Search

The HEXAFLY-INT flight vehicle is a small-scale flight demonstrator of a supersonic passenger aircraft [8,9]. In order to determine the flight angles, Mach number and altitude for this vehicle a set of pressure sensors can be used to derive this data. In the frame of this study such a system, usually called Flush Air Data Sensing system (FADS), was designed and adapted to the constrains imposed by the vehicle shape of HEXAFLY-INT. Different theoretical, analytic and numerical approaches from local inclination method to numerical simulations were used to optimize sensor positions for the flight path of HEXAFLY-INT. Afterwards these different approaches was assessed and benchmarked against each other. In the second part of this work different algorithms are investigated to determine the flight properties for simulated inputs and where analyzed in terms of accuracy and real-time performance.

The startup represents a very critical phase during the whole operational life of solid rocket motors. This paper provides a detailed study of the effects on the ignition transient of the main design parameters of solid-propellant motors. The analysis is made with the use of a quasi-one-dimensional unsteady model of solid rocket ignition transient, extensively validated, and used in the frame of the Vega program, for ignition transient predictions, reconstructions, and analyses. Two baseline solid rocket motor configurations are selected for the parametric analysis: a big booster with a three-segment propellant grain shape, similar to Ariane 5, and a small booster/solid stage with an aft-finocyl grain shape, similar to Vega solid rocket motors. The discussion of the results is particularly addressed on the possible onset of the pressure oscillations during the startup of the two solid rocket motor configurations, pointing out the design parameters that affect them in terms of occurrence and amplitude.

The multigrid performance of pointwise, linewise and blockwise Gauss-Seidel relaxations for compressible laminar and turbulent Navier-Stokes equations is illustrated on two low-speed test problems: a flat plate and a backward facing step. The line method is an Alternating Symmetric Line Gauss-Seidel relaxation. In the block methods, the grid is subdivided into geometric blocks of n × n points with one point overlap. With in the blocks, the solution is obtained by a direct method or with an alternating modified incomplete lower-upper decomposition. The analysis is focused on flows typical for boundary layers, stagnation and recirculation regions. These are characterized by very small Mach numbers, high Reynolds numbers and high mesh aspect ratios.

Copyright © 2017 ASME. Over the last years, innovative concepts of civil high-speed transportation vehicles were proposed. In this framework, the Hexafly-INT project intends to test in free-flight conditions an innovative gliding vehicle with several breakthrough technologies on-board. This approach will help to gradually increase the readiness level of a consistent number of technologies suitable for hypervelocity flying systems. The vehicle design, manufacturing, assembly and verification is the main driver and challenge in this project. The prime objectives of this free-flying high-speed cruise vehicle shall aim at a conceptual design demonstrating a high aerodynamic efficiency in combination with high internal volume; controlled level flight at a cruise Mach number of 7 to 8;an optimal use of advanced high-temperature materials and structures. Present research describes the aero-thermal design process of the Experimental Flight Test Vehicle, namely EFTV. The glider aeroshape design makes maximum use of databases, expertise, technologies and materials elaborated in previously European community co-funded projects LAPCAT I & II [1][2], ATLLAS I & II [3][4] and HEXAFLY [5]. The paper presents results for both CFD and Finite Element aero-thermal analysis, performed in the most critical phase of the experimental flight leading to the selection of materials for the different components and to a suitable Thermal Protection System. ispartof: PROCEEDINGS OF THE ASME INTERNATIONAL MECHANICAL ENGINEERING CONGRESS AND EXPOSITION, 2017, VOL 1 vol:1 ispartof: ASME International Mechanical Engineering Congress and Exposition location:Tampa, FL date:3 Nov - 9 Nov 2017 status: published

© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Over the last years, innovative concepts of civil high-speed transportation vehicles were proposed. These vehicles have a strong potential to increase the cruise range efficiency at high Mach numbers, thanks to efficient propulsion units combined with high-lifting vehicle concepts. In this framework the Hexafly-INT project has the scope to test in free-flight conditions an innovative gliding vehicle with several breakthrough technologies on-board. This work describes the aero-thermal design processes of the Hexafly-INT Experimental Flight Test Vehicle, namely EFTV. ispartof: Proceedings of SPACE 2016 ispartof: SPACE 2016 Conferences and Exposition location:Long Beach, California date:13 Sep - 16 Sep 2016 status: published

ispartof: Proceedings of AIDAA2015 ispartof: 23rd Conference of the Italian Association of Aeronautics and Astronautics (AIDAA2015) location:Torino, Italy date:17 Nov - 19 Nov 2015 status: published

This paper deals with the design trade-off activities undertaken to provide a trim-able, a statically and dynamically stable vehicle configuration able to perform a nominal experimental scramjet-propelled flight. The flight control activities and their impacts on vehicle layout and global aerodynamic performance are also addressed. In particular, different competing aeroshapes have been investigated to assess the best one camplyant with project requirements. In this framework, trade-off results in terms of: setup and/or analysis of aero-propulsive databases; design loops for the aileron (shape, span, length); design loops for the vertical tail (shape, size, toe-angle); analysis of aerodynamic performances; analysis of longitudinal trimming conditions; sensitivity to centre of gravity position of static longitudinal stability and trimming conditions; static stability analysis (for longitudinal and lateral-directional flight) in clean and flapped configuration, static margins (pitch, roll, yaw); dynamic stability analysis with a focus on roll-yaw coupling (linearized model analysis and Dutch-Roll period evaluation); characterization of hinge-moments; and preliminary selection of flight control equipment are provided and described in detail in the paper.