Structural Analysis of a Composite Target-drone

Park, Yong Bin; Nguyen, Khanh-Hung; Kweon, Jin‐Hwe; Choi, Jin‐Ho; Han, Jong-Su

doi:10.5139/ijass.2011.12.1.84

Cited by 21 publications

(9 citation statements)

References 7 publications

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“…Yong-Bin Park et al [9] did structural analysis for the wing and landing gear of a composite target-drone. The analysis predicted the maximum stress at the curved region where supports were attached to the landing gear and found safe.…”

Section: Literature Reviewmentioning

confidence: 99%

Simulation and Analysis of a Quadrotor UAV while Landing.

Sawalakhe,

Shaaikh

2020

IJRTE

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Unmanned aerial vehicles are widely used in military and civilian fields in recent years. Quadrotor Unmanned Aerial Vehicles (UAV) have high advantage among other UAV’s, in different categories, due to their ability to hover, and Vertical Take-Off and Landing (VTOL) capability. The mathematical simulation method can be adopted for analysis of UAV. The simulation method can reduce the flight period, cost and risk and improve its performance while Vertical take-off and landing (VTOL). While landing of UAV, the kinetic energy of vehicle is absorbed by UAV frame resulting in high stress concentration. The stresses are also produced in other parts of the UAV. The effect of the landing loads and stresses on the airframe of the quadrotor unmanned air vehicle must be completely understood and the UAV must be designed accordingly in order not to damage during landing.These stresses can be analyzed by simulation method to ensure the sustainability of UAV structure. This work includes structural and frequency analysis for Quadrotor UAV chassis.

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Section: Literature Reviewmentioning

confidence: 99%

Simulation and Analysis of a Quadrotor UAV while Landing.

Sawalakhe,

Shaaikh

2020

IJRTE

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“…The specimen geometry was created in MSC Patran. Models were meshed with 4-node shell elements (CQUAD) with the laminate option, where the definition of each ply is implemented [23]. A maximum stress failure criterion was used.…”

Section: Comparison Of Measured and Predicted Mechanical Propertiesmentioning

confidence: 99%

AFP mandrel development for composite aircraft fuselage skin

Kumar¹,

Ko²,

Roy³

et al. 2014

International Journal of Aeronautical and Space Sciences

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Automatic fiber placement (AFP) has become a popular processing technique for composites in the aerospace industry, due to its ability to place prepregs or tapes precisely in the exact position when complex parts are being manufactured. This paper presents the design, analysis, and manufacture of an AFP mandrel for composite aircraft fuselage skin fabrication. According to the design requirements, an AFP mandrel was developed and a numerical study was performed through the finite element method. Linear static load analyses were performed considering the mandrel structure self-weight and a 2940 N load from the AFP machine head. Modal analysis was also performed to determine the mandrel's natural frequencies. These analyses confirmed that the proposed mandrel meets the design requirements. A prototype mandrel was then manufactured and used to fabricate a composite fuselage skin. Material load tests were conducted on the AFP fuselage skin curved laminates, equivalent flat AFP, and hand layup laminates. The flat AFP and hand layup laminates showed almost identical strength results in tension and compression. Compared to hand layup, the flat AFP laminate modulus was 5.2% higher in tension and 12.6% lower in compression. The AFP curved laminates had an ultimate compressive strength of 1.6% to 8.7% higher than flat laminates. The FEM simulation predicted strengths were 4% higher in tension and 11% higher in compression than the flat laminate test results.

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“…The National Aerospace Laboratory (NLR) [8] evaluated the components of a composite landing gear and reported 20% weight reduction, 15% lower manufacturing costs, and reduced lead time. Park et al conducted a finite element analysis using NASTRAN for the wing and landing gear of a composite drone air vehicle [9]. They applied forces of 5 g and −1.5 g to the wing and 2 g to the main landing gear.…”

Section: Introductionmentioning

confidence: 99%

Design and Manufacture of Composite Landing Gear for a Light Unmanned Aerial Vehicle

et al. 2021

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Unmanned aerial vehicles (UAVs) have become popular for military applications as well as for use in structural inspection, weather monitoring, and festival demonstrations. Suitable landing gears to ensure that the UAV can take off and land safely are important when the price of the cargo and UAV increase. A lightweight and high-strength landing gear is desirable to overcome accidents during service. Composite materials are a promising, excellent solution for this purpose. This study demonstrated the design, numerical analysis (Ansys), manufacture, and experimental verification (LabVIEW) of a composite landing gear for a UAV. In particular, landing gears with different carbon fiber-reinforced polymer (CFRP) composite fiber orientations were analyzed, manufactured, and experimentally verified in this study.

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Structural Analysis of a Composite Target-drone

Cited by 21 publications

References 7 publications

Simulation and Analysis of a Quadrotor UAV while Landing.

Simulation and Analysis of a Quadrotor UAV while Landing.

AFP mandrel development for composite aircraft fuselage skin

Design and Manufacture of Composite Landing Gear for a Light Unmanned Aerial Vehicle

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