scholarly journals Semi-Analytical Multidimensional Algorithm for Aircraft Design Optimisation: Student Design Build Fly (DBF) Competition

2019 ◽  
Vol 65 (11-12) ◽  
pp. 728-740
Author(s):  
Viktor Šajn
Keyword(s):  
Systems Design ◽  
Aircraft Design ◽  
Sandwich Composite ◽  
Aircraft Model ◽  
Design Build ◽  
Scientific Approach ◽  
Competition Rules ◽  
Institute Of Technology ◽  
Empirical Coefficients ◽  
Fine Tune

The winner of American Institute of Aeronautics and Astronautics (AIAA)/Textron Aviation/Raytheon Missile Systems Design/Build/Fly (DBF) Competition 2019 was Edvard Rusjan team from Faculty of Mechanical Engineering, University of Ljubljana, Slovenia. Edvard Rusjan team use a strict scientific approach to beat opposing teams from most prestigious US Universities. Team developed a semi-analytic multidimensional algorithm for aircraft design optimization with an aim to maximize competition score in accordance with the competition rules. Two intermediate prototype models were produced and tested for single ground and three flying missions to fine tune algorithm empirical coefficients. Aircraft model aerodynamics was predicted with RANS numerical simulations and dynamic stability with Inviscid Panel method. By measurement in Low Turbulence Wind Tunnel the low drag of selected aircraft external load configuration was verified. Wing and fuselage of competition aircraft model named by Ljubljana students "Pretty Boy" were made of carbon-glass sandwich composite and Aramide honeycomb as sandwich filler. At final fly-off at TIMPA field in Tucson, in final flight mission team pilot Timotej Hofbauer with "Pretty Boy" scored 18 laps in 10 minutes time slot which was absolute record of competition. Runner-up Georgia Institute of Technology team was 22% slower and finished with 14 scored laps.

scholarly journals Semi-Analytical Multidimensional Algorithm for Aircraft Design Optimisation: Student Design Build Fly (DBF) Competition

2019 ◽  
Vol 65 (11-12) ◽  
pp. 728-740
Author(s):  
Viktor Šajn
Keyword(s):  
Systems Design ◽  
Aircraft Design ◽  
Sandwich Composite ◽  
Aircraft Model ◽  
Design Build ◽  
Scientific Approach ◽  
Competition Rules ◽  
Institute Of Technology ◽  
Empirical Coefficients ◽  
Fine Tune

The winner of American Institute of Aeronautics and Astronautics (AIAA)/Textron Aviation/Raytheon Missile Systems Design/Build/Fly (DBF) Competition 2019 was Edvard Rusjan team from Faculty of Mechanical Engineering, University of Ljubljana, Slovenia. Edvard Rusjan team use a strict scientific approach to beat opposing teams from most prestigious US Universities. Team developed a semi-analytic multidimensional algorithm for aircraft design optimization with an aim to maximize competition score in accordance with the competition rules. Two intermediate prototype models were produced and tested for single ground and three flying missions to fine tune algorithm empirical coefficients. Aircraft model aerodynamics was predicted with RANS numerical simulations and dynamic stability with Inviscid Panel method. By measurement in Low Turbulence Wind Tunnel the low drag of selected aircraft external load configuration was verified. Wing and fuselage of competition aircraft model named by Ljubljana students "Pretty Boy" were made of carbon-glass sandwich composite and Aramide honeycomb as sandwich filler. At final fly-off at TIMPA field in Tucson, in final flight mission team pilot Timotej Hofbauer with "Pretty Boy" scored 18 laps in 10 minutes time slot which was absolute record of competition. Runner-up Georgia Institute of Technology team was 22% slower and finished with 14 scored laps.

AIAA Student Aircraft Design, Build & Fly Competition

2003 ◽  
Author(s):  
Gregory Page ◽  
Chris Bovias ◽  
Michael Selig ◽  
Stephen Brock
Keyword(s):  
Aircraft Design ◽  
Design Build

A Method for Determining Mode Shapes and Frequencies Above the Fundamental by Matrix Iteration

1950 ◽  
Vol 17 (3) ◽  
pp. 249-256
Author(s):  
H. I. Flomenhoft
Keyword(s):  
Dynamic Systems ◽  
Aircraft Design ◽  
Basic Knowledge ◽  
Mode Shapes ◽  
Massachusetts Institute Of Technology ◽  
Influence Coefficients ◽  
The Matrix ◽  
Acceleration Method ◽  
Matrix Iteration ◽  
Institute Of Technology

Abstract Recently, an increasing use has been made of the matrix-iteration method for determining mode shapes and frequencies, particularly with regard to dynamic problems in aircraft design. Its particular advantage is the relative ease with which it handles complex discontinuous structures whose elastic properties can be defined adequately only in terms of influence coefficients. The disadvantage of tedious calculations has been alleviated greatly by an “acceleration method” for convergence which has been described by Isakson. The predominant disadvantage to matrix iteration, however, has been the difficulty in obtaining mode shapes and frequencies higher than the fundamental. The purpose of this paper is to establish a technique for accomplishing this in a manner that is practical for use in industry, as proved by its successful application to many problems of this type in the Aero-Elastic and Structures Research Laboratory at the Massachusetts Institute of Technology. This is accomplished by applying a device worked out by L. A. Pipes, and extending it to the general case, at the same time organizing the computations in tabular form. Only a basic knowledge of matrix notation and dynamic systems is necessary to understand this development, and this can be obtained easily by a review of von Kármán and Biot’s work on this subject.

Low noise engine design for the Silent Aircraft Initiative

2009 ◽  
Vol 113 (1147) ◽  
pp. 599-607 ◽  
Author(s):  
C. A. Hall
Keyword(s):  
Aircraft Design ◽  
Low Noise ◽  
Urban Environments ◽  
Massachusetts Institute Of Technology ◽  
Engine Noise ◽  
Novel Technologies ◽  
Component Design ◽  
Design Changes ◽  
Institute Of Technology ◽  
The University

Abstract The Silent Aircraft Initiative was a Cambridge-MIT Institute programme involving a large team of researchers from both the University of Cambridge and the Massachusetts Institute of Technology (MIT). The aim of the project was to produce a concept aircraft design that would be so quiet it would be imperceptible in the urban environments around airports.. This paper gives an overview of how all the sources of engine noise were carefully addressed within the Silent Aircraft design. Novel technologies, a new engine configuration, improved airframe integration, new operational procedures and advanced component design were all required in order to reduce the overall engine noise level to the Silent Aircraft target. The study suggests that in order to dramatically reduce the noise of future aircraft engines a number of major design changes must be combined.

scholarly journals Preliminary Sub-Systems Design Integrated in a Multidisciplinary Design Optimization Framework

2017 ◽  
Vol 2017 (4) ◽  
pp. 9-23
Author(s):  
Marco Fioriti ◽  
Luca Boggero ◽  
Sabrina Corpino
Keyword(s):  
Design Optimization ◽  
Multidisciplinary Design Optimization ◽  
Systems Design ◽  
Aircraft Design ◽  
Multidisciplinary Design ◽  
Design Parameters ◽  
Preliminary Design ◽  
Horizon 2020 ◽  
Optimization Framework ◽  
Complex Subject

Abstract The aircraft design is a complex subject since several and completely different design disciplines are involved in the project. Many efforts are made to harmonize and optimize the design trying to combine all disciplines together at the same level of detail. Within the ongoing AGILE (Horizon 2020) research, an aircraft MDO (Multidisciplinary Design Optimization) process is setting up connecting several design tools and competences together. Each tool covers a different design discipline such as aerodynamics, structure, propulsion and systems. This paper focuses on the integration of the sub-system design discipline with the others in order to obtain a complete and optimized aircraft preliminary design. All design parameters used to integrate the sub-system branch with the others are discussed as for their redefinition within the different detail level of the design.

Design of SUV Differential Braking Controller Considering the Interactions of Driver and Control System

2014 ◽  
Author(s):  
Shenjin Zhu ◽  
Yuping He
Keyword(s):  
Real Time ◽  
Degrees Of Freedom ◽  
Systems Design ◽  
Stability Control ◽  
Double Line ◽  
The Road ◽  
Labview Software ◽  
Yaw Stability ◽  
Institute Of Technology ◽  
Real Time Simulations

This paper presents the design and validation of a differential braking controller for sport utility vehicles (SUVs) using driver-in-the-loop real-time simulations. SUVs are constructed with high ground clearance, which is the main reason for their high rollover rate. A nonlinear 3 degrees-of-freedom (DOF) SUV model with the Dugoff’s tire model is generated to design a differential braking controller. The desired states will be decided using a 2-DOF bicycle model and the automated lane-keeping control results derived from the vehicle velocity and the curvature of the road to negotiate. Actual vehicle states, observed from the nonlinear model, may deviate from the desired ones. A nonlinear robust controller, namely sliding model controller (SMC), is designed to minimize the state error so as to improve the performance measures, e.g., yaw stability. The proposed controller constructed in Labview software is integrated with a virtual SUV developed in CarSim package for co-simulations. The effectiveness of the controller is first investigated using the emulated sine-with-dwell maneuver specified in FMVSS 126. The overall SUV performance depends not only on the control scheme, but on its interaction with the human driver. To investigate the interaction of the driver and the controller, the dynamics of the overall system is simulated using driver-software-in-the-loop real-time simulations (DSIL) under a double-line-change (DLC) maneuver emulated on the DSIL platform in the Multidisciplinary Vehicle Systems Design Laboratory (MVSDL) at the University of Ontario Institute of Technology (UOIT). The simulations show that, even equipped with the electronic stability control (ESC) system, the driver still plays an important role in the vehicle dynamics. The simulations demonstrate the effectiveness of the proposed differential braking controller for enhancing the lateral stability of the SUV. Furthermore, the research discloses important interactions of the driver and the ESC system, and a driver’s training program is highly recommended.

D/B/F 98: Final Report Of the AIAA Student Aircraft Design, Build & Fly Competition

1998 ◽  
Author(s):  
Gregory Page ◽  
Chris Bovias ◽  
Michael Selig ◽  
Robert Paczula
Keyword(s):  
Aircraft Design ◽  
Final Report ◽  
Design Build

Support of AIAA Student Aircraft Design/Build/Fly Competition

2000 ◽  
Author(s):  
Gregory S. Page ◽  
Chris Bovias ◽  
Michael Selig
Keyword(s):  
Aircraft Design ◽  
Design Build

scholarly journals Innovative Scaled Test Platform e-Genius-Mod—Scaling Methods and Systems Design

Aerospace ◽  
2019 ◽  
Vol 6 (2) ◽  
pp. 20 ◽  
Author(s):  
Dominique Bergmann ◽  
Jan Denzel ◽  
Asmus Baden ◽  
Lucas Kugler ◽  
Andreas Strohmayer
Keyword(s):  
Financial Risk ◽  
New Technologies ◽  
Systems Design ◽  
Aircraft Design ◽  
Cost Effective ◽  
Unmanned Aircraft ◽  
Scale Model ◽  
Successful Implementation ◽  
Free Flight ◽  
Drag And Lift

Future aircraft design highly depends on the successful implementation of new technologies. However, the gap between conventional designs and new visions often comes with a high financial risk. This significantly complicates the integration of innovations. Scaled unmanned aircraft systems (UAS) are an innovative and cost-effective way to get new configurations and technologies in-flight. Therefore the Institute of Aircraft Design developed the e-Genius-Mod taking into account all relevant similitude requirements. It is a scale model of the electric motor glider e-Genius. Since the Reynolds number for the free-flight model cannot be adhered to, an airfoil was developed with lift-to-drag and lift-to-angle-of-attack courses reproducing the full-scale e-Genius flight characteristics. This will enable testing and assessment of new aviation technologies in a scaled version with an opportunity for free-flight demonstration in relevant environment.

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