54results about "Aircraft black boxes" patented technology

An apparatus includes a body. The body includes an electronics chamber and an inflation chamber. The apparatus further includes a pressure sensor coupled to the body. The apparatus further includes a plurality of connector assemblies coupled to the inflation chamber. The apparatus further includes inflatable bags, where each inflatable bag is coupled to an individual connector assembly of the plurality of connector assemblies. The apparatus further includes a transmitter located within the electronics chamber. The apparatus further includes a processor located within the electronics chamber and coupled to a memory device. The processor is configured to detect submersion of the body in water, send a signal to cause initiation of a reaction in the inflation chamber, and cause the transmitter to send a data transmission.

An apparatus associated with a vehicle, includes a body, wherein the body includes a chamber. The apparatus further includes a buoyancy ring coupled to the body. The apparatus further includes a battery located within the chamber. The apparatus further includes a transmitter, wherein a portion of the transmitter is disposed within a recess of the body. The apparatus further includes a processor located within the chamber and coupled to a memory device, wherein the processor is configured to: receive a signal indicating detection of submersion of the vehicle in water, send a signal to switch a power source from the vehicle to the battery, send a signal to cause inflation of an inflatable bag, and cause the transmitter to send a data transmission.

An avionics system can provide data to first receiving components associated with a proprietary first protocol and second receiving components associated with a non-proprietary second protocol. A configuration tool generates a first configuration file including instructions for a data access component to provide a first data output to the first receiving components and a second data output to the second receiving components. The configuration tool can generate a second configuration file including instructions to translate the second data output. The data access component can receive a definition database defining the first protocol to translate data according to the non-proprietary second protocol. The data access component can provide requested data to the first and second receiving components according to the non-proprietary second protocol. The second receiving components are configured to translate data received based on the second configuration file.

Systems and methods for locating UAV. The methods comprise: causing a physical joining of a payload with a fuselage of the UAV (where the payload comprises a communication relay); using a power source to supply power to the payload that is independent from a main power source of the UAV; and continuing to perform relay operations by the communication relay and location operations by a first locator, when power is no longer being supplied by the main power source.

A method for automatically decoding aircraft Cockpit Voice Recorder (CVR) encoded data includes loading a definitions class and a decoder class into a memory via a driver class, loading configuration files into the memory via the definitions class, receiving from an aircraft CVR one or more hex files that include the CVR encoded data into the memory, generating via the decoder class and the configurations file one or more decoded objects based on the one or more hex files, respectively, and displaying the one or more decoded objects in a human readable format. A system to automatically decode aircraft CVR encoded data includes a user interface, a processor, and a memory having a computer program configured to generate one or more decoded objects based on one or more hex files of CVR encoded data, and to display the one or more decoded objects in a human readable format.

An aircraft recorder system is provided in which a vibration sensor including at least one of a micro-electromechanical systems (MEMS) microphone and a MEMS accelerometer. The system further includes a cockpit voice recorder (CVR) and an active microphone. The active microphone and the vibration sensor each output signals to a signal processor including a subtractor configured to output, to the CVR, a signal that is a result of a subtraction of the signal from the vibration sensor from the signal from the active microphone.

The invention provides a thermal shock buffering device and an opening control method thereof, the thermal shock buffering device comprises two buffering devices, each buffering device comprises a hollow shell, a storage chip is clamped between the two shells, and the shells are formed through a blow molding process. The shell is made of other molding materials not limited to PP, PE, HDPE or PET, the cost of raw materials is reduced, and meanwhile the phenomenon that the whole device loses efficacy due to the fact that a pressure relief hole of the shell is blocked and other sealing performance problems exist is avoided. The shell is integrally formed through the blow molding process, the production process is simple, and the sealing performance of the shell is improved. The shell is integrally formed, the structure is simplified, the internal space of the phase change unit is increased, the volume of the phase change material is increased, and thermal performance is improved. After the phase change units of the two shells are assembled, a protection cavity is formed in the center, and the interior of the protection cavity is used for installing and protecting a core storage chip.

A data recording apparatus, data recording system and an orientation determination method thereof is disclosed. The data recording apparatus may include a housing, a wireless communication interface, one or more memories that store executable code; and one or more processors configured to execute the executable code, which causes the one or more processors to: control the communication interface to obtain data from Flight Data Acquisition Unit (FDAU) and store the obtained data in the one or more memories. The obtained data may include one or more of flight data, cockpit data (e.g., cockpit voice data), or cabin data (e.g., cabin voice data). The data recording apparatus may include a detachable attachment means for allowing the data recording apparatus to separate from the airplane in the event of a crash via a passive detachment means.

The present invention relates to a novel cloud-based server storage system for aircrafts' black box data. The cloud-based server is connected to the black box of aircrafts via a secure satellite communication channel for receiving black box data in real-time. The received black box data is securely stored in a memory module of the server along with identifying information including, but not limited to, aircraft tail number, flight number, timestamp, and more. In some embodiments, the system compares the black box data with baseline metrics for identifying distress conditions in the aircraft for enabling authorities to take quick corrective actions. In some embodiments, an alert is generated and transmitted to a cockpit and to authorities (i.e., air traffic control). The data is securely transmitted between the aircraft and the cloud-based server.

The present application relates to the field of avionics technology for civil aircraft, and in particular to an ejectable flight recording system. The ejectable flight recording system provided in the embodiment of the present application, the application stages of the ejectable flight recording system include the ADT stage and the PFLR stage; the ADT stage includes a processing component, the PFLR stage includes a detachable component, the detachable component includes an emergency positioning transmitter and an antenna, the antenna is connected to the emergency positioning transmitter, and the emergency positioning transmitter is connected to the data management memory and the processing component to realize position reporting and alarming in the ADT stage and the PFLR stage. The ejectable flight recording system provided in the present application uses one emergency positioning transmitter in the ADT stage and the PFLR stage. Such a setting can not only meet the system's requirements for advancing aircraft tracking and monitoring, but also realize the reuse, integration and weight reduction of the emergency positioning transmitter, further saving aircraft costs.

A method to record low-latency data in real-time with a single tread onto a storge medium is disclosed. The method includes instantiating, by a single thread of a scheduler of a real-time operating system executed by a hardware processor, a write command to write data from a data queue to a storage medium; determining, by the single thread, that the data is in the data queue; obtaining, by the single thread, the data from the data queue; and saving, by the single thread and the write command, the data that is obtained from the data queue to the storage medium as an output file.

A connector for connecting a sensor to a data recorder, the connector comprising: circuitry configured to receive a signal from the sensor and to transmit a digital signal to the data recorder; and a memory storing one or more of: sensor configuration data or sensor calibration data.

A data recording apparatus, data recording system and an orientation determination method thereof is disclosed. The data recording apparatus may include a housing, a wireless communication interface, one or more memories that store executable code; and one or more processors configured to execute the executable code, which causes the one or more processors to: control the communication interface to obtain data from Flight Data Acquisition Unit (FDAU) and store the obtained data in the one or more memories. The obtained data may include one or more of flight data, cockpit data (e.g., cockpit voice data), or cabin data (e.g., cabin voice data). The data recording apparatus may include a detachable attachment means for allowing the data recording apparatus to separate from the airplane in the event of a crash via a passive detachment means.

A flight recorder system of an aircraft includes a resource controller module (RCM) communicatively coupled, via a switch fabric, to a set of flight recorder system modules (FRM). Each FRM comprises a respective control module, a respective local memory, and a respective set of input and output (I / O) ports communicatively coupled to the switch fabric. The RCM is configured to detect a respective FRM coupled to the switch fabric, and based on the detection, configure an operation of the FRM, and wherein the respective local memory of the FRM is readable by the RCM, and shareable with the other FRMs via the switch fabric.

Embodiments of the disclosure provide for improving passenger assistance. In the context of a method, the method includes obtaining vehicle data associated with operation of a vehicle; determining the vehicle data satisfies one of a plurality of conditions stored in at least one data store, wherein: respective subsets of the plurality of conditions are associated with one of a plurality of categories comprising emergency, precaution, and entertainment; and causing at least one computing device in a passenger portion of the vehicle to output at least one predefined media element based at least in part on the condition satisfied by the vehicle data and one of the plurality of categories that is associated with the condition.

An improved D.C. power supply for an emergency locator transmitter ELT mounted on an aircraft that does not require lithium batteries but instead uses conventional alkaline batteries in conjunction with a supercapacitor network to provide a reliable power source even when the ELT that is airborne is subjected to extreme cold temperatures that can affect the alkaline battery operation. Alkaline battery pack with a 12 V output is connected to a supercapacitor network board. The supercapacitors are charged when the ELT is activated ON using the comparator network.

A flight data recording and analysis system for an aircraft (A) comprising integrated sensors (A1), the system comprising: an onboard unit (1) installed in the aircraft (A) containing independent sensors, separate from the integrated sensors (A1), and operating autonomously without connection to the integrated sensors (A1) of the aircraft (A); the onboard unit (1) comprising a connectivity module for transmitting flight data from the independent sensors to the ground, and an analysis module, remaining on the ground and equipped with receiving means, which receives the flight data transmitted by the connectivity module of the onboard unit (1); the analysis module comprising means for analyzing the received flight data. Abstract Figure: Figure 1

The present invention relates to a device and method for managing a cluster of information transmission devices that can be reversibly fixed to an aircraft turbine engine, comprising: associating (S02) a device in the device cluster with a turbine engine in the turbine engine cluster, fixing (S03) and obtaining (S04) at least one operating parameter of the turbine engine, generating (S04) at least one indicator, which allows the digital twin of the turbine engine to be updated based on the obtained operating parameter, and transmitting (S05) the indicator allowing the digital twin to be updated to an entity for storing the digital twin.

The invention relates to a method for backing up flight data and a method for generating a module for detecting an abnormal event used to trigger the backup. The method for generating a module (MDEA) for detecting anomalous events during a flight comprises the steps of:-obtaining (E10) data of a healthy flight; associating (E30) a threshold value (THi) for a subset of indicators (EIi) of a reference event occurring during the healthy flight so as to determine a partial opinion for the reference event based on the values of these indicators; configuring the module with a threshold (THi) and a decision model (LD) for determining an explicit opinion for the event of interest based on the partial opinions determined for the event of interest; the module is configured to generate a distress signal depending on an explicit opinion determined for an event occurring during flight.

Various systems may benefit from appropriate triggers to action. For example, various deployable safety devices, such as emergency locator transmitters and flight recorders, may benefit from a multiple input release mechanism. A method can include identifying the presence of at least one crash indicator. The method can also include performing an analysis of aircraft distress based on aircraft parameters other than the at least one crash indicator to provide an analysis result of aircraft distress. The method can further include triggering the release of a safety device contingent upon the presence of the at least one crash indicator being accompanied by a positive result of aircraft distress.

Disclosed herein are methods, devices, and systems for facilitating pilots in determining current and predicted performance specifications of their aircraft. According to one embodiment, a method is implemented on a mobile computing device. The method includes receiving static pilot data, receiving static aircraft data associated with an aircraft, receiving dynamic aircraft data over a time period, determining aircraft performance data based on the static aircraft data and the dynamic aircraft data, providing the aircraft performance data to a graphical user interface (GUI) associated with the mobile computing device, and storing the static pilot data and the aircraft performance data.

An avionics system (102) can provide data to a first receiving component (117) associated with a proprietary first protocol (109) and a second receiving component (116) associated with a non-proprietary second protocol (111). A configuration tool (108) generates a first configuration file (106) comprising instructions for a data access component (104) to provide a first data output to the first receiving component (117), and a second data output to the second receiving component (116). The configuration tool (108) can generate a second configuration file (120) including instructions to convert the second data output. The data access component (104) can receive a definition database (107) defining the first protocol (109) to convert the data according to the non-proprietary second protocol (111). The data access component (104) can provide the requested data to the first and second receiving components (117), (116) in accordance with the non-proprietary second protocol (111). The second receiving component (116) is configured convert the data received based on the second configuration file (120).

Methods for backing up flight data and generating an abnormal event detection module used to trigger said backup. This method, a module (MDEA) for detecting an abnormal event during a flight, comprises the following steps: - obtaining (E10) data from healthy flights; - associating (E30), for subsets (EIi) of reference event indicators produced during healthy flights, thresholds (THi) allowing the determination of partial opinions on said reference event from the values ​​of these indicators; - configuring said module with said thresholds (THi) and with a decision model (LD) allowing the determination of a definitive opinion on an event of interest from partial opinions determined for this event of interest; - said module being configured to generate a distress signal based on said definitive opinion determined for an event produced during a flight. Fig. 9

Provided is an aerial vehicle including an emergency control device through power regulation. The aerial vehicle includes a power unit configured to supply power for the aerial vehicle, a flight control device configured to receive a wireless control signal from control terminal, and control a movement of the aerial vehicle based on the received control signal, and a power regulation device arranged between the power unit and the flight control device and configured to transmit the power from the power unit to the flight control device, wherein the power regulation device includes a communication unit configured to externally receive an emergency control signal through certain radio waves, a verification unit configured to verify whether the received emergency control signal is given according to a predetermined authority, and a power regulation unit configured to cut off the power supplied from the power unit to the flight control device by activating a power regulation function of the power regulation device, only when the emergency control signal is verified to be given according to the predetermined authority.

A CVFDR system of an aircraft includes a cockpit voice and flight data recorder (CVFDR) communicatively coupled, via a data communication network, to a set of flight recorder modules. The CVFDR receives a first voltage from a remote first power source. In the event of an interruption of the first voltage, the CVFDR receives a second voltage from a local second power source for a predetermined period.

A deployable emergency transmitter device is configured to be launched from an aircraft in an initial passive flight state. It comprise an internal chassis, and an inertial mass member, rotatable relative to the internal chassis, for stabilising flight during the initial passive flight state. It has a powered drive system, mounted to the internal chassis and configured for providing lift while the deployable emergency transmitter device is in an active flight state. It has a radio transmitter configured for transmitting an emergency signal after being launched from the aircraft. The device is configured to transition from the initial passive flight state to the active flight state, after being launched from the aircraft.

A flight recorder system of an aircraft includes a cockpit voice and flight data recorder communicatively coupled, via a data communication network, to a first flight recorder module (FRM). The first FRM includes a first sensor configured to generate a first analog signal, a first controller, and a first analog to digital converter (ADC) configured to sample the analog signal based on a received master clock signal and to convert the first analog signal to a first digital data signal.

Aircraft-mounted data recorder, aircraft, recording method, and associated computer program. The present invention relates to a data recorder (12) (D) suitable for installation on board an aircraft (10), the recorder (12) comprising: an acquisition module configured to acquire a set of recording parameter(s), a detection module configured to detect at least one event of interest related to the aircraft (10), via at least one model of the aircraft, a recording module configured to record data (D) received by the recorder into a storage memory according to the set of recording parameter(s), the recording module being connected to the acquisition module and the detection module, the detection module being configured to modify the set of recording parameter(s) according to the at least one detected event of interest. Figure for the abstract: Figure 1

The invention relates to the technical field of the aerospace industry, in particular to a flight parameter recorder, a card reader module is installed in a shell module, a video card module is inserted into one side of the card reader module, the card reader module comprises a card inserting assembly, a card reading assembly and a transmission and induction assembly, and the card reading assembly is connected with the video card module. A transmission and induction assembly is installed on the surface of the card insertion assembly. According to the invention, the complex processing technology of the flight parameter recorder is solved, and the defects of the existing technology in the aspects of efficiency, cost, precision, material utilization rate, environmental protection and the like are overcome; the complex technological process is simplified, the production efficiency is improved, the cost is reduced, the product quality is improved, and the increasingly complex and diversified requirements in the modern industrial field are better met; meanwhile, the functions of high-strength impact resistance, high-temperature resistance, fire resistance, water resistance, corrosion resistance and the like are achieved; and through the modular design, disassembly and data reading are convenient, wind resistance can be reduced, and the damage probability is reduced when the aircraft is disassembled.

Various systems may benefit from appropriate triggers to action. For example, various deployable safety devices, such as emergency locator transmitters and flight recorders, may benefit from a multiple input release mechanism. A method can include identifying the presence of at least one crash indicator. The method can also include performing an analysis of aircraft distress based on aircraft parameters other than the at least one crash indicator to provide an analysis result of aircraft distress. The method can further include triggering the release of a safety device contingent upon the presence of the at least one crash indicator being accompanied by a positive result of aircraft distress.