scholarly journals Devising a concept of integrated design and modeling of aircraft

2021 ◽  
Vol 5 (1(113)) ◽  
pp. 15-23
Author(s):  
Oleksandr Grebenikov ◽  
Andrii Humennyi ◽  
Oleksandr Dveirin ◽  
Oleksandr Soboliev ◽  
Lilia Buival
Keyword(s):  
Three Dimensional ◽  
Integrated Design ◽  
Aircraft Design ◽  
Parametric Modeling ◽  
Parametric Models ◽  
Space Distribution ◽  
Design Parameters ◽  
Combat Aircraft ◽  
Cad Cam ◽  
And Training

The analysis of aircraft design methods reported here has revealed that building a competitive aircraft necessitates devising a scientifically based concept of integrated aircraft design employing CAD/CAM/CAE/PLM software suites. A generalized concept of integrated design and three-dimensional computer modeling of aircraft involving the CAD/CAM/CAE/PLM systems has been developed. Based on the proposed concept, the principles of integrated design of aircraft were devised. The features of designing the training and training-combat aircraft, transport-category aircraft, light civilian aircraft have been described. A method for determining the take-off weight, design parameters, and formation of the general appearance of aircraft has been improved. The method is intended to form the appearance of the aircraft at the stages of preliminary design, the purpose of which is reduced to determining the permissible version of the aircraft project. The project must meet the predefined requirements and restrictions in the selected aircraft scheme and the assigned set of parameters that characterize its airframe and power plant. A method of parametric modeling of aircraft has been improved, which includes the stages of creating a master geometry of the aircraft and a model of space distribution. Parametric models of master geometry and models of space distribution, training and training-combat aircraft, transport-category aircraft, light civilian aircraft have been constructed. Methods of integrated design of aircraft main units have been devised and theoretically substantiated. Parametric models of master geometry of the wing for a training aircraft, the wings, appendage, and fuselage of a light civilian aircraft were built, taking into consideration the design features of aircraft units of various categories

scholarly journals МЕТОД ІНТЕГРОВАНОГО ПРОЕКТУВАННЯ НОСОВОЇ ЧАСТИНИ ФЮЗЕЛЯЖУ ЛІТАКА ТРАНСПОРТНОЇ КАТЕГОРІЇ

2021 ◽  
pp. 4-36
Author(s):  
О. З. Двейрін ◽  
О. Г. Гребеніков ◽  
А. М. Гуменний ◽  
А. С. Чумак
Keyword(s):  
Aerodynamic Drag ◽  
Fuel Efficiency ◽  
Integrated Design ◽  
Aircraft Design ◽  
Operating Conditions ◽  
Parametric Models ◽  
Technical Documentation ◽  
Design Features ◽  
Aircraft Fuselage ◽  
Cad Cam

Regulatory and technical documentation, design features and methods of fuselage transport category aircraft design was performed and identified the need to update design methods and calculate the characteristics of the fuselage using parametric models and integrated design systems CAD / CAM / CAE / PLM. The method of integrated fuselage design of transport category aircraft is developed and theoretically substantiated. Within the framework of the proposed method, parametric models of master geometry, aerodynamic flow and mass-inertial characteristics of the fuselage were created, taking into account the design features of transport aircraft.The proposed method was used to study the influence of geometric parameters of fuselage nose section on aerodynamic and mass characteristics of the fuselage, showing the efficiency of work with parametric models.The choice of parameters of the fuselage nose section in preliminary and sketch design of a promising aircraft for local airlines is justified, which allowed to implement and test the suitability of the proposed method for in new competitive aircraft designing process.The use of the method for integrated fuselage design for local aircraft allowed to determine the rational configuration of the nose section of the fuselage and increase the fuel efficiency of the aircraft by 6.4%, reduce the aerodynamic drag of the fuselage by 10%, increase the viewing angle from the cockpit by 10%. and ensure compliance with current regulatory and technical documentation, as well as determine the mass-inertial characteristics of the fuselage and its parts and form a list of cockpit equipment that will meet flight safety requirements, taking into account the operating conditions and modifications of the aircraft.The configuration of the nose section of the aircraft fuselage for local airlines has been developed, which allows to fit modern requirements for cockpit equipment and layout, low fuselage impedance and high aerodynamic quality and fuel efficiency in cruising mode at speeds up to 850 km / h (M = 0, 8). As a result of verification using other methods and parameters of existing aircraft, the accuracy of the results obtained using the proposed method at the level of 5% was confirmed.

scholarly journals АНАЛІЗ КОНСТРУКТИВНО-ТЕХНОЛОГІЧНИХ ОСОБЛИВОСТЕЙ ЛОПАТЕЙ НЕСУЧИХ ГВИНТІВ ВАЖКИХ ТРАНСПОРТНИХ ВЕРТОЛЬОТІВ

2021 ◽  
pp. 59-103
Author(s):  
А. Г. Гребеников ◽  
Ю. В. Дьяченко ◽  
В. В. Коллеров ◽  
В. Ю. Коцюба ◽  
И. В. Малков ◽  
...  
Keyword(s):  
Service Life ◽  
Rotor Blade ◽  
Parametric Modeling ◽  
Rotor Blades ◽  
Parametric Models ◽  
Space Distribution ◽  
Main Rotor ◽  
Mixed Design ◽  
Helicopter Main Rotor ◽  
Main Rotor Blade

The analysis of the design and technological features of the rotor blades of heavy transport helicopters is carried out. The main performance characteristics of heavy helicopters are presented. General requirements to helicopter main rotor blades design and specifications for their production are formulated. The design and force diagram of heavy helicopter main rotor blades is considered. The features of structural materials for the main rotor blades of heavy transport helicopters are marked. The main rotor blades differ in their design due to different approaches to materials, manufacturing and layout of blade elements. The main rotor blades of an all-metal design, for design and technological reasons, are divided into two groups: a frame structure with a tubular steel spar and an aluminum extruded spar. As a result of a number of design and technological measures the service life of the main rotor blade of helicopter Mi-6 was brought from 50 hours to 1500 hours. The principal peculiarity of the steel tubular spar of the main rotor blade of the Mi-26 helicopter is the absence of the shaft lug. The features of mixed design main rotor blades are presented. The method of parametric modeling of helicopter main rotor blades is presented. The application of the three-dimensional parametric models of structural elements in practice of designing and construction enables to perform numerical calculations of aerodynamic and strength characteristics both of separate aggregates, units and details and of the helicopter as a whole by means of the finite element method. The method of parametric modeling of the main rotor blade of the transport helicopter with the computer system CATIA V5 is a modification of the method of integrated designing of the elements of aviation constructions. Parametric master geometry of the main rotor blade is a linear surface, created by basic profiles of the blade. On the basis of parametric master geometry a space distribution model is created that determines the position of axial planes of the power set of the blade for further creation of the blade detail models. Technological flowchart of main rotor blade manufacturing is presented, manufacturing and surface hardening technology of steel tubular spar is considered. The technology of manufacturing and molding the nose part of the blade of the main rotor mixed design. The technological features of slipway assembly-gluing of the main rotor blade are considered, the content of off-slipway work is given.These materials can be useful in theoretical and experimental studies to extend the service life of the rotor blades of Mi-26 helicopters, which are currently in operation in Ukraine.

Application of Pro/Engineer in Mug Product Development and Mould Design

2014 ◽  
Vol 722 ◽  
pp. 254-257
Author(s):  
Feng Chen
Keyword(s):  
High Efficiency ◽  
Parametric Design ◽  
Three Dimensional ◽  
Parametric Modeling ◽  
Mold Design ◽  
Product Modeling ◽  
Modeling Technology ◽  
Cad Cam ◽  
Mould Design ◽  
New Generation

Pro/E was developed by the American company PTC CAD / CAM software, it is a new generation product modeling system with features as parametric design, three-dimensional solid model, feature-driven and single database. Pro/E software uses object-oriented unified database and parametric modeling technology, which has conceptual design, basic design and detailed design features,and provides excellent platforms for integrated manufacturing molds.Take Mug for example, the process of product modelling and mold design used by Pro/E software was introduced. The mold design cycle , the parting surface, the mold die space and the core was focused. The high efficiency characteristic of plastic mold design used by Pro/E was elaborated.

Study on Key Techniques of Parametric Design System Based on Solid Works and KBE

2011 ◽  
Vol 71-78 ◽  
pp. 3861-3867 ◽  
Author(s):  
Du Yao ◽  
Zhi Yong Chang ◽  
Jie Zhao ◽  
Yang Liu Dou
Keyword(s):  
Parametric Design ◽  
Three Dimensional ◽  
Parametric Models ◽  
Current Status ◽  
Design Parameters ◽  
Design System ◽  
Design Quality ◽  
Element Analysis ◽  
Solid Works ◽  
Key Techniques

This paper analyzes the current status and inadequate of three-dimensional parametric design, and introduces the conceptions and principles of KBE (Knowledge Based Engineering) technology and the parametric design. The key techniques of parametric design system are studied based on the platform of combination of SolidWorks as three-dimensional feature modeling software, Microsoft Access as supported database and Microsoft Visual Basic as the development tool. Firstly, we divide the product into modules by functions. Secondly, invoke corresponding knowledge and methods of design and calculation in the KBE knowledge base to perform design and calculation. Then we use parametric modification method combined with equations, values link and design tables to get the parametric models, judge the rationality of the design parameters through finite element analysis, and create the drawings which meet the processing and production requirements using drawings automatically adjustment technology. Finally a case study of stacker design is given to validate these techniques of parametric design system, and show that the techniques have great significance for improving product design quality, shorting the design cycle and improving the competitiveness of enterprises.

The Study of Reliability in MDO of Aircraft

2012 ◽  
Vol 226-228 ◽  
pp. 598-601
Author(s):  
Qing Xia ◽  
Man Li ◽  
Zong Jie Cao ◽  
Hong Wei Wang
Keyword(s):  
Integrated Design ◽  
Aircraft Design ◽  
Reliability Function ◽  
Design Parameters ◽  
Objective Functions ◽  
Interference Theory ◽  
Constraint Function ◽  
Reliability Design

MDO and reliability design are independently processed in the traditional aircraft design. The designs process is thus consuming compute intensive, so that integrated design of MDO and reliability is required. To achieve the integration, there are two problems needed to be solved. First, a reliability function needs to be expressed by performance design parameters in a probability form. Second, the reliability function needs to be imported into MDO arithmetic. For the first one, stress-strength interference theory is useful. According to the theory, performance design parameters are described in the formulas which calculate probability of reliability. For the second, the reliability function is considered as a part of optimization objective functions or as a constraint function. The simulation of aircraft design shows that the above method is useful and effective to the actual project.

scholarly journals ОСОБЛИВОСТІ ІНТЕГРОВАНОГО ПРОЕКТУВАННЯ РЕГІОНАЛЬНИХ ПАСАЖИРСЬКИХ ЛІТАКІВ

2020 ◽  
pp. 37-60
Author(s):  
О. Г. Гребеніков ◽  
А. М. Гуменний ◽  
О. Д. Донець ◽  
С. В. Трубаєв ◽  
А. С. Чумак
Keyword(s):  
Production Systems ◽  
Three Dimensional ◽  
Integrated Design ◽  
Weather Conditions ◽  
World Market ◽  
Space Distribution ◽  
Distribution Model ◽  
Analytical Geometry ◽  
High Level ◽  
Passenger Aircraft

The features of the integrated design of competitive regional passenger airplanes intended to carry passengers, baggage, mail and cargo on domestic and international airlines with the possibility of operation at paved aerodromes and prepared unpaved runways are given. It is planned that application of the proposed features of the concept and principles, and their implementation will create aircraft to replace the previous generation of the regional passenger aircraft fleet of airlines of different countries. The concept and principles of its implementation are based on the use of integrated design and production systems. The proposed opportunity to study influence of aircraft parameters on aerodynamic and mass characteristics, provided that the requirements of Aviation Regulations (AP) for the layout and flight safety are met. For testing, the results of such studies shown for various modifications of passenger aircraft of the ANTONOV State Company.The features of creating a three-dimensional computer model of the designed aircraft master geometry, developing a space distribution model, analytical standards for structural load-bearing elements designed using analytical geometry methods with the help of integrated CAD \ CAM \ CAE \ PLM systems in a single information environment for supporting the aircraft life cycle are shown.The aircraft under design must fully comply with the AP-25 Airworthiness Requirements.The main technical characteristics of the designed aircraft, taking into account the proposed solutions, are close in magnitude to the characteristics of the similar aircraft. If necessary it is possible to take into account the peculiarities of aircraft operation at aerodromes with badly paved and unpaved runways to provide the opportunity of its usage on any airways, in simple and difficult weather conditions, during day and night, as well as on routes with a high flight intensity with a high level of crew comfort, which will ensure a high level of competitiveness of the aircraft in the world market.

Mass Customized Design of Cosmetic Masks Using Three-Dimensional Parametric Human Face Models Constructed From Anthropometric Data

2018 ◽  
Vol 18 (3) ◽  
Author(s):  
Chih-Hsing Chu ◽  
I-Jan Wang
Keyword(s):  
Large Scale ◽  
Outer Boundary ◽  
Three Dimensional ◽  
Parametric Modeling ◽  
Parametric Models ◽  
Design System ◽  
Shape Distortion ◽  
Anthropometric Data ◽  
Mask Design ◽  
2D Pattern

Cosmetic mask is a popular skincare product widely accepted by the youth and female. Most cosmetic masks in the current market offer very few sizes to choose from, thus producing misfit masks with reduced wearing comfort and skincare functionality. This paper describes how to realize customized design of cosmetic masks using three-dimensional (3D) parametric face models derived from a large amount of scanned facial data. The parametric models approximate individual faces using a nonlinear regression model controlled by a set of facial parameters easy to be measured. They serve as effective reference geometry to conduct 3D mask design. A prototyping mask design system implementing the parametric modeling method demonstrates the customized design process. The system allows the user to construct the mask shape directly on 3D meshes of a face model by specifying inner and outer boundary curves. An automatic flattening function unfolds the trimmed meshes into a two-dimensional (2D) pattern with a reduced shape distortion. This research enhances the practical value of large-scale anthropometric data by realizing human centric design customization using cosmetic facial mask as an example.

Design and optimization of bump (compression surface) for diverterless supersonic inlet

2021 ◽  
pp. 095441002110029
Author(s):  
Irsalan Arif ◽  
Hassan Iftikhar ◽  
Ali Javed
Keyword(s):  
Fitness Function ◽  
Supersonic Jet ◽  
Three Dimensional ◽  
Flow Characteristics ◽  
Least Square ◽  
Pressure Recovery ◽  
Design Parameters ◽  
Inlet System ◽  
Design And Optimization ◽  
Supersonic Inlet

In this article design and optimization scheme of a three-dimensional bump surface for a supersonic aircraft is presented. A baseline bump and inlet duct with forward cowl lip is initially modeled in accordance with an existing bump configuration on a supersonic jet aircraft. Various design parameters for bump surface of diverterless supersonic inlet systems are identified, and design space is established using sensitivity analysis to identify the uncertainty associated with each design parameter by the one-factor-at-a-time approach. Subsequently, the designed configurations are selected by performing a three-level design of experiments using the Box–Behnken method and the numerical simulations. Surrogate modeling is carried out by the least square regression method to identify the fitness function, and optimization is performed using genetic algorithm based on pressure recovery as the objective function. The resultant optimized bump configuration demonstrates significant improvement in pressure recovery and flow characteristics as compared to baseline configuration at both supersonic and subsonic flow conditions and at design and off-design conditions. The proposed design and optimization methodology can be applied for optimizing the bump surface design of any diverterless supersonic inlet system for maximizing the intake performance.

scholarly journals Virtual Surgical Planning, Stereolitographic Models and CAD/CAM Titanium Mesh for Three-Dimensional Reconstruction of Fibula Flap with Iliac Crest Graft and Dental Implants

2021 ◽  
Vol 10 (9) ◽  
pp. 1922
Author(s):  
Carlos Navarro Cuéllar ◽  
Manuel Tousidonis Rial ◽  
Raúl Antúnez-Conde ◽  
Santiago Ochandiano Caicoya ◽  
Ignacio Navarro Cuéllar ◽  
...  
Keyword(s):  
Bone Resorption ◽  
Surgical Planning ◽  
Iliac Crest ◽  
Three Dimensional ◽  
Titanium Mesh ◽  
Iliac Crest Graft ◽  
Virtual Surgical Planning ◽  
Fibula Flap ◽  
Dimensional Reconstruction ◽  
Cad Cam

Mandibular reconstruction with fibula flap shows a 3D discrepancy between the fibula and the remnant mandible. Eight patients underwent three-dimensional reconstruction of the fibula flap with iliac crest graft and dental implants through virtual surgical planning (VSP), stereolitographic models (STL) and CAD/CAM titanium mesh. Vertical ridge augmentation and horizontal dimensions of the fibula, peri-implant bone resorption of the iliac crest graft, implant success rate and functional and aesthetic results were evaluated. Vertical reconstruction ranged from 13.4 mm to 10.1 mm, with an average of 12.22 mm. Iliac crest graft and titanium mesh were able to preserve the width of the fibula, which ranged from 8.9 mm to 11.7 mm, with an average of 10.1 mm. A total of 38 implants were placed in the new mandible, with an average of 4.75 ± 0.4 implants per patient and an osseointegration success rate of 94.7%. Two implants were lost during the osseointegration period (5.3%). Bone resorption was measured as peri-implant bone resorption at the mesial and distal level of each implant, with a variation between 0.5 mm and 2.4 mm, and with a mean of 1.43 mm. All patients were rehabilitated with a fixed implant prosthesis with good aesthetic and functional results.

Sign in / Sign up

Export Citation Format

Share Document