88 results about "Aircrew" patented technology

The invention provides a voice instruction intelligent analysis method and system applied to an air traffic control scene, relates to the technical field of air traffic control, and aims at the characteristics of voice instruction interaction between a controller and a flight crew in the air traffic control scene to construct an instruction interaction expectation model. The instruction interaction expectation model comprises an instruction sequence association rule and a semantic constraint condition set which are generated based on historical controlled call data, and an interaction feature set of speaker identity features, instruction component time sequence features, voice intonation fluctuation features and the like in a real-time capture voice interaction process; inputting an instruction interaction expectation model for dynamic matching and deviation identification, generating an interaction deviation analysis result, triggering an intention clarification and instruction confirmation process based on the analysis result, obtaining a complete instruction component set, generating an instruction analysis result meeting an air traffic control data exchange standard after structured conversion processing, and pushing the instruction analysis result to an air traffic control automation system. The accuracy and efficiency of air traffic control voice instruction analysis are effectively improved.

The invention discloses an aircraft performance monitoring method, device, terminal and system and a storage medium, and the method comprises the steps: obtaining a preprocessed flight data stream from an airborne flight data preprocessing device in the flight process of a target leg, analyzing and processing the flight data meeting the effective leg screening condition in the preprocessed flight data stream to obtain the flight data of the effective leg; based on the flight data of the effective leg, calling an embedded performance factor analysis logic to carry out performance factor analysis so as to obtain a performance factor of the effective leg; and in response to a flight end instruction of the target leg, displaying a performance monitoring result on a display based on the performance factor of each effective leg. According to the invention, while the timeliness of airplane performance monitoring is improved, the interference on airborne system data is avoided, the safety is ensured, and an airplane crew can master the performance condition of an airplane in time.

The technology subject of the present application generally concerns an aerial munition unit comprising a proximity fuze functionality and an impact fuze functionality, selectable by a crew member of an aircraft bearing the munition, after the aircraft has taken off and prior to munition release, to render active or operable the proximity fuze functionality or the impact fuze functionality.

The invention discloses a flight plan automatic filling method and device for an electronic flight bag. The method comprises the following steps: extracting waypoint information of an original flight path from an original flight plan; acquiring a real-time position of the aircraft based on a preset time period; based on the real-time position and the waypoint information, determining a flight leg of the aircraft at the current moment through a preset leg discrimination algorithm; based on the flight segment, determining a newly added passed waypoint and a pre-flight waypoint of the aircraft; updating the state information of the newly-added passed waypoint into a passed state, and recording updating time; and based on the update time, filling the actual arrival time of the newly added passed waypoint in the flight plan electronic form, and correcting the predicted arrival time of the pre-flight waypoint. According to the method, the actual arrival time of the current waypoint in the flight plan can be automatically filled in, and the predicted arrival time of the next waypoint can be automatically corrected, so that the operation burden of flight crew is effectively reduced, and human errors are reduced.

The utility model belongs to the technical field of cockpit integration and industrial design, and relates to an active reporting system for abnormal conditions of a driving unit. The system comprises a processing unit, and a camera, an active reporting key and a microphone array which are integrated in a cockpit, the camera is used for acquiring an action signal of a crew driver in real time; the microphone array is used for collecting voice signals of a driver crew in real time; the active report key is used for collecting an active report key signal of a driver; the processing unit is used for receiving an action signal, a voice signal and an active report key signal; and identifying a trigger action in the action signal, identifying a trigger statement in the voice signal, and identifying a key trigger signal in the active report key signal, so as to accurately judge the abnormal state of the driving unit.

An object of a system according to an embodiment is to improve motivation by effectively transmitting a praise comment of a customer to a crew.SOLUTION: A system according to an embodiment includes a comment collection unit, a comment analysis unit, a comment generation unit, and a comment transmission unit. A comment collection part collects praise comments of customers. The comment analysis unit analyzes the praise comment collected by the comment collection unit. A comment generation part generates an appropriate praise comment on the basis of the content analyzed by the comment analysis part. The comment transmission unit transmits the praise comment generated by the comment generation unit to the crew.SELECTED DRAWING: Figure 1

The invention relates to the technical field of intelligent security check, and discloses a video analysis and prediction system applied to intelligent scheduling management of a security check channel, and the system comprises a data processing module which obtains flight information from a flight information system of an airport, fuses real-time passenger flow data collected by video monitoring, and constructs a multi-dimensional data set; the multi-curve analysis module is used for generating a full-load curve, an actual attendance curve, a historical prediction curve and a crew curve based on the multi-dimensional data set; and the intelligent scheduling recommendation module is used for calculating the number of security check channels required at the current time point according to the real-time number of people obtained by superposing the full load curve, the actual attendance curve, the historical prediction curve and the crew curve in combination with a preset security check speed. By means of the scheme, minute-level data processing, multi-dimensional prediction analysis and intelligent scheduling can be achieved, so that the security check efficiency and the resource utilization rate are improved, and efficient and safe operation of air transportation is guaranteed.

The application provides a helicopter high-temperature air-bleed oxygen production control device and method. The device comprises an engine air-bleed channel (14), an outlet end of the engine air-bleed channel (14) is connected with an inlet end of a heat dissipation assembly (3), an outlet end of the heat dissipation assembly (3) is connected with an inlet of an oxygen production main machine (7) through an air-bleed pipeline (10), and an outlet of the oxygen production main machine (7) is connected with an oxygen supply mask (9) through an oxygen supply pipeline (11). A shut-off valve (2) is arranged on the engine air-bleed channel (14). The outlet of the heat dissipation assembly (3) is respectively provided with a filter (5) and a temperature and pressure sensor (6). The shut-off valve (2) and the temperature and pressure sensor (6) are all connected with an oxygen production controller (1). The application can improve the reliability and safety of a molecular sieve oxygen supply system, avoid high-temperature air from entering the oxygen production main machine, damage the molecular sieve material, and scald the machine personnel.

The invention relates to the technical field of aviation unit management, and discloses an intelligent scheduling system based on an aviation unit, which comprises a unit management module and an intelligent scheduling module. According to the system, plan operation data and actual operation data of all flights and management data of all crew personnel are obtained through a crew management module and are classified to form a data set, and an intelligent scheduling module judges whether different flights conform to a loop line standard or not, generates a plan data set and a flight loop, optimizes continuous use of crew resources, and improves the working efficiency. The vacancy time is reduced, the unit utilization rate is improved, the flight matching flexibility is high, the intelligent scheduling module evaluates the operation state of each flight ring, generates a flight data set and a scheduling early warning signal, then evaluates the working state of each crew, generates a fatigue index and outputs a corresponding scheduling suggestion, and the scheduling efficiency is improved. The scheduling personnel are helped to visually identify a problem flight ring and a high-risk unit, chain delay is avoided, the overall operation efficiency is improved, and the efficient scheduling optimization effect is good.

The invention relates to a seat (10) for a cabin crew mounted in an aircraft cabin, comprising: a seat structure (11) fastened to an aircraft floor; a cushion plate (12) and a backrest (13) mechanically connected to the seat structure (11), the cushion plate (12) being movable between a raised position and a lowered position; a space filling device (17) between a seat structure (11) and a bulkhead (16) of an aircraft cabin, the space filling device (17) comprising: a fixing part (20) fastened to the seat structure (11); and a movable part (21) which can be moved in translation relative to the fixed part (20) in order to be able to adjust the width of the space filling device (17) to a gap between the seat structure (11) and the partition plate (16).

The invention belongs to the field of design of systems for preventing out-of-control accidents of aircrafts, and particularly relates to an integrated platform and method for preventing out-of-control accidents of aircrafts. The comprehensive platform comprises an airborne modeling and simulation unit used for describing changes of aircraft dynamics and control characteristics caused by aircraft damage and external threats; the aircraft health management unit is used for monitoring and predicting the state of the aircraft and continuously evaluating and managing the health condition and the remaining life of the aircraft; the elastic guidance and control unit is used for aircraft out-of-control prevention and recovery and external threat suppression; and the man-machine interface unit is used for realizing man-machine information exchange and coordination under the condition that the airplane is out of control. The aircraft dynamics and control characteristics can be effectively represented under the condition that the aircraft is abnormal, aircraft health and flight safety are evaluated in real time, and effective context awareness and decision support are provided for flight crew, so that the aircraft out-of-control accident risk is reduced, and related accidents are prevented.

The present invention pertains to the field of life-saving equipment having accommodation for passengers and crew, comprising capsules (1), wherein each capsule (1) is impact-resistant, has an oval shape, and comprises a seat (2), wherein said seat (2) is provided with safety belts (4), wherein a sphere (6) is mounted to withstand an initial impact, such that when they undergo said initial impact, the spheres (6) issue a command to the seat, assisting in cushioning the impact inside the capsule (1), which is oval and formed in two parts, and is further provided with a plurality of airbags (7) strategically fastened to the internal walls, as well as apertures (8) to enable oxygen exchange with the environment, and wherein each capsule additionally comprises a manual safety system equipped with an internal battery for use in the event of aircraft failure.

An on-board system and method for leveraging multi-modal means of detecting runway incursions to increase aircraft safety, and to provide a necessary enabler for both reduced crew operations and autonomous flights in the future. The system and method detect incursions using visual perception for all types of vehicles and objects that may incur, and an ADS-B for self-reporting vehicles. The system and method fuse prior known information (such as ownship pose and map data) with detections from sensors and other sources. The system actively tracks detections and computes the current and predicted future states to decide if there is an on-going incursion on the runway. The system reports the runway state to the pilots and / or autonomous receivers.

A seat assembly for a passenger cabin of an aircraft having a holding wall which is permanently secured to the base structure of the aircraft and a seat for the cabin crew. The seat is secured to the holding wall solely by a rotational axis and being rotatable by 30° to 300° between two end positions and between seat positions in which a sitting position of a seat surface of the seat is facilitated. The aircraft has the base structure, the passenger cabin, and the seat assembly with the permanently secured holding wall in the intended installation state. The seat can be rotated about each of the rotational axes between the two end positions and between the seat positions, and the sitting position of the seat surface is facilitated in each of the seat positions.

The present invention relates to a method for simulating an engine failure on a rotorcraft (1) comprising several engines (10) for setting a rotary wing (6) in motion. The method includes a training mode comprising control with a governor (30) for each engine (10) to simulate an engine failure, this control including a limitation of the power of each engine (10) to a respective control limit. The training mode comprises the following steps: i) determining, with the governor (30), on the one hand, a maximum mass based on at least external conditions and, on the other hand, an initial mass of the rotorcraft (1) based on at least the empty mass of the rotorcraft (1), the mass of a crew present in the rotorcraft (1), and an estimated mass of fuel on board; ii) comparing, with the governor (30), the initial mass to the maximum mass; iii) determining, with the governor (30), each control limit based on said comparison.Abbreviated figure: figure 1.

The invention discloses a cursor skipping method and system for an electronic checklist of an aircraft, electronic equipment and a storage medium. The method comprises the following steps: updating a check state of at least one closed loop item in all check items in an electronic check list at least partially based on a received closed loop signal; monitoring a target check item in the electronic checklist in response to the update, wherein the target check item indicates that the check state of the at least one closed-loop item automatically cancels check due to the update and is a first check item located on a front page in the electronic checklist; and in response to monitoring the target check item, executing cursor skipping. According to the method, the system, the electronic equipment and the storage medium, information omission can be prevented, the flight safety is improved, the operation efficiency of aircraft crew personnel is improved, and the man-machine interaction process is optimized. Numerous other aspects are also disclosed.

The invention relates to the technical field of aviation, in particular to a helicopter anti-crash buffer device which comprises a helicopter body. The mounting platform is fixed on the belly or the side surface of the helicopter body; one end of the supporting leg main rod is hinged to the mounting platform, and the other end of the supporting leg main rod is hinged to the inner end of an energy absorption module; one end of the auxiliary supporting leg is hinged to the mounting platform, and the other end of the auxiliary supporting leg is hinged to the supporting leg main rod; the outer end of the energy absorption module is connected with the inner end of the foot pad through a spherical hinge; one end of the pyrotechnic actuating cylinder is connected with the helicopter body through a spherical hinge, and the other end of the pyrotechnic actuating cylinder is connected with the outer end of the energy absorption module through a spherical hinge. When the helicopter works normally, the device is in a folded and compressed state and is arranged in the shell. When the helicopter crashes accidentally, the device shell falls off and is thrown away, impact energy is absorbed through the air bag after the helicopter touches the ground, safe landing of the helicopter is achieved, and life safety of flight crew is guaranteed.

A central cabin control system comprises a central controller in operable communication with various sub-systems in an aircraft cabin. The central controller is configured to provide data of various systems to crew members and / or facilitate interactions with various passengers. The central controller is configured for operable communication with each controller disposed in the aircraft cabin.

Embodiments herein describe how a computer can receive scheduling requests for various user types. The computer can iteratively allocate the aircraft to determine a schedule for each aircraft based on the requests and determining an availability for crews associated with the aircraft. The computer can iteratively execute the algorithm for each updated scheduling request. The computer can generate schedule change sets for a graphical user interface based on an allocation of the aircraft and crews from the algorithm. Generating the schedule change sets can include determining a viability of the plurality of change sets; determining a cost associated with each of the viable schedule change sets according to a predetermined cost function; and selecting a change set based on the cost thereof. The computer can automatically generate and transmit the change set to schedule propagation nodes.

The invention discloses a unit meal selection method. The method comprises the following steps: acquiring a meal selection request of a person to select meal for aviation meals; outputting a corresponding aviation meal selection interface based on the meal selection request; generating a meal order according to aviation meal selected by a person waiting for meal selection in the aviation meal selection interface according to a preset meal selection rule; generating a payment instruction based on the meal order, and displaying prompt information of successful payment after the person waiting for meal selection successfully pays according to the payment instruction; the efficiency of the meal selection process can be improved, diversified meal selection requirements of flight crew are met, and the user experience is remarkably improved.

A seafarer safety device (500) includes an evaluator (510a) and an inboard outputter (510k). The evaluator (510a) executes an evaluation process of evaluating whether a crew in emergency circumstances, on the basis of the intensities of notification radio waves indicating the existence of the crew on a craft and transmitted from a wearable transmitting device that repetitively transmits the notification radio waves, and on the basis of the strengths of rocking motions of the craft detected by a craft rocking-motion sensor that detects the strengths of rocking motions. The inboard outputter (510k) outputs, to an alarm unit, an emergency evaluation signal indicating a result of evaluation, when the evaluator (510a) evaluates that the crew is in emergency circumstances.

The invention belongs to the field of international flight personnel exit and entry security check, and provides a flight personnel information forecasting method and device and electronic equipment, and the method comprises the steps: responding to a target user request, determining the business type of a to-be-forecasted business, the business type comprises a first forecasting business and a second forecasting business, the first forecasting service is a real-time forecasting service of passengers, and the second forecasting service is a non-real-time forecasting service of flight crew; distributing corresponding target distribution tasks for the services of different service types; matching a corresponding target processing flow based on the target distribution task; and based on the service type of the current service, executing a corresponding target processing flow, and generating a forecast result. Through the forecasting method, the flight personnel information can be accurately forecasted based on the forecasting method.

An inflatable bladder configured to be carried by an aircrew garment worn on the body of the aircrew and to apply pressure to the body when inflated by a gas to counteract effects of high G-forces during flight. the bladder includes a gas-permeable material allowing the passage of the gas therethrough to cool the body

A fire detection device is designed to make hydrogen fires detectable in aviation operations and similar applications, whether it is for the purpose of detecting a fire around an aircraft prior to passenger and crew emergency evacuation, or to identify fires in proximity to airport ground vehicles that utilise hydrogen as a fuel or vehicles that are used for transporting or transforming hydrogen in any transport context. The device can be designed to be non-toxic and safe for use in proximity to humans.

A head armature for a respiratory system includes a cradle and a retention mechanism. The cradle is configured to receive a respiratory mask assembly in a stand-by position. The retention mechanism is configured to detachably connect the respiratory mask assembly with the head armature such that the respiratory mask assembly is movable from the stand-by position to a use position while connected to the head armature and such that the respiratory mask assembly is selectively detachable from the head armature in a stand-alone configuration whereby the respiratory mask assembly is disconnected from the head armature. In the use position, the respiratory mask assembly is configured to provide oxygen to a user. The head armature is configured to be worn on a head of the user such that the cradle is between the respiratory mask assembly and the user's head when the respiratory mask assembly is in the stand-by position.

A prediction system with a unit for generating a current value of a parameter relating to the movement of an aircraft, a selection unit for a crew member of the aircraft to select an exit of the runway used for landing, an avionics computer for computing a value of the time of occupancy of the runway and a unit for transmitting this value to a user system. The avionics computer using an initial ground speed and an exit type and an exit distance of the exit selected, and computes the value of the time of occupancy of the runway, with the data and by using a prediction model comprising a neural network trained on the basis of landing data originating from previous landings.

The invention relates to the technical field of virtual simulation, in particular to an amphibious aircraft marine take-off and landing safety assessment method, which comprises the following steps of: acquiring physiological parameters and marine and meteorological parameters of flight crew in real time to construct environmental parameters; fusing and preprocessing the parameters to form a multi-source data set; constructing an analytic hierarchy process model based on the data set, and constructing a judgment matrix through the model to calculate the subjective weight of each parameter; collecting index data of a plurality of take-off and landing schemes, calculating an objective weight by using an entropy weight method, and optimizing and determining a target weight in combination with a subjective weight; based on the target weights, analyzing each take-off and landing scheme to determine positive and negative ideal solutions, and calculating the relative closeness of each scheme; and finally, determining an optimal take-off and landing scheme according to the relative close degree sequence, and generating an evaluation report. According to the method, physiological, ocean and meteorological parameters are integrated, subjective and objective weights are combined, a scientific basis is provided through comprehensive analysis, and the safety of offshore take-off and landing of the amphibious aircraft is effectively improved.