23 results about "Line-replaceable unit" patented technology

A drive system for an aircraft. The drive system includes a controller, a motor coupled to an H-bridge network, a DC link that can be coupled to the motor; and an electrical braking system configured to be electrically coupled to the motor. The electrical braking system includes: a sense circuit configured to sense a condition of the DC link; a brake resistor coupled to the DC link; a temperature sensor; a drive circuit coupled to the sense circuit; and a coil for breaking in an inductive braking mode or generating heat in a cold start mode, wherein the coil is located in or near a line replaceable unit chassis that includes printed circuit boards.

A line replaceable unit (LRU) includes a data communication interface configured to receive identification (ID) data from an aircraft communication bus, an aircraft systems interface configured to receive aircraft systems data corresponding to an operation of at least one aircraft system, and an LRU data interface configured to receive LRU data corresponding to the LRU. The LRU further includes a processor and a memory unit. The processor processes the aircraft systems data and the LRU data and determine at least one data category. The memory unit includes a plurality of data partitions. The processor is configured to generate at least one configuration data package by combining the ID data with one or both of the aircraft systems data and the LRU data, and to store the configuration data package in a given data partition based on the data category.

A system includes avionics line-replaceable units (LRUs); a mission manager including application programming interfaces (API); a processing device; and a memory storing one or more machine readable instructions causing the system to: communicatively couple the mission manager to external avionics services via a data gateway to receive updated mission conditions at the mission manager; register one of the avionics LRUs with one of the mission manager APIs; receive, at the mission manager, updated mission conditions from the external avionics services via the data gateway; provide one or more of the one or more updated mission conditions to the registered avionics LRU based on one or more of an updated mission plan and an unexpected update to the mission condition; and control one or more aircraft systems based on one or more of the updated mission plan and the unexpected update to the mission condition.

The invention discloses an intelligent fault diagnosis device and method with BIT capability, and the method comprises the steps: enabling one or more tested devices to be connected to the intelligent fault diagnosis device, and enabling the one or more tested devices to be a field replaceable unit (LRU); a plurality of sensors are arranged at internal and external interfaces of each LRU, and collected data are transmitted to a central processing unit; analyzing the collected data by adopting a self-adaptive algorithm, and outputting a fault risk score A of the current system state; based on the fault risk score A, parameters of a fault prediction model lambda (t) are adjusted; and based on the fault risk score A and the fault prediction model lambda (t), obtaining an overall fault diagnosis index FD, and generating a fault diagnosis report. According to the invention, the fault diagnosis accuracy can be improved, the fault prediction capability can be enhanced, complex working conditions can be adapted, the maintenance cost and downtime can be reduced, and a real-time monitoring and feedback mechanism, expandability and compatibility and data-driven intelligent decision support can be realized.

A simulator box for troubleshooting or testing an aircraft oxygen system and associated system and method are disclosed. The simulator box includes a connection port configured to be removably connectable to a transmission line of an oxygen line replaceable unit (LRU). The simulator box also includes a controller configured to mimic functionality of the oxygen LRU. The simulator box further includes a controller area network (CANBUS) configured to facilitate communication between the controller and the transmission line. Additionally, the simulator box includes a plurality of selectively-activatable indicia. Each one of the plurality of selectively-activatable indicia corresponds to one of a plurality of power characteristics. The plurality of selectively-activatable indicia are configured to generate an indicia when a corresponding one of the plurality of power characteristics is receiving a signal from the transmission line.

A modular VTOL drone aircraft can include a primary processor, a plurality of propellers, one or more line replacement modules (“LRMs”) and one or more line replacement units (“LRUs”). LRMs can include a fuselage, a center wing, two booms, two outer wings, two vertical tails, a horizontal tail, and / or an engine. LRUs can include an avionics module, a radio communications assembly, a sensor package assembly, an ISR assembly, and / or a deployable payload assembly. Each LRM and LRU can be self-contained and removably attached to the remainder of the VTOL drone. Each LRM can be readily interchanged with another similar LRM, which can be of a different size. LRM interfaces can include a blind mate electric connector and / or a floating connector.

A motor has a housing which comprises a cavity and a socket accessible from outside the housing. The socket has an interior surface. The motor includes a LRU sensor system which comprises an LRU sensor having electrical conductors and internal sensor wiring that is electrically connected to the electrical conductors and electrical conductors on the interior surface of the socket, wherein when the LRU sensor is positioned in the socket, the electrical conductors on the LRU sensor contact the electrical conductors on the interior surface of the socket.

A circuit for detecting discrete inputs includes a first line replaceable unit, LRU (104). A second LRU (102) includes an LRU circuit that includes a power source (106), a diode set (108) coupled to the power source (106), a resistor (R3) connecting from a node Vc between the diode set (108) and the first LRU (104) to ground, and a logic detection and processing circuit (110). The logic detection and processing circuit (110) is operably connected to the diode set (108), and is configured to detect a state of the first LRU (104) based on a detected voltage. The detected voltage is either open, or 28-Volts.

The present disclosure relates to apparatuses, methods, and aircraft for line replaceable units. The apparatus includes a housing, a first interface on a first side of the housing, a second interface on a second side of the housing opposite the first side, and circuitry within the housing. The first interface is configured to couple to a multi-mode receiver (MMR) rack. The second interface is configured to couple to an MMR external to the housing. The circuitry is configured to receive, via the first interface, digital data representative of a navigation signal received at an antenna. The circuitry is configured to perform time, space, and frequency filtering operations using the digital data to generate modified digital data. The circuitry is configured to output, via the second interface, a modified analog navigation signal to the MMR based on the modified digital data.

Embodiments of the disclosure provide for importing and transforming interface control document (ICD) data. In the context of a method, the method includes obtaining a first ICD protocol specification and a second ICD protocol specification, wherein a respective ICD protocol specification comprises a plurality of protocol parameters for intercommunication between a plurality of line replaceable units (LRUs) of a vehicle; generating a first set of parameter definitions based on the first ICD protocol specification; generating a second set of parameter definitions based on the second ICD protocol specification; and generating at least one cross-relational data representation of the first ICD protocol specification and the second ICD protocol specification based on the first set of parameter definitions and the second set of parameter definitions. The method may further include generating transformed ICD data in accordance with the second ICD protocol specification based on input ICD data and the cross-relational data representation.

A circuit for detecting discrete inputs includes a first line replaceable unit (LRU). A second LRU includes an LRU circuit that includes a power source, a diode set coupled to the power source, a resistor R3 connecting from a node Vc between the diode set and the first LRU to ground, and a logic detection and processing circuit. The logic detection and processing circuit is operably connected to the diode set, and is configured to detect a state of the first LRU based on a detected voltage. The detected voltage is either open, or 28-Volts.

To eliminate drawbacks associated with the design and re-design of line replaceable units (LRUs) having a built-in transceiver.SOLUTION: A pluggable active optical connector (14) is modular with one or more channels and converts electrical signals to optical signals and vice versa. On one side, the apparatus has a pluggable electrical interface (16) to a line replaceable unit (LRU) (10a); and, on the other side, the apparatus has a pluggable optical interface (18) to an aircraft fiber optic wiring bundle (20a, 20b). The apparatus is pluggable to different types of LRUs, including rack-mounted and bolted-down LRUs. The apparatus includes electronic and optical communication components sufficient to enable electrical / optical conversion totally within a standard-sized aircraft connector. The apparatus is adaptable to various data communication protocols and has the flexibility to be used in both single-fiber and dual-fiber bidirectional data links.SELECTED DRAWING: Figure 2

A method for performing dataload protocol operation testing in an avionics Line Replaceable UNIT (LRU) is disclosed. In some embodiments, the method includes sending a request to initiate transfer of a dataload sequence from an external data loader to a target hardware. The method further includes receiving an acceptance status from the target hardware to initiate transfer of the dataload sequence based on at least one of the valid or invalid dataload sequence request or response. The method further includes determining, based on the invalid dataload sequence request or response, occurrence of one or more failure scenarios associated with at least one of: the transmission of the dataload sequence; and the receiving of the acceptance status from the target hardware on different stages of dataload operation.

The present invention is entitled "System and method for automatically creating aircraft maintenance records through aircraft data". The present invention discloses a method implemented by a processor, which is used to automatically create aircraft maintenance records and work logs during aircraft maintenance operations. The method includes: using a processor to retrieve fault data, test data, maintenance data and status data about line replaceable units (LRUs) on the aircraft via a central maintenance computer (CMC) on the aircraft; automatically collecting data about maintenance operations performed using the remote terminal from a remote terminal on the aircraft; automatically recording the fault data, test data, maintenance data, status data and data about maintenance operations performed using the remote terminal in a maintenance database by the processor; and automatically filling in information in multiple fields in the maintenance work log using the data in the maintenance database by the processor.

A system is disclosed for thermal coupling and fastening of circuit card assemblies of line-replaceable units (LRUs). The LRU may include a chassis configured to house one or more circuit card assemblies. The chassis may include external coupling features configured to receive fasteners. The circuit card assembly may include a heat sink with corresponding coupling features configured to align with the external coupling features and to receive the fasteners. The chassis may include a mateable surface. The circuit card assembly may include a corresponding mateable surface configured to mate to and thermally couple with the mateable surface of the chassis. The chassis may include an electrically conducting surface and the circuit card assembly may include a corresponding electrically conducting surface.

A latch assembly for securing a passenger seat tray table including a spring-loaded sliding latch and a spring-loaded rotating catch. The spring-loaded latch interacts with the spring-loaded catch such that, when the spring-loaded latch is closed, the tab engages the spring-loaded catch to prevent the spring-loaded catch from pivoting open. The spring-loaded catch interacts with the spring-loaded latch such that, when the spring-loaded catch is open, the tab engages the spring-loaded catch to prevent the spring-loaded latch from sliding closed. The latch assembly operates by push-to-close and the latch resets automatically when the tray table is secured. The latch assembly may be a line replaceable unit, part of a tray table assembly, and part of an aircraft passenger seat assembly.

An energy management system (EMS) for an aircraft is provided. The aircraft may have one of a plurality of propulsion systems such as a parallel hybrid electric propulsion system, a parallel turbo electric propulsion system, an electric propulsion system, a turbo electric propulsion system and a turbo hybrid electric propulsion system. The EMS comprises redundant control paths for controlling safety critical operation. Each redundant control path is configured to independently determine whether to electrically isolate a line replaceable unit (LRU) from a high voltage DC link (HVDC link) based on status information from the LRU. The isolation is based on the independent determination. The HVDC link is used for propulsion. The number of the redundant control paths and components may be depending on the type of the propulsion system.

A line-replaceable device configured for installation in a docking station comprising: - at least one first operational connector configured for connection to a second operational connector of the docking station in order to exchange operational data during nominal operation of the device, - at least one first detection connector configured for connection to a second detection connector of the docking station in order to exchange detection data before nominal operation of the device, - at least one first detection module coupled to the first detection connector and configured to determine an installation position of the device in the station from detection data exchanged with a second detection module of the station, via the first and second detection connectors.

A power supply system for use in an airplane is described. The power supply system includes N alternating current (AC) power outlets configured to provide AC power output at a passenger seat in an airplane, M direct current (DC) power outlets configured to provide DC power output at the passenger seat and a controller configured to control allocation of power from a power supply to the N AC power outlets and M DC power outlet according to a phase of a plurality of phases of operation of the power supply system, where N and M are positive integers.

The invention provides a reusable eVTOL electric propulsion system safety modeling method, and belongs to the technical field of aviation simulation, and the method comprises the steps: defining an electrical interface and a signal interface according to a cross-linking interface between an electric propulsion system and other systems, and defining basic information of the electrical interface and the signal interface; modeling products related to the electric propulsion system; establishing an equivalent function module of each product according to the mechanism of the product; for each product, if a workshop replaceable unit (SRU) hierarchy fault exists in the product, a fault tree module is established in an equivalent function module of the product, a top event of the fault tree module is a route replaceable unit (LRU) hierarchy event, and a basic event is an SRU hierarchy event; and an LRU-level fault simulation module is established, and product interface modeling is carried out. The method provided by the invention can be adapted to different eVTOL models with similar architectures, the design efficiency is improved, and the research and development risk is reduced.

An energy management system (EMS) for an aircraft is provided. The aircraft may have one of a variety of propulsion systems, such as a parallel hybrid electric propulsion system, a parallel turbine electric propulsion system, an electric propulsion system, a turbine electric propulsion system, and a turbine hybrid electric propulsion system. The EMS includes redundant control paths for controlling safety critical operations. Each redundant control path is configured to independently determine whether to electrically isolate a line replaceable unit (LRU) from a high voltage direct current link (HVDC link) based on state information from the LRU. The isolation is based on an independent determination. The HVDC link is used for propulsion. The number of redundant control paths and components may depend on the type of propulsion system.

A drive system for an aircraft. The drive system includes a controller, a motor coupled to an H-bridge network, a DC link that can be coupled to the motor; and an electrical braking system (100) configured to be electrically coupled to the motor. The electrical braking system includes: a sense circuit configured to sense a condition of the DC link; a brake resistor coupled to the DC link; a temperature sensor; a drive circuit coupled to the sense circuit; and a coil for breaking in an inductive braking mode or generating heat in a cold start mode, wherein the coil is located in or near a line replaceable unit chassis that includes printed circuit boards.

A method, apparatus, system, and computer program product for managing a platform. Sensor information for a platform health of the platform is received from a sensor system for the platform. The sensor information for the platform health of the platform is sent by a computer system into a machine learning model trained using historical sensor information indicating a historical platform health and historical context information corresponding to the historical sensor information in which the historical context information is for a set of operating conditions. A remaining useful life of a component in the platform is received by the computer system from the machine learning model.