Advanced aircraft performance analysis

2018 ◽  
Vol 90 (4) ◽  
pp. 627-638 ◽  
Author(s):  
Marc Immer ◽  
Philipp Georg Juretzko
Keyword(s):  
Performance Analysis ◽  
Design Process ◽  
Performance Optimization ◽  
Electric Propulsion ◽  
Vertical Plane ◽  
Aircraft Design ◽  
Efficient Design ◽  
Content Type ◽  
Aircraft Performance ◽  
Hybrid Electric

Purpose The preliminary aircraft design process comprises multiple disciplines. During performance analysis, parameters of the design mission have to be optimized. Mission performance optimization is often challenging, especially for complex mission profiles (e.g. for unmanned aerial vehicles [UAVs]) or hybrid-electric propulsion. Therefore, the purpose of this study is to find a methodology that supports aircraft performance analysis and that is applicable to complex profiles and to novel designs. Design/methodology/approach As its core element, the developed method uses a computationally efficient C++ software “Aircraft Performance Program” (APP), which performs a segment-based mission computation. APP performs a time integration of the equations of motion of a point mass in the vertical plane. APP is called via a command line interface from a flexible scripting language (Python). On top of APP’s internal radius of action optimization, state-of-the-art optimization packages (SciPy) are used. Findings The application of the method to a conventional climb schedule shows that the definition of the top of climb has a significant influence on the resulting optimum. Application of the method to a complex UAV mission optimization, which included maximizing the radius of action, was successful. Low computation time enables to perform large parametric studies. This greatly improves the interpretation of the results. Research limitations/implications The scope of the paper is limited to the methodology that allows for advanced performance analysis at the conceptual and preliminary design stages with an emphasis on novel propulsion concepts. The methodology is developed using existing, validated methods, and therefore, this paper does not contain comprehensive validation. Other disciplines, such as cost analysis, life-cycle assessment or market analysis, are not considered. Practical implications With the proposed method, it is possible to obtain not only the desired optimum mission performance but also off-design performance of the investigated design. A thorough analysis of the mission performance provides insight into the design’s capabilities and shortcomings, ultimately aiding in obtaining a more efficient design. Originality/value Recent developments in the area of hybrid or hybrid-electric propulsion systems have shown the need for performance computation tools aiding the related design process. The presented method is especially valuable when novel design concepts with complex mission profiles are investigated.

Environmental assessment of hybrid-electric propulsion in conceptual aircraft design

2020 ◽  
Vol 247 ◽  
pp. 119477 ◽  
Author(s):  
João Ribeiro ◽  
Frederico Afonso ◽  
Inês Ribeiro ◽  
Bruna Ferreira ◽  
Hugo Policarpo ◽  
...  
Keyword(s):  
Environmental Assessment ◽  
Electric Propulsion ◽  
Aircraft Design ◽  
Conceptual Aircraft Design ◽  
Hybrid Electric

A roadmap for BIM adoption and implementation in developing countries: the Pakistan case

2019 ◽  
Vol 14 (1) ◽  
pp. 112-132 ◽  
Author(s):  
Suzan Girginkaya Akdag ◽  
Uzair Maqsood
Keyword(s):  
Developing Countries ◽  
Performance Analysis ◽  
Design Process ◽  
Cost Estimation ◽  
Architectural Design ◽  
Facilities Management ◽  
Content Type ◽  
Adoption And Implementation ◽  
Whole Life Cycle ◽  
And Training

Purpose Digital media is reshaping architectural design by introducing new tools, methods and workflows. Among various AEC tools, Building Information Modeling (BIM) has gained popularity due to its collaboration platform enabling cross-disciplinary teamwork during whole life cycle of buildings. BIM has further transformed culture and processes associated with design, construction and operation of buildings, hence triggering new building regulations in developed countries. However, in developing countries, BIM implementation is facing several barriers, such as lack of investment in technology and training, hesitation in quitting traditional tools and practices, etc. The purpose of this paper is to highlight potentials of BIM for developing countries, which are in need of more sustainable policies for enhancing their economic and environmental performances. Design/methodology/approach Throughout the text, a literature review on BIM including its dimensions and benefits, impacts on architectural design and adoption in global and local contexts is provided. In case study, surveys and structured interviews are conducted with BIM user and non-BIM user architects throughout Pakistan. Beyond 2D/3D modeling, the use of BIM applications for sustainable design process such as scheduling (4D), cost estimation (5D), performance analysis and facilities management (6D) is investigated. Findings Using analytical tools of an online surveying tool and SPSS statistical software, barriers and motivations for BIM implementation in Pakistan are determined. Strategies for further BIM adoption and implementation via “education and training institutions” and “supporting organizations and institutions” are defined. Originality/value As a developing country, Pakistan shall be moving the barriers for the spread of BIM technology. Recent research covered the entire AEC sector (Masood et al., 2014; Sohu et al., 2017; Ali et al., 2018), yet this paper focuses specifically on architectural design and practice field. In order to find out experiences and expectations about BIM technology in the architecture sector, professionals are surveyed and four chief architects are interviewed. How far have Pakistani architects adopted BIM? For which project types and scales is BIM more serviceable for them? Which BIM applications are they implementing to overcome the limitations in their professional practice? In Pakistan, where sustainability, in terms of scheduling, cost estimation, performance analysis and facilities management, is an indispensible measure for local practices, has implementation of BIM technology achieved sustainability in architectural design process? What are the motivations of Pakistani architects for becoming BIM users in future?

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.

The effect of wing-tip propulsors on Icaré 2 aeroelasticity

2019 ◽  
Vol 91 (3) ◽  
pp. 509-524
Author(s):  
Wojciech Chajec ◽  
Wieslaw A. Krzymien ◽  
Andreas Strohmayer
Keyword(s):  
Electric Propulsion ◽  
Aircraft Design ◽  
Design Modification ◽  
Content Type ◽  
Test Execution ◽  
Strip Theory ◽  
Flutter Analysis ◽  
Solar Powered ◽  
The Impact ◽  
Wing Tip

Purpose The separation of energy conversion and propulsor is a promising aspect of hybrid-electric propulsion systems, allowing for increased installation efficiencies and setting the basis for distributed propulsion concepts. University of Stuttgart’s Institute of Aircraft Design has a long experience with electrically powered aircraft, starting with Icaré 2, a solar-powered glider flying, since 1996. Icaré 2 recently has been converted to a three-engine motor glider with two battery-powered wing-tip propellers, in addition to the solar-powered main electric motor. This adds propulsion redundancy and will allow analyzing yaw control concepts with differential thrust and the propeller-vortex interaction at the wing-tip. To ensure airworthiness for this design modification, new ground vibration tests (GVTs) and flutter calculations are required. The purpose of this paper is to lay out the atypical approach to test execution due to peculiarities of the Icaré 2 design such as an asymmetrical aileron control system, the long wing span with low frequencies of the first mode and elevated wing tips bending under gravity and thus affecting the accuracy of the wing torsion frequency measurements. Design/methodology/approach A flutter analysis based on GVT results is performed for the aircraft in basic configuration and with wing tip propulsors in pusher or tractor configuration. Apart from the measured resonant modes, the aircraft rigid body modes and the control surface mechanism modes are taken into consideration. The flutter calculations are made by a high-speed, low-cost software named JG2 based on the strip theory in aerodynamics and the V-g method of flutter problem solution. Findings With the chosen atypical approach to GVT the impact of the suspension on the test results was shown to be minimal. Flutter analysis has proven that the critical flutter speed of Icaré 2 is sufficiently high in all configurations. Practical implications The atypical approach to GVT and subsequent flutter analysis have shown that the effects of wing-tip propulsors on aeroelasticity of the high aspect ratio configuration do not negatively affect flutter characteristics. This analysis can serve as a basis for an application for a permit to fly. Originality/value The presented methodology is valuable for the flutter assessment of aircraft configurations with atypical aeroelastic characteristics.

Knowledge-enabled digital twin for smart designing of aircraft assembly line

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Xiao Chang ◽  
Xiaoliang Jia ◽  
Kuo Liu ◽  
Hao Hu
Keyword(s):  
Design Process ◽  
Assembly Line ◽  
Design Method ◽  
Physical Interaction ◽  
Efficient Design ◽  
Content Type ◽  
Improve Design ◽  
Aircraft Assembly ◽  
Digital Twin ◽  
Design Scheme

Purpose The purpose of this paper is to provide a knowledge-enabled digital twin for smart design (KDT-SD) of aircraft assembly line (AAL) to enhance the AAL efficiency, performance and visibility. Modern AALs usually need to have capabilities such as digital-physical interaction and self-evaluation that brings significant challenges to traditional design method for AAL. The digital twin (DT) combining with reusable knowledge, as the key technologies in this framework, is introduced to promote the design process by configuring, understanding and evaluating design scheme. Design/methodology/approach The proposed KDT-SD framework is designed with the introduction of DT and knowledge. First, dynamic design knowledge library (DDK-Lib) is established which could support the various activities of DT in the entire design process. Then, the knowledge-driven digital AAL modeling method is proposed. At last, knowledge-based smart evaluation is used to understand and identify the design flaws, which could further improvement of the design scheme. Findings By means of the KDT-SD framework proposed, it is possible to apply DT to reduce the complexity and discover design flaws in AAL design. Moreover, the knowledge equips DT with the capacities of rapid modeling and smart evaluation that improve design efficiency and quality. Originality/value The proposed KDT-SD framework can provide efficient design of AAL and evaluate the design performance in advance so that the feasibility of design scheme can be improved as much as possible.

scholarly journals Sizing implications of a regional aircraft for inner-city operations

2017 ◽  
Vol 89 (4) ◽  
pp. 520-534 ◽  
Author(s):  
Philipp Heinemann ◽  
Michael Schmidt ◽  
Felix Will ◽  
Sascha Kaiser ◽  
Christoph Jeßberger ◽  
...  
Keyword(s):  
Inner City ◽  
Design Process ◽  
Aircraft Design ◽  
Low Noise ◽  
Load Factor ◽  
Concept Design ◽  
Holistic View ◽  
Content Type ◽  
Fuel Burn ◽  
Flight Path Optimization

Purpose The paper aims to assess the potential of aircraft operation from city centres to achieve shortened travel times and the involved aircraft design process. Design/methodology/approach The paper describes the methodical approach and iterative procedure of the design process. An assessment of potential technologies is conducted to provide the required enhancements to fulfil the constraints following an inner-city operation. Operational procedures were analysed to reduce the noise propagation through flight path optimization. Furthermore, a ground-based assisted take-off system was conceived to lower required take-off field length and to prevent engine sizing just for the take-off case. Cabin design optimization for a fast turnaround has been conducted to ensure a wide utilization spectrum. The results prove the feasibility of an aircraft developed for inner city operation. Findings A detailed concept for a 60-passenger single aisle aircraft is proposed for an Entry-Into-Service year 2040 with a design range of 1,500 nautical miles for a load factor of 90 per cent. Although the design for Short Take-off and Landing and low noise operation had to be traded partly with cruise efficiency, a noteworthy reduction in fuel burn per passenger and nautical mile could be achieved against current aircraft. Practical implications The findings will contribute to the evaluation of the feasibility and impact of the Flightpath 2050 goal of a 4-h door-to-door by providing a feasible but ambitious example. Furthermore, it highlights possible bottlenecks and problems faced when realizing this goal. Originality/value The paper draws its value from the consideration of the overall sizing effects at aircraft level and from a holistic view on an inner-city airport/aircraft concept design for a 4-h door-to-door goal.

Using additive manufactured parametric models for wind tunnel test-based aerodynamic shape optimization

2020 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Hyoung Seog Chung ◽  
Seung Pil Kim ◽  
Younseok Choi
Keyword(s):  
Wind Tunnel ◽  
Shape Optimization ◽  
Design Process ◽  
Wind Tunnel Test ◽  
Aircraft Design ◽  
Parametric Models ◽  
Shape Design ◽  
Wind Tunnel Tests ◽  
Content Type ◽  
Aerodynamic Shape

Purpose The purpose of this paper is to propose a new approach of using additively manufactured parametric models in the wind tunnel test-based aerodynamic shape optimization (ASO) framework and to present its applicability test results obtained from a realistic aircraft design problem. Design/methodology/approach For aircraft shape optimization, the following three methodologies were used. First, as a validation study, the possibility of using rapid prototyping (RP) model in the wind tunnel test was verified. Second, through the wind tunnel test-based ASO, the application and feasibility of the real fighter aircraft shape optimization were verified. A generic fighter configuration is parameterized to generate various test models using additive manufacturing. Wind tunnel tests are conducted to measure their stability criteria in high angle of attack (AOA). Finally, a computational fluid dynamics (CFD) study was performed and analysis procedures, costs and results compared to the wind tunnel test were compared and reviewed. Findings RP technology can significantly reduce the time and cost of generating parametric wind tunnel models and can open up new possibilities for wind tunnel tests to be used in the rigorous aerodynamic design loop. There was a slight difference between the results of the RP model and the metallic model because of rigidity and surface roughness. However, the tendency of the aerodynamic characteristics was very similarly predictable. Although there are limitations to obtaining precise aerodynamic data, it is a suitable method to be applied to comparative studies on various shapes with large geo-metric changes in the early phase of design. The CFD analysis indicates that the wind tunnel-based ASO using the RP model shows the efficiency corresponding to the CFD shape optimization. Research limitations/implications The RP parametric models may have various assembly error sources and rigidity problems. The proposed methodology may not be suitable for collecting the accurate aerodynamic database of a final design; rather, the methodology is more suitable to screen out many configurations having fairly large shape variation in the early stage of the design process. Practical implications The wind tunnel test-based ASO can replace or supplement CFD-based ASO. In areas where CFD accuracy is low, such as high AOA flight characteristics, RP model wind tunnel-based ASO can be a research method that can secure both efficiency and accuracy advantages, providing ten times more effective in terms of cost and time. The wind tunnel test is used to obtain aerodynamic data at the final stage of shape design. It can be extended to a comparative study of several shapes in the early design phase. This procedure can be applied for both industrial level and educational aircraft design activities. Originality/value This study is the application to be applied as a parametric study on the whole aircraft, rather than using the RP model applying a simple partial control surface or configuration change of a part of the wing. The possibility of using the RP model was confirmed by comparing and verifying each other in a medium-sized wind tunnel using a relatively large RP model and a metallic model. It was verified that it can be applied in the shape design process, not the shape verification in the traditional design procedure, and a comparison with the CFD method was also performed. With further development and validation efforts, the new design framework may become an industrial standard for future aircraft development.

Synergistic hybrid-electric liquid natural gas drone: S.H.I.E.L.D

2020 ◽  
Vol 92 (5) ◽  
pp. 757-768 ◽  
Author(s):  
Thierry Sibilli ◽  
Capucine Senne ◽  
Hugo Jouan ◽  
Askin T. Isikveren ◽  
Sabrina Ayat
Keyword(s):  
Thermal Management ◽  
Synergistic Effects ◽  
Energy System ◽  
Sensitivity Study ◽  
Coolant Temperature ◽  
Electrical System ◽  
Content Type ◽  
Electric Aircraft ◽  
Aircraft Performance ◽  
Hybrid Electric

Purpose With the objective to assess potentially performant hybrid-electric architectures, this paper aims to present an aircraft performance level evaluation, in terms of range and payload, of the synergies between a hybrid-electric energy system configuration and a cryogenic fuel system. Design/methodology/approach An unmanned aerial vehicle (UAV) is modeled using an aircraft performance tool, modified to take into account the hybrid nature of the system. The fuel and thermal management systems are modeled looking to maximize the synergistic effects. The electrical system is defined in series with the thermal engine and the performance, in terms of weight and efficiency, are tracked as a function of the cooling temperature. Findings The results show up to a 46 per cent increase in range and up to 7 per cent gain on a payload with a reference hybrid-electric aircraft that uses conventional drop-in JP-8 fuel. The configuration that privileges a reduction in mass of the electric motors by taking advantage of the cryogenic coolant temperature shows the highest benefits. A sensitivity study is also presented showing the dependency on the modeling capabilities. Practical implications The synergistic combination of a cryogenic fuel and the additional heat sources of a hybrid-electric system with a tendency to higher electric component efficiency or reduced weight results in a considerable performance increase in terms of both range and payload. Originality/value The potential synergies between a cryogenic fuel and the electrical system of a hybrid-electric aircraft seem clear; however, at the present, no detailed performance evaluation at aircraft level that includes the fuel, thermal management and electric systems, has been published.

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