Autor: Brewczyński, D. - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Dynamics model of stabilization mechanism for helicopter PAD
Autorzy:: Brewczyński, D.
Tora, G.
Powiązania:: https://bibliotekanauki.pl/articles/241532.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: maritime engineering
kinematic analysis
dynamic analysis
mechanism design
safety
Opis:: Helipad located on ships greatly increases their ability to perform tactical and logistical abilities. They allow performing reconnaissance from the air, transportation of cargos and people to and from the ship. Landing on a moving ship particularly small size during bad weather is not a safe manoeuvre. Article provides an overview of existing solutions that improve safety during the landing manoeuvre of the helicopter to the ship and describes an innovative mechanism with can stabilize helicopter pad in four degrees of freedom. This solution is characterized in that the landing plate is movable and actuated simultaneously by two support plates and two levers. Plates and levers are driven by separate linear motors that move along the guides connected to the base. The main feature of the mechanism is that when the base is not stable, it can reduce the linear movement of the landing platform in the vertical and transverse direction and angular displacement around an axis perpendicular and parallel to the axis of the ship. A preferred feature of the mechanism is that in folded position it occupies relatively little space. In addition, advantageous attribute of the mechanism is its large working area, enabling the reduction of high amplitude vibration. The article contains a calculation of the kinematics for the proposed structure of the mechanism. It also includes speed drives waveforms, which are the result of simulations for the input parameters of the ship movement.
Źródło:: Journal of KONES; 2016, 23, 2; 61-68
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Stabilization mechanism for helicopter pad with four degrees of freedom
Autorzy:: Brewczyński, D.
Tora, G.
Powiązania:: https://bibliotekanauki.pl/articles/242515.pdf
Data publikacji:: 2015
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: mechanical engineering
maritime engineering
kinematic analysis
mechanism design
safety
Opis:: Helipad located on ships greatly increases their ability to perform tactical and logistical abilities. They allow performing reconnaissance from the air, transportation of cargos and people to and from the ship. Landing on a moving ship particularly small size during bad weather is not a safe manoeuvre. Article provides an overview of existing solutions that improve safety during the landing manoeuvre of the helicopter to the ship and describes an innovative mechanism with can stabilize helicopter pad in four degrees of freedom. This solution is characterized in that the landing plate is movable and actuated simultaneously by two support plates and two levers. Plates and levers are driven by separate linear motors that move along the guides connected to the base. The main feature of the mechanism is that when the base is not stable, it can reduce the linear movement of the landing platform in the vertical and transverse direction and angular displacement around an axis perpendicular and parallel to the axis of the ship. A preferred feature of the mechanism is that in folded position it occupies relatively little space. In addition, advantageous attribute of the mechanism is its large working area, enabling the reduction of high amplitude vibration. The article contains a calculation of the kinematics for the proposed structure of the mechanism. It also includes speed drives waveforms, which are the result of simulations for the input parameters of the ship movement.
Źródło:: Journal of KONES; 2015, 22, 3; 7-12
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Analysis of the wheel orientation angles in lockheed F-104S starfighter aircraft
Autorzy:: Brewczyński, D.
Tora, G.
Powiązania:: https://bibliotekanauki.pl/articles/241534.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: mechanical engineering
aircraft engineering
kinematic analysis
Opis:: This article contains kinematic analysis of the chassis mechanism used in Lockheed F-104S Star fighter aircraft, which is recently used by the NATO military aviation as an interceptor. The mechanism of the chassis is made up of several smaller subsystems with different functions. The first mechanism is used to eject the chassis before landing (touchdown) and fold it to hatchway after the lift off. The second mechanism is designed to perform rotation of the crossover with the wheel, in order to adjust the position of the wheel to fit it in the limited space in the hold. The third mechanism allows movement of the chassis resulting from the change in length of the damper. To determine the position of the following links of the mechanism was used calculus of vectors in which unit vectors were used to represent the angular position of the links. Often used equation, which describes a polygon vector, and the equation of unknown unit vector possible to determine if the other two and the angles between them are known. Calculations were performed in the three local systems of reference, thus were obtained the simplest forms of solutions for links positions. The corresponding scalar products of unit vectors are elements of two transition matrices. These matrices are needed for the vectors calculation in each of the three coordinate systems. The result of the analysis is to determine the angle of convergence and the angle of heel wheels as a function of variable length of hydraulic cylinder and the length of the shock absorber. It has been shown that length of the shock absorber has little effect on angle of convergence, but has a significant effect on the angle of the tilt-wheel landing gear.
Źródło:: Journal of KONES; 2013, 20, 3; 79-87
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Working area of the helicopter PAD stabilization mechanism
Autorzy:: Brewczyński, D.
Tora, G.
Powiązania:: https://bibliotekanauki.pl/articles/242778.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: mechanical engineering
maritime engineering
mechanism design
safety
Inżynieria mechaniczna
inżynieria morska
bezpieczeństwo
Opis:: Helicopter pad located on the ship significantly increase the operational capabilities of military and civilian ships. During the storm, especially side tilts of the ship hinder or even prevent the safe use of the helicopter pad. It is proposed to apply the system placed between the deck of the ship and landing site plate, driven by four independent cable drives located under the deck. The task of the system will be preventing from transferring to Helicopter pad the tilt of the ship around the longitudinal and transverse axis and the displacement of the deck along the transverse and vertical axis within the limits of the work area. The mechanism consists of four movable links on which the movable helicopter pad platform is located. As the linear actuators, trolleys moving along horizontal guides were used, powered by system of steel cables with four independent electric motors. In folded state the mechanism, take up appropriately little space under the deck area. For the assumed extreme amplitudes of the ship motion, minimum dimensions of the mechanism links that meets the requirement to work in one configuration and lack of collisions were determined. Kinematic relationships were created indicate which mechanical quantities should be measured in real time to determine the momentary drives speeds. For the adopted assumptions simulation was performed, confirming the predicted behaviour of the system. Based on the kinematic equations of system and taking in consideration collisions and geometrical limits, working area for the flat part of the mechanism was determined.
Źródło:: Journal of KONES; 2017, 24, 1; 59-66
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Dynamic positioning system of helicopter pad on the ship
Autorzy:: Brewczyński, D.
Tora, G.
Powiązania:: https://bibliotekanauki.pl/articles/243395.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: mechanical engineering
maritime engineering
kinematic analysis
mechanism design
Opis:: Helicopter pad located on the ship significantly increase the operational capabilities of military and civilian ships. During the storm, especially side tilts of the ship hinder or even prevent the safe use of the helicopter pad. It is proposed to apply the system placed between the deck of the ship and landing site plate, driven by three independent linear drives located under the deck. The task of the system will be preventing from transferring to Helicopter pad the tilt of the ship around the longitudinal axis and the displacement of the deck along the transverse and vertical axis within the limits of the work area. The mechanism consists of the three movable pillars with the plate on top, which is the movable helicopter pad platform. As the linear actuators, plates moving along a horizontal guide were used, powered by system of steel cables with three independent electric motors. In folded state the mechanism, take up appropriately little space in the deck area. For the assumed extreme amplitudes of the ship motion, minimum dimensions of the mechanism links that meets the requirement to work in one configuration and lack of collisions were determined. Kinematic relationships were created indicate which mechanical quantities should be measured in real time to determine the momentary drives speed. For the adopted assumptions simulation was performed, confirming the predicted behaviour of the system. Based on the dynamics equations of system, drives loads, their power and individual links and joints load were determined.
Źródło:: Journal of KONES; 2014, 21, 4; 21-27
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Dimensional synthesis of active suspension cab mechanism links
Autorzy:: Brewczyński, D.
Tora, G.
Powiązania:: https://bibliotekanauki.pl/articles/243397.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: active vibration damping
platform mechanism
synthesis of the mechanism’s dimensions
Opis:: One of the directions of the heavy duty machine is the operator cabin construction, which provides a high level of comfort. Adequate control of active suspension drives can reduce low frequency and large amplitude vibrations occurring in a number of cabin degrees of freedom. The main link of the mechanism is the platform with cab suspended on two rockers and one actuator. Article proposes methods for determining the length of suspension arms, the width of the platform and centres of the joints, which are connected to the suspension. It has been proved for the flat case that if the momentary centre of rotation of the platform relative to the machine frame is located inside the road roughness zone is a single drive can effectively reduce transverse vibration and angle vibration around the longitudinal machine axis. Further conditions that determine links size are to prevent from peculiar positions, to avoid collision between cab wall and suspension joints. Presented relations between the height of the waist rough roads, wheelbase machine, cab mounting height on the machine and the dimensions of the link suspension mechanism. Presented dimensional calculation results cab suspension links dedicated to Caterpillar 924 GZ loader. Assuming the vertical driving cab calculated inaccuracy of its transverse displacements. Presented the results showing influence of the cab assembly height on the cabin mounting links dimensions.
Źródło:: Journal of KONES; 2013, 20, 4; 47-53
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Analysis of links positions in landing gear mechanism
Autorzy:: Brewczyński, D.
Tora, G.
Powiązania:: https://bibliotekanauki.pl/articles/955121.pdf
Data publikacji:: 2014
Wydawca:: Uniwersytet Zielonogórski. Oficyna Wydawnicza
Tematy:: samolot
podwozie samolotu
kinematyka
aircrafts
landing gear
mechanics
kinematics
Opis:: This article contains a kinematic analysis of an aircraft chassis mechanism in a range of positions. The mechanism of the chassis is made up of several smaller subsystems with different functions. The first mechanism is used to eject the chassis before landing (touchdown) and fold it to hatchway after the lift off. The second mechanism is designed to perform rotation of the crossover with the wheel, in order to adjust the position of the wheel to fit it in the limited space in the hold. The third mechanism allows movement of the chassis resulting from the change in length of the damper. To determine the position of the following links of the mechanism calculus of vectors was applied in which unit vectors were used to represent the angular position of the links. The aim of the analysis is to determine the angle of convergence and the angle of heel wheels as a function of the variable length of hydraulic cylinder, length of the shock absorber, length of the regulations rods.
Źródło:: International Journal of Applied Mechanics and Engineering; 2014, 19, 3; 503-512
1734-4492
2353-9003
Pojawia się w:: International Journal of Applied Mechanics and Engineering
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Optimal service term of the bridge cranes
Autorzy:: Kovalenko, V.
Vishnevetsky, S.
Brewczyński, D.
Tora, G.
Powiązania:: https://bibliotekanauki.pl/articles/245050.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: bridge cranes
resource
modelling
constructive parameters
Opis:: The questions of the rational/optimal service term of the warehouse bridge cranes on the exploitation and projection stages are observed. The method of the residual crane resource’s definition by the criterion of the specific reduced responses is suggested. On the stage of the crane projection, the forecasting of the warehouse cranes’ resource in coordination with their constructive parameters is expedient. The existing task has main aspects: recognition of the residual crane resource and definition of the project crane resource. In course of time in the massive of the sample from the low carbon steel occur changes: grows firmness, equalize the internal tensions, little internal cracks “overgrow”, sometimes the groups of little cracks create macrocracks. This are a diffusion action. The definition of the rational constructive parameters is being carried out on the base of the work processes’ mathematical modelling. On the base of modelling is defined the size of the residual deflection of the main beam that is formed during one work crane cycle considering the action of the main beams’ free vibrations in the processes of start and braking considering the factor of the attenuation of those vibrations. In result of the modelling, we receive the microscopic size of the residual deflection, formed during one work cycle. On the base of the multisession modelling is noticed that the crane resource can be prolonged on 20-50%.
Źródło:: Journal of KONES; 2013, 20, 4; 169-176
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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