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.

Conceptual design and integration of a propulsion system for a supersonic transport aircraft

2021 ◽  
pp. 095441002110169
Author(s):  
Rhys Hutchinson ◽  
Jeremy Lawrence ◽  
Keith F Joiner
Keyword(s):  
High Speed ◽  
Engine Performance ◽  
Cost Effective ◽  
Flight Test ◽  
Combined Cycle ◽  
Propulsion System ◽  
Technological Advancement ◽  
High Speed Design ◽  
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 whether the configuration of a 200-passenger Mach 3.0 aircraft is feasible using extant technology. This research article is the second part of two and covers a suitable and cost-effective propulsion system for the executive supersonic passenger aircraft. Through this high-speed design, the research examines modern propulsion technology and the performance advancements it affords through higher efficiencies, higher metallurgical thermal limits, variable cycle engines and variable stator technology. The analysis was conducted on several potential propulsion systems using GasTurb software to obtain engine performance data. The performance results led to a combined cycle turbofan–ramjet engine as being the engine that could yield the most extensive range for the aircraft. Further investigation is needed on aircraft noise, engine emissions, the accuracy of the thrust-critical lift-to-drag ratios and the aeroelastic effects that can be closely coupled to noise and performance.

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.

Practical problems of numerical optimization in aerospace sciences

2017 ◽  
Vol 89 (4) ◽  
pp. 570-578 ◽  
Author(s):  
Jacek Mieloszyk
Keyword(s):  
Design Process ◽  
Numerical Optimization ◽  
Optimization Problems ◽  
Aircraft Design ◽  
Lessons Learned ◽  
Multidisciplinary Optimization ◽  
Content Type ◽  
Design Procedures ◽  
Industry Practice

Purpose The paper aims to apply numerical optimization to the aircraft design procedures applied in the airspace industry. Design/methodology/approach It is harder than ever to achieve competitive construction. This is why numerical optimization is becoming a standard tool during the design process. Although optimization procedures are becoming more mature, yet in the industry practice, fairly simple examples of optimization are present. The more complicated is the task to solve, the harder it is to implement automated optimization procedures. This paper presents practical examples of optimization in aerospace sciences. The methodology is discussed in the article in great detail. Findings Encountered problems related to the numerical optimization are presented. Different approaches to the solutions of the problems are shown, which have impact on the time of optimization computations and quality of the obtained optimum. Achieved results are discussed in detail with relation to the used settings. Practical implications Investigated different aspects of handling optimization problems, improving quality of the obtained optimum or speeding-up optimization by parallel computations can be directly applied in the industry optimization practice. Lessons learned from multidisciplinary optimization can bring industry products to higher level of performance and quality, i.e. more advanced, competitive and efficient aircraft design procedures, which could be applied in the industry practice. This can lead to the new approach of aircraft design process. Originality/value Introduction of numerical optimization methods in aircraft design process. Showing how to solve numerical optimization problems related to advanced cases of conceptual and preliminary aircraft design.

scholarly journals Numerical continuation and bifurcation analysis in aircraft design: an industrial perspective

2015 ◽  
Vol 373 (2051) ◽  
pp. 20140406 ◽  
Author(s):  
Sanjiv Sharma ◽  
Etienne B. Coetzee ◽  
Mark H. Lowenberg ◽  
Simon A. Neild ◽  
Bernd Krauskopf
Keyword(s):  
Steady State ◽  
Design Process ◽  
Bifurcation Analysis ◽  
Aircraft Design ◽  
Numerical Continuation ◽  
Valuable Insight ◽  
Systems Software ◽  
Control Community ◽  
Passenger Aircraft ◽  
The Military

Bifurcation analysis is a powerful method for studying the steady-state nonlinear dynamics of systems. Software tools exist for the numerical continuation of steady-state solutions as parameters of the system are varied. These tools make it possible to generate ‘maps of solutions’ in an efficient way that provide valuable insight into the overall dynamic behaviour of a system and potentially to influence the design process. While this approach has been employed in the military aircraft control community to understand the effectiveness of controllers, the use of bifurcation analysis in the wider aircraft industry is yet limited. This paper reports progress on how bifurcation analysis can play a role as part of the design process for passenger aircraft.

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.

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