Investigation of wrought steel railway car wheels : part I, tests of strength properties of wrought steel car wheels

Cover title.Prepared as part of an investigation conducted by the Engineering Experiment Station, University of Illinois at Urbana-Champaign

Division by zero in common meadows

Common meadows are fields expanded with a total inverse function. Division by zero produces an additional value denoted with "a" that propagates through all operations of the meadow signature (this additional value can be interpreted as an error element). We provide a basis theorem for so-called common cancellation meadows of characteristic zero, that is, common meadows of characteristic zero that admit a certain cancellation law.Comment: 17 pages, 4 tables; differences with v3: axiom (14) of Mda (Table 2) has been replaced by the stronger axiom (12), this appears to be necessary for the proof of Theorem 3.2.

Locomotion and restraint aid Patent

Gravity environment simulation by locomotion and restraint aid for studying manual operation performance of astronauts at zero gravit

Planters and their Components: Types, attributes, functional requirements, classification and description

Crop Production/Industries, Farm Management,

Development of Urban Electric Bus Drivetrain

The development of the drivetrain for a new series of urban electric buses is presented in the paper. The traction and design properties of several drive variants are compared. The efficiency of the drive was tested using simulation calculations of the vehicle rides based on data from real bus lines in Prague. The results of the design work and simulation calculations are presented in the paper

Universality of Univariate Mixed Fractions in Divisive Meadows

Univariate fractions can be transformed to mixed fractions in the equational theory of meadows of characteristic zero.Comment: 12 page

Modelling commercial vehicle handling and rolling stability

YesThis paper presents a multi-degrees-of-freedom non-linear multibody dynamic model of a three-axle heavy commercial vehicle tractor unit, comprising a subchassis, front and rear leaf spring suspensions, steering system, and ten wheels/tyres, with a semi-trailer comprising two axles and eight wheels/tyres. The investigation is mainly concerned with the rollover stability of the articulated vehicle. The models incorporate all sources of compliance, stiffness, and damping, all with non-linear characteristics, and are constructed and simulated using automatic dynamic analysis of mechanical systems formulation. A constant radius turn test and a single lane change test (according to the ISO Standard) are simulated. The constant radius turn test shows the understeer behaviour of the vehicle, and the single lane change manoeuvre was conducted to show the transient behaviour of the vehicle. Non-stable roll and yaw behaviour of the vehicle is predicted at test speeds .90 km/h. Rollover stability of the vehicle is also investigated using a constant radius turn test with increasing speed. The articulated laden vehicle model predicted increased understeer behaviour, due to higher load acting on the wheels of the middle and rear axles of the tractor and the influence of the semi-trailer, as shown by the reduced yaw rate and the steering angle variation during the constant radius turn. The rollover test predicted a critical lateral acceleration value where complete rollover occurs. Unstable behaviour of the articulated vehicle is also predicted in the single lane change manoeuvre

Algorithms for aircraft trim analysis on ground 13; AIAA-96-350513;

In the analysis of aircraft dynamics far up and13; away flight, the general practice consists of trimming13; the aircraft for a specific maneuvers at a specified13; Altitude and Mach number. In this paper conditions for13; Quasi-steady equilibrium are motivated for aircraft13; dynamics in the ground roll phase. Algorithms for13; implementation of these conditions are also described.13; By use of these algorithms, the locus of trim points is13; obtained for a comprehensive take-off maneuvers of a13; delta wing aircraft beginning with ground roll,13; followed by rotation and ending in lift-off. This result13; is compared with approximate calculations wherein the13; landing gear states are ignored and linear13; aerodynamics is assumed. The exact result is also13; compared with the simulation of the take-off13; maneuvers in a pilot in the loop simulator.13