Operational Capability of High Altitude Solar Powered Airships

Miller, G.A.; Stoia, Tina; Harmala, Devin; Atreya, Shailesh

doi:10.2514/6.2005-7487

Cited by 12 publications

(11 citation statements)

References 3 publications

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“…As is well known, the output power of solar array on stratospheric airship is governed by the incident solar radiation on the array, the performance characteristics, the geometry of the solar array, the time of year (the day number) and stationary latitude [17]. To analyze the output power of solar array on stratospheric airship, fundamental assumptions made in this paper are as follows:…”

Section: Theorymentioning

confidence: 99%

“…The scattered radiation sij q on the tilted grid ij can be given by 181 (17) In the body coordinate system, the incident solar radiation is different with the change of position (characterized as the y coordinate and the rotation angle θ) on airship envelop when the time is certain. Therefore, it is conceivable to study incident solar radiation on the curved surface solar array during the day and night.…”

Section: Incident Solar Radiation Model On the Solar Arraymentioning

confidence: 99%

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Simplified Analytical Model for Investigating the Output Power of Solar Array on Stratospheric Airship

Zhang¹,

Li²,

Lv³

et al. 2016

International Journal of Aeronautical and Space Sciences

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Solar energy is the ideal power choice for long-endurance stratospheric airships. The output performance of solar array on stratospheric airship is affected by several major factors: flying latitude, flight date, airship's attitude and the temperature of solar cell, but the research on the effect of these factors on output performance is rare. This paper establishes a new simplified analytical model with thermal effects to analyze the output performance of the solar array. This model consisting of the geometric model of stratospheric airship, solar radiation model and incident solar radiation model is developed using MATLAB computer program. Based on this model, the effects of the major factors on the output performance of the solar array are investigated expediently and easily. In the course of the research, the output power of solar array is calculated for five airship's latitudes of 0°, 15°, 30°, 45° and 60°, four special dates and different attitudes of five pitch angles and four yaw angles. The effect of these factors on output performance is discussed in detail. The results are helpful for solving the energy problem of the long endurance airship and planning the airline.

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Section: Theorymentioning

confidence: 99%

Section: Incident Solar Radiation Model On the Solar Arraymentioning

confidence: 99%

Simplified Analytical Model for Investigating the Output Power of Solar Array on Stratospheric Airship

Zhang¹,

Li²,

Lv³

et al. 2016

International Journal of Aeronautical and Space Sciences

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“…where t day and t night are the day time and night time respectively, and they are calculated in energy subsystem; η convert is the convert efficiency from the solar array to the equipment for storing energy with the value 19 of η convert =88%-91%.…”

Section: Energy Requirement Of the Airshipmentioning

confidence: 99%

Conceptual Design Optimization of High Altitude Airship in Concurrent Subspace Optimization

Liang

Zhu

Guo

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Science and Technology on Aircraft Control LaboratoryMultidisciplinary design optimization (MDO) is introduced to the conceptual design optimization of high altitude airship (HAA). The framework of concurrent subspace optimization (CSSO), as a MDO methodology, is established for HAA conceptual design. Three subsystems, including aerodynamic and propulsion, structure, and energy subsystem, are discussed in detail. The coupled information in subsystem analysis is supplied by the response surface approximations. And the shape of envelope and the location of solar array are optimized simultaneously with the goal of minimum total mass. In addition, the optimization process and an optimal design that includes shape of envelope, location of solar array and weight components, are obtained. Nomenclature a = major radius of ellipse in Fig. 2 b = minor radius of ellipse in Fig. 2 C DV,hull = volumetric coefficient of the envelope drag which is based on V 2/3 C DV,total = volumetric coefficient of the total drag C F = coefficient of the skin friction D total = total drag of the airship E 0 = eccentricity correction factor of the Earth's orbit E t = different time g = standard specific gravitational force h = design altitude I 0n = intensity of the normal solar radiation without atmosphere attenuation I n = intensity of the normal solar radiation with atmosphere attenuation I SC = normal extraterrestrial solar radiation L = buoyance of the envelope L bg = rotation matrix from the north-east-down frame to the airship body frame L e , L s = local longitude and longitude of the standard meridian for the local time zone l = length of the envelope l I = direction of the rays from the Sun in the north-east-down frame MW gas = molecular weight of the lifting gas MW air = molecular weight of air m array = mass of solar array m c = mass of other components in structure subsystem m energy = mass of energy subsystem m fin = mass of fins 1 2 m gas = mass of the lifting gas m hull = mass of the envelope m payload = mass of payload m store = mass of equipment for storing energy m structure = mass of structure subsystem m thrust = mass of aerodynamic and propulsion subsystem m total = total mass of airship N = ratio C DV,total /C DV,hull n b = normal direction of solar array surface at some point P control = power to control system P payload = power to payload P thrust = power to overcome the drag of airship P total = total power requirement of the airship Q req = energy requirement among one day Q sup = energy supply generated by solar array among one day Re = Reynolds number S array = area of the solar array S fin = fin area S hull = surface area of the envelope T a = aerosol scattering and absorption attenuation factor to the solar radiation T g = permanent gas absorption attenuation factor to the solar radiation T R = Rayleigh scattering attenuation factor to the solar radiation T w = water vapor absorption attenuation factor to the solar radiation t day , t night = day time and night time t LAT , t LST = local apparent time and loca...

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“…A wing/airship arrangement can particularly be found in one of proposed wing/propulsion modules by Liu and Liou (2006), as well as in many envisioned airship concepts for the future (Snodgrass, 2007). Despite the fact that airships are constantly proposed for different missions (Wang et al , 2009; Dorrington, 2005; Newcome, 2006; Folks, 2008; Miller et al , 2005), a basic system engineering perspective reveals that many safety assessment processes associated with airships are more convoluted than airplanes. Different system usage choices at different phases of operation and shared functions between systems are examples of these complexities (Schaefer, 2002).…”

Section: Traces Of the Guav Technologiesmentioning

confidence: 99%

Ceramic engine considerations for future aerospace propulsion

Gohardani

2012

Aircraft Engineering and Aerospace Technology

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Purpose -The purpose of this paper is to outline the potential usage of ceramic engines in combination with other technologies as a possible propulsion contender for future aerospace applications. Design/methodology/approach -The possibility of enabling novel propulsion systems in aerospace engineering is examined through a multilateral review study concerning ceramic engines and a proposed design approach. In view of the benefits and challenges of employing ceramic engines as possible candidates for the sustainable solutions of the future, a fundamental design proposal is presented for a conceptual generic unmanned air vehicle (GUAV). Findings -The findings of this article identify a number of useful scenarios for future ceramic engine applications and considerations. Research limitations/implications -It is imperative to emphasize that this conceptual article solely sheds light on a limited number of key ideas associated with ceramic engines and their possible applications. Thus, many new areas may emerge and impact the application of ceramic engines in light of more in-depth conceptual studies. Practical implications -Implications of ceramic engine utilization in aeronautical applications may result in enhanced performance characteristics and less operational costs. Further implications could possibly be extended to various naval/automotive applications and new configurations of transportation vehicles. Social implications -The paper aims to generate an interest amongst younger individuals and environmental aware enthusiasts to consider ceramic engines for transportation applications to a greater extent than before. Originality/value -The implementation of this particular conceptual design results in a synergistic ceramic engine combination with a hybrid airship design in novel aeronautical applications.

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Operational Capability of High Altitude Solar Powered Airships

Cited by 12 publications

References 3 publications

Simplified Analytical Model for Investigating the Output Power of Solar Array on Stratospheric Airship

Simplified Analytical Model for Investigating the Output Power of Solar Array on Stratospheric Airship

Conceptual Design Optimization of High Altitude Airship in Concurrent Subspace Optimization

Ceramic engine considerations for future aerospace propulsion

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