Your Selections

AeroTech Europe
Show Only

Collections

File Formats

Content Types

Dates

Sectors

Topics

Authors

Publishers

Affiliations

Events

   This content is not included in your SAE MOBILUS subscription, or you are not logged in.
new

Automation of Sorting and Kitting from Cutting Tables

Broetje-Automation GmbH-Erik Berg
Published 2019-09-16 by SAE International in United States
Within the current part production of carbon fiber parts a lot of manual work is included for sorting and kitting of automatic cut plies. This is required due to the high raw material costs and enables a good utilization of the materials. Automation of this non-value adding process will be a big benefit for the part production. The high variety of shapes and the different materials to be processed are complex boundary conditions, which are to be overcome.Broetje is in development of handling systems and automation solutions, which are used for a high variety of materials as well as for a high variety of shapes. These systems are meant to be an add-on for existing cutting tables as well as for fully integrated production systems with downstream automation equipment like draping hoods.Mayor challenges to overcome are safe gripping capabilities, detection of non-cut fibers, high variety of shapes, complex logistic management. These challenges are addressed with Broetje’s ASK solution.This paper will focus on the innovative ASK solution invented by Broetje-Automation.
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.
new

Energy Recovery Rate from an Electric Air-Cycle System under the Cruising Altitude and Speed

Akita University-Takahiro Adachi, Mikio Muraoka
IHI Corporation-Naoki Seki, Hitoshi Oyori
Published 2019-09-16 by SAE International in United States
A new electric air-cycle system of aircrafts is investigated focusing on energy recovery from the exhaust air. The working fluid of air has the higher energy level in the cabin than in the outside during the cruise because the outside air is at low pressure and low temperature. In the system, by setting a recovery turbine behind the cabin, the discharged energy can be collected, although the working fluid through the system has been only discharged from the cabin into the outside. We perform a thermodynamic cycle-analysis, where the temperature, pressure, entropy, etc. are calculated at each position of the cycle by considering the two pressure ratios of the compressors as variable parameters to show T-s diagram. In addition, we obtain an energy recovery rate of the recovery energy to the necessary power for the electric compressor. The energy recovery rate is roughly estimated 40-80% under the reasonable practical operating conditions.
This content contains downloadable datasets
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.
new

Hypersonic Flow Simulation towards Space Propulsion Geometries

Universidade Da Beira Interior-Odelma Teixeira, Jose Pascoa
Published 2019-09-16 by SAE International in United States
This work aims to expand the applicability of an open-source numerical tool to solve hypersonic gas dynamic flows for space propulsion geometries. This is done by validating the code using two well-known hypersonic test cases, the double cone and the hollow cylinder flare, used by the NATO Research and Technology Organization for the validation of hypersonic flight for laminar viscous-inviscid interactions (D. Knight, “RTO WG 10 - Test cases for CFD validation of hypersonic flight,” in 40th AIAA Aerospace Sciences Meeting & Exhibit, 2002). The Computational Fluid Dynamic (CFD) simulation is conducted using the two-temperature solver hy2Foam that is capable to study external aerodynamics in re-entry flows. In the present work the assessment of hy2Foam to solve hypersonic complex flow features with strong interactions including non-equilibrium effects was demonstrated. Freestream conditions with stagnation enthalpy of 5.44 MJ/kg and Mach number of 12.2, for the double cone case, and stagnation enthalpy of 5.07 MJ/kg and Mach number of 11.3 for the hollow cylinder case were considered. Comparison with newer existing numerical data and experimental data from…
This content contains downloadable datasets
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.
new

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

Mentor-Muhammad Askar
Published 2019-09-16 by SAE International in United States
The complex and risky process of designing derivative aircraft, especially when it comes to electrical systems, can be a daunting task at best. There are a number of design strategies that can be employed to mitigate risk and increase the overall efficiency. Quite simply, the current methods of manual processes, design and integration approaches that were optimized from mechanical approaches, are no match for today’s complexities.One method gaining significant traction is to employ a central database serving global interface definitions for the entire design process. Automation through generative design minimizes manual intervention and repetitive work. Furthermore, detecting changes through design rule checks allows system engineers to verify their designs, capturing both inadvertent and planned changes. The ability to instantly update the design content from the new definition streamlines the change management process.Employing these technologies in a digital, connected thread, ensures that intelligent information is leveraged at every step along the way from aircraft conception, realization, and finally to utilization - thereby minimizing risk and maximizing efficiency.
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.
new

Gradationally Controlled Voltage Inverter for More Electric Aircrafts

IHI Corporation-Hitoshi Oyori
Mitsubishi Electric Corp.-Tetsuya Kojima, Masahiro Sugahara, Yusuke Shirouchi, Hisatoshi Fukumoto, Akihiko Iwata
Published 2019-09-16 by SAE International in United States
The more electric aircraft (MEA) concept has been attracting attention over recent decades to reduce emissions and fuel consumption. In MEAs, many subsystems that previously used hydraulic or pneumatic power have been replaced by electrical systems, and hence the weight of inverters has significant importance. The weight of inverters is largely attributed to passive filters that reduce the derivative of output voltages dv/dt and electromagnetic interference noises caused by common-mode voltages. To reduce the size of passive filters, multilevel inverters with 5 or more voltage steps are preferred. However, classic multilevel inverters have some challenges to achieve these step numbers without using plural dc power supplies that require massive transformers. In this work, a gradationally controlled voltage (GCV) inverter is proposed for MEAs. The GCV inverter can supply gradational quasi-sinusoidal voltages with 7 voltage steps, combining two different voltages from a three-level (main) inverter and H-bridge (sub) inverters. In addition, only one dc power supply is required for the main inverter. Furthermore, when sub inverters have faults, the GCV inverter can continue operation using the…
This content contains downloadable datasets
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.
new

Low Cost Reconfigurable Jig Tooling and In-Process Metrology for High Accuracy Prototype Rotorcraft Wing Assembly

University of Nottingham-Richard J. Crossley, Svetan Ratchev
Published 2019-09-16 by SAE International in United States
Reconfigurable tooling frames consisting of steel box sections and bolted friction clamps offer an opportunity to replace traditional expensive welded steel tooling. This well publicized reconfigurable reusable jig tooling has been investigated 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 end to end accuracy, over the 4m length, than conventional wings. During the investigation some fundamental issues are approached, including:Potential cost savings and variables which effect the business case.Achievable Jig accuracy.Potential sources of instability that may affect accuracy over time.Repeatability of measurements with various features and methods.Typical jig stability over 24hrs including effects of small temperature fluctuations.Deflections that occur due to loading.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 the accurate build and certification documentation to be completed. A prototype 4m test jig comprising of commercially available components and bespoke machined ‘pick-ups’ is presented.Hardware and…
This content contains downloadable datasets
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.
new

Design and Experimental Verification of a High Force Density Tubular Permanent Magnet Linear Motor for Aerospace Application

Daido University-Yoshiaki Kano
KYB Corporation-Kousuke Satou
Published 2019-09-16 by SAE International in United States
This paper presents the design and construction of a high force density tubular permanent-magnet (PM) linear motor. A strut structure of a tubular PM linear motor developed to improve resistance to impurities and structural rigidity is described.In the design, computationally efficient two-dimensional finite-element analysis is used to estimate the motor force density. The motor’s design is optimized for the major pole number/slot number combinations of 8/24, 16/24, 20/24, 28/24, 32/24, and 40/24. The optimized motor design of a three-phase 16/24 combination with one-layer winding achieved the highest force-to-mass density. The force-to-mass density of the designed motor is higher than that of the first prototype motor by a factor of 5. The validity of the proposed design method and the expected drive characteristics are experimentally verified using the prototype.
This content contains downloadable datasets
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.
new

A Service-Based Modelling Approach to Ease the Certification of Multi-Core COTS Processors

ONERA-Frédéric Boniol, Youcef Bouchebaba, Julien Brunel, Kevin Delmas, Claire Pagetti, Thomas Polacsek, Nathanaël Sensfelder
Published 2019-09-16 by SAE International in United States
The Phylog project aims at offering a model-based software-aided certification framework for aeronautical systems based on multi/many-core architectures. Certifying such platforms will entail fulfilling the high level objectives of the MCP-CRI / CAST-32A position paper. Among those, two types of analysis are required: interference and safety analyses. Because of the large size of the platforms and their complexity, those analyses can lead to combinatorial explosion and to some misinterpretation. To tackle these issues, we explore a service-based modelling approach that leads to a simplification of the analyses and to the highlighting of salient properties, making the adaptation of the certification argumentation efficient.
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.
new

Optimization of Automated Airframe Assembly Process on Example of A350 S19 Splice Joint

Airbus-Elodie Bonhomme, Pedro Montero-Sanjuan
Peter the Great St. Petersburg Polytechnic University-Sergey Lupuleac, Julia Shinder, Maria Churilova, Nadezhda Zaitseva, Valeriia Khashba
Published 2019-09-16 by SAE International in United States
The paper presents the numerical approach to simulation and optimization of A350 S19 splice assembly process. The main goal is to reduce the number of installed temporary fasteners while preventing the gap between parts from opening during drilling stage. The numerical approach includes computation of residual gaps between parts, optimization of fastener pattern and validation of obtained solution on input data generated on the base of available measurements. The problem is solved with ASRP (Assembly Simulation of Riveting Process) software. The described methodology is applied to the optimization of the robotized assembly process for A350 S19 section.
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.
new

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

Hamburg University of Technology-Hartmut Hintze, Fabian Giertzsch, Ralf God
Published 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…
This content contains downloadable datasets
Annotation ability available