Abstract: Methods and systems for facilitating efficient travel management in a manner such that the carbon emissions produced by vehicle travel are reduced are disclosed. Different vehicle travel modes under consideration for use to satisfy a travel plan are evaluated and selected based at least in part on their relative environmental impacts such that an aggregate reduction in carbon emissions can be achieved via a judicious selection of vehicle travel modes used to carry out a vehicle travel plan.

Abstract: Methods for minimizing the effects of pylori induced disturbances of the airflow at the propeller blades (2) of propeller propulsion devices (3) attached to an aircraft component (5) by means of upstream pylons (4), comprising steps of injecting fluid on the zone of the propeller blades (2) from the rear part of said pylons (4) for minimizing the effects of said disturbances detected through the values of a first set of parameters such acoustic pressure and vibration in the aircraft structure and vibration in the propeller blades (2) that are obtained continuously or according to models linked to one or more parameters of a second set of parameters indicative of the aircraft flight conditions such as flight altitude, flight speed propulsion power, propeller rotation speed obtained from a tachometer signal, ambient temperature of the air. The invention also refers to systems for implementing said methods.

Abstract: An apparatus for supplying a person with information for statically adjusting wheels, or tyres, of a motor vehicle comprises: a data storage module defining a model of vehicle operation through a plurality of model parameters; a control module adapted to set a parameter for evaluating the on-road behaviour of the vehicle and to receive values of measurement parameter correlated with the on-road behaviour of the vehicle and measured on the vehicle wheels, in order to set values of model parameters defining a starting configuration of the model parameters; a processing module adapted to perform simulations of the on-road behaviour of the vehicle using said model, while varying the value of at least one of the model parameters in order to determine, according to the set evaluation parameter, a modified model parameter configuration corresponding to an on-road behaviour of the vehicle that is better than that corresponding to the starting configuration; a module for presenting to the person service information fo

Abstract: The portable simulation system is a computer-based driving simulator, which uses an actual vehicle as an input device, and a portable display to present a Virtual Driving Environment (VDE) to the driver. Vehicle's steered wheels are placed atop of the turntables permitting free operation of the steering wheel. The vehicle remains immobile while its engine and power steering can be turned off during the simulation. External non-invasive sensors can be placed under the gas and brake pedals, permitting any vehicle to be used in the simulator, including the driver's own vehicle. A digital interface to the vehicle's systems, like OBD II, can be used to increase the fidelity of the simulation. A portable computer used for driving simulation and VDE presentation provides a low cost simulation option. A simple configuration of the portable simulator does not require an external power source and can be set-up and operated at any parking space.

Abstract: Systems and methods of limiting contact penetration in numerical simulation of non-linear structure response using implicit finite element analysis are described. According to one aspect, a finite element analysis (FEA) model of a structure is defined as a number of nodes and elements based on geometry and material properties of the structure. A time-marching analysis of the FEA model is then performed. The time-marching analysis results contain a number of solutions of non-linear structure response at respective time steps. Solution at each time step requires at least one iteration to compute. Non-linear structure response is determined in the following manner: 1) determining a search direction; 2) calculating a contact penetration parameter in the search direction; and 3) finding a minimum energy imbalance location along the search direction as a solution which is further restricted by the CPP such that contact penetration of the structure is substantially limited.

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: Certain exemplary embodiments can comprise obtaining and analyzing data from at least one discrete machine, automatically determining relationships related to the data, taking corrective action to improve machine operation and/or maintenance, automatically and heuristically predicting a failure associated with the machine and/or recommending preventative maintenance in advance of the failure, and/or automating and analyzing mining shovels, etc.

Abstract: A product design method includes accessing a defined product design structure. The product design structure includes a number of customer concerns, a number of physical properties associated with components of the product, and a number of relation models. Each customer concern is associated with at least one physical property via at least one mathematical relationship defined in at least one of the relation models. The method also includes receiving a value associated with one or more of the physical properties and calculating (using one or more of the relation models) the effect of the received value associated with the one or more physical properties on one or more of the customer concerns. Furthermore, the method includes displaying the calculated effect on the one or more customer concerns and receiving one or more adjustments of the value associated with one or more of the physical properties to create a desired effect on one or more of the customer concerns.

Abstract: A system is described that treats a solver as an ordered sequence of steps involving the different objects that have to be simulated and relationships between them. Tasks and the order of the tasks are obtained from each object and relationship. The tasks are merged into a sorted list. The solver traverses the list and passing each task to a corresponding object and relationship where the objects are interleaved during processing. The object or relationship then executes the task.

Abstract: The present invention generally relates to processes for predicting airflow rates. According to some embodiments, some process steps can include developing a three-dimensional computer-aided design model of a test body topology; discretizing the test body topology; discretizing a volume surrounding the test body topology, the volume being bounded by a test chamber; identifying test body components upon which to collect empirical data; obtaining empirical data for identified components; establishing an airflow model; validating the airflow model in comparison to experimental data; obtaining a flow rate from the validated airflow model; and determining whether the mass flow rate is acceptable.

Abstract: A simulation system provides a simulated environment to at least one user in a simulation area. The simulation system includes a video system configured to provide high definition video of the simulated environment across a field of view of the user. The video system provides high definition live action video. The simulation system also includes an audio system configured to provide high definition audio related to the provided high definition video of the simulated environment and a motion system configured to move the at least one user on x, y, and z axes to simulate movement in the simulated environment.

Abstract: A train simulator, including a microprocessor, a display and an input device for the microprocessor. A program drives the display with the track data during simulation, determines if an exception has occurred during the simulation; and provides a multimedia message if an exception has occurred.

Abstract: A method for designing a flight vehicle includes determining a preferred aerodynamic shape of a structure of the vehicle; modifying the preferred aerodynamic shape based upon constraints; and determining, using aerodynamic computational fluid dynamics, limit loading conditions for the modified aerodynamic shape. A computer-implemented system for designing a flight vehicle includes at least one computer operable to determine a preferred aerodynamic shape of a structure of the vehicle; modify the preferred aerodynamic shape based upon constraints; and determine, using aerodynamic computational fluid dynamics, limit loading conditions for the modified aerodynamic shape.

Abstract: A method and device for testing a vehicle design under predefined ambient conditions. A test driver is subjected to impressions of movement, which are generated as a function of the vehicle design and the ambient conditions, the vehicle design being present during the generation of the impressions of movement exclusively as a visual model, which is displayed to the test person.

Abstract: A support vector machine with wavelet kernel was developed for accurate modeling of nonlinear systems. A method of providing an optimized model of a nonlinear system includes using a support vector machine (SVM) having a wavelet kernel, where support vectors include a family of multidimensional wavelets. Training the SVM allows optimization of the number of support vectors, the weights of the support vectors, and the translation factors of the support vectors. Use of a novel linear programming approach reduces computational demands required for training, allowing optimized support vectors to give an optimized model of the nonlinear system. Further, on-line retraining is possible, so that the model can be adapted to changing conditions.

Abstract: In a method for estimating an entrance angle of a V-ribbed belt from a flat pulley to a V-ribbed pulley, the entrance angle is estimated easily at a stage of pulley layout design. The V-ribbed belt 10 forms a track which enters at an entrance angle of approximately zero degree (substantially perpendicular to a plane that includes an axis 3a of rotation) into the flat pulley 3, is wound along the outer peripheral face of the flat pulley 3 without deviating in the axial direction thereof, and extends substantially linearly from a winding end point c at the flat pulley 3 to a winding start point d at a drive pulley 1. The entrance angle ? of the V-ribbed belt 10 from the flat pulley 3 to the drive pulley 1 is obtained on the basis of the track of the V-ribbed belt by, for example, a three-dimensional CAD or the like.

Abstract: A process and device for optimising the performance of an aircraft in the presence of a lateral dissymmetry is disclosed. The device (1) includes means (2, 3, 4, 5, 7, 9) for controlling, during a lateral dissymmetry, at least one rudder such as to generate an optimum sideslip for reducing the drag of the aircraft.

Abstract: The invention is directed to a procedure for fitting relevant parameters in SCR catalyst models and to an apparatus for carrying out such procedures. Following the procedure of the present invention, it is possible to make a first estimate of the SCR model parameters by fitting the parameters individually. This is possible because of special measurements that simplify and isolate reactions in the SCR model. The set of parameters determined via this method are used as a starting point for a global optimization of the model parameters.

Abstract: Computer-assisted systems and methods for integrating aesthetic and functional design processes for real-world objects can include a computerized module for defining an aesthetic representation of a real-world object, and a computing module supplied with approximation model data of a CAE simulation module to calculate functional quality value(s) using a parametric description of the aesthetic representation as input. An interface can issue a physical signal to a user, with the physical signal communicating the quality value(s) to the user. A computerized module can change the parametric description of the aesthetic representation of the object in the aesthetic design process taking the obtained functional quality value into account.

Abstract: This procedure proposes the appropriate equations that determine the rotor movement in order to obtain the aerodynamic actions for each blade in each iteration (the forces that are transmitted to the helicopter and the moments with respect to the articulations), and they are resolved by discretizations made in the rotor disc, such that that the blade elements of the partition are connected to the disc, which does not rotate, instead of to each blade. The blades pass through an azimuth range in each iteration, making a division of each blade longitudinally into ne elements, and the rotor disc into na sectors, corresponding to divisions of the range of azimuth angles. Therefore, partitions are made on ne·na blade elements, identifying each blade element by means of its distance to the rotor axis and its azimuth angle.

Abstract: A method for transmitting data from and to a control device, in particular an engine control device for a motor vehicle that has a first communication interface and a second communication interface , the method having the following steps: connecting the first communication interface to a development tool, and connecting the second communication interface to one or more function units during the development phase of the control device, transmitting data from the control device to the development tool via the first communication interface using a first communication protocol, transmitting data from the development tool to the control device via the first communication interface using the first communication protocol, breaking the connection between the first communication interface and the development tool, connecting the first communication interface to one or more additional 20 function units, and transmitting data between the control device and the other function unit or function units via the first communic

Abstract: A system and method for collecting and modeling simulated movement data on a graphical display is provided. Simulated movement data from a simulation is accessed from a database. The simulated movement data comprises each location of a object on a graphical display for multiple points in time of the simulation. A three-dimensional representation is associated with the object and the three-dimensional representation is displayed at each location on the graphical display for each point in time of the simulation.

Abstract: A system and method for receiving and displaying simulated movement data on a graphical display in real-time is provided. Simulated movement data from a simulation is received. The type and location of each object to be displayed on a graphical display for a time step is extracted from the simulated movement data. The extracted data is transferred to an application for determining an appropriate three-dimensional representation to associate with each type of object in the first point in time. Each three-dimensional representation is displayed according the location of each object for the first point in time of the simulation.

Abstract: Disclosed is a 3D vehicle simulator system for an ECU embedded system comprising an external input apparatus 130, to which signals of one or more external sensors are inputted, an ECU embedded system 120 for processing and executing signals inputted form the external input apparatus 130, an external output apparatus 140 for receiving and outputting the output signals of the ECU embedding system 120, a vehicle simulator 110 for calculating at real time the signals inputted from the ECU embedded system 120, and for 3D-modeling and outputting the status of the vehicle, and a display 150 for displaying the 3D-modeled vehicle outputted form the vehicle simulator 110.

Abstract: A computer reads data from a database in an external recording device to generate an analysis model which represents the surface profile of a member with a mesh. Next, the computer initializes the meshes of the analysis model by setting thereto a gas attribute corresponding to a non-leakage site and thereafter sets to any mesh a liquid attribute corresponding to a leakage site, and changes the attribute of meshes adjacent to the meshes having the liquid attribute from the gas attribute to the liquid attribute. Then, the computer connects meshes of which attribute has been set to the liquid attribute to generate a leakage path and outputs information relating to the leakage path on a display device.

Abstract: In accordance with preferred embodiments and applications of the invention, an automated custom configuration system (and method) is provided for facilitating the configuration and customization of desired products, services, or other objects that require users to gather and assimilate disparate relevant information (e.g., knowledge of makes, models, types, features, options, limitations, codes, and prices of the desired product/service (or group of the same) to be configured and customized). In accordance with a preferred embodiment, custom configuration may be facilitated through a parametric drawing engine which provides illustrations of configuration data.

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 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 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: 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 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: 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 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 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 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.