned Aerial Vehicle) UAV and composite aircraft flight testing capability is described in this research. Nowadays, UAV development becomes more creative and high technology. Mapping and monitoring process from a UAV will be more effective and efficient. Mapping and monitoring process needs high durability UAV so that development with lightweight and strong material is needed. Lightweight technology is very suitable applied in the UAV technology. The composite material has many benefits for an aerodynamics world. The composite material was made of fiberglass and resin, and this material was used in components that are not loaded to high loads. The aircraft industry uses fiberglass composites widely because of the stiffness, strength, and toughness of composite.This research was conducted by manufacturing an aircraft with a fiberglass composite. The first manufacturing process was making a master prototype from styrofoam and then the styrofoam master was used to make a mold. The next process is called hand lay-up in which fiberglass and resin were laid to the model to produce half side of the aircraft. The process refined by vacuum bag to obtain a thin, flat, and good surface of the aircraft. Aircraft flight testing is needed to obtain statistical of the stability in pitch, roll and altitude, so the data result will determine the feasibility of composite aircraft in this research. The flight data have shown that the aircraft has high stability on roll and pitch.

Modeling and flight testing of wing shaping for roll control of an unmanned aerial vehicle

2015 ◽  
Vol 3 (4) ◽  
pp. 192-204 ◽  
Author(s):  
Michael A. Thamann ◽  
Suzanne Weaver Smith ◽  
Sean C.C. Bailey ◽  
E. Brady Doepke ◽  
Scott W. Ashcraft
Keyword(s):  
Numerical Model ◽  
Unmanned Aerial Vehicle ◽  
Flight Testing ◽  
Flight Tests ◽  
Autonomous Flight ◽  
Roll Control ◽  
Modeling Process ◽  
Aerodynamic Properties ◽  
Aerial Vehicle

In this paper, an approach is described to implement autonomous (waypoint tracking) flight in a testbed airframe, which uses wing twist for roll control. These flights were performed using an existing commercial autopilot. Aileron effectiveness was identified as a parameter that could be modified to maintain roll control during autonomous flight. A modeling process was then developed to calculate the aileron effectiveness for a wing shaping demonstrator aircraft utilizing numerically determined aerodynamic properties. Simulations and flight tests with the testbed aircraft were performed that demonstrated suitability of the approach for autonomous flight. In-flight aileron doublets were used to validate the aileron effectiveness predicted by the numerical model, which matched within 7%.

Analysis of an Additive Manufacturing Process for an Unmanned Aerial Vehicle

2017 ◽  
Vol 30 (6) ◽  
pp. 04017070
Author(s):  
Rafał Dalewski ◽  
Konrad Gumowski ◽  
Tomasz Barczak ◽  
Jan Godek
Keyword(s):  
Additive Manufacturing ◽  
Unmanned Aerial Vehicle ◽  
Manufacturing Process ◽  
Aerial Vehicle

Aero-structural numerical analysis of a blended wing body unmanned aerial vehicle using a jute-based composite material

2022 ◽  
Vol 49 ◽  
pp. 50-57
Author(s):  
Edgar Sarmiento ◽  
Carlos Díaz-Campoverde ◽  
José Rivera ◽  
Cristian Cruzatty ◽  
Edgar Cando ◽  
...  
Keyword(s):  
Composite Material ◽  
Numerical Analysis ◽  
Unmanned Aerial Vehicle ◽  
Aerial Vehicle ◽  
Blended Wing Body

scholarly journals Flight testing full conversion of a 40-kg-class tilt-duct unmanned aerial vehicle

2021 ◽  
pp. 106611
Author(s):  
Sungho Chang ◽  
Am Cho ◽  
Seongwook Choi ◽  
Youngshin Kang ◽  
Yushin Kim ◽  
...  
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Flight Testing ◽  
Aerial Vehicle ◽  
Full Conversion

THE DEVELOPMENT OF TILT-ROTOR UNMANNED AERIAL VEHICLE

2016 ◽  
Vol 40 (5) ◽  
pp. 909-921 ◽  
Author(s):  
Jie-Tong Zou ◽  
Pan Zheng-Yan
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Dynamic Equations ◽  
Tilt Rotor ◽  
Aircraft Flight ◽  
Aerial Vehicles ◽  
Flight Mode ◽  
Aerial Vehicle

In this research, we had developed quad-rotor unmanned aerial vehicles with the tilt-rotor mechanism. People are eager to fly therefore the development of aerial vehicles, such as fixed-wing aerial vehicles and multi-rotor aerial vehicles, has grown rapidly in recent years. The multi-rotor vertical take-off and landing (VTOL) unmanned aerial vehicle which can fly stably and hover in a fix position developed the fastest. Comparing the general fixed-wing aircrafts and rotorcrafts, fixed-wing aircrafts can fly with a higher speed than rotorcrafts, but they do not have the VTOL and hovering abilities. The proposed quad-rotor aerial vehicle with tilt-rotor mechanism has two flight modes: rotorcraft and fixed-wing aircraft flight mode. It can take-off and land vertically in rotorcraft mode and can also fly faster in fixed-wing aircraft flight mode. The dynamic equations of the proposed quad-rotor aerial vehicle with tiltrotor mechanism are also studied in this paper.

scholarly journals Stability study and flight simulation of a blended-wing-body UAV

2019 ◽  
Vol 304 ◽  
pp. 02013
Author(s):  
Thomas Dimopoulos ◽  
Pericles Panagiotou ◽  
Kyros Yakinthos
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Computational Simulation ◽  
Stability Study ◽  
Flight Simulation ◽  
Stability Studies ◽  
Aircraft Flight ◽  
Aerial Vehicle ◽  
Blended Wing Body ◽  
Drag Ratio ◽  
Lift To Drag Ratio

This article is a product of the design process of a Blended-Wing- Body Unmanned Aerial Vehicle (BWB UAV). The BWB geometry blends the wing and the fuselage so that the fuselage also contributes in lift generation. This geometry reduces the lift to drag ratio significantly, however it also compromises the aircraft’s stability and controllability, since there is no horizontal and vertical tail. As these features are absent from the BWB layout, the need to incorporate their functions in the new geometry arises so that they cover stability demands sufficiently, according to aircraft of similar size, use and speed. Additionally, the method used for stability studies of conventional aircraft must also be adapted. This article covers the adaptation of the method to the new BWB geometry, its results in comparison to those of conventional aircraft and the use of the results for a computational simulation of the aircraft’ flight.

scholarly journals Development of Unmanned Aerial Vehicle (UAV) Fixed-Wing for Monitoring, Mapping and Dropping applications on agricultural land

2021 ◽  
Vol 2111 (1) ◽  
pp. 012051
Author(s):  
ML Hakim ◽  
H Pratiwi ◽  
AC Nugraha ◽  
S Yatmono ◽  
ASJ Wardhana ◽  
...  
Keyword(s):  
Data Processing ◽  
Unmanned Aerial Vehicle ◽  
Development Process ◽  
Agricultural Land ◽  
Electronic Components ◽  
Monitoring Process ◽  
Mapping Process ◽  
Aerial Vehicle ◽  
The Military

Abstract UAV technology is used in various fields, namely the military, to strengthen defence, surveillance, dropping logistics. In addition, UAV applications are also used in agriculture. In this study, a fixed-wing UAV will be developed as a monitoring, mapping and dropping process. Several things were carried out in the development process, namely design, manufacturing, installing electronic components, and test flights. The results showed that the vehicle could carry out the mission well. The monitoring process is carried out to review land security. Besides that, it can monitor if there is a fire in agricultural land. In the mapping process, photo data processing taken in the context of the mapping is carried out into an orthophoto map. Meanwhile, in the dropping stage, the aircraft managed to drop a payload weighing 0.5 kg with a distance of 20m from a predetermined centre point. The dropped payload is also equipped with a parachute for increased safety and reduced speed when the payload is dropped.

scholarly journals The Application of Empty Palm Fruit Bunch (EPFB) As a Material for Fixed Wing Type Unmanned Aerial Vehicle Fuselage Production

2019 ◽  
Vol 63 (3) ◽  
pp. 13-16
Author(s):  
Muhammad Teguh ◽  
◽  
Kaspul Anuar ◽  
Muhammad Taslim ◽  
Rexy Guruh Saputra ◽  
...  
Keyword(s):  
Composite Material ◽  
Unmanned Aerial Vehicle ◽  
Impact Test ◽  
Alkali Treatment ◽  
Flight Test ◽  
Palm Fruit ◽  
Hybrid Composite Material ◽  
Aerial Vehicle ◽  
Deflection Test ◽  
Bagging Method

One of a potential application of Empty Palm Fruit Bunch (EPFB) is the material of fuselage on Unmanned Aerial Vehicle (UAV). This study was began by Alkali Treatment on EPFB. Then, the fuselage was molded using Vacuum Bagging Method. There are three unit of mold with combination of fiberglass + carbon fiber, fiberglass + EPFB fiber and full EPFB fiber. The measurement show fuselage with hybrid composite material (fiberglass and EPFB) has the lightest mass of 559 gram. Deflection Test of all three fuselages show that the maximum deflections were under 1 mm. Next, the Static Impact Test show no damages or cracks on all three fuselages. The result of Flight Test show all fuselages could do well fly and survive belly landing.

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