Design of a tethered aerostat system for animal and bird hazard mitigation

Bajoria, Aditya; Mahto, Navin Kumar; Boppana, Chaitanya Kumar; Pant, Rajkumar S.

doi:10.1109/icraae.2017.8297244

Cited by 5 publications

(3 citation statements)

References 6 publications

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“…The aerostat design is an iterative process in which the size of hulls and fins is increased in every iteration until the system is capable of carrying the required payload mass (Pant and Kapoor, 2013; Kumar et al , 2016; Bajoria et al , 2017). The design process in detail has been presented by Pant and Kapoor (2013) that shows the process of calculation of the hull size, fin size, tether profile and confluence point.…”

Section: Methodsmentioning

confidence: 99%

“…The aerostat has a floating altitude of 300 m and systems with a floating height less than 500 m can be designed without a ballonet (Bajoria et al , 2017). The mass of the aerostat hull m h can be calculated by hull volume, surface area, LTA gas density ρ LTA and fabric density ρ f given in kilogram per square meter.…”

Section: Methodsmentioning

confidence: 99%

“…The symmetric NACA0018 airfoil is selected as fin cross-section in this study, following previous approaches (Lambert and Nahon, 2003; Bajoria et al , 2017). The aerostat fins are designed with the intent to be constructed from the same fabric material used for hull.…”

Section: Methodsmentioning

confidence: 99%

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The effect of hull fineness ratio and fin parameters on the optimization of tethered aerostat

Mahmood

Ismail

2021

AEAT

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Purpose This paper aims to optimize the mass of a tethered aerostat to achieve optimum hull volume, and fins to generate aerodynamic lift to reduce the blow-by. Design/methodology/approach The design code of aerostat involving structure, aerostatics, aerodynamics and stability has been developed using MATLAB®. The design code is used to obtain the baseline configuration for a tactical aerostat mission by using the statistical values of the hull fineness ratio and the fin parameters of in-service aerostats. The effect of the design variables that include the hull fineness ratio, fin area and fin position on the aerostat mass and blow-by is determined through sensitivity analysis. The aerostat is optimized with an objective function of minimization of mass for the bounded values of design variables and taking blow-by limit as a constraint. Findings This study reveals that the simultaneous optimization of the aerostat hull fineness ratio, fin area and fin position results in an improvement in the design. The aerostat design with optimum values of these parameters helps in a reduction in its size and mass without compromising the blow-by limits. Research limitations/implications This study has been conducted by keeping the hull shape constant by selecting standard National Physics Laboratory envelope shape. The aerodynamic model used in the design code is based on empirical relationships that can be improved in future studies that can use high fidelity aerodynamic models using CFD based surrogate models. Originality/value The previous studies on optimization of aerostats are limited to hull envelope shape only, whereas this paper presents the optimization of the hull and fin together. The optimized configuration obtained has a reduced mass and can operate within the specified blow-by limits.

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