Contribution to an improved crash design for a composite transport aircraft fuselage—development of a kinematics model and an experimental component test setup

2013 ◽  
Vol 4 (3) ◽  
pp. 265-275 ◽  
Author(s):  
M. Waimer ◽  
D. Kohlgrüber ◽  
R. Keck ◽  
H. Voggenreiter
Keyword(s):  
Test Setup ◽  
Transport Aircraft ◽  
Kinematics Model ◽  
Aircraft Fuselage ◽  
Component Test

scholarly journals Connections between steel and aluminium using adhesive bonding combined with self-piercing riveting

2018 ◽  
Vol 183 ◽  
pp. 04010 ◽  
Author(s):  
Matthias Reil ◽  
David Morin ◽  
Magnus Langseth ◽  
Octavian Knoll
Keyword(s):  
Adhesive Bonding ◽  
Numerical Models ◽  
Dissimilar Materials ◽  
Material Design ◽  
Connected Components ◽  
Adhesively Bonded ◽  
Test Setup ◽  
Vehicle Crash ◽  
Component Test ◽  
Development And Validation

The multi-material design of modern car bodies requires joining technologies for dissimilar materials. Adhesive bonding in combination with self-piercing riveting is widely used for joining steel and aluminium structures. To guarantee crashworthiness and reliability of a car body, accurate and effcient numerical models of its materials and connections are required. Suitable component test setups are necessary for development and validation of such models. In this work, a novel test setup for adhesively bonded and point-wise connected components is presented. Here, load combinations comparable to a vehicle crash are introduced into the connections. The developed setup facilitates successive failure of multiple connections and enables a broad validation of numerical connection models.

scholarly journals МЕТОД ВИЗНАЧЕННЯ ОСНОВНИХ ПАРАМЕТРІВ ВАНТАЖНОГО ЛЮКА В ХВОСТОВІЙ ЧАСТИНІ ФЮЗЕЛЯЖУ ЛІТАКІВ ТРАНСПОРТНОЇ КАТЕГОРІЇ

2020 ◽  
pp. 52-71
Author(s):  
Д. С. Конышев
Keyword(s):  
Extreme Points ◽  
Load Bearing ◽  
Transport Aircraft ◽  
Aircraft Fuselage ◽  
Door Opening ◽  
Source Data ◽  
Correct Calculation ◽  
Regulatory Bodies ◽  
System Extension ◽  
Bearing Structure

A method has been developed for determining principal parameters for aft cargo door of transport aircraft. A list of input data is given and a technique for finding them is described. An example based on an existing transport aircraft is considered. The following has been used as source data: basic cargo nomenclature to be transported by the designed aircraft, cargo overall dimensions and weight, methods of loading and mooring, loading facilities. More over the design, operational and regulatory parameters are needed, such as landing gear configuration, its bottoming system, extension of rails of the upper equipment for loading/unloading, cargo trajectories during loading and airdropping, codes of the international regulatory bodies such as FAR, CS, AP. Based on the source data, the principle of determining the dimensions of the cargo compartment, cargo floor and the loading sites in the form of a ramp with a pressure bridge, and air stairs is given. The relation between the ramp length and the cargo floor length is described taking into account the loading, unloading and air dropping operations. Correct calculation of these parameters is the most important task, because performance of the future transport aircraft directly depends on the solution. The technique of determining the cargo door opening, development of the load-bearing structure of the transport aircraft fuselage aft  section,  its  main  strong  elements  –  the  cargo  door  beam,  the  ramp,  the attachment units, the ramp locks – is given. The interconnection of the ramp load-bearing structure with the load-bearing structure of the fuselage aft part, the options for transferring loads perceived by the ramp to the frame are described. Examples of two types – flat and volumetric – of the cargo door beams, as well as the method of their assignment are considered. Trajectories of the extreme points of the in-gauge load are determined using graphical method for loading, unloading, and airdropping operations. Taking into account the positions of these trajectories makes it possible to select the desired cutout in the fuselage aft section. While designing the aft cargo doors the main features are highlighted. These features when considered make it possible to determine the most optimal parameters of the cutout, the cargo door type and its components.

scholarly journals ПРОЕКТУВАННЯ СТУЛКОВОГО ВІДСІКУ ХВОСТОВИХ ВАНТАЖНИХ ЛЮКІВ ЛІТАКІВ ТРАНСПОРТНОЇ КАТЕГОРІЇ

2021 ◽  
pp. 27-58
Author(s):  
А. Г. Гребеников ◽  
А. З. Двейрин ◽  
Д. С. Конышев
Keyword(s):  
Initial Data ◽  
Cross Section ◽  
Transport Aircraft ◽  
Aircraft Fuselage ◽  
Operational Characteristics ◽  
Parameters Selection ◽  
Tail Part ◽  
Closed Position ◽  
Loading And Unloading ◽  
Main Components

The method for determining the main parameters of the tail cargo doors of transport category aircraft is developed. There have been prepared initial data and described the methodology for finding them. An example based on an existing transport aircraft is considered. The basic nomenclature of transported cargoes of the designed aircraft, its dimensions and weight, methods of loading and mooring, additional loading equipment were taken as initial data. As well as such necessary design, operational and regulatory parameters and data as landing gear type, its “kneeling” system, rails of the upper loading equipment for loading and unloading, cargo trajectories during loading and landing, requirements of international regulatory organizations FAR, CS, AP. The principle of determining the dimensions of the cargo compartment, cargo floor and the hitting platforms in the form of ramp with pressure door, ladders is presented, based on the initial data. Taking into account the loading and unloading, landing operations described the dependence of the ramp length on the length of the cargo floor. The correct formation of these parameters is one of the most important tasks, from the solution of which directly depend the operational characteristics of the future transport aircraft. A method for designing cargo door fairings in the transport category aircraft fuselage tail part is also presented. There have been determined the main features of the fairings compartment, its main components and their varieties, depending on the scheme of the cargo door. At the stage of preliminary design, the principles for determining the main parameters of the fairings compartments based on their design purpose are outlined.Also provided information on the fairings compartment structural elements parameters selection: the axes of the fairings hinge, the selection of control cylinders and their installation, the parameters of the open and closed position locks, pressurization and sealing of the fairings compartment. Considered the design features of the fuselage tail section various theories fairings compartment - made in cross-section with one radius (in the shape of a cylinder) and given in cross-section with two radii (double-deck).

Structural design methodology of electro-optical system installation on special mission jet transport aircraft

2016 ◽  
Vol 231 (5) ◽  
pp. 887-903
Author(s):  
Mohammad Ali Vaziri Zanjani ◽  
Abdollah Panahi ◽  
Shahram Yousefi
Keyword(s):  
Optical System ◽  
Structural Design ◽  
Design Methodology ◽  
Observation System ◽  
Transport Aircraft ◽  
Aircraft Fuselage ◽  
Road Map ◽  
Design Requirements ◽  
Definition Of

The research reported in this paper investigated the structural design methodology of equipping a jet aircraft modified for maritime patrol with any type of observation system. The study includes installation feasibility, definition of mounting types (fix/retractable), installation location, airworthiness requirements, design considerations, structural design requirements, and static/dynamic analysis considerations. Due to lack of design publication in this field, this study focuses on methodology of electro-optical sensor installation as a flowchart leading to a road map to equip an aircraft with any type of maritime sensor. For validation of above methodology, a case study for installation of an electro-optical system on a particular jet aircraft with new mission is presented. By comparison of system and aircraft specification based on methodology flowchart, a retractable mounting was chosen. To accomplish a safe installation, an optimal mechanism suitable with aircraft fuselage and required backup structure was designed using reinforced cut out. The design was then analyzed for static and dynamic critical load cases using MSC/NASTRAN software.

Quantification of crew workload imposed by communications-related tasks in commercial transport aircraft

1983 ◽  
Author(s):  
William H. Acton ◽  
Mark S. Crabtree ◽  
John C. Simons ◽  
Frank E. Gomer ◽  
J. Steven Eckel
Keyword(s):  
Transport Aircraft

INFLUENCE OF LATERAL CONTROL SYSTEM ON TRANSPORT AIRCRAFT SPIN

2018 ◽  
Vol 49 (1) ◽  
pp. 77-92
Author(s):  
Diana Aleksandrovna Alieva ◽  
Maria Evguenievna Sidoryuk ◽  
Alexander Nikolaevich Khrabrov
Keyword(s):  
Control System ◽  
Lateral Control ◽  
Transport Aircraft
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