An approach for shape optimization of stratosphere airships based on multidisciplinary design optimization

Wang, Quanbao; Chen, Jian; Gong-yi, FU; Duan, Dengping

doi:10.1631/jzus.a0820814

Cited by 34 publications

(14 citation statements)

References 8 publications

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“…This was achieved by imitating the morphological features of an aquatic animal (Physalia physalis). Other low-drag profiles were also reported for specific applications, such as the Zhiyuan shape [30] and Wang shape [42].…”

Section: Introductionmentioning

confidence: 85%

Stability Derivatives of Various Lighter-than-Air Vehicles: A CFD-Based Comparative Study

Anoop

Velamati

Janardhanan

et al. 2022

Drones

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An aerostat with a single tether is proposed for the application of wind measurements at low altitudes. In the current study, the aerodynamic model parameters (stability derivatives) of the aerostat are investigated based on a CFD-based approach. The static, as well as the dynamic stability derivatives of the aerostats are presented. The calculation of the dynamic stability derivatives involves the simulation of the oscillations of the aerostats in their axial direction (surge), the vertical direction (heave) and angular motions with respect to the lateral direction (pitch). A forced sinusoidal oscillation is used for the simulation of the aerostat, and one stable period of oscillation is taken for the derivatives’ extraction. Four different aerostats are considered for the current study with four different angles of attack. The Zhiyuan aerostat, HAA aerostat, NPL aerostat and GNVR aerostat are the aerostats considered for this study. The stability derivative results obtained for the four aerostats are analyzed and compared with respect to their geometrical features. From the static aerodynamic characteristics, the Zhiyuan aerostat shows better performance than the other aerostats in terms of the lift–drag ratio. The dynamic stability derivatives of the Zhiyuan aerostat suggest its application as the proposed low-altitude wind measurement system.

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Section: Introductionmentioning

confidence: 85%

Stability Derivatives of Various Lighter-than-Air Vehicles: A CFD-Based Comparative Study

Anoop

Velamati

Janardhanan

et al. 2022

Drones

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“…Yin et al (2019) has obtained an airship envelope with a fineness ratio of 3.2 through MDO. Wang et al (2009) obtained an optimized airship envelope with a fineness ratio of 2.7 for stress minimization, 3.7 for drag reduction and 3.2 for the composite objective function, respectively. The fineness ratio also depends upon the hull structure and for rigid hull used in earlier airships has a higher the fineness ratio between 4 and 8 (Gaspet, 1988).…”

Section: Hull Sizingmentioning

confidence: 99%

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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“…Table 4, in which , , and represent material thickness, differential pressure, and elastic modulus, respectively. Except for the constraints for the optimization variables, the envelope volume, which is directly related with the payload capacity and maximum operating altitude [41], is fixed as 12.6 × 10 4 m 2 . The value of is calculated based on the value of 1 and 2 .…”

Section: Optimization Of An Airship Envelopementioning

confidence: 99%

A Novel Multiobjective Optimization Method Based on Sensitivity Analysis

Sun

et al. 2016

Mathematical Problems in Engineering

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For multiobjective optimization problems, different optimization variables have different influences on objectives, which implies that attention should be paid to the variables according to their sensitivity. However, previous optimization studies have not considered the variables sensitivity or conducted sensitivity analysis independent of optimization. In this paper, an integrated algorithm is proposed, which combines the optimization method SPEA (Strength Pareto Evolutionary Algorithm) with the sensitivity analysis method SRCC (Spearman Rank Correlation Coefficient). In the proposed algorithm, the optimization variables are worked as samples of sensitivity analysis, and the consequent sensitivity result is used to guide the optimization process by changing the evolutionary parameters. Three cases including a mathematical problem, an airship envelope optimization, and a truss topology optimization are used to demonstrate the computational efficiency of the integrated algorithm. The results showed that this algorithm is able to simultaneously achieve parameter sensitivity and a well-distributed Pareto optimal set, without increasing the computational time greatly in comparison with the SPEA method.

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An approach for shape optimization of stratosphere airships based on multidisciplinary design optimization

Cited by 34 publications

References 8 publications

Stability Derivatives of Various Lighter-than-Air Vehicles: A CFD-Based Comparative Study

Stability Derivatives of Various Lighter-than-Air Vehicles: A CFD-Based Comparative Study

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

A Novel Multiobjective Optimization Method Based on Sensitivity Analysis

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