Airbus A320 Research Articles

A Scheduling Tool for Bridging the Gap Between Aircraft Design and Aircraft Manufacturing

For aircraft manufacturers, the market demand in the nowadays aeronautical industry requires a high reactivity between teams in charge of the design of the aircraft and teams in charge of its production system. One way to increase this reactivity is to help the design architects understand the way the aircraft is produced together with the bottlenecks in the manufacturing process, and to help them evaluate the impact of a design modification on the production system. This paper addresses these two needs. We formally describe the scheduling problem considered, the algorithmic approaches developed, the implemented tool, and results obtained on data from a real production line of the Airbus A320 aircraft family.

Super high-speed electric motor with amorphous magnetic circuit for the hydrogen fuel cell air supply system

Hydrogen fuel cells are one of the important directions of development of the global energy. Hydrogen fuel cells are being actively implemented in the aviation systems, for example in Airbus A320. Boeing and Airbus announced creation of an auxiliary power unit fuel cell with capacity up to 200 kW in 2017–2018. In the automotive industry hydrogen fuel cells are also widely used. But the efficient use of hydrogen fuel cells is not possible without establishment of effective systems related to their operation.Therefore, our article proposes a new topology of high-speed motor for compressor of the hydrogen fuel cell. An original solution to raise the energy efficiency of high-speed motor presented in our article, the novelty of which is the use of amorphous alloys. Research of the new design methods of computer modeling in Ansys Maxwell was conducted; optimal geometric dimensions of the high-speed motor with two-pole and four-pole magnetic system were obtained in this article. In the modeling losses on eddy currents in permanent magnets and iron of the rotor for two-pole and four-pole magnetic systems were taken into account. All the theoretical results have been experimentally verified. For this purpose the layout of the high-speed motor with the perforated winding was created. Design of the experimental model is also described in this article. The high-speed motor testing and analysis of test data take a special place in this article. In the experimental tests was found that the efficiency of our topology is 92.8% and the power density of our high-speed motor is 0.21 kg/kW with air cooling. These experimental tests prove the effectiveness of our topology compared to the known world analogues. Also in the article was proven that the use of our topology allows minimizing the mass of a hydrogen fuel cell with improved energy efficiency. This is especially important for the aerospace applications and automotive industry.

Penetration depth of RC panels subjected to the impact of aircraft engine missiles

The aircraft collision with RC structures would lead to the global response and local damage, which are mainly caused by the impact of the entire aircraft and the massive engines, respectively. This paper mainly aims to study the penetration depth of RC structures, particularly for the nuclear power plant (NPP) containment, subjected to the impact of aircraft engine missiles. Firstly, the widely-used empirical formulae for predicting the penetration depth of rigid projectiles, as well as the existing notable engine missile impact test are introduced briefly. Then, by utilizing an advanced large-caliber air gas gun, a series of 1/10 reduce-scaled engine impact test on the 150 mm thick RC panels was conducted. The striking velocities were ranged from 94 m/s to 184 m/s, considering the taking off/landing and maximal cruising speeds of common commercial aircrafts, e.g., Airbus A320. The impact processes, missile deformation and panel damage were recorded and assessed. Finally, based on the present and existing tests data, the Haldar and Hamieh (1984) formula for rigid projectile was modified by introducing a reduction coefficient of 0.5 to predict the penetration depth of RC panels hit by the deformable engine, which is more accurate and practical than NEI (Nuclear Energy Institute) recommendation.

A Wavelet-Enhanced PWTD-Accelerated Time-Domain Integral Equation Solver for Analysis of Transient Scattering From Electrically Large Conducting Objects

A wavelet-enhanced plane-wave time-domain (PWTD) algorithm for efficiently and accurately solving time-domain surface integral equations (TD-SIEs) on electrically large conducting objects is presented. The proposed scheme reduces the memory requirement and computational cost of the PWTD algorithm by representing the PWTD ray data using local cosine wavelet bases (LCBs) and performing PWTD operations in the wavelet domain. The memory requirement and computational cost of the LCB-enhanced PWTD-accelerated TD-SIE solver, when applied to the analysis of transient scattering from smooth quasi-planar objects with near-normal incident pulses, scale nearly as $O(N_{s} \log N_{s})$ and $O(N_{s}^{1.5})$ , respectively. Here, $N_{s} $ denotes the number of spatial unknowns. The efficiency and accuracy of the proposed scheme are demonstrated through its applications to the analysis of transient scattering from a 185-wavelength long NASA almond and a 123-wavelength long Airbus A-320 model.

Analysis of runway pavement response under aircraft moving load by FEM

PurposeGiven the importance of airports and the need to develop this issue in runway, the purpose of this study, pavement response values under loading of different aircraft have been obtained using tire and pavement modeling by finite element method (FEM). To predict the actual behavior of pavements under aircraft loading, dynamic analysis of runway flexible pavement was performed using Abaqus software version 6.10.Design/methodology/approachThe method is based on finite element analysis and software simulation. And the main goal to obtain the amount of pavement stress and deflection at different speeds.FindingsThe results of modeling showed that aircraft movement at a speed of 5-8 km/h leads to the highest stresses and deflections in the pavement. Moreover, the effect of elastic modulus variations of the asphalt concrete on the tensile strain under advisory circular layer was calculated for Airbus A380 by using FEM. To validate the results of the runway pavement dynamic analysis, the results of modeling have been compared with the field test results of National Airport Pavement Test Facility.Originality/valueStresses and deflections of pavement during aircraft movement at different speeds of 5, 8 and 20 km/h on the runway have been presented, and the critical points in length, width and depth of runway pavement, as well as the most critical speed of aircraft in terms of induced damage to the pavement, have been obtained.

Impact of Alternative Jet Fuels on Engine Exhaust Composition During the 2015 ECLIF Ground-Based Measurements Campaign.

The application of fuels from renewable sources ("alternative fuels") in aviation is important for the reduction of anthropogenic carbon dioxide emissions, but may also attribute to reduced release of particles from jet engines. The present experiment describes ground-based measurements in the framework of the ECLIF (Emission and Climate Impact of Alternative Fuels) campaign using an Airbus A320 (V2527-A5 engines) burning six fuels of chemically different composition. Two reference Jet A-1 with slightly different chemical parameters were applied and further used in combination with a Fischer-Tropsch synthetic paraffinic kerosene (FT-SPK) to prepare three semi synthetic jet fuels (SSJF) of different aromatic content. In addition, one commercially available fully synthetic jet fuel (FSJF) featured the lowest aromatic content of the fuel selection. Neither the release of nitrogen oxide or carbon monoxide was significantly affected by the different fuel composition. The measured particle emission indices showed a reduction up to 50% (number) and 70% (mass) for two alternative jet fuels (FSJF, SSJF2) at low power settings in comparison to the reference fuels. The reduction is less pronounced at higher operating conditions but the release of particle number and particle mass is still significantly lower for the alternative fuels than for both reference fuels. The observed correlation between emitted particle mass and fuel aromatics is not strict. Here, the H/C ratio is a better indicator for soot emission.

TECHNICAL EFFICIENCY AND TECHNICAL LEVEL INDICATORS APPLICATION FOR CIVIL AIRCRAFT FUNCTIONAL PROPERTIES ANALYSIS

Functional properties characterize the purpose of the aircraft and are described by its flight performance characteristics such as range and cruising speed, payload, runway characteristics, etc. Functional properties also characterize the aircraft efficiency that determines the objective need for their analysis by both aircraft designers and operators in conditions of permanent and systematic efficiency increase necessity. When choosing the aircraft, it is important for the operator to make sure that a selected aircraft type has a high level of functional properties, which will allow it to provide high operational efficiency without obsolescence in the long term. However, when choosing from several aircraft types the operator has to face the fact that some characteristics of considered aircraft variants are better and the others are worse that does not allow to definitely determine what aircraft type has a higher level of functional properties. The possibility of applying technical efficiency indicators and a generalized technical level indicator for analyzing the functional properties of civil aviation aircraft is explored in this article. Fuel, weight and target efficiency values as well as the previously improved technical level indicator value were calculated for the different generations and modifications of Boeing 737 and Airbus A320 families of medium-range airplanes, which was followed by the results interpretation within one airplane generation and when moving historically from one airplane generation to another. According to analysis results it is concluded that it is impossible to define the change of the aircraft functional properties level by the change in the values of separate technical efficiency indicators. Thus, it is proposed to use a generalized technical level indicator that determines the level of aircraft technical perfection for purpose and to use efficiency indicators to analyze the cost of providing this level of properties at aircraft production and operation phases.

Perception of time in microgravity and hypergravity during parabolic flight.

We explored the effect of gravity on the accuracy for estimating durations of 3.5, 7, and 14 s. Experiments were performed on board an Airbus A310 during parabolic flights eliciting repeated exposures to short periods of 0, 1, and 1.8 g. Two methods for obtaining duration estimates were used, reproduction and production of duration, in two conditions: a control counting condition and a concurrent reading condition. Simple reaction times were also measured to assess attention. The results showed that the temporal accuracies during the reproduction task in the concurrent reading condition were significantly underestimated in 0 g compared with 1 g. Reaction times were also longer in 0 g. However, there was no difference in duration estimates in the production tasks. These results suggest that the temporal underestimation in 0 g is caused by decreased selective attention and impaired retrieval of information in episodic memory.

Full Circle

The Boeing 787's troubled service entry and new engine technology have given the Airbus A330 a new lease of life

A Novel Adaptive Joint Time Frequency Algorithm by the Neural Network for the ISAR Rotational Compensation

We propose a novel adaptive joint time frequency algorithm combined with the neural network (AJTF-NN) to focus the distorted inverse synthetic aperture radar (ISAR) image. In this paper, a coefficient estimator based on the artificial neural network (ANN) is firstly developed to solve the time-consuming rotational motion compensation (RMC) polynomial phase coefficient estimation problem. The training method, the cost function and the structure of ANN are comprehensively discussed. In addition, we originally propose a method to generate training dataset sourcing from the ISAR signal models with randomly chosen motion characteristics. Then, prediction results of the ANN estimator is used to directly compensate the ISAR image, or to provide a more accurate initial searching range to the AJTF for possible low-performance scenarios. Finally, some simulation models including the ideal point scatterers and a realistic Airbus A380 are employed to comprehensively investigate properties of the AJTF-NN, such as the stability and the efficiency under different signal-to-noise ratios (SNRs). Results show that the proposed method is much faster than other prevalent improved searching methods, the acceleration ratio are even up to 424 times without the deterioration of compensated image quality. Therefore, the proposed method is potential to the real-time application in the RMC problem of the ISAR imaging.

Experimental Investigation of Cycle Properties, Noise, and Air Pollutant Emissions of an APS3200 Auxiliary Power Unit

Auxiliary power unit (APU) operators face increasingly stricter airport requirements concerning exhaust gas and noise emission levels. To simultaneously reduce exhaust gas and noise emissions and to satisfy the increasing demand of electric power on board, optimization of the current technology is necessary. Prior to any possible demonstration of optimization potential, detailed data of thermodynamic properties and emissions have to be determined. Therefore, the investigations presented in this paper were conducted at a full-scale APU of an operational aircraft. A Pratt & Whitney (East Hartford, CT) APS3200, commonly installed in the Airbus A320 aircraft family, was used for measurements of the reference data. In order to describe the APS3200, the full spectrum of feasible power load and bleed air mass flow combinations were adjusted during the study. Their effect on different thermodynamic and performance properties, such as exhaust gas temperature, pressure as well as electric and overall efficiency is described. Furthermore, the mass flows of the inlet air, exhaust gas, and fuel input were determined. Additionally, the work reports the exhaust gas emissions regarding the species CO2, CO, and NOx as a function of load point. Moreover, the acoustic noise emissions are presented and discussed. With the provided data, the paper serves as a database for validating numerical simulations and provides a baseline for current APU technology.

Friction Stir Welding of Dissimilar Metal: A Review

Friction Stir Welding (FSW) is a solid-state welding process which produces welds due to the compressive force contact of work pieces which are either rotating or moving relative to each other. The heat required to join different specimens is generated by heating due to friction at the interface. Application of Friction Stir Welding in aerospace industries is very broad. Rolls-Royce now uses friction welding processes for its modern Trent aero engines that drive the Airbus A380 and the Boeing 787. In this paper, Friction Stir Welding of various dissimilar metals is reviewed. The microstructure, hardness, and flow characteristics are also reviewed.

Friction Stir Welding of Dissimilar Metal: A Review

Friction Stir Welding (FSW) is a solid-state welding process which produces welds due to the compressive force contact of work pieces which are either rotating or moving relative to each other. The heat required to join different specimens is generated by heating due to friction at the interface. Application of Friction Stir Welding in aerospace industries is very broad. Rolls-Royce now uses friction welding processes for its modern Trent aero engines that drive the Airbus A380 and the Boeing 787. In this paper, Friction Stir Welding of various dissimilar metals is reviewed. The microstructure, hardness, and flow characteristics are also reviewed.

Performance Analysis of Ply Orientation in Composite Laminates

With advancement in Material Sciences new types of materials are being invented and researched every day. Composite materials are globally used in aircraft design to decrease emissions and significant weight reduction. Advanced composite materials, which are usually continuous fibers (mostly carbon and glass) within a polymer matrix provide superior material properties than metals and enable lighter structural designs to be achieved in aerospace applications. In recent years, advanced composites have replaced traditional structural materials in aircrafts to a significant extent (e.g. Boeing 787, Airbus A350, with more than 50% composites by weight. The evaluation technique generally involves the implementation of ANSYS & MATLAB softwares that help in designing, drafting, and analysis. The scope of this paper is to highlight the researches done in composite laminates, new fibers and resins and to create future applications for composites. Eco-friendly resins will replace recycled plastics and bio-based polymers by composites. The present paper entitled “Performance Analysis of Ply Orientation in Composite Laminates” is the work done to perform the analysis on CFRP laminate with in-plane loading condition. In this research the mathematical calculation of determining the failure criteria of the laminate with ply orientation of [90/0/0/-45/+45]s is done by writing stress program on MATLAB and further analysis is performed using ANSYS. After obtaining both the results the design is validated.

Modeling of aircraft jet noise in airports

A mathematical model with 4 degree of freedom created in Matlab for aircraft final landing trajectory is described in this paper. A midsize commercial passenger aircraft similar to an Airbus A320 has been chosen as a reference aircraft. The parameters of model are obtained from Airbus, Eurocontrol and the approach procedure at the Munich airport is selected up from Jeppesen Airway manual. A semi-empirical model of Stone for predicting the jet noise has been used. The proposed model was validated against 10 real flights obtained from Aircraft noise monitoring at Munich airport. The computed error between the real data and modelling is reported on. Obtained results are presented numerical and graphically. The observed effects of aircraft speed, aircraft angle of descent and aircraft weight for reduction of aircraft jet noise in airports represent subjects of discussions in the paper.

Reliability analysis of the aircrafts normal braking system

An identified component of Airbus A-330 aircraft which should be maintained properly is the normal braking system. The objectives of this study are to: (1) identify the critical component of the normal braking system; and (2) determine the optimal replacement time interval of replacement of the normal braking system component. This study is conducted in Garuda Maintenance Facility Aero Asia company. Primary data in this study are the components replacement data of normal braking system in period January 2015 - January 2017. The life distribution such as Mean Time to Failure (MTTF), reliability, probability density function, cumulative distribution function, and failure rate are obtained by the Weibull++ software. Results show that the critical component of the normal braking system is the brake unit assembly. Meanwhile, the life distribution analysis show that the reliability of importance value of the normal breaking system IR is 74.07 percent which occurs at MMTF and system reliability are 4365.5 hours and 55.58 percent, respectively. These values indicate that optimal replacement time interval of the Brake Unit Assembly is 5599.7 hours.

Texture and properties evaluation of pipes made of the Ti-3al-2.5V alloy after hot deformation pressing

Titanium and its alloys are widely adopted in the aircraft equipment due to the high mechanical durability which remains at high temperatures, corrosion resistance, thermal stability, specific durability, small density and other useful properties.The Ti-3Al-2.5V alloy pipes investigated in this work are used for hydraulic systems of the Boeing planes and the Airbus A320. One of the requirements to these pipes is the coefficient to relative compression (CRC) which characterizes pipes texture. For the correct technological process of pipes production it is necessary to know what texture pipes have exactly on all technological repartitions and how it changes in the course of the production. Pressed billets are used for pipes production.

In-Flight Observation of Gamma Ray Glows by ILDAS.

An Airbus A340 aircraft flew over Northern Australia with the In‐Flight Lightning Damage Assessment System (ILDAS) installed onboard. A long‐duration gamma ray emission was detected. The most intense emission was observed at 12 km altitude and lasted for 20 s. Its intensity was 20 times the background counts, and it was abruptly terminated by a distant lightning flash. In this work we reconstruct the aircraft path and event timeline. The glow‐terminating flash triggered a discharge from the aircraft wing that was recorded by a video camera operating onboard. Another count rate increase was observed 6 min later and lasted for 30 s. The lightning activity as reported by ground networks in this region was analyzed. The measured spectra characteristics of the emission were estimated.

Preliminary development of an onboard weight and balance estimator for commercial aircraft

A novel approach to onboard in-flight weight and balance estimation systems is presented. Data from an Airbus A320 fleet from an airline were used to assess the feasibility of the approach. Simple flight mechanics in combination with statistics allowed for the identification of weight and center of gravity position using cruise angle of attack, Mach number and elevator deflection values. The good agreement between the theoretical model and the obtained values for the lift curve slope as a function of Mach as well as the standard error of the estimate for center of gravity position and cruise flying weight indicate that the method is sound. The major implication of this work is that the development of onboard and in-flight weight and balance systems can be significantly simpler than previous literature suggested. The impact of this paper could be immediate for airlines since all the tools required to implement the system as described are readily available. This could have an effect in operating costs, safety and environment.

Measurements of aircraft wake vortex parameters by a Stream Line Doppler lidar

Results of measurements of the parameters of aircraft wake vortices by a Stream Line coherent Doppler lidar during the three-day experiment on the airfield of Tolmachevo Airport are presented. The spatial dynamics and evolution of the wake vortices generated by landing aircraft of different types, from Airbus A319 passenger aircraft to heavy Boeing 747-8 cargo aircraft, are analyzed. It is shown that Stream Line lidars may be used to receive reliable information about the presence and intensity of aircraft wake vortices in the vicinity of а runway.