Design of High Altitude Long Endurance UAV: Structural Analysis of Composite Wing using Finite Element Method

Rumayshah, Khodijah Kholish; Prayoga, Aditya; Moelyadi, Ing. Mochammad Agoes

doi:10.1088/1742-6596/1005/1/012025

Cited by 7 publications

(4 citation statements)

References 2 publications

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“…For aerospace applications it can be noticed that the shell elements are common choices for the wing skin, spar and rib models made of the layered composite materials [15][16][17][18]. FEM software can be used for the structural analysis of, for example, the composite wing made of woven carbon epoxy of unmanned aerial vehicle (UAV) [15]. In order to reduce the calculation time the numerical analysis can be performed only for one-half wing span due to symmetric geometrical structure.…”

Section: Description Of Experimental Resultsmentioning

confidence: 99%

Verification of FEM modelling of composite materials based on the results of static strength test

Gojny

2019

Mechanik

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The article presents the verification of FEM modelling of composite materials based on the results of static strength test. The aim of the work was to examine whether the applied modelling of composite materials is correct and verify it with finite element method (FEM). The composite structure of the PW-6U glider was used as a model. In the program the numerical model (geometry and finite element mesh) of the glider’s wing was created. The wing is made of glass fabrics and a spar with flanges with a glass roving. The composite structure of the wing, including composition, layout and thickness of laminate layers, fiber arrangement was exactly modelled in the program and then subjected to loads. Having the measurements from the static strength tests of the glider, the numerical results were compared with the experimental results. Thanks to the applied modelling, the obtained numerical results were satisfactory and very close to the experimental results from the structural static tests of the glider. Therefore, it can be concluded that the conducted verification of FEM modelling of composite materials is correct. Nowadays application of composite materials is increasingly expanding. Therefore, the modelling of composites becomes a significant issue. FEM modeling allows verification of the structure. At the stage of modelling modifications can be implemented and thus time and costs associated with subsequent changes in the production process may be saved. This is a very good solution which already at the design stage of the structure allows examination of its strength.

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Section: Description Of Experimental Resultsmentioning

confidence: 99%

Verification of FEM modelling of composite materials based on the results of static strength test

Gojny

2019

Mechanik

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“…In the last century, celestial navigation has been applied to aircrafts such as long-range bombers, large transport aircrafts and reconnaissance aircrafts [45]. In recent decades, unmanned aerial vehicles (UAVs) are increasingly developed and are used in a series of missions, including military and civil [46,47]. The development of long endurance UAVs is one of the focuses.…”

Section: B Potential Applicationsmentioning

confidence: 99%

An All-Day Attitude Sensor Integrating Stars and Sun Measurement Based on Extended Pixel Response of CMOS APS Imager

Cao

Zhan

et al. 2023

IEEE Trans. Instrum. Meas.

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For celestial measurement, it is difficult to enable a single optical system to image and measure both stars and the sun due to vastly different light intensity of targets and limited response capability of the image sensor pixel. Here, we develop an all-day optical attitude sensor integrating stars and the sun measurement based on extended pixel response model of the CMOS APS (Active-pixel sensor) imager. For extremely large light intensity, we extend the conventional pixel response model to the oversaturated stage where the pixel values reverse and drop below the saturation value. Based on this, the integration of the star sensor and the sun sensor is realized. The pixels image the starry sky with linear response, and make use of the oversaturation response to image the sun and obtain a black spot on the bright background. This principle enables the capability of all-day high-precision attitude measurement using a single miniaturized sensor. An integrated optical attitude sensor is designed and manufactured. Ground-based observation results show that the orientation accuracy from sun measurement is better than 9" (3σ), and the attitude accuracy from star measurement is better than 5" (3σ) for pointing and 11" (3σ) for rolling. The sensor can be applied to high-precision all-day navigation systems for miniaturized spacecrafts and aircrafts.

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“…Since, the space is considerably low in case of UAVs, the design of airframe should be such that all the required sensors and payloads can be mounted on the airframe, without compromising the aerodynamics or flight performance. Hence, the airframe plays a major role in the development of unmanned aerial vehicles [5].…”

Section: Introductionmentioning

confidence: 99%

Finite Element Analysis on the Arms of Multirotor UAV

Abuzar Ulla Khan,

Justus Shadrach J,

Karan H

et al. 2023

acsjse

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As the development and applications of UAV is been increasing significantly in various fields. The main focus is towards the design and structural analysis of the UAV. As the initial step of initialization of any UAV prior condition is to design. The structural analysis of a UAV frame is important since it has to withstand the forces due to aerodynamic and gravitational forces due to the mounted weights. As design optimisation plays an important role for an efficient structure, a finite element analysis provides an efficient methodology to meet the desired objectives related to structural elements. This project mainly focuses on the structural loads and vibrations acting on the arms of multirotor UAV. Finite element analysis is been carried out on the arms of multirotor UAV to understand the structural loads acting on the arms of the UAV. A small deformation occurred on the arms are safe and within the limit. Therefore, this study aimed to analyse the strength and durability of UAV arms during the in-flight conditions through the analysis.

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Design of High Altitude Long Endurance UAV: Structural Analysis of Composite Wing using Finite Element Method

Cited by 7 publications

References 2 publications

Verification of FEM modelling of composite materials based on the results of static strength test

Verification of FEM modelling of composite materials based on the results of static strength test

An All-Day Attitude Sensor Integrating Stars and Sun Measurement Based on Extended Pixel Response of CMOS APS Imager

Finite Element Analysis on the Arms of Multirotor UAV

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