Flight Mechanical Modelling considering Flexibility and Flight Control Functions in Preliminary Aircraft Design

2017 ◽  
Author(s):  
Vikram Krishnamurthy ◽  
Robert Luckner
Keyword(s):  
Flight Control ◽  
Aircraft Design ◽  
Control Functions ◽  
Preliminary Aircraft Design ◽  
Mechanical Modelling

Method for Estimation of Electrical Wiring Interconnection Systems in Preliminary Aircraft Design

2019 ◽  
Vol 56 (3) ◽  
pp. 1259-1263 ◽  
Author(s):  
Francesca Tomasella ◽  
Marco Fioriti ◽  
Luca Boggero ◽  
Sabrina Corpino
Keyword(s):  
Aircraft Design ◽  
Preliminary Aircraft Design ◽  
Electrical Wiring

UAV Autopilot Design for the AUVSI, UAS International Competition

2009 ◽  
Author(s):  
Muhammad M. Mahmood ◽  
Md S. Chowdhury ◽  
Rizwan Ihsan ◽  
Umar M. Yousaf ◽  
Mohamed W. Afifi ◽  
...  
Keyword(s):  
Undergraduate Students ◽  
Flight Control ◽  
Computer Network ◽  
Imaging System ◽  
Aircraft Design ◽  
Unmanned Aircraft ◽  
American University ◽  
Ground Station ◽  
Aerial Imaging ◽  
Safety Features

This paper provides an overview of the first participation of the design developed by the undergraduate students of American University of Sharjah to meet the requirements laid forth in the 2008 Association for Unmanned Vehicle Systems International (AUVSI) Student UAS competition. The overall objective of the competition is to fly autonomously over a GPS waypoint defined route and also to identify and locate ground based targets within a confined area. To meet the objectives an unmanned aircraft is equipped with autonomous functionality and aerial imaging system. A ground station and supportive software to keep track of the aircraft routine and log the raw data gained from the flight is also designed. Achieving complete success depends upon mission elements which include autonomous take-off and landing, autonomous control and waypoint navigation. The onboard equipment used was a flight control computer network, IMU, GPS, an air data system and a camera. Additionally, safety features such as manual override was also installed. Presented in this report are aircraft design and testing, the processes involved in accomplishing the goal, and the results and achievements.

Application of Agile Model-Based Systems Engineering in aircraft conceptual design

2019 ◽  
Vol 123 (1268) ◽  
pp. 1561-1601 ◽  
Author(s):  
G. P. Krupa
Keyword(s):  
Systems Engineering ◽  
Flight Control ◽  
System Analysis ◽  
Object Oriented ◽  
Aircraft Design ◽  
System Engineering ◽  
Smooth Transition ◽  
Model Based ◽  
Agile Model ◽  
Aircraft Conceptual Design

ABSTRACTOne of the challenges of modern engineering design is the amount of data that designers must keep track while performing system analysis and synthesis. This task is particularly important in the design process of complex systems such as novel aerospace systems where Modeling and Simulation play an essential role. The Agile philosophy stems from the field of Software Engineering and describes an approach to development in which requirements and solutions gradually develop through collaboration between self-organising cross-functional teams and end users. Agile Model-Based System Engineering (AMBSE) is the application of the Agile philosophy to Model-Based System Engineering. In this paper, AMBSE is accomplished through the application of the Object-Oriented System Engineering Method (OOSEM). OOSEM employs a top-down scenario-driven process that adopts System Modeling Language (SysML) and leverages the object-oriented paradigm to support the analysis, specification, design, and verification of systems. AMBSE assisted by mathematical modelling and safety assessment techniques is applied to the first design iterations of the main aircraft systems, allowing a comprehensive design exploration. The flight control system was chosen to illustrate the procedure in detail, emphasising the synthesis of a six-degrees-of-freedom model augmented by dynamic inversion control for a hypothetical supersonic transport aircraft satisfying class II MIL-F-8785C handling qualities. It is concluded that AMBSE presents promising properties to support future aircraft development within the current regulatory framework for aircraft design, while enabling a smooth transition from conceptual to preliminary design.

A distributed toolbox for multidisciplinary preliminary aircraft design

2011 ◽  
Vol 2 (1-4) ◽  
pp. 57-68 ◽  
Author(s):  
Carsten M. Liersch ◽  
Martin Hepperle
Keyword(s):  
Aircraft Design ◽  
Preliminary Aircraft Design

Genetic Optimization Applied in Conceptual and Preliminary Aircraft Design

2008 ◽  
Author(s):  
R. Oliveira ◽  
A. Cortellazzi ◽  
P. Nakamura ◽  
R. Neto ◽  
E. Belo ◽  
...  
Keyword(s):  
Aircraft Design ◽  
Genetic Optimization ◽  
Preliminary Aircraft Design

EPISTLE: High lift system design for low-noise applied to a supersonic aircraft

2006 ◽  
Vol 110 (1107) ◽  
pp. 327-331 ◽  
Author(s):  
U. Herrmann
Keyword(s):  
System Design ◽  
Aircraft Design ◽  
Reynolds Numbers ◽  
Low Noise ◽  
High Lift ◽  
New Approach ◽  
Low Speed ◽  
Supersonic Aircraft ◽  
Preliminary Aircraft Design ◽  
High Reynolds

Abstract A new approach for low-drag high-lift system design based on the application of viscous flow solvers was developed in the EC research project EPISTLE. Two high-lift systems for a supersonic commercial transport aircraft (SCT) wing were designed, manufactured and wind-tunnel tested. The predicted large drag reductions were fully confirmed by tests at high Reynolds numbers. These drag reductions significantly reduce the low-speed noise of future SCT configurations. This was estimated by preliminary aircraft design tools. Low-speed noise reduction by aerodynamic means is obtained, as effective high-lift systems enable these aircraft to climb faster.

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