4th Aircraft Design, Flight Test, and Operations Meeting

1972 ◽  
Keyword(s):  
Aircraft Design ◽  
Flight Test

scholarly journals UAS as flexible and innovative test platform for aircraft configuration and systems testing

2018 ◽  
Vol 233 ◽  
pp. 00001
Author(s):  
Dominique Paul Bergmann ◽  
Jan Denzel ◽  
Andreas Strohmayer
Keyword(s):  
Financial Risk ◽  
New Technologies ◽  
Aircraft Design ◽  
Flight Test ◽  
Scale Model ◽  
Efficient Test ◽  
Consumption Reduction ◽  
Test Platform ◽  
Cost Efficient ◽  
Configuration Changes

Today new technologies are available, which can be decisive for the success of future aircraft design. However, the gap between conventional designs and new visions often comes with a high financial risk. This complicates the integration of innovations significantly. The “Flightpath 2050 Europe’s Vision for Aviation” asks for new aircraft concepts and configurations to meet future requirements such as emission (CO2, NOx), noise and fuel consumption reduction. Scaled UAS are one way for getting new configurations and technologies into flight test while reducing the risk of exploding costs. UAS are cost-efficient test platform systems for two main tasks of future aircraft tests: Testing new configurations and advancing new aircraft systems and technologies from upstream research to TRL5-6. UAS can represent a connection between innovative research and flight demonstration. This paper focuses on the UAS as an innovative test platform and a tool for feasibility demonstration as well as its impact on new technologies and the implementation of innovative concepts. An example of a UAS test platform is given in the paper based on a 33,3% scale model of the e-Genius. It is developed as flying wind tunnel in order to better understand the effects of configuration changes on flight performance.

A review of supersonic business jet design Issues

2007 ◽  
Vol 111 (1126) ◽  
pp. 761-776 ◽  
Author(s):  
H. Smith
Keyword(s):  
Global Economy ◽  
Aircraft Design ◽  
Flight Test ◽  
Specific Aspect ◽  
Air Travel ◽  
Sonic Boom ◽  
Enabling Technologies ◽  
Business Jet ◽  
Depth Analysis ◽  
Theoretical And Numerical Analysis

Abstract Key issues relating to the Supersonic Business Jet (SBJ) concept are reviewed with the intent to assess the readiness of enabling technologies and hence the concept itself. The multidisciplinary nature of aircraft design precludes an in-depth analysis of each specific aspect, which could individually be the subject of a separate discipline review, hence an overview is presented. The review looks at the market, environmental issues, with particular reference to the sonic boom phenomenon & solutions, technological issues, including prediction methods, flight testing, systems, certification and interested aerospace companies and design organisations. It is apparent that the need to reduce the sonic boom signature is vital if the vehicle is to be permitted to operate over land and hence be economically viable. It is clear that sonic boom acceptability requirements must be set if resources are to be effectively focused and designs are to converge. Despite this challenge, considerable investment is aimed at de-risking many of the enabling technologies and raising readiness levels. Many technologies are moving beyond theoretical and numerical analysis into the experimental and flight test domains. Collaboration between the civil and military sectors is increasing. Clearly, supersonic air travel is not an efficient means of personal conveyance; however, concerns for the environment are difficult to balance against the ‘value of time’ benefits offered by the SBJ concept. Air travel, of which this is a specialised form, is important to the global economy. Continued effort in the areas of human factors, customer demand and certification & requirements would be beneficial.

scholarly journals Improved Immune Genetic Algorithm to Optimize the Design of Wing Structure of Competition Aircraft

2021 ◽  
Vol 2137 (1) ◽  
pp. 012075
Author(s):  
Xi Feng ◽  
Yafeng Zhang
Keyword(s):  
Genetic Algorithm ◽  
Aircraft Design ◽  
Flight Test ◽  
Optimization Methods ◽  
Optimization Method ◽  
Design Parameters ◽  
Immune Genetic Algorithm ◽  
Maximum Deformation ◽  
Design Variables ◽  
Wing Structure

Abstract An improved immune genetic algorithm is used to design and optimize the wing structure parameters of a competition aircraft. According to the requirements of aircraft design, multi-objective optimization index is established. On this basis, the basic steps of using immune algorithm to optimize the main design parameters of aircraft wing structure are proposed, and the optimization of the wing parameters of a competition aircraft is used as an example for simulation calculation. The design variables in the optimization are the size of the wing components, and the optimization goal is to minimize the weight of the wing and the maximum deformation of the wing structure. Research shows that compared with traditional optimization methods; the improved immune genetic algorithm is a very effective optimization method. At the same time, a prototype is made to check the validity and feasibility of the design. Flight test results show that the optimization method is very effective. Although the method is proposed for competition aircraft, it is also applicable to other types of aircraft.

scholarly journals The UNMANNED AERIAL VEHICLE (UAV) AIRCRAFT DESIGN GALAK-24 WITH AUTONOMOUS METHOD

2021 ◽  
Vol 2 (Oktober) ◽  
pp. 66-74
Author(s):  
Argo Surono ◽  
Imam Ashar ◽  
Muhamat Maariful Huda
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicle ◽  
Hydraulic System ◽  
Aircraft Design ◽  
Flight Test ◽  
Radio Waves ◽  
Remote Control System ◽  
Aerial Vehicle ◽  
Unmanned System ◽  
Very High

Abstract: Unmanned Aerial Vehicle is a type of aircraft that is controlled by a remote-control system via radio waves. UAV is an unmanned system (Unmanned System), which is an electro-mechanical-based system that can carry out programmed missions with the characteristics of a UAV that is able to fly without a pilot capable of controlling automatically and can run again by carrying several weapons or other tools. An autopilot is a mechanical, electrical, or hydraulic system that guides a vehicle without human intervention. The application of the Autonomous control system on the UAV is carried out by using Autonomous equipment in the form of components such as Flight Controller, GPS, Mission Planner Software and Telemetry. The number of parameters set by the observations made on the movement of the UAV when in Auto mode. The flight test used a square waypoint with a distance of 500 meters on each side. The UAV is able to fly in an Autonomous manner stably using a predetermined Waypoint. This is a pure experiment by means of tool testing and data collection that requires very high attention from the crew and results in fatigue.

scholarly journals Project of high altitude balloon launched micro glider: Aircraft design, control and flight test

2020 ◽  
Vol 12 ◽  
pp. 175682932097995
Author(s):  
Zhengyu Qu ◽  
Cuichun Li ◽  
Yong Hao ◽  
Feng Yan ◽  
Yanchu Yang
Keyword(s):  
High Altitude ◽  
System Design ◽  
Target Position ◽  
Aircraft Design ◽  
Flight Test ◽  
Roll Angle ◽  
Guidance System ◽  
Circuit Board ◽  
Wind Condition ◽  
Flight Tests

This paper presents the design details and flight tests validation of printed circuit board fabricated micro gliders. The purpose of the micro glider is to be launched from a super pressure balloon at high altitude, glide to the target position to collect data and upload data to the staying balloon. The mission demand requires the micro glider to finish precise landing with small size and low fabrication cost. To complete this concept, we designed a PCB fabricated aircraft with limited sensors including GPS and IMU. The first part of the article describes the aerodynamic design methods. The second part introduced the control and guidance system design by controlling the roll angle and flight path angle to complete the precise landing. In the simulation results presented in the third part, launch with no wind condition shows desirable precise landing ability. As a contrast, wind direction and magnitude have significant effects on the guidance ability and accuracy. In the last part, two real flight tests conducted in Inner Mongolia of China are described to compare the flight performance with the current aerodynamics and control system design. Returned data indicated the micro gliders could successfully fly at high altitude. The control algorithm can compute the command roll angle only with GPS and IMU, but some design details still need to be improved to achieve precise landing ability.

Conceptual aerodynamic design of an executive supersonic passenger aircraft – ESPA

2021 ◽  
pp. 095441002110251
Author(s):  
Jeremy P Lawrence ◽  
Rhys J Hutchinson ◽  
Keith F Joiner
Keyword(s):  
Aircraft Design ◽  
Flight Test ◽  
Research Literature ◽  
Multidisciplinary Optimization ◽  
Technological Advancement ◽  
Design Evolution ◽  
Design Detail ◽  
Shock Wave Formation ◽  
Passenger Aircraft ◽  
Multifactor Regression

Despite 50 years of technological advancement since the inception of Concorde, research on supersonic passenger aircraft has only recently resulted in design and flight test of several small 12- to 55-passenger business jets with supersonic cruises between Mach 1.2 and 2.2. Analytical research designs of larger 300-passenger aircraft have been conducted only to speeds of Mach 2.0 and 2.2, mainly avoiding moving beyond turbojet propulsion. This research extends on an earlier multifactor regression sizing study to determine in greater design detail what the configuration of a 200-passenger Mach 3.0 aircraft could be using extant technology. This research article is the first part of two and covers the conceptual aircraft design evolution focussing on the aerodynamics, wing and fuselage. In contrast, the second article covers engine conceptual design and placement. Wing shape optimization is performed using fundamental CFD analysis to arrive at a configuration suitable for both subsonic and supersonic flight. Noise considerations and shock wave formation drive further design iterations based on the research literature. The viability of this research design informs a future multidisciplinary optimization like those recently published in the literature for smaller supersonic business jets.

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