Abstract: The present invention models dynamic behavior of flight vehicles for simulation, analysis, and design. The present invention allows a user to define the complexity of a flight vehicle model, and such models may be simple rigid body models, models of medium complexity, or very complex models including high order dynamics comprising hundreds of structural flexibility modes and variables related to aero-elasticity, fuel sloshing, various types of effectors, tail-wags-dog dynamics, complex actuator models, load-torque feedback, wind gusts, and other parameters impacting flight vehicles. The present invention accommodates and analyzes multiple vehicle and actuator concepts and configurations as defined in flight vehicle input data, which specifies flight vehicle parameters at a steady-state condition for modeling flight vehicle response to dynamic forces and flight control commands with respect to steady state operation.

Abstract: A method for selecting, from a set of possible configurations, an optimized tire configuration for fitting a vehicle intended to run on a circuit following a predefined route, oriented in a single course direction (SU) and including bends. This method comprises: developing a physical model of the vehicle fitted with a first tire configuration; simulating the route course by the modeled vehicle, optimizing the speed of said vehicle; storing in memory the course time taken by the vehicle to cover the route at least once; comparing the course time to at least one reference time and producing a comparison result; and optionally selecting the first configuration at the optimized configuration as a function of the comparison result.

Abstract: Systems and methods involving engine models are provided. A representative method for updating a gas turbine engine reference model includes: determining whether an absolute difference between a dominant time constant of a sensor and an assumed sensor model time constant is outside a tolerance value; and responsive to determining that the absolute difference is outside the tolerance value, updating the assumed sensor model time constant with the dominant time constant of the sensor.

Abstract: A method for analyzing the behavior of complex systems, particularly internal combustion engines, wherein a model is established which shows the dependence of test variables on input variables, calibrating the model based on test values of the real system obtained at the test points subdividing into at least two partial models a first principal influential parameter is identified for the first partial model, an optimal value of the first principal influential parameter is determined at each test point, the first principal influential parameter is interpolated for all plausible constellations of input variables to calibrate the first partial model, another partial model is established to show another subset of test variables in accordance with the input variables and the previously determined first subset of test variables, an additional principal influential parameter is identified for the other partial model, and an optimal value of the additional principal influential parameter is determined at each test po

Abstract: A system, method and program to improve the processing speed of a simulation system. A processing system finds an entry point so that functional blocks cover a broad range. The processing system places code of a look-ahead dispatcher for assigning processing. The look-ahead dispatcher monitors an input state at the entry point to determine whether the input state is a stable state. If the input state is stable, the look-ahead dispatcher calls an adaptive execution module at some frequency or otherwise calls an idle execution module. The adaptive execution module performs processing on multiple timestamps at once. When a discrete system receives an input event, the look-ahead dispatcher calls a recovery execution module. Based on the input event on that occasion, the timestamp, and a value stored in a state vector, the recovery execution module calculates a state for which recovery is performed.

Abstract: Iterative (nondeterministic) optimization of aerodynamic and hydrodynamic surface structures can be accomplished with a computer software program and a system using a combination of a variable encoding length optimization algorithm based on an evolution strategy and an experimental hardware set-up that allows to automatically change the surface properties of the applied material, starting with the overall shape and proceeding via more detailed modifications in local surface areas. The optimization of surface structures may be done with a computing device for calculating optimized parameters of at least one (virtual) surface structure, an experimental hardware set-up for measuring dynamic properties of a specific surface structure, and an interface for feeding calculated parameters from the computing device to the experimental set-up and for feeding measured results back to the computing device as quality values for the next cycle of the optimizing step.

Abstract: Method and arrangements for predicting life-affecting damage on a rotary member subjected to repeated loading during operation. A number of operating parameters are measured, and a temperature increase during each loading is calculated from the operating parameters. More precisely, a total temperature in a part of the rotary member is calculated for each loading by summation of basic temperature of the rotary member before the loading concerned and the temperature increase, and the values for the total temperature are used as a measure of the damage. The part of the rotary member for which the total temperature is calculated defines a surface that is acted on when the rotary member is loaded. Two sets of predetermined functions (M, N), which each comprise at least one function, are used for temperature-increase calculation, and the set which is used for temperature-increase calculation is selected depending on at least the nature of the rotary member.

Abstract: The invention discloses differing embodiments of finite element modeling methods utilizing mass distribution to model an object. In one embodiment, the finite element model of the object may be partitioned into sub-models. A determination may be made as to which elements in the finite element model are structural and as to which elements in the finite element model are non-structural. Mass properties for both the structural and non-structural elements in each sub-model may be determined. The significant non-structural masses within each sub-model may be selected and added to the finite element model. The remaining insignificant, non-structural masses may be incorporated onto the structural masses by scaling densities of the structural masses. The scaled structural masses may then be added to the finite element model. In other embodiments, objects are provided which were modeled utilizing finite element models under the invention.

Abstract: Specific tests on vehicles or parts thereof must be performed and analyzed according to a prescribed standard. The verification of an automation system for performing such a test and the final result of such a test is a complex and time-consuming procedure, however. So as not to have to repeat the complex verification in the case of changes in the automation system, it is proposed that the correctness of a test run only be checked once and in the case of established correctness, the reference data defining the test run be stored as the reference standard. If a change is performed in the automation system, it is sufficient to perform the test run again and to compare the reference data of the reference standard to the new reference data.

Abstract: Iterative (nondeterministic) optimization of aerodynamic and hydrodynamic surface structures can be accomplished with a computer software program and a system using a combination of a variable encoding length optimization algorithm based on an evolution strategy and an experimental hardware set-up that allows to automatically change the surface properties of the applied material, starting with the overall shape and proceeding via more detailed modifications in local surface areas. The optimization of surface structures may be done with a computing device for calculating optimized parameters of at least one (virtual) surface structure, an experimental hardware set-up for measuring dynamic properties of a specific surface structure, and an interface for feeding calculated parameters from the computing device to the experimental set-up and for feeding measured results back to the computing device as quality values for the next cycle of the optimizing step.

Abstract: The invention relates to an arrangement and a method for the adaptation of parameters in a transport system. The arrangement of the invention comprises a power model (1), wherein power flow in the transport system is described by means of transport system parameters (2,3,4,13), which include input parameters (2,3,13) and status parameters (4). The arrangement also comprises the determination of at least a first (2) and a second (2) input parameter, and the power model (1) is updated on the basis of at least the first input parameter (2). At least one transport system status parameter (4) is adapted using at least the updated power model (1) and the second input parameter (3) thus determined.

Abstract: The invention relates to a method for predicting the aerodynamic performance of an aircraft element under predetermined conditions, the said aircraft element having at least one break (5) at least partially separating two parts (1, 2) that cannot or should not be modeled with a common envelope form, in which: a digital form representative of the form that the aircraft element assumes under the predetermined conditions studied and in which each break (5) is represented, is created, for each break (5), a totally non-coincident boundary surface (7) at the joining of the two parts (1 and 2) is created, and a partial structured meshing around each part (1, 2) is generated, the two partial meshings made in this way being independent of one another, digital aerodynamic simulation computations using this meshing are carried out with the aid of an aerodynamic computation code capable of processing a totally non-coincident join.

Abstract: The present invention is generally directed toward testing devices. For example, one aspect of the invention is directed toward a simulation device that includes an indicator circuit configured to simulate a characteristic of a countermeasure initiation device. The indicator circuit can be switchable between at least two states including a ready state and an unavailable state. The system can further include a switching circuit operably coupled to the indicator circuit to switch the indicator circuit between the at least two states.

Abstract: A method and apparatus may be present for managing rework. A section in a location of a platform having a number of composite materials needing rework may be identified to form an identified section. A layup for the number of composite materials in the identified section of the platform may be determined. A patch for the identified section of the platform and the layup for the number of composite materials may be generated. A simulation may be performed of a selected rework process and the patch in the identified section.

Abstract: The invention relates to a method of computer simulation of the aerodynamic behaviour of an aircraft (10) in flight close to the ground. This method is used to identify the slope effect relative to the ground effect. To achieve this, a uniform boundary condition comprising a predetermined speed (UP) with a non-zero tangential component and a non-zero normal component is imposed on a plane (21) modelling the ground; and a discrete numerical model of the Navier-Stokes equations is solved by computer on a volume mesh with said boundary condition imposed on said plane (21), so as to obtain a numerical solution for a fluid flow inside a computational domain defined by said mesh.

Abstract: A running pattern calculating apparatus and running pattern calculating method that stores road information; predicts a running state when the vehicle will travel on a road, based on the stored road information; divides the road into a plurality of sections based on the predicted running state and sets an evaluation function for each road section; and calculates a running pattern of the vehicle that will travel on the road, based on the evaluation function set for each road section.

Abstract: A method is disclosed of identifying or fixing the value of the parameters (aerodynamic data) of a pre-determined set of equations forming the aerodynamic models of an aircraft in various configurations, so as to minimize the variance between the values anticipated by using these aerodynamic data, and reference data in cases of known configurations, includes the use of learning or optimization methods to determine at least one portion of the parameters' values. The method includes storing database data, choosing an optimization method or a neural network method, breaking the identification down into several partial identifications, carrying out successive partial identifications, validating the values found for the aerodynamic model's parameters or iterating the method according to a threshold criterion determined on the value of variances between the reference data and the values measured by the identified model.

Abstract: A command sequence for an autonomous UAV mission is optimized by simulating the performance of a mission in a model environment. Using a genetic algorithm, neural net, or other suitable technique this command sequence is then optimized, to improve the outcome of the mission. A factor in selecting an optimal command sequence will be its compressability. A set of one or more optimal command sequences is compiled. Each optimal command sequence is encoded into an algorithmic active packet of minimum size for uploaded to the UAV, which then executes the mission. To track the UAV in its performance of the mission without compromising its location, the active packets are executed in the simulated environment. The simulated environment is continually updated with the most current available information. The simulation results are an approximation of the current state of the UAV.

Abstract: A method for estimating the cylinder interior pressure of an internal combustion engine from a cylinder pressure model having at least the input variables load, speed of rotation, and crank angle (Ppressure model), which forms the cylinder interior pressure (Pgas) to be determined, corrected by a pressure correction value (?Pgas). The pressure correction value (?Pgas) is determined from an observation of the alternating moments at the crankshaft. The modeled value of the cylinder interior pressure from the pressure model is obtained as a pre-control value, and corrected with a correction value formed from the measured value of the non-uniformity of rotation.

Abstract: A method of providing rapid business support of insured property using image analysis can include the step of receiving at least one digital image of damaged property. Damage can be automatically accessed for insurance purposes based upon the received images. An incident response can be automatically determined based at least in part upon the damage assessment. Incident responses can include, but are not limited to, tendering a claim payoff offer, referring a claim to a human agent, providing repair instructions, and/or arranging for a physical damage assessment of the damaged property.

Abstract: A computer-aided method suitable for assisting in the design of an aircraft by providing a variable distribution V over an aircraft surface inside a predefined parameter space by means of a reconstruction of the results obtained through computations for an initial group of points in the parameter space using a CFD model comprising in each of said computations the following steps: a) Selecting relevant shock wave structures being defined by its thickness ?sw, its position ssw and the variable jump ?V; b) Decomposing said variable distribution V into a smooth variable distribution Vsmooth and a shock wave variable distribution Vjump corresponding to said relevant shock wave structures; c) Obtaining the variable distribution V at any point of the parameter space as a reconstruction of the smooth variable distribution Vsmooth and the shock wave variable distribution Vjump obtained for said point.

Abstract: A flight simulator adapted for a family of aircraft may include a computer having a hardware unit common to the family of aircraft and capable of carrying out a function by implementing a software program that is supported by a nonvolatile memory of a module. The module is electrically and mechanically connected in a removable manner to the hardware unit and has a plurality of independent memories. Each of the memories stores a specific software program for implementing the function related to a given type of aircraft. A controllable component of the module may select, when the module is connected to the hardware unit, one of the memories whose software program is then implemented by the hardware unit.

Abstract: A method of designing a motor vehicle is disclosed. The method includes simulating a collision of a motor vehicle using a computer model that corresponds to the motor vehicle. Collision data is collected from the simulation and used to determine calibration information for an air bag system.

Abstract: A gas turbine performance analysis system includes a performance computation module for receiving an actual measured value of an inlet air temperature introduced to a compressor, a compressor pressure ratio, and a flow rate of fuel supplied to the gas turbine, and for calculating and outputting values of the gas turbine's power output and exhaust temperature based on these actual measured values. A performance estimation module evaluates the performance of the gas turbine based on the deviation between the values of power output and exhaust temperature outputted from the performance computation module and the actual measured values of power output and exhaust temperature. An adjustment module calculates a corrected value of the fuel flow rate based on the actual measured values of inlet air temperature, compressor pressure ratio and fuel flow rate, and inputs the corrected fuel flow rate value into the performance computation module.

Abstract: A computer based system and method for establishing one or more patches related to a seat to be designed is provided. The system method establish a set of environment characteristics, a set of interface characteristics, and a pool of body templates. The pool of body templates are representative of target occupants of the seat. The system and method further establish a seat design as a function of the established environment characteristics, interface characteristics, and body templates by defining a plurality of patches.

Abstract: A system and method for modeling supervisory control of heterogeneous unmanned vehicles through discrete event simulation is provided. Generally, the system contains a memory and a processor configured by the memory to perform the steps of: simulating events in the system; simulating arrival processes for the events in the system; simulating how long a human operator takes to respond to the simulated events in the system, where the time that the human operator takes to respond to a simulated event is referred to as a service time; and prioritizing the events to be handled by the human operator, wherein the system models human operator involvement in the unmanned vehicle system.

Abstract: A method for estimating the performance, during a braking situation, of a tire to be provided to a vehicle, this method comprising an experimental phase (EXPERIM) including a step (EVAL_MU) of assessing the grip coefficient (?) of the tire on the ground. This assessment step is performed for different values (Vi) of the relative displacement speed of the tire axis with regard to the ground and for different values (gi%) of the tire slip rate on the ground. The experimental phase (EXPERIM) further comprises a modelization step (MODEL) of representing the grip coefficient of this tire, as resulting from the assessment step (EVAL_MU), by a function (MU3D) of the relative displacement speed of the tire axis with regard to the ground and of the slip rate of this tire on the ground.

Abstract: Values of multiple tire dynamic element parameters are set for a tire dynamic model constructed using the tire dynamic element parameters for calculating a tire axial force and a self-aligning torque under a given slip ratio. Next, the values of the tire axial force and the self-aligning torque are calculated using the tire dynamic model and output. The tire dynamic model allows a center position of a contact patch thereof against a road surface to move in accordance with a longitudinal force that occurs as the tire axial force when a slip ratio in a braking/driving direction is given so that a position of the contact patch moves in a longitudinal direction due to the longitudinal force. When designing a vehicle or when designing a tire, the tire dynamic model is used.

Abstract: Methods for optimizing at least one operating parameter of an engine component using an experimentally measured 3D flow field involving providing a magnetic resonance imaging machine, providing a model of an engine component, placing the model into the magnetic resonance imaging machine with a fluid flow source for applying an external fluid flow, applying the external fluid flow to the model, collecting data related to the external fluid flow about the model, and optimizing at least one operating parameter of the component using the data.

Abstract: A system for subjective evaluation of a vehicle design within a virtual environment includes a scaleable physical property representative of the vehicle design and a computer system for digitally creating a virtual environment having a virtual human immersed within. The system also includes a motion capture system for sensing a motion of an evaluator and communicating the sensed motion of the evaluator to the computer system and a virtual reality display mechanism for providing the evaluator a view of the virtual environment while evaluating the vehicle design.

Abstract: A method and device for creating an accurate simulation or model of the performance of a vehicle or an internal combustion engine in accordance with the invention comprises accessing the engine on-board diagnostic port (OBD), reading data from the desired industry standard parameter indicators (PID), using these data to produce a basic simulation of the engine operating characteristics, accessing and reading non-industry standard PIDs and using the output from the basic simulation in order to identify the non-industry standard PIDs with a high degree of certainty.

Abstract: A method of setting a parameter in a method of detecting a decreased tire air pressure for detecting a decreased tire air pressure based on a wheel rotational speed obtained from tires attached to a four-wheel driving vehicle. The method includes a vehicle model preparation step of preparing a vehicle model including a suspension member; a tire model preparation step of preparing a tire model; a step of inputting a friction coefficient between a tire and a road surface; and a simulation step of performing a running simulation of the vehicle model attached with the tire model. A determination parameter for determining whether the tire has a decreased air pressure or not is set based on wheel rotational speeds of the tires of the respective four wheels obtained in the simulation step.

Abstract: The present invention's new calculative methodology models the motion of a seagoing vessel in six dimensions, uniquely employing a total velocity potential as the sole parameterization for taking into consideration all linear and nonlinear dynamical effects involved in interaction between the vessel and environmental water. The solid-body rotational motion of the vessel about the vessel's center of mass is determined in three dimensions (roll, pitch, yaw) by calculating the pressure torque and the buoyancy torque. The solid-body translational motion of the vessel's center of mass is determined in three dimensions (heave, surge, sway) by calculating the pressure force and the buoyancy force. The pressure torque and the pressure force are each associated with pressure (e.g., non-hydrostatic pressure) of water on the vessel's surface. The buoyancy torque and the buoyancy force are each associated with the displacement of the vessel with respect to the vessel's equilibrium position in the water.

Abstract: A simulator is provided for simulating a real-water-droplet for an arbitrary simulation time in an entire space to be observed in which the real-water-droplets collide by a certain probability within a predetermined volume in a predetermined time interval, and in which the real-water-droplet is specified by a group of an arbitrary number of attributes and position coordinates at an initial time in one of divided spaces into which the entire space is divided, a super-water-droplet representing a group of an arbitrary number of the real-water-droplets which have a predetermined identical group of the attributes, when the multiplicity which is the arbitrary number of the real-water-droplets represented by the super-water-droplet changes when the super-water-droplet collides with another by a probability based on the certain probability and the multiplicity, calculating data about the super-water-droplet to output data about the real-water-droplet after the arbitrary simulation time elapses.

Abstract: In a remote control system, the remote control of a vehicle function is executed. The remote control system includes a control terminal and a cancellation device. The control terminal transmits a request for the remote control of the vehicle function to a vehicle. The cancellation device cancels the remote control of the vehicle function if the local control of the vehicle function is requested before the remote control of the vehicle function is executed according to the request for the remote control.

Abstract: Methods and systems are provided for adjusting liability estimates associated with past or theoretical accidents. Embodiments may be used in association with methods and systems for estimating liability in a vehicle accident. In an embodiment, liability estimates may be associated with past or theoretical accidents. The liability estimates associated with the past or theoretical accidents may be used in methods and systems for estimating liability in a vehicle accident. The liability estimates associated with the past or theoretical accidents may be tested to determine if they yield a desired or expected liability estimate for a real accident. If the liability estimates associated with the past or theoretical accidents do not yield the desired or expected liability estimate for the real accident they may be adjusted.

Abstract: Use of scientific models to generate graphical virtual environments is described. In an embodiment at least two different scientific models are used. Input data which is representative of a real world environment is used by a first scientific model, such as a climate model, and data output by the first scientific model is then fed into a second, different, scientific model, such as an ecological model, in order to generate simulation data. The simulation data, which may, for example, detail the required population density of particular plant species and their size and age, is then used by a graphical simulation engine to generate a graphical virtual environment which may, for example, be used in a computer game such as a flight simulation game.

Abstract: Disclosed is a configurable cockpit system based on design parameters, which comprises: a configurable cockpit which has an interface between a user and the cockpit, and various sub-systems for efficiently measuring design parameters; an interface for synchronizing configuration which converts the design parameters measured in the configurable cockpit to the cockpit design parameters for the CAD system, or converts the cockpit design parameters of the CAD system to the design parameters of the configurable cockpit; and cockpit design parameter database which accumulates cockpit design parameters and automatically modifies the CAD 3D configuration through automatic linking to the cockpit configuration template based on the cockpit design parameters.

Abstract: A method and a device are described for acquiring driving data of a vehicle. Moreover, a computer program and a computer program product are put forward for carrying out the method. In the method described, a three-dimensional, kinematic vehicle model is calculated, including linear-motion-dynamics signals and lateral-motion-dynamics signals. This model can be utilized for reconstructing the vehicle movement.

Abstract: In one embodiment a device is provided for visually demonstrating stagger. In this embodiment, the device includes first and second tires coaxially mounted on an axle, wherein the first tire has a smaller diameter than the second tire. The device also includes a member configured to be pushed or pulled by a person. The device may be pushed or pulled on a flat surface, such as a paved road. When the device is pushed or pulled in a forward direction, the first and second tires will rotate at the same rotational speed, but because the second tire has a larger diameter than the first tire, the second tire will travel a greater distance than the first tire during each tire rotation. Thus, the device will move in a curved path.

Abstract: A wind tunnel testing technique or method involves using feedback to position control surfaces of a model so that there is substantially no moment on the model for its given orientation to the airstream. The model is mounted on a sting that allows change in orientation of the model relative to the airstream. A balance is used to provide data regarding the forces and/or moments on the model. This data on forces and/or moments is used in one or more feedback loops to position the control surfaces of the model so that there are substantially no moments on the model. This may be done automatically, with a controller automatically controlling the position of the control surfaces to zero out the moments on the model. The use of the method may allow faster determination of model characteristics, such as determination of the trim envelope of the model.

Abstract: Each spot weld in a structure is represented by a cluster of at least one solid element in a finite element analysis model of the structure. Each spot weld is used for tying together two parts. Each of the two parts are generally represented or modeled as a number of two-dimension shell elements. Since the tie-connection between the spot weld and the two parts can be located arbitrarily within the respective part, the shell elements representing the two parts do not have to be aligned in space. The only requirement is the two shell elements must be overlapped each other such that the spot weld can tie the two shell elements (i.e., one from each part) together. A spot weld failure criterion used for determining failure including shear and axial stresses acted on the spot weld, shell element size and spot weld location sensitivity scale factors and strain rate effect.

Abstract: A process for simulating and assembling flexible parts includes creating an ideal path between first and second planes and placing a virtual rigid envelope around the ideal path, and possibly tubular extensions beyond the path. A virtual flexible part is marked with reference features and pulled through the virtual rigid envelope, such that the path of the virtual flexible part is constrained but may rotate. Removing the virtual rigid envelope allows the virtual flexible part to relax, causing it to move to its lowest energy state. Zero-twist end conditions on the virtual flexible part are marked, corresponding to the intersection of the reference features with the planes. Identification marks are placed on a real flexible part, corresponding to the reference strips on the virtual flexible part. The real flexible part may then be assembled by aligning zero-twist marks on mating features to the identification marks on the real flexible part.

Abstract: Methods and systems for the design and execution of an aerospace or aeronautic system are provided. The aerospace or aeronautic system may incorporate planetary environment models and models of equations of motion. The planetary environment models mathematically represent planetary environment specifications, such as atmosphere and wind. Atmosphere models include standard day atmosphere models and non-standard day atmosphere models, and wind models include continuous wind turbulence models and discrete wind turbulence models. The models of equations of motion include models of three-degree-of-freedom equations of motion with variable mass and models for six-degree-of-freedom equations of motion with variable mass. As a result, the present invention can design and execute a target system more accurately than the conventional system that provides only standard day planetary environment models, continuous wind turbulence models, or fixed mass equations of motion models.

Abstract: A system and method for planning/replanning collision free flight plans in real-time (or accelerated-time) including planning individual flight plans for each flying asset, executing (or simulating) the planned individual flight plans, detecting violations of safety zones of each of the flying assets by negotiation and by other assets monitoring (radar sensing), and repairing the individual flight plans by real-time replanning.

Abstract: A simulation system is provided. A simulator is configured to execute simulation of a simulation object at a processing speed. A user interface module is configured to generate at least one of a first operation screen for inputting simulation conditions on the simulation executed by the simulator and an output screen for representing a result of the simulation executed by the simulator, and to display the at least one of the first operation screen and the output screen on a display unit. An adjustor is configured to adjust an updating speed of the at least one of the first operation screen and the output screen which are displayed on the display unit by the user interface module to be different from the processing speed.

Abstract: A method and apparatus for synchronous communication in a control system is disclosed. Within a first time interval, a first source task is executed to broadcast a first destination task, within a second sequential time interval, the first destination task is communicated over a channel to a first destination, and within a third sequential time interval, the first destination task is consumed. Within the first time interval, a second source task may be executed to broadcast a second destination task, within the second sequential time interval, the second destination task may be communicated over the channel to a second destination, and within the third sequential time interval, the second destination task may be consumed. The first source task is allowed to be scheduled ahead of the second source task, and the second source task is allowed to be scheduled ahead of the first source task.

Abstract: A transmission modeling system includes an in-gear module that determines an in-gear acceleration when a vehicle is in gear. A shift module determines a shift acceleration based on a clutch torque when the vehicle is shifting between gears. A shaft acceleration determination module determines a shaft acceleration based on at least one of the in-gear acceleration and the shift acceleration.

Abstract: A method for automatically generating a multi-component multilevel model for simulation of an automotive propulsion system and/or subsystem. The method comprises a capture component and a build component. The capture component operates to automatically parse all relevant information of an existing model and to generate one or more files indicative of the systems and subsystems of the model. The files are created such that they may be efficiently searched, manipulated, and applied for subsequent use in various user defined models created through the build component. The build component obtains the information in the one or more files and additional user defined files based on user selections to automatically create an executable model ready for analysis.

Abstract: A simulation system (30) for simulating an operation of an automotive vehicle includes an input (34) providing vehicle information and path information and a controller (38) having a vehicle computer model therein. The controller (38) is programmed to determine an initial steering wheel angle input to the computer model; determine a first steering wheel angle input to the computer model at a time later than the initial steering wheel angle input by comparing a look ahead point and an intended path; when the vehicle model is understeering, operate the computer model with the initial steering wheel angle input until an error of the first steering wheel angle and the initial is decreasing; when the error decreases, operate the computer model with the first steering wheel angle input; and generate an output in response to the vehicle model and the initial steering wheel input or the first steering wheel input.