Abstract: A system and method for aircraft performance predictions for descent and approach phases are disclosed. In one embodiment, cruise computation is stopped substantially around a default distance from a destination. Further, current predicted aircraft state is determined using a total energy of the aircraft starting from the default distance. Furthermore, descent and approach phase profiles are computed using the determined current predicted aircraft state. In addition, the aircraft performance predictions are obtained using the computed descent and approach phase profiles.

Abstract: A system and method for computing thermal boundary conditions from an unstructured computational fluid dynamics (CFD) simulation for a thermal simulation of a structural component are disclosed. The thermal boundary conditions include convective heat transfer coefficient (HTC) and reference temperature (Tref). In one embodiment, prism cells are formed to capture boundary layer substantially next to a wall of the structural component. Further, tetrahedral cells are formed to capture a diffused temperature layer substantially next to the formed last prism cell and in a direction normal to the wall. Furthermore, temperature of each of the prism cells is computed in the direction normal to the wall until a substantially first tetrahedral cell. In addition, the computed temperature of the prism cell that is substantially adjacent to the first tetrahedral cell is declared as the Tref. Also, the HTC is computed using the obtained Tref.

Abstract: A system and method for collaborative building of a shared self-refining surrogate model for engineering simulations are disclosed. In one embodiment, a method includes running a reduced order engineering simulation model on a complex system, and querying a shared self-refining surrogate model upon receiving a request for a higher order simulation for a reduced order simulated item. The method also includes estimating a required higher order simulation result having a desired confidence interval for the reduced order simulated item, and determining whether the required higher order simulation result having the desired confidence interval is in the shared self-refining surrogate model.

Abstract: An improved Modal Assurance Criterion for comparing two mode shapes obtained from modal analysis of a multi-component structure is disclosed. In one embodiment, a first mode shape vector and second mode shape vector for a first mode shape and second mode shape of the multi-component structure, respectively, are formed by grouping modal displacement at each node associated with each component in the multi-component structure. Further, modal assurance criterion (MAC) between the first mode shape vector and second mode shape vector is computed by dividing a square of sum of magnitudes of correlation of the modal displacement at each component for the first mode shape vector and second mode shape vector in the multi-component structure with a product of squared magnitudes of the first mode shape vector and second mode shape vector. Furthermore, the first mode shape and second mode shape of the multi-component structure are compared using the MAC.

Abstract: A system and method for an adaptable oxygen regulator with an electronic control device is disclosed. In one embodiment, an oxygen regulator system includes an electronic control device which includes a non-volatile memory for storing a first reference point. The electronic control device also includes a pressure sensor configured for generating pressure data of the pressurized aircraft cabin. The electronic control device further includes a logical control unit for generating a control signal by processing the first reference point and the pressure data. Further, the electronic control unit includes a rotary actuator for generating a rotary displacement based on the control signal. Moreover, the oxygen regulator system includes a demand dilution oxygen regulator coupled to the electronic control unit and configured to control the supply of oxygen and the flow of dilution air from the pressurized aircraft cabin based on the control signal.

Abstract: A system and method for automatic generation and usage of fluid flow loss coefficients for T-junctions is disclosed. In one embodiment, a list of possible T-junctions is created using given geometric and flow parameters. Further, journal files are created using the geometric and the flow parameters associated with each T-junction. The journal files associated with each T-junction are pre-processed for creating a volume mesh. Boundary conditions and material properties for the volume mesh associated with each T-junction are defined. Simulation is performed using the volume mesh, the boundary conditions and the material properties associated with each T-junction to determine flow characteristics. Fluid flow loss coefficients for each T-junction are computed using the flow characteristics.

Abstract: A technique for providing multiple undo and redo operations for flight management systems is disclosed. In one embodiment, in a method of providing multiple undo and redo operations for a flight plan in a flight management system, a temporary flight plan and a reference flight plan are created upon initiating a first revision on a created or default active flight plan. The temporary flight plan includes a copy of the active flight plan and the initiated first revision. The reference flight plan is a copy of the active flight plan. Further, multiple undo and redo functions are enabled upon initiating multiple revisions on the temporary flight plan for performing multiple undo and redo operations on the temporary flight plan.

Abstract: A system and method for aircraft performance predictions for climb flight phase is disclosed. In one embodiment, a method of aircraft performance predictions for climb flight phase in a flight management system (FMS) includes determining current predicted aircraft state using a total energy of the aircraft. Further, excess energy available in an engine of the aircraft is computed. Furthermore, a change of speed of the aircraft is computed at a given point in the climb flight phase. Kinetic energy (KE) change required is then computed for the computed speed change. Remaining energy available is then computed based on the computed KE change. The aircraft performance predictions for the climb flight phase are then computed using the determined current predicted aircraft state.

Abstract: A system and method for generating three dimensional functional space reservation systems of a vehicle from a conceptual space reservation is disclosed. In one embodiment, in a method for generating three dimensional functional space reservation systems, functional, connectivity and geometrical information associated with two conceptual space reservation versions of the vehicle is collected from design databases. The two conceptual space reservation versions include current and previous conceptual space reservation versions. Then, mathematical models are created in organized binary form. Delta information detected from the two conceptual space reservation versions of the vehicle is outputted. Further, a set of rules and checks is applied in the mathematical model of the current conceptual space reservation version and standardized entities information is outputted.

Abstract: A system and method for extracting relevant computational data are disclosed. In one embodiment, one or more physical quantities and/or one or more functions of physical quantities of interest, associated with a larger volume, to be measured are identified. Further, any non-available identified functions of physical quantities are computed for each smaller volume of the larger volume using the available physical quantities in the computational data. Furthermore, regions in computational domain are identified along with ranges of identified physical quantities and functions of physical quantities of interest for carrying out the extraction from the computational data. Moreover, geometrical and connectivity information of smaller volumes associated with the identified regions/ranges that are obtained by filtering the computational data associated with the larger volume are obtained.

Abstract: A novel automatic standardization and verification process for system design requirements in a product development project is disclosed. In one embodiment, a method for automatic standardization and verification of system design requirements in a product development project using a standardization and verification tool embedded in a computer aided design (CAD) application includes obtaining a desired standardized requirement from a requirements database, retrieving compliance criteria from the standardized requirement, obtaining one or more components associated with the standardized requirement from one or more data sources, and obtaining relevant extracted and derived attributes from the one or more components, associated with the standardized requirement.

Abstract: A system and method for aircraft taxiing and guidance using ground station's communication network is disclosed. In one embodiment, in a method of aircraft taxiing and guidance, a communication link between an aircraft computing system and a ground station system is established using a communication network provided by the ground station system. An aircraft taxi selection and guidance application residing in the aircraft computing system is displayed on a display device upon establishing the communication link. Further, one or more pilot selectable taxiing and ground services are displayed upon selecting the aircraft taxi selection and guidance application. One of the displayed pilot selectable taxiing and ground services is selected by a pilot of an aircraft. Information associated with the selected pilot selectable taxiing and ground service is then displayed on the display device using ground station data. The aircraft is taxied and guided by the pilot using displayed information.

Abstract: A system and method for generating three dimensional functional space reservation systems of a vehicle from a conceptual space reservation is disclosed. In one embodiment, a method includes collecting functional, connectivity and geometrical information from design databases associated with a conceptual space reservation of a vehicle upon receiving a request from a client device for three dimensional functional space reservation systems. The method also includes creating a mathematical model in a binary form using the functional, connectivity and geometrical information. The method further includes applying a set of rules and checks governing a design of the vehicle to the mathematical model, and applying a set of functional attributes to the mathematical model for creating connectivity information in the mathematical model.

Abstract: A system and method for providing an aircraft noise advisory during departure and/or arrival of an aircraft are disclosed. In one embodiment, predefined allowable aircraft noise level information associated with a plurality of aircraft noise sensors located in the vicinity of airports are obtained. Further, predefined allowable aircraft noise level information associated with one or more of the plurality of aircraft noise sensors is presented on a display device in the aircraft, based on a current location of the aircraft, upon receiving noise data request from a pilot. Furthermore, current aircraft noise level information is obtained from one of the one or more aircraft noise sensors. In addition, the current aircraft noise level information is compared with predefined allowable aircraft noise level information associated with the one of the one or more aircraft noise sensors. Also, the aircraft noise advisory is displayed based on an outcome of the comparison.

Abstract: A system and method for automatic modal parameter extraction in structural dynamics analysis are disclosed. In one embodiment, a stabilization diagram of a structure is obtained using a frequency domain parameter extraction technique. The stabilization diagram is a graph of measured transfer functions which include stable poles of the structure for each modal order versus frequencies which include modal frequencies of each stable pole. Further, a user is allowed to input user modal parameters, such as a maximum damping ratio, maximum number of stable poles to be selected from the stabilization diagram, and minimum separation in frequency between consecutive stable poles. Furthermore, stable poles having a damping ratio less than or equal to the maximum damping ratio are obtained. A histogram having bins, with a width equal to the minimum separation in frequency, is obtained. Also, the modal parameter of the structure is automatically extracted using the histogram.

Abstract: A method of automatic delivery of appropriate flow rate of oxygen to a person flying in a pressurized aircraft cabin is disclosed. In one embodiment, a first aneroid valve that is responsive to differential gas pressure in a first altitude range is preset to close at a oxygen starting altitude point based on apriori lung capacity test. Further, flow of oxygen is initiated from an oxygen bottle using quarter turn switching regulator connected to the oxygen bottle via a minimum flow area of main valve to output a mixture of the flow of oxygen and aircraft cabin air into a mixing chamber. Furthermore, the first aneroid valve is gradually closed in response to increasing aircraft cabin pressure altitude to stop the pilot flow of oxygen during the first altitude range. Then, main valve is opened upon closing the first aneroid valve to flow pressurized oxygen into the mixing chamber.

Abstract: Shape memory stainless steels with rare earth elements Cerium (Ce) and Lanthanum (La) are disclosed. In one embodiment, raw materials including Manganese (Mn), Silicon (Si), Chromium (Cr), Nickel (Ni), Carbon (C), Ce, La and Iron (Fe) are melted to form a molten alloy of the shape memory stainless steels with rare earth elements Ce and La. Further, the molten alloy is solidified to form an ingot. Furthermore, the ingot is subjected to nondestructive evaluation to assess internal soundness of the ingot. In addition, the evaluated ingot is homogenized to form homogenized shape memory stainless steels with rare earth elements Ce and La.

Abstract: A method of a flight management system (FMS) of an aircraft for generating an equi-time point (ETP) for an emergency landing of the aircraft includes receiving at least two reference points for landing the aircraft upon an occurrence of an emergency. The method also includes determining an equi-distance point (EDP) for the aircraft by locating a first point on the remaining flight path of the aircraft which is equidistant from the at least two reference points. The method further includes generating an ETP for the aircraft by locating a second point on the remaining flight path such that time difference between any two of expected flight times of the aircraft from the second point to the at least two reference points is less than a threshold value.

Abstract: A method of a flight management system (FMS) of an aircraft for computing flight time from an equi-distance point (EDP to a reference point for an emergency landing of the aircraft includes receiving at least two reference points for landing the aircraft upon an occurrence of an emergency and determining a remaining flight path for the aircraft based on a current location of the aircraft and a flight plan serviced by the FMS. Further, the method includes generating the EDP for the aircraft by locating a point in the remaining flight path, and calculating an expected flight time of the aircraft from the EDP to each of the at least two reference points based on a plurality of factors affecting the flight time of the aircraft.

Abstract: A system and method for simulating aerodynamics over an aircraft for a deflected position of a movable aircraft control surface using a structured chimera mesh are disclosed. In one embodiment, a mesh assembly of the aircraft is created by overlapping a background mesh and a structured chimera mesh for the deflected position of the movable aircraft control surface. Further, mesh cell sizes within overlapping boundaries of the background mesh and the structured chimera mesh are analyzed. Furthermore, the structured chimera mesh is regenerated based on the analysis. In addition, the mesh assembly of the aircraft is reformed based on the regenerated structured chimera mesh. Also, a masked mesh of the aircraft is created by auto masking the reformed mesh assembly. Moreover, aerodynamics is simulated over the aircraft for the deflected position of the movable aircraft control surface using the masked mesh.