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 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.

Secondary power system study for the Hytex RA3 flight test vehicle

1995 ◽  
Author(s):  
T Saetmark ◽  
H Streifinger ◽  
J Kretschmer ◽  
G Moser
Keyword(s):  
Power System ◽  
Flight Test ◽  
System Study ◽  
Test Vehicle ◽  
Secondary Power

Real-Time Simulation of Rotor Blade Aeroelasticity for the Multidisciplinary Design of Rotorcraft

2014 ◽  
Author(s):  
Ioannis Goulos ◽  
Vassilios Pachidis
Keyword(s):  
Real Time ◽  
Rotor Blade ◽  
Flight Test ◽  
Flight Mechanics ◽  
Multidisciplinary Design ◽  
Mathematical Approach ◽  
Real Time Simulation ◽  
Analysis Methods ◽  
Time Simulation ◽  
Blade Loads

This paper elaborates on the theoretical development of a mathematical approach, targeting the real-time simulation of aeroelastic rotor blade dynamics for the multidisciplinary design of rotorcraft. A Lagrangian approach is formulated for the rapid estimation of natural vibration characteristics of rotor blades with nonuniform structural properties. Modal characteristics obtained from classical vibration analysis methods, are utilized as assumed deformation functions. Closed form integral expressions are incorporated, describing the generalized centrifugal forces and moments acting on the blade. The treatment of three-dimensional elastic blade kinematics in the time-domain is thoroughly discussed. In order to ensure robustness and establish applicability in real-time, a novel, second-order accurate, finite-difference scheme is utilized for the temporal discretization of elastic blade motion. The developed mathematical approach is coupled with a finite-state induced flow model, an unsteady blade element aerodynamics model, and a dynamic wake distortion model. The combined aeroelastic rotor formulation is implemented in a helicopter flight mechanics code. The aeroelastic behavior of a full-scale hingeless helicopter rotor has been investigated. Results are presented in terms of rotor blade resonant frequencies, airframe–rotor trim performance, oscillatory structural blade loads, and transient rotor response to control inputs. Extensive comparisons are carried out with wind tunnel and flight test measurements found in the open literature, as well as with non-real-time comprehensive analysis methods. It is shown that, the proposed approach exhibits good agreement with flight test data regarding trim performance and transient rotor response characteristics. Accurate estimation of structural blade loads is demonstrated, in terms of both amplitude and phase, up to the third harmonic component of oscillatory loading. It is shown that, the developed model can be utilized for real-time simulation on a modern personal computer. The proposed methodology essentially constitutes an enabling technology for the multidisciplinary design of rotorcraft, when a compromise between simulation fidelity and computational efficiency has to be sought for in the model development process.

scholarly journals Control and flight test of a tilt-rotor unmanned aerial vehicle

2017 ◽  
Vol 14 (1) ◽  
pp. 172988141667814 ◽  
Author(s):  
Chao Chen ◽  
Jiyang Zhang ◽  
Daibing Zhang ◽  
Lincheng Shen
Keyword(s):  
Unmanned Aerial Vehicle ◽  
High Speed ◽  
Cross Coupling ◽  
Flight Test ◽  
Control Allocation ◽  
Tilt Rotor ◽  
Satisfactory Performance ◽  
Allocation Method ◽  
Aerial Vehicle ◽  
The Cost

Tilt-rotor unmanned aerial vehicles have attracted increasing attention due to their ability to perform vertical take-off and landing and their high-speed cruising abilities, thereby presenting broad application prospects. Considering portability and applications in tasks characterized by constrained or small scope areas, this article presents a compact tricopter configuration tilt-rotor unmanned aerial vehicle with full modes of flight from the rotor mode to the fixed-wing mode and vice versa. The unique multiple modes make the tilt-rotor unmanned aerial vehicle a multi-input multi-output, non-affine, multi-channel cross coupling, and nonlinear system. Considering these characteristics, a control allocation method is designed to make the controller adaptive to the full modes of flight. To reduce the cost, the accurate dynamic model of the tilt-rotor unmanned aerial vehicle is not obtained, so a full-mode flight strategy is designed in view of this situation. An autonomous flight test was conducted, and the results indicate the satisfactory performance of the control allocation method and flight strategy.

System Identification Modeling and Flight Characteristics Analysis of Miniature Coaxial Helicopter

2014 ◽  
Vol 59 (4) ◽  
pp. 36-51 ◽  
Author(s):  
Navid Dadkhah ◽  
Bérénice Mettler
Keyword(s):  
System Identification ◽  
High Speed ◽  
Tracking System ◽  
Flight Test ◽  
Lumped Parameter Model ◽  
Test Facility ◽  
Modeling And Analysis ◽  
Characteristics Analysis ◽  
Parameterized Model ◽  
Coaxial Helicopter

This paper describes the identification modeling and analysis of a miniature coaxial helicopter. The first part of the paper focuses on the development of the parameterized model with an emphasis on the coaxial rotor configuration. The model explicitly accounts for the dynamics of the lower rotor and uses an implicit lumped parameter model for the upper rotor and stabilizer bar. The parameterized model was identified using frequency domain system identification. The flight data collection experiments were performed in an indoor flight-test facility built around a commercial vision-based tracking system. The second part of the paper focuses on the verification of the model's accuracy, the consistency of the identified parameters, and the analysis of the flight dynamics. The accuracy was verified by comparing model-predicted responses with flight experimental responses. The identified parameters and model's physical consistency were examined using experiments in which specific aspects of the dynamics were isolated. For example, we used video images from a high-speed camera to verify the rotor and stabilizer bar time constants. Finally, the identified derivatives were verified based on first principles to demonstrate that the derivatives are physically meaningful.

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