scholarly journals Hexafly-INT Experimental Flight Test Vehicle (EFTV) Aero-Thermal Design

2017 ◽  
Author(s):  
Roberto Scigliano ◽  
Giuseppe Pezzella ◽  
Sara Di Benedetto ◽  
Marco Marini ◽  
Johan Steelant
Keyword(s):  
High Speed ◽  
Thermal Protection ◽  
Flight Test ◽  
Thermal Design ◽  
Test Vehicle ◽  
Aerodynamic Efficiency ◽  
Main Driver ◽  
Readiness Level ◽  
Manufacturing Assembly ◽  
Internal Volume

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.

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

2015 ◽  
Author(s):  
Roberto Scigliano ◽  
Valerio Carandente ◽  
Nunzia Favaloro ◽  
Salvatore Cardone ◽  
Johan Steelant
Keyword(s):  
High Temperature ◽  
Structural Design ◽  
High Speed ◽  
Flight Test ◽  
Flight Trajectory ◽  
Test Vehicle ◽  
Structural Layout ◽  
Fundamental Information ◽  
Readiness Level ◽  
Combining Information

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.

The high-speed experimental flight test vehicle of HEXAFLY-INT: a multidisciplinary design

2021 ◽  
Author(s):  
Sara Di Benedetto ◽  
Maria Pia Di Donato ◽  
Antonio Schettino ◽  
Roberto Scigliano ◽  
Francesco Nebula ◽  
...  
Keyword(s):  
High Speed ◽  
Flight Test ◽  
Multidisciplinary Design ◽  
Test Vehicle

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

2015 ◽  
Author(s):  
Nunzia Favaloro ◽  
Giuseppe Pezzella ◽  
Valerio Carandente ◽  
Roberto Scigliano ◽  
Marco Cicala ◽  
...  
Keyword(s):  
High Speed ◽  
Flight Test ◽  
Design Analysis ◽  
Test Vehicle

scholarly journals Analysis and Study of Heat Transfer Resistance Inside and Outside the Reentry Capsule

2019 ◽  
Vol 257 ◽  
pp. 01001
Author(s):  
Chen Yang ◽  
Ning Xianwen ◽  
Su Sheng
Keyword(s):  
Heat Transfer ◽  
High Speed ◽  
Thermal Protection ◽  
Calculation Model ◽  
Thermal Design ◽  
Heat Transfer Characteristics ◽  
Internal Radiation ◽  
Transfer Resistance ◽  
Atmospheric Reentry ◽  
Typical Calculation

According to the heat transfer characteristics inside and outside of the lunar-earth high-speed reentry capsule, a typical calculation model of heat conduction in external thermal protection system(TPS) coupled with internal radiation was established. The thermal properties of thermal resistance inside and outside the reentry capsule were analysed. The effects of thickness of the TPS, surface conditions and atmospheric pressures on the temperature were further explored. The results showed that atmosphere pressure was necessary to be controlled under 10Pa to ensure the safety temperature of the equipment and pipe. Based on the critical pressure, the configuration was optimized. The results provide detailed data for the system design of the lunar exploration, and also provide a reference for the thermal design of the atmospheric reentry spacecraft.

scholarly journals Recent advancements in shape optimization of aero spiked high speed re-entry vehicle using CFD

2018 ◽  
Vol 172 ◽  
pp. 01007
Author(s):  
Harish Panjagala ◽  
E L N Rohit Madhukar ◽  
I Ravi Kiran
Keyword(s):  
High Speed ◽  
Structural Integrity ◽  
Elevated Temperatures ◽  
Thermal Protection ◽  
Space Vehicle ◽  
Protection Systems ◽  
Ultimate Outcome ◽  
Increasing Demand ◽  
Space Activities ◽  
Intense Heat

Due to increasing demand of High Speed Re-entry vehicles for Space activities within the world, a serious issue associated with the method of deceleration down a vehicle is by the intense heat generated because of development of stronger shocks at the nose. The price of thermal protection systems (TPS) to cut back the warmth generated by the return vehicles is extremely high. In this paper, the ultimate outcome is to cut back the aero heating which is achieved by introducing a spike at frontal region of the nose. Additionally, this spike avoids the deterioration and preserves the structural integrity of space vehicle over elevated temperatures. Further, four totally different geometries of tip specifically Blunt, Slender, Snap and Pan for the aerospike has been introduced and their impact on performance is evaluated and compared with the vehicle having TPS. Hence, usage of aerospike in return vehicles is the most successful and economical over different protection system.

GT36 Turbine Aero-Thermal Development and Validation

2017 ◽  
Author(s):  
S. Naik ◽  
J. Krueckels ◽  
M. Henze ◽  
W. Hofmann ◽  
M. Schnieder
Keyword(s):  
Gas Turbine ◽  
High Speed ◽  
Pressure Sensors ◽  
Thermal Design ◽  
Local Pressure ◽  
Cooling Systems ◽  
Wide Range ◽  
Turbine Vanes ◽  
Thermal Development ◽  
Development And Validation

This paper describes the aero-thermal development and validation of the GT36 heavy duty gas turbine. The turbine which has evolved from the existing and proven GT26 design, consists of an optimised annulus flow path, higher lift aerofoil profiles, optimised aerodynamic matching between the turbine stages and new and improved cooling systems of the turbine vanes and blades. A major design feature of the turbine has been to control and reduce the aerodynamic losses, associated with the aerofoil profiles, trailing edges, blade tips, endwalls and coolant ejection. The advantages of these design changes to the overall gas turbine efficiency have been verified via extensive experimental testing in high-speed cascade test rigs and via the utilisation of high fidelity multi-row computational fluid dynamics design systems. The thermal design and cooling systems of the turbine vanes, blades have also been improved and optimised. For the first stage vane and blade aerofoils and platforms, multi-row film cooling with new and optimised diffuser cooling holes have been implemented and validated in high speed linear cascades. Additionally, the internal cooling design features of all the blades and vanes were also improved and optimised, which allowed for more homogenous metal temperatures distributions on the aerofoils. The verification and validation of the internal thermal designs of all the turbine components has been confirmed via extensive testing in dedicated Perspex models, where measurements were conducted for local pressure losses, overall flow distributions and local heat transfer coefficients. The turbine is currently being tested and undergoing validation in the GT36 Test Power Plant in Birr, Switzerland. The gas turbine is heavily instrumented with a wide range of validation instrumentation including thermocouples, pressure sensors, strain gauges and five-hole probes. In addition to performance mapping and operational validation, a dedicated thermal paint validation test will also be performed.

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