Sizing of a Fully Integrated Hypersonic Commercial Airliner

Ingenito, Antonella; Gulli, Stefano; Bruno, Claudio; Colemann, G.; Chudoba, Bernd; Czysz, Paul A.

doi:10.2514/1.c000205

Cited by 11 publications

(10 citation statements)

References 8 publications

(16 reference statements)

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“…Of the three fuels that meet the high thrust requirement, beryllium offers the best yield. However, since the data available on beryllium are scarce, and there are no experimental data on the temperature auto ignition [3], that option was discarded, while recognizing its validity when more accurate data are available. Ideal performance of Aluminum and Magnesium reacting with CO2 in a rocket chamber have been calculated at 70 km altitude, and assuming the combustor inlet conditions at M = 8 flight speed, (i.e.…”

Section: Investigation Of Fuels For the Venusian Atmospherementioning

confidence: 98%

“…Recent studies [3] have shown that fuels that provide the best performance when reacting with the CO2-rich atmosphere of Mars/Venus are light metals such as beryllium, magnesium and aluminum. This is because of the high specific impulse potentially available is at the highest possible O/F ratio, therefore maximizing also thrust.…”

Section: Investigation Of Fuels For the Venusian Atmospherementioning

confidence: 99%

See 1 more Smart Citation

Feasibility of high speed atmospheric flight on Venus

Ingenito

Agresta

Andriani

et al. 2015

8th Symposium on Space Resource Utilization

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Exploring Venus is difficult, so far, probes have managed to survive only few hours. However, Venus' atmosphere, composed of 96.5 % CO2 might provide an unique opportunity for a airbreathing vehicle. In this context, this paper intends to study the feasibility of a scramjet/ramjet engine for flying in Venus' atmosphere at an altitude of ~70 km. The first part of the work focuses on the choice of fuel. The most promising candidates to burn in CO2 are metals and their hydrides. In this context, the analysis of a wider range of these candidates including lithium (Li), beryllium (Be), magnesium (Mg), aluminum (Al), silicon (Si), beryllium hydride (BeH2), magnesium hydride (MgH2) and silane (SiH4) has been done. Once the fuel with better performance was chosen, weight and volume of a supersonic aircraft capable of carrying 200 kg of payload and operating range of 1000 km were estimated. The results showed that with a total weight of 995 kg it is possible to keep the size of the aircraft within the limits imposed by modern launchers, leaving enough room and mass weights for an orbital module to be attached to a future venus sound spacecraft. Nomenclature η = combustion efficiency Splan [m 2] = Wing area. Fuel V [m 3] = Volume of fuel. W fuel [kg] = weight of the fuel. W str [kg] = Weight of the structure vacuum, without payload and propellant. V tot [m 3] = Total volume

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Section: Investigation Of Fuels For the Venusian Atmospherementioning

confidence: 98%

Section: Investigation Of Fuels For the Venusian Atmospherementioning

confidence: 99%

Feasibility of high speed atmospheric flight on Venus

Ingenito

Agresta

Andriani

et al. 2015

8th Symposium on Space Resource Utilization

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“…The L/D ratio is the most important parameter driving hypersonic flight range. Generally speaking, as speed increases past M = 1, the aerodynamic lift coefficient CL diminishes while drag increases and, past M ~ 3, L/D drops rapidly: Figure 1 shows aerodynamic test data for the maximum L/D (as a function of the angle of attack) starting at M = 3, together with two theoretical curves developed by Küchemann [3][4][5] in the 1970s. Both are partially satisfactory, in the sense that the theoretical curves fit only parts of the data, and the data themselves are scattered.…”

Section: Cruisersmentioning

confidence: 99%

Some Key Issues in Hypersonic Propulsion

Bruno

Ingenito

2021

Energies

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This paper summarizes and discusses some critical aspects of flying hypersonically. The first is the L/D (lift over drag) ratio determining thrust and that in turn depends on the slenderness Küchemann’s τ parameter. This second parameter is found to depend on the relative importance of wave versus friction drag. Ultimately, all engineering drag is argued to depend on vorticity formed at the expense of the vehicle kinetic energy, thus requiring work by thrust. Different mixing strategies are discussed and shown to depend also on mechanisms forming vorticity when the regime is compressible. Supersonic combustion is briefly analyzed and found, at sufficiently high combustor Mach, to take place locally at constant volume, unlike conventional Brayton cycles.

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“…6 Furthermore, in other cases, multidimensional or parametric analyses have been included to assess the reliability of the solutions. 7,8…”

Section: Introductionmentioning

confidence: 99%

“…6 Furthermore, in other cases, multidimensional or parametric analyses have been included to assess the reliability of the solutions. 7,8 In this context, this paper aims at further extending the current version of the MC methodology and tool to specifically manage the design of high-speed vehicles, providing updated and/or brand-new mathematical formulations to cope with the supersonic and hypersonic mission phases. The development of such a powerful tool, based on a rigorous methodology, will provide engineers with a valuable support to address the worldwide incentive to consider commercial high-speed transportation systems for both aeronautical and space applications.…”

Section: Introductionmentioning

confidence: 99%

Innovative Multiple Matching Charts approach to support the conceptual design of hypersonic vehicles

Ferretto

Fusaro

Viola

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Several well-established best practices and reliable tools have been developed along the years to support aircraft conceptual and preliminary design. In this context, one of the most widely used tool is the Matching Chart (MC), a graphical representation of the different performance requirements (curves representing the thrust-to-weight ratio (T/W) requirement as function of the wing loading (W/S)) for each mission phase. The exploitation of this tool allows the identification of a feasible design space as well as the definition of a reference vehicle configuration in terms of maximum thrust, maximum take-off weight, and wing surface since the very beginning of the design process. Although the tool was originally developed for conventional aircraft, several extensions and updates of the mathematical models have been proposed over the years to widen its application to innovative configurations. Following this trend, this paper presents a further evolution of the MC model to support the conceptual design of high-speed transportation systems, encompassing supersonic and hypersonic flight vehicles. At this purpose, this paper reports and discusses the updates of the methodology laying behind the generation of the MC for high-speed transportation. Eventually, the results of the validation of the updated methodology and tool are reported, using as case study, the STRATOFLY MR3 vehicle configuration, a Mach 8 antipodal civil transportation system, currently under development within the H2020 STRATOFLY project.

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Sizing of a Fully Integrated Hypersonic Commercial Airliner

Cited by 11 publications

References 8 publications

Feasibility of high speed atmospheric flight on Venus

Feasibility of high speed atmospheric flight on Venus

Some Key Issues in Hypersonic Propulsion

Innovative Multiple Matching Charts approach to support the conceptual design of hypersonic vehicles

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