Your Selections

Show Only


File Formats

Content Types












Numerical Prediction of Aeroacoustic Noise for Bluff Bodies at Various Reynolds Numbers with Vortex Suppression Methods

SRM Institute of Science and Technology-Sanhita Padia, Dewanshu Deep, Senthilkumar Sundararaj
  • Technical Paper
  • 2019-28-0118
To be published on 2019-10-11 by SAE International in United States
Noise of almost every form is considered undesirable and hence its reduction is an important area of study. Aerodynamically generated noise due to vortex shedding in the wake of bluff bodies is a major source of such undesirable noise in applications involving overhead wires, poles, automotive components and aircraft landing gears. Vortex suppression methods are employed in these cases to reduce the noise generated by suppressing the pressure fluctuations arising near the bluff body surface. For the present study, flow past different bluff bodies is simulated using commercial CFD software, ANSYS FLUENT, with and without involving suppression methods. The calculations for flow field are performed by solving the two-dimensional governing equations for unsteady isothermal incompressible viscous flow. Turbulence modelling is performed using Large Eddy Simulation (LES) with Smagorinsky-Lilly subgrid model. Simulations for far-field noise are carried out using Ffowcs-William and Hawking model and different aeroacoustic parameters like overall sound pressure level and sound pressure level are computed for different receiver locations. The effectiveness of different suppression methods is tested at different Reynolds numbers and their…

Investigation of thermal shock resistance of CeO2 coating on Titanium alloy by magnetron sputtering

AAA College of Engineering & Techology-Balamurugan Subburaj
Mepco Schlenk Engineering College-Bala Manikandan Cheirmakani, Balamurugan Pandian, Lionel Beneston
  • Technical Paper
  • 2019-28-0103
To be published on 2019-10-11 by SAE International in United States
Titanium alloy (Grade V) is used in aerospace, medical, marine and chemical processing industries. To improve the thermal shock resistance and corrosion resistance of the titanium alloy at elevated temperatures, Thermal barrier coating (TBC) has been predominantly used. Cerium oxides have been proposed as TBC, due to their high thermal expansion coefficient, higher thermal shock resistance, good adhesion strength, low corrosion rate and excellent tribological performance. In this study, CeO2 were coated on Titanium alloy by magnetron sputtering by varying the deposition time. The microstructure and mechanical properties of CeO2 coatings were systematically investigated. Deposition time was varied as 30 mins, 60 mins and 90 mins respectively, to achieve the variation in thickness of the coating on the substrate. The thickness of the coated specimen was measured by atomic force microscopy and found to be 500 nm, 180 nm and 70 nm respectively. Surface roughnesses of the coated surface are 152.28 nm, 86.25 nm and 18.65 nm. The Vickers hardness was found to increase with increasing amount of CeO2. Corrosion ability of the coated specimen…

Step & Repeat: Reduce Derivative Aircraft Development Risk with Design Reuse

Mentor-Muhammad Askar
  • Technical Paper
  • 2019-01-1871
To be published on 2019-09-16 by SAE International in United States
Designing derivative aircraft is a complex process with potentially large amounts of program risk. In this paper we present new technologies such as digital interface control documents, and generative design that can transform this process. Employing these types of technologies makes the process more verifiable and repeatable. The paper explains how the technologies can be adopted from the early definition of components & LRUs, to their aggregation into reusable subsystems, as well as the automation and validation processes that can be built around them to reduce the associated complexity and program risk.

Reconfigurable Jig Tooling and In-Process Metrology for High Accuracy Prototype Compound Helicopter Wing Assembly

University of Nottingham-Richard J. Crossley, Svetan Ratchev
  • Technical Paper
  • 2019-01-1877
To be published on 2019-09-16 by SAE International in United States
This paper documents the potential use of reconfigurable reusable jig tooling based on the box-joint system for use in the assembly of a prototype compound helicopter wing. Due to the aircraft configuration the wing design is pinned at both ends and therefore requires a higher degree of accuracy (typically 0.2mm), over the 4m length, than conventional wings. In this paper the cost benefit of reusable tooling in a low volume prototype scenario is examined followed by the design of the jig and location features to enable accurate build and metrology documentation. A prototype 4m test jig comprising of commercially available components and bespoke machined ‘pick-ups’ is presented here. Hardware and measurement process cost modelling is documented along with results for the positional and hinge-line concentricity setting accuracy that was achieved using a laser tracking system. Subsequent measurements over a 24hr period are also discussed along with potential sources of the observed reduction in jig accuracy over time.

Design Approach for Secure Networks to introduce Data Analytics within the Aircraft Cabin

Hamburg University of Technology-Hartmut Hintze, Fabian Giertzsch, Ralf God
  • Technical Paper
  • 2019-01-1853
To be published on 2019-09-16 by SAE International in United States
In the past, aircraft network design did not demand for information security considerations. The aircraft systems were simple, obscure, proprietary and, most importantly for security, the systems have been either physically isolated or they have been connected by directed communication links. The union of the aircraft systems thus formed a federated network. These properties are in sharp contrast with today’s system designs, which rest upon platform-based solutions with shared resources being interconnected by a massively meshed and shared communication network. The resulting connectivity and the high number of interfaces require an in-depth security analysis as the systems also provide functions that are required for the safe operation of the aircraft. This network design evolution, however, resulted in an iterative and continuous adaption of existing network solutions as these have not been developed from scratch. Now, with the upcoming trend of data analytics and artificial intelligence applications, which demand for an extensive availability of data, holistic aircraft cabin networks are necessary to satisfy the associated requirements. For the development of such networks this paper proposes a…

New Technologies for Airframe Structural Assemblies

LISI Aerospace-Mehdi Dahane
  • Technical Paper
  • 2019-01-1915
To be published on 2019-09-16 by SAE International in United States
With air traffic demand constantly increasing and several years of aircraft production in their backlog, major aircraft manufacturers are now shifting their focus toward improving assembly process efficiency. One of the most promising solutions, known as “One Side Assembly”, aims to perform the whole assembly sequence from one side of the structure (drilling, temporary fastener installation and removal, blind fastener installation, assembly control) and with a high level of integrated automation. Investments in robotic equipment, automation engineering and innovation are very active and automation capabilities have already increased a lot in the aerospace industry. As an example, drilling operations for large dimensions airframe are clearly moving from manual to automated. However, despite more and more clever and sophisticated robotics, the use of historical fasteners with two side installation method remains a strong limitation to innovative automated assembly sequences. A blind fastener which can provide the same mechanical characteristics than current structural fasteners, while providing automation friendly features and meeting cost objectives is a real “must have” for assembly process efficiency improvements. It is also full…

Intelligent Real Time Inspection of Rivet Quality Supported by Human-Robot-Collaboration

PIKON Deutschland AG-Benjamin Duppe, Albert Schulz
ZeMA GmbH-Rainer Mueller, Matthias Vette, Tobias Masiak
  • Technical Paper
  • 2019-01-1886
To be published on 2019-09-16 by SAE International in United States
Aircraft production is facing various technical challenges, such as large product dimensions, complex joining processes and the organization of assembly tasks. Meeting the requirements that come with large dimensions, low tolerances and small batch sizes, in combination with complex joining processes, automation and labour-intensive inspection task, is often difficult to achieve in an economically viable way. ZeMA believes that a semi-automated approach is the most effective for optimizing aircraft section assembly. An effective optimization of aircraft production can be achieved with a semi-automated riveting process for solid rivets using Human-Robot-Collaboration in combination with an intuitive Human-Machine-Interaction operating concept. While using dynamic task sharing between human and robot based on their skills, and considering ergonomics, the determined ideal solution involves placing a robot inside the section barrel. The robot’s workspace is expanded by mounting it on top of a lifting unit so that it can properly position the anvil. In the meantime, the human performs the more complex tasks of inserting the solid rivets and operating the riveting hammer from the outside of the section barrel.…

Low Cost, Fireproof, and Light Aircraft Interior

Sardou Societe Anonyme-Max Sardou
  • Technical Paper
  • 2019-01-1857
To be published on 2019-09-16 by SAE International in United States
Low cost, fireproof, and light aircraft interior Fire is a dramatic issue in aircraft nowadays, especially with composite air crafts. An additional issue is the dangerous use of flammable Li-Ion batteries in a lot of appliances. we propose in order to avoid dramas to produce aircraft interiors, fire doors, cargo bay walls, as well than cargo container able to contain a fire inside them, with our ceramic composite called TOUGHCERAM ®. We have developed a low-cost, ceramic, damage tolerant, this ceramic is flexible between minus 100°C and plus 350°C. TOUGHCERAM ® poly-crystalize between 60°C and 110°C and can be reinforced with fibbers like carbon or basalt one. TOUGHCERAM ® survive 90 minutes to a propane 1900°C torches. TOUGHCERAM ® does not burn, nor smoke. In this paper we will explain how it is possible to develop a fully mineral ceramic offering such unique mechanical and fire properties.

Advanced Exergy Analysis of an Air Craft Gas Turbine Engine at Different Power Loading Operations.

GIFT, Bhubaneshwar-Alok Kumar Mohapatra
VIT Universtity Vellore-Tapano Hotta
  • Technical Paper
  • 2019-01-1863
To be published on 2019-09-16 by SAE International in United States
The innovations in aircraft propulsion have been identified as the key parameter towards the progress in transportation. Continuous advancement in the performance and efficiency of propulsion has enabled aircraft to travel over larger distances with higher speed. Aviation is also responsible for approximately 2% of total greenhouse gases emission and is expected to grow around 3% by 2050. The present study aims to use the exergetic analysis of a turboprop engine which should be helpful in designing of such engines and also helps these engine users to regulate and select the operation modes. A gas turbine with film air cooling of turbine blades has been proposed to be the turboprop engine. The engine is analyzed on exergy point of view at different power loading operation modes and the performance is studied. Selected exergetic measures under consideration are Exergy Efficiency, Fuel Exergy Depletion Ratio, Relative Exergy Consumption Ratio, Exergetic Improvement potential and Productivity Lack ratio. The total fuel exergy depletion ratio of the turboprop engine is estimated to be around 44%. . Also, among the identified…

Landing Gear Integration into Aircraft Structure in Early Design Stage

Bauhaus Luftfahrt EV-Ulrich Kling, Mirko Hornung
  • Technical Paper
  • 2019-01-1890
To be published on 2019-09-16 by SAE International in United States
The demanded development towards various emission reduction goals set up by several institutions forces the aerospace industry to think about new technologies and alternative aircraft configurations. With these alternative aircraft concepts, the landing gear layout is also affected. Turbofan engines with very high bypass ratios could increase the diameter of the nacelles extensively. In this case, mounting the engines above the wing could be a possible arrangement to avoid an exceedingly long landing gear. Thus, the landing gear could be shortened and eventually mounted at the fuselage instead of the wings. Other technologies such as high aspect ratio wings have an influence on the landing gear integration as well. To assess the difference, especially in weight, between the conventional landing gear configuration and alternative layouts a method is developed based on preliminary structural designs of the different aircraft components, namely landing gear, wing and fuselage. Simplified parametric finite element structural models for the different components are introduced. These models are used to investigate different aircraft configurations with special regard on the landing gear integration. The…