scholarly journals Bifurcation Study of a Dynamic Model of a Landing-Gear Mechanism

2016 ◽  
Vol 53 (5) ◽  
pp. 1468-1477 ◽  
Author(s):  
James A. C. Knowles
Keyword(s):  
Dynamic Model ◽  
Landing Gear ◽  
Gear Mechanism

scholarly journals Numerical Continuation Analysis of a Dual-sidestay Main Landing Gear Mechanism

2012 ◽  
Author(s):  
James Knowles ◽  
Bernd Krauskopf ◽  
Mark Lowenberg ◽  
Simon Neild ◽  
P. Thota
Keyword(s):  
Landing Gear ◽  
Numerical Continuation ◽  
Gear Mechanism

Cable-Driven Four-Bar Link Robotic Landing Gear Mechanism: Rapid Design and Survivability Testing

2018 ◽  
Author(s):  
Claudio V. Di Leo ◽  
Benjamin Leon ◽  
Jacob Wachlin ◽  
Martin Kurien ◽  
Julian J. Rimoli ◽  
...  
Keyword(s):  
Landing Gear ◽  
Rapid Design ◽  
Gear Mechanism

The Effect of Thrust Eccentric and Erection Cylinder Anchor Position on the Initial Disturbances

2014 ◽  
Vol 889-890 ◽  
pp. 165-169
Author(s):  
Miao Chen ◽  
Yi Jiang
Keyword(s):  
Dynamic Model ◽  
Landing Gear ◽  
Software Simulation ◽  
Adams Software ◽  
Weapons Systems

A certain type of vehicle missile launch system is selected as the research object in this paper. The dynamic model is established on the base of reasonable hypothesis and simplification and by using of PRO / E software. In this paper, we find out the most dangerous thrust eccentric position of the missile and a better anchor position between the erection cylinder and the landing gear by using ADAMS software simulation of different conditions. The research is to provide a reference for the design of relevant weapons systems.

The Design of Dynamic Model of Engineering Material Arresting System

2014 ◽  
Vol 607 ◽  
pp. 435-439
Author(s):  
Na Liu ◽  
Hong Bin Yu
Keyword(s):  
Numerical Simulation ◽  
Dynamic Model ◽  
Landing Gear ◽  
Soft Ground ◽  
Engineering Material ◽  
Aircraft Landing ◽  
Aircraft Landing Gear ◽  
New Type

Engineered Material Arresting System (EMAS) is a new type of soft ground arresting system that can safely arrest the overrun aircraft in an allowed distance without injuring aircraft passengers and damaging aircraft landing gear. The paper provides an overview of the EMAS background firstly. A numerical simulation is carried out by VB.NET software through reasonable hypothesis and simplification the system of dynamic model. The model is reasonable and feasible compared with prototype experiment results.

scholarly journals Unlocking a nose landing gear in different flight conditions: folds, cusps and a swallowtail

2021 ◽  
Author(s):  
James A. C. Knowles ◽  
Bernd Krauskopf ◽  
Etienne B. Coetzee
Keyword(s):  
Steep Descent ◽  
Landing Gear ◽  
Steady States ◽  
Numerical Continuation ◽  
Continuation Methods ◽  
Physical Factors ◽  
Special Focus ◽  
Gear Mechanism ◽  
Cusp Points ◽  
External Forces

AbstractThis paper investigates the unlocking of a non-conventional nose landing gear mechanism that uses a single lock to fix the landing gear in both its downlocked and uplocked states (as opposed to having two separate locks as in most present nose landing gears in operation today). More specifically, we present a bifurcation analysis of a parameterized mathematical model for this mechanical system that features elastic constraints and takes into account internal and external forces. This formulation makes it possible to employ numerical continuation techniques to determine the robustness of the proposed unlocking strategy with respect to changing aircraft attitude. In this way, we identify as a function of several parameters the steady-state solutions of the system, as well as their bifurcations: fold bifurcations where two steady states coalesce, cusp points on curves of fold bifurcations, and a swallowtail bifurcation that generates two cusp points. Our results are presented as surfaces of steady states, joined by curves of fold bifurcations, over the plane of retraction actuator force and unlock actuator force, where we consider four scenarios of the aircraft: level flight; steep climb; steep descent; intermediate descent. A crucial cusp point is found to exist irrespective of aircraft attitude: it corresponds to the mechanism being at overcentre, which is a position that creates a mechanical singularity with respect to the effect of forces applied by the actuators. Furthermore, two cusps on a key fold locus are unfolded in a (codimension-three) swallowtail bifurcation as the aircraft attitude is changed: physical factors that create these bifurcations are presented. A practical outcome of this research is the realization that the design of this and other types of landing gear mechanism should be undertaken by considering the effects of forces over considerable ranges, with a special focus on the overcentre position, to ensure a smooth retraction occurs. More generally, continuation methods are shown to be a valuable tool for determining the overall geometric structure of steady states of mechanisms subject to (external) forces.

Kinematic Analysis and Synthesis Type III Movable Spatial 6R Mechanism With Three Adjacent Parallel Axes

1992 ◽  
Author(s):  
Chung-Ching Lee ◽  
Hong-Sen Yan
Keyword(s):  
Computer Animation ◽  
Kinematic Analysis ◽  
Special Form ◽  
Matrix Algebra ◽  
Landing Gear ◽  
Type Ii ◽  
Kinematic Synthesis ◽  
Aircraft Landing ◽  
Analysis And Synthesis ◽  
Gear Mechanism

Abstract Based on matrix algebra, we derive the general analytical kinematic solutions of Type II movable spatial 6R mechanism with three adjacent parallel axes. This 6R mechanism was previously identified by the authors, and one of its special form is proposed as the retracting and wheel twisting mechanism for aircraft landing gears. A graphical synthesis technique by descriptive geometry is presented for the kinematic synthesis of the landing gear mechanism. A numerical example is given, and the mobility of this design is verified by computer animation of motions.

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