A Modular Sizing Model for High-Altitude/Long-Endurance Airships

Lobbia, Marcus; Gong, Richard

doi:10.2514/6.2006-821

Cited by 7 publications

(5 citation statements)

References 2 publications

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“…The propellers are currently available with an efficiency of higher than 80 percent, and mass of approximately 100 W/kg (Zhibin et al , 2007; Knaupp and Mundschau, 2004). As mentioned previously, and refer to papers associated with the modeling and analysis of high‐altitude airships (Xiaoliang and Xuexiong, 2006; Busman, 1995; Lobbia and Gong, 2006; Jenkins et al , 2005; Yangjin et al , 2003; Haifeng et al , 2007b; Wei et al , 2007; Ganglin et al , 2008), the details of baseline technology parameters for airship design in this paper are given in Table I.…”

Section: High‐altitude/long‐endurance Airship Parameters Sensitivity Analysismentioning

confidence: 99%

“…Several methodologies and procedures for obtaining baseline specifications of airship were available (Pant, 2003; Xiaoliang and Xuexiong, 2006; Busman, 1995; Lobbia and Gong, 2006; Jenkins et al , 2005; Wujun et al , 2007; Lan et al , 2007; Yangjin et al , 2003; Haifeng et al , 2007b; Wei et al , 2007; Ganglin et al , 2008). Pant (2003) presented a methodology for determination of baseline specifications.…”

Section: Introductionmentioning

confidence: 99%

“…Busman (1995) investigated the some parameters affecting altitude performance of tethered aerostats. Lobbia and Gong (2006) developed a spreadsheet model to provide subsystem‐level mass sizing of airship configurations. Jenkins et al (2005) demonstrated that genetic algorithms can be used to design high‐altitude reconnaissance vehicle.…”

Section: Introductionmentioning

confidence: 99%

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Configurations analysis for high‐altitude/long‐endurance airships

2010

Aircraft Engineering and Aerospace Technology

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PurposeIn recent years, high‐altitude/long‐endurance airship platforms have generated great interest as a means to provide communications and surveillance capabilities. The purpose of this paper is to develop a model for airship conceptual design and help provide insight into the viability of high‐altitude/long‐endurance airships.Design/methodology/approachA configuration analysis model with the consideration of pressure difference, temperature difference, and helium purity, etc. was developed. The influences of the airship payload, size and area required of solar cell with environment and operation parameters, such as operation latitude, pressure difference, temperature difference, helium purity, seasons, latitude, and wind speed, etc. were analyzed.FindingsThe results show that the area of solar cell required for stratospheric airship is very large under the condition of low altitude, high latitude, wind, and in winter, etc. which might make the design of high‐altitude/long‐endurance airship an elusive goal. They also show that the solar cell efficiency is the key technology in the control of solar cell area required for airships, and the technology advances in regenerative fuel cells and propeller efficiency have significant effects among on the airship payload, size, and solar cell area required for airship.Originality/valueThe paper analyses the energy balance of the high‐altitude/long‐endurance airship.

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Section: High‐altitude/long‐endurance Airship Parameters Sensitivity Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Configurations analysis for high‐altitude/long‐endurance airships

2010

Aircraft Engineering and Aerospace Technology

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“…So far, there are two mainly method to calculate the solar cells' surface power. One is to approximate the wing surface as a plane, then the solar cells power can be calculated [2][3][4][5]. This method is simple, but the calculation error is relatively large [6], and the error is not easy to control.…”

Section: Introductionmentioning

confidence: 99%

The Calculation and Analysis of UAV Solar Array Power Generation

Zhang

Wang

Guo

2014

AMR

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In view of the solar array of the solar wing UAV, this paper presents a method of using Bird model and HDKR model to calculate the solution of sun light intensity, and thus the power can be calculated. According to the engineering requirements, it is convenient to calculate the results using DO model in fluent software. Both methods are relatively easy to calculate the surface of the solar array power generation. Finally, this paper makes a detailed analysis on the UAV solar array power characteristics. The flight latitude, season, heading angle and pitch angle of the solar powered UAV have an influence on the power generation characteristics and rules. The results show that the power of the solar power generation quantity, is not only related with the attributes of the battery itself, but also greatly influenced by the weather, season, the UAV flight attitude as well as the latitude and longitude.

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“…Krausman analyzed that environment parameters had effects on the performance of tethered airship, such as temperature, pressure and wind and pointed out the numerous parameters which must be considered in sizing include such items as weight, material effects, temperature, pressure, and mission altitude and duration [4]. Marcus A. Lobbia and Richard H. Gong presented a modular sizing model which has been proved useful in implementing a variety of submodels, and identified that rigid airship configuration has more difficulties in capability of reaching high altitude using traditional approaches [5]. Jason E. Jenkins, etc applied genetic algorithms to optimal design the HARVe power generation system, subject to constraints on vehicle buoyancy and energy balance [6].…”

Section: Introductionmentioning

confidence: 99%

Analysis to Effects on Conceptual Parameters of Stratospheric Airship with Specified Factors

Chen¹,

Zhu²,

Sun³

2011

JCP

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<p>Stratospheric airship is capable of station-keeping at high altitude in precondition of the balance of buoyancy and weight, thrust and drag. Based on specific computation process, when some hypotheses are given, the length of airship can be calculated and it is emphasized to analyze the impacts on payload capability performance and conceptual parameters (such as length, surface area and volume) with altitude, latitude of station-keeping and pressure difference, temperature difference, helium purity. It is shown from the analyses that pressure difference, temperature difference and helium purity have fewer effects on payload capability and length of airship, and in contrast, altitude and latitude of station-keeping have the larger effects. On the other hand, effects on payload capability and length with each technology guideline are also discussed when specified operation parameters keep constant, such as altitude and design wind of station-keeping. It is concluded that the benefit to length and payload capability is the largest with improvement of envelope mass/area ratio but the least with improvement of propeller system efficiency.</p>

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A Modular Sizing Model for High-Altitude/Long-Endurance Airships

Cited by 7 publications

References 2 publications

Configurations analysis for high‐altitude/long‐endurance airships

Configurations analysis for high‐altitude/long‐endurance airships

The Calculation and Analysis of UAV Solar Array Power Generation

Analysis to Effects on Conceptual Parameters of Stratospheric Airship with Specified Factors

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