Aircraft Position Prediction during the Crosswind Approach

Testing the impact of the drag coefficient on an F16 aircraft model, depending on the angle of attack a was performed. First, a navigation model was introduced describing the preliminary and computational assumptions of the model. The final part of the present paper contains the relationships between the wind angle and the wind correction angle at the angle of attack a = 00, a = 110, a = 130 for a full-scale F-16 aircraft. The tables present results of all the calculations for individual angles of attack, taking into account variable wind angles relative to the longitudinal axis of the runway. The values show the corrections calculated for an 1/19 scale aircraft model and for a full-scale F16 aircraft. The "right" and "left" designations represent the direction from which the wind blows in relation to the aircraft.

Research Civil Aircraft Model (RCAM) Dengan Metode Dinamis 6 Derajat Kebebasan Menggunakan MATLAB

Model Pesawat merupakan suatu usaha untuk menciptakan atau membuat simulasi pesawat yang sebenarnya dan model ini bisa disebut Research Civil Aircraft Model (RCAM), yaitu model pesawat sipil bermesin ganda yang dikembangkan oleh Group for Aeronautical Riset dan Teknologi di Eropa (GARTEUR). Model pesawat ini mirip dengan Boeing 757-200. Research Civil Aircraft Model yang dibuat menggunakan 6 derajat kebebasan. 6 derajat kebebasan terdiri dari 3 translasi yaitu 3 derajat untuk koordinat kartesian pada sumbu (x,y,z) dan 3 rotasi yaitu 3 derajat (pitch, roll, dan yaw) yang digunakan untuk mengontrol defleksi surface dan posisi throttle. Untuk membuat model, diperlukan parameter, yaitu parameter dari massa pesawat dan parameter dari chord aero dan juga CoG (Center of Gravity) dari suatu pesawat. Algoritma yang dimasukkan berasal dari control limits/Saturasi, Variabel Intermediate, Koefisien Force, Koefisien Momen, Efek Propulsi, Efek Gravitasi hingga akhirnya disimulasikan menggunakan “Simulink” pada MATLAB. Agar yang dihasilkan tidak hanya grafik maka diperlukannya animasi untuk melihat sikap pesawat sehingga digunakanlah 3D Animation pada MATLAB. Hasil dari permodelan pesawat sipil ini untuk melihat simulasi stabilitas dari aileron, rudder, elevator, dan throttle saat pesawat itu terbang. Hasil yang ada dapat berubah-ubah karena pada 3D Animation, pesawat dapat dikendalikan dari sikap pesawat saat miring kanan atau kiri dan juga saat pesawat berguling. Dengan adanya hal ini diharapkan simulasi tersebut bisa effective untuk melihat hasil yang sebenarnya saat pesawat terbang dan juga bisa dijadikan untuk simulator sebelum pesawat tersebut lepas landas.

Aerodynamic analysis of aircraft model using indigenously developed wind tunnel facility

This paper presents a design of force balance setup that can measure lift force acting on the aircraft model. The setup was developed indigenously and installed in an open circuit low-speed wind tunnel. It mainly consists of two components viz. a traverse mechanism that can hold the model in the test section at different angles of attack and air speeds and a supporting frame to hold the traverse mechanism over it. The spring balances are used to obtain lift force readings at different angles and air speeds. The experimental and numerical investigations were done in the wide range of Reynolds number (range: 0.55 to 1.12 lakh) and angle of attack (range: -6° to 20°). The results are presented in terms of pressure contours, velocity contours, pressure coefficient and lift coefficient. From the experiments it was found that value of lift coefficient increases with angle of attack and stalling occurs at 18° for all the air speeds. However, in the numerical results the stalling was observed little earlier than 18° angle of attack. The experimental results were compared with CFD results and an average relative error of 18% was observed which may be due to assumption of 2-D airfoil in CFD analysis.

Specifics of application of videogrammetric system Vic-3D in aerodynamic experiment

The main objective of this work was testing a possibility of application of commercial videogrammetric system Vic-3D for measuring position and deformation of the aircraft model and its elements in an industrial the TsAGI transonic wind tunnel T-128. The object of research was a model of passenger aircraft with a wingspan of 2010 mm, fixed on the rear sting. The Vic-3D system used for measuring the position and deformation of the aircraft model was applied for the runs with and without flow at the pitch angles range from − 3 to +12 degrees. Model was tested in wind tunnel up to Mach number M = 0.853. An algorithm of working with the Vic-3D system was described in the article, some specifics of obtained results were underlined. An additional program to derive bend and twist deformations of a wing was developed. Results of an experiment were given, errors and inaccuracy were analyzed. Recommendations for using the system Vic-3D in an aerodynamic experiment were given.

DEVELOPMENT OF ONTOLOGICAL DECISION MAKING SYSTEM OF THE NEGOTIATION PROCESS ON COOPERATION PRODUCTION IN AIRCRAFT

Subject matter: means of information support for the negotiation process on the organization of cooperative production of aircraft. Goal: an outline of the process of developing effective means of information support for negotiations on cooperative production, which will provide financial savings, firstly, by reducing the negotiation time, and secondly, is reducing the likelihood of making irrational decisions that can lead to additional costs during project implementation. Tasks: Increase the efficiency of the negotiation process on the organization of cooperative production by creating a problem-oriented methodological basis, and on this basis - software tools for the development, deployment and operation of the appropriate decision support system. Methods: system analysis and set theory, for the formal presentation of relevant information about the subject area "Negotiations on cooperative aircraft production"; ontological engineering, in particular the IDEF5 standard, as well as elements of expert systems technology, for building an ontological decision support system. Results: an aggregate of methodological tools for the synthesis of ontological decision support systems was developed during negotiations on the organization of cooperative production of aircraft, a scenario example of organizing an ontological dialogue in the environment of an ontological decision support system for defining an aircraft model as an object of cooperative production was given. Conclusions: the need to supplement the mathematical support of traditional negotiation support systems with special methodological means is shown to increase the efficiency of information support for the negotiation process on organizing cooperative production in aircraft construction; it is substantiated that for the program implementation of the system of information support for negotiations on the organization, it is advisable to use the ontological approach; the architecture of the intellectual core of the ontological decision support system for organizing the negotiation process for organizing the cooperative production of aircraft in the form of a hierarchy of frames, with the organization of knowledge-based inference by means of attached procedures is proposed; a scenario example of the formation of a decision on the choice of an aircraft model for the organization of cooperative production in the environment of an ontological decision support system is given.

Aircraft Type Recognition in Remote Sensing Images: Bilinear Discriminative Extreme Learning Machine Framework

Small inter-class and massive intra-class changes are important challenges in aircraft model recognition in the field of remote sensing. Although the aircraft model recognition algorithm based on the convolutional neural network (CNN) has excellent recognition performance, it is limited by sample sets and computing resources. To solve the above problems, we propose the bilinear discriminative extreme learning machine (ELM) network (BD-ELMNet), which integrates the advantages of the CNN, autoencoder (AE), and ELM. Specifically, the BD-ELMNet first executes the convolution and pooling operations to form a convolutional ELM (ELMConvNet) to extract shallow features. Furthermore, the manifold regularized ELM-AE (MRELM-AE), which can simultaneously consider the geometrical structure and discriminative information of aircraft data, is developed to extract discriminative features. The bilinear pooling model uses the feature association information for feature fusion to enhance the substantial distinction of features. Compared with the backpropagation (BP) optimization method, BD-ELMNet adopts a layer-by-layer training method without repeated adjustments to effectively learn discriminant features. Experiments involving the application of several methods, including the proposed method, to the MTARSI benchmark demonstrate that the proposed aircraft type recognition method outperforms the state-of-the-art methods.