Abstract: An aircraft hydraulic fluid heating system and method are disclosed. In one embodiment, pump characteristics of a hydraulic pump coupled to a reservoir are obtained. Further, total demand of the hydraulic fluid for hydraulically controlled flight controls in the aircraft is determined. Furthermore, the hydraulic fluid in the reservoir is dynamically heated based on the pump characteristics and the total demand of the hydraulic fluid.

Abstract: Prediction methods and systems including a central processing unit including a data acquisition unit configured to acquire experimental data of a parameter characterizing the time-dependent phenomenon, a data acquisition unit configured to acquire digital data of the parameter characterizing the phenomenon, and a data processing unit configured to combine the experimental data and the digital data, by using a proper orthogonal decomposition POD that makes it possible to obtain an effective prediction of the time-dependent phenomenon, combining the advantages of the experimental data (accuracy) and those of the digital data (spatial resolution).

Abstract: Disclosed is an example for performing aircraft braking based on real time runway condition. In one example, during landing, real time data of runway condition may be obtained using at least one sensor disposed around an aircraft. At least one brake factor may be determined based on the real time data of the runway condition. Aircraft braking may be controlled based on the at least one brake factor.

Abstract: A system and method for providing in-flight weather information to compute an optimized vertical flight profile are disclosed. In one embodiment, on-board weather information is obtained from one or more aircraft at regular intervals during flight. Further, weather information is identified for a predicted flight trajectory of an aircraft from the obtained on-board weather information. For example, the aircraft is preceding the at least one aircraft. Furthermore, a subset of the identified weather information is dynamically provided to a flight management system (FMS) in the aircraft, during flight, to compute the optimized vertical flight profile.

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 system and method for aircraft cabin activity management occurring during turnaround using video analytics are disclosed. In one embodiment, real-time video feed of the aircraft cabin activities is obtained during the turnaround from at least one video camera disposed in an aircraft cabin. Further, aircraft cabin activity time stamps and progress associated with one or more aircraft cabin activities are determined by applying video analytics on the obtained video feed. Furthermore, the aircraft cabin activities are managed using the determined aircraft cabin activity time stamps and the progress associated with the one or more aircraft cabin activities.

Abstract: A system and method for estimating frost mass formed in a design component of a multi-component structure are disclosed. In one embodiment, the frost mass formed in the design component is iteratively estimated using a heat transfer rate at an interface between fluid and a frost layer in the design component, a height of the frost layer and a density of the frost layer.

Abstract: A system and method for estimating frost mass formed in a design component of a multi-component structure are disclosed. In one embodiment, the frost mass formed in the design component is iteratively estimated using a porosity parameter associated with a fluid medium, a height of a frost layer and/or a density of the frost layer in the design component.

Abstract: An aviation mask is disclosed which includes an augmented reality visor, sensors, and a display computational unit. The sensors are communicatively connected to the augmented reality visor. The sensors detect a portion of a cockpit area of an aircraft that is viewed by an aircraft crew member wearing the augmented reality visor during a vision obscured emergency. The display computational unit is communicatively connected to the augmented reality visor and the sensors. The display computational unit projects a prestored image associated with the portion of the cockpit area in front of the augmented reality visor. Further, the display computational unit superimposes the prestored image over the portion of the cockpit area viewed by the aircraft crew member. The superimposed prestored image being viewed by the aircraft crew member through the augmented reality visor to identify objects in the portion of the cockpit area during the vision obscured emergency.

Abstract: An aircraft occupant seat for providing health, safety, and comfort management to aircraft occupants is disclosed. In one embodiment, an aircraft occupant, seated in an aircraft occupant seat in an aircraft, is monitored for health, safety and comfort information using at least one sensor disposed in the aircraft occupant seat. Further, background auditory, electrical noise, temperature and mechanical vibration associated with the aircraft occupant seat is measured using the at least one sensor. The health, safety and comfort information associated with the aircraft occupant is then obtained using the monitored health safety and comfort information and the measured background electrical noise and mechanical vibration. Health, safety and comfort of the aircraft occupant are then managed based on the obtained health, safety and comfort information.

Abstract: A technique for performing thermal analysis of an electronics rack is disclosed. In one embodiment, the electronics rack having multiple heat generating components is modeled. Further, thermal boundary conditions for each of the heat generating components are computed, by a computation fluid dynamics tool (CFD) tool, based on an initial temperature and a heat flux corresponding to each of the heat generating components in a first cycle, upon modeling the electronics rack. Furthermore, an actual temperature of each of the heat generating components is determined, by a one dimensional (1D) tool, using the computed thermal boundary conditions for estimating heat dissipated by each of the heat generating components in the first cycle.

Abstract: An aircraft occupant health, safety, and comfort management is disclosed. In one embodiment, an aircraft occupant, seated in an aircraft occupant seat in an aircraft, substantially around the aircraft occupant seat is monitored for health, safety and comfort information using at least one sensor disposed in the aircraft occupant seat and/or substantially around the aircraft occupant seat. Further, background auditory, electrical noise, temperature and mechanical vibration associated with the aircraft occupant seat is measured using the at least one sensor. The health, safety and comfort information associated with the aircraft occupant is then obtained using the monitored health safety and comfort information and the measured background electrical noise and mechanical vibration. Health, safety and comfort of the aircraft occupant are then managed based on the obtained health, safety and comfort information.

Abstract: In one example, a method to guide and navigate the aircraft during a complete engine failure is disclosed. Nearby airport data is obtained based on aircraft current location upon detecting the complete aircraft engine failure. Minimum and maximum glide distances of the aircraft are computed based on the current aircraft state parameters and environmental parameters. Candidate reachable airports are determined using the obtained nearby airport data for safe landing based on the computed minimum and maximum glide distances. A glide path for each candidate reachable airport is determined. The aircraft is navigated and guided to a selected one of the candidate reachable airports using an associated glide path.

Abstract: A system for monitoring scheduled turnaround activities and alerting on time deviation from the scheduled turnaround activities is disclosed. The system includes a ground computing station system, an aircraft on-board system, a cloud, and user interface. The cloud is communicatively coupled to the ground station computing system and the aircraft on-board system. The cloud includes processor and memory. The memory includes an analytics module to obtain actual start and end time stamps associated with scheduled turnaround activities, from touchdown to takeoff of an aircraft, from aircraft on-board systems and a ground station system. The analytics module to determine time deviation of scheduled turnaround activities by analyzing the obtained actual start and end time stamps. The user interface to present each scheduled turnaround activity and determined time deviation of the scheduled turnaround activities.

Abstract: System and method of converting geometric entities of 1D elements in a finite element model (FEM) from a source finite element analysis (FEA) tool format to a destination FEA tool format is disclosed. In one embodiment, coordinates of all the geometric entities associated with each 1D element in the FEM are transformed from the source FEA tool format to a global coordinate system. The geometric entities of the ID elements in the FEM are then converted from the source FEA tool format to the destination FEA tool format using the transformed coordinates of all the geometric entities associated with each 1D element.

Abstract: An aviation mask is disclosed which includes a first set of sensors that monitors cockpit ambient air and health of an aircraft crew member for detecting parameters that cause respiratory disorder to the aircraft crew member an oxygen regulator that switches between a dilution mode, an emergency mode, and a recirculation mode to supply respiratory gas to the aircraft crew member, an augmented reality visor, a second set of sensors that detects a portion of a cockpit area that is viewed by the aircraft crew member, and a display computational unit that projects a prestored image associated with the portion onto the augmented reality visor which is superimposed over the portion of the cockpit area. The first set of sensors also monitors aircraft cockpit area for detecting vision obscured emergencies. The superimposed prestored image is used to identify objects in the portion during the vision obscured emergency.

Abstract: A method for en-route flight path optimization is disclosed. A plurality of alternate flight paths between an origin and a destination of the aircraft in flight is determined based on real-time weather data, air traffic conflict data, and air space constraint data. Further, flight time savings and fuel savings for each of the plurality of alternate flight paths with respect to an actual path is computed. Furthermore, an optimal flight path from the plurality of alternate flight paths is determined based on the computed flight time savings, fuel savings, and a priority for the flight time savings and the fuel savings.

Abstract: A system and method for airside activity management using video analytics are disclosed. In one embodiment, video data of a survey area is obtained, in real time, from one or more video cameras. Further, time stamps associated with one or more airside activities of an aircraft from touchdown to takeoff are determined by applying video analytics on the obtained video data to manage the one or more airside activities.

Abstract: A system and method for sending weather alerts to an aircraft during flight are disclosed. In one embodiment, in-flight weather information is obtained from one or more aircrafts at regular intervals. Further, weather conditions along a predicted flight trajectory of the aircraft are determined using the obtained in-flight weather information. The aircraft is preceding the one or more aircrafts. Furthermore, the weather alerts associated with the weather conditions are sent to a display in the aircraft during flight.

Abstract: An on-board aircraft nitrogen enriched air and cooling fluid generation system and method are disclosed. In one embodiment, the system includes a first heat exchanger which is configured to receive pressurized air from a source of pressurized air. Further, the first heat exchanger cools the pressurized air to a temperature in the range of ?120° C. to ?70° C. Furthermore, the system includes a separation unit is configured and dimensioned to communicate with the first heat exchanger. The separation unit generates nitrogen enriched air from the cooled air at the temperature range of ?120° C. and ?70° C.