Design Analysis of the High-Speed Experimental Flight Test Vehicle HEXAFLY-International

Favaloro, Nunzia; Rispoli, Attilio; Vecchione, Ludovico; Pezzella, Giuseppe; Carandente, Valerio; Scigliano, Roberto; Cicala, Marco; Morani, Gianfranco; Steelant, Johan

doi:10.2514/6.2015-3607

Cited by 19 publications

(12 citation statements)

References 6 publications

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“…A modified HL-20 lifting-body model [20] is adopted here. In this model, C D is in a quadratic correlation with C L , as shown in (3). C D0 and K D are decided by Mach number (or kinetic energy), as shown in (4) and (5).…”

Section: Periodic Hypersonic Cruise Trajectory a Problem Formulamentioning

confidence: 99%

“…Its high speed is helpful to shorten endurance, especially that of long-range flights. This advantage facilitates the research of hypersonic airliners such as LAPCAT [1], HIKARI [2], and HEXAFLY-Int [3], [4]. Besides, the high speed also endows hypersonic missiles like Boeing X-51A [5], [6] with high penetration ability [7], which is desirable in military [8].…”

Section: Introductionmentioning

confidence: 99%

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Optimal Periodic Control of Hypersonic Cruise Vehicle: Trajectory Features

et al. 2019

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Optimal periodic control is an effective technique to reduce aerodynamic heating and fuel consumption of hypersonic cruise vehicles. Herein, this optimal control problem has been solved by nonlinear programming and passed the posteriori check of optimality. The results indicate that the lift coefficient and velocity in dynamical model could be recognized as constants. Accordingly, the original 3D system consists of velocity, flight path angle, and altitude, which could be decoupled into a 2D subsystem and a 1D one. The 2D subsystem could describe the correlation between the flight path angle and altitude. And the period length is mainly dependent on the maximum altitude difference. The 1D subsystem has been proved to be feasible to describe the variation of kinetic energy or velocity. On basis of the subsystems, the heating and fuel performances of periodic cruise have been studied. The heating performance is mainly dependent on the maximum altitude difference, and the fuel consumption is mainly dependent on the drag coefficient. The features concluded in this paper can support rapid trajectory planning or suboptimal feedback design of hypersonic cruise vehicles. INDEX TERMS Optimal periodic control, hypersonic cruise vehicle, trajectory features, performances.

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Section: Periodic Hypersonic Cruise Trajectory a Problem Formulamentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Optimal Periodic Control of Hypersonic Cruise Vehicle: Trajectory Features

et al. 2019

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“…The HEXAFLY-INT mission is conceived to achieve a hypersonic levelled flight at an altitude of about 30 km, while being injected from a semi-ballistic trajectory depicted in Figure 3, and described below. 4 The vehicle (EFTV) is detached from the ESM when ESM-EFTV separation conditions are reached, i.e. 4 The vehicle (EFTV) is detached from the ESM when ESM-EFTV separation conditions are reached, i.e.…”

Section: Reference Mission Scenariomentioning

confidence: 99%

“…In this frame the HEXAFLY-INT project, funded by European Commission by means of 7 th Framework Programme, intends to test in free-flight conditions an innovative (unpowered) gliding high-speed vehicle with several breakthrough technologies on-board 4 . This approach will create the basis to gradually increase the readiness level of a consistent number of technologies suitable for high-speed flying systems.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Design Analysis of the Hexafly-INT Hypersonic Glider

Brummen¹,

Pezzella²,

Andreutti

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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This paper deals with the aerodynamic performance analysis of the expendable Experimental Flight Test Vehicle under development in the seventh framework programme, namely HEXAFLY-INT. A mission scenario, the different flight segments and events to which the payload is exposed to are described and justified. This allowed the definition of the aerothermo-mechanical loads required to conceptually design all elements on board of the vehicle. This flying test bed is a self-controlled glider configuration that shall face a hypersonic flight starting at about Mach 8, just after the separation from the experimental support module at about 50 km altitude, up to vehicle loss. During this flight, several experiments shall be carried out. The appraisal of the vehicle aerodynamic performance is needed for Flight Mechanics and Guidance, Navigation and Control analysis. In particular, hinge line moments for the EFTV's aileron are also addressed to design the actuation line and to select the actuator device itself. The vehicle made maximum use of databases, expertise, technologies and materials elaborated in previously European community co-funded projects ATLLAS I & II, LAPCAT I & II, and HEXAFLY.

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“…The HEXAFLY-INT project aims at the free flight testing of an innovative high-speed vehicle with several breakthrough technologies on board [6,7]. This approach will create the basis to gradually increase the TRL.…”

Section: Introductionmentioning

confidence: 99%

Thermo-Structural Design of the HEXAFLY-INT Experimental Flight Test Vehicle (EFTV)

Scigliano

Carandente

Favaloro

et al. 2015

Volume 1: Advances in Aerospace Technology

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The Hexafly-INT project intends to test in free-flight conditions an innovative gliding vehicle with several breakthrough technologies on-board. This approach will create the basis to gradually increase the readiness level of a consistent number of technologies suitable for high-speed flying systems. This paper presents a Finite Element thermal analysis of the Experimental Flight Test Vehicle, combining information coming from the flight trajectory, the structural layout, the vehicle aerothermodynamics and the thermal behavior of the preliminarily selected materials in high temperature conditions. Numerical results show the thermal performances of the selected high temperature resistant materials in moderate enthalpy flow conditions and provide fundamental information on the thermal loads to be considered for structural analyses.

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Design Analysis of the High-Speed Experimental Flight Test Vehicle HEXAFLY-International

Cited by 19 publications

References 6 publications

Optimal Periodic Control of Hypersonic Cruise Vehicle: Trajectory Features

Optimal Periodic Control of Hypersonic Cruise Vehicle: Trajectory Features

Aerodynamic Design Analysis of the Hexafly-INT Hypersonic Glider

Thermo-Structural Design of the HEXAFLY-INT Experimental Flight Test Vehicle (EFTV)

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