136 results about "Airborne Networking" patented technology

An airborne network system (ANS) on a member aircraft receives incoming geo-referenced atmospheric data regarding atmospheric conditions from other member aircraft and can re-transmit the data to other members. An air data system senses local pressure and temperature conditions. A navigation system calculates geo-referenced aircraft position. An inertial data system senses member aircraft attitude, angular rates and accelerations. A data processing system (DPS) generates the member aircraft's perspective of the atmospheric conditions, based on input data from the above-mentioned systems. Network directed DPS output atmospheric data is provided to the ANS to be transmitted to other airborne network systems positioned on other member aircraft. An airborne display system is adapted to receive crew directed DPS output atmospheric data and in response thereto display desired atmospheric forecast conditions. An airborne caution / advisory system receives the crew directed DPS output atmospheric data and alerts the pilot(s) of hazardous flight conditions.

A weather data aggregation and display system for displaying weather radar information to a pilot of a member aircraft of an airborne network of member aircraft. The weather data aggregation and display system includes an airborne network system (ANS) positioned on the member aircraft adapted to receive incoming geo-referenced weather data regarding Significant Meteorological Systems (SMS) from associated airborne network systems positioned on other member aircraft. A data processing system (DPS) is coupled to the airborne network system for generating the member aircraft's perspective of the SMS, based on the incoming weather data and the member aircraft's navigation and attitude information. The DPS provides DPS output weather data. An airborne display system (ADS) is positioned on the member aircraft and coupled to the data processing system. The airborne display system is adapted to receive the DPS output weather data and in response thereto display desired weather imagery of the Significant Meteorological Systems. The ANS is adapted to re-transmit the incoming geo-referenced weather data to associated airborne network systems positioned on other member aircraft.

A digital airborne situational awareness system and method. The system is installed on multiple aircraft to generate an airborne network providing collision avoidance without ground control. A global positioning system (GPS) receiver unit is coupled to a microprocessor in each aircraft equipped with the system. A software engine receives the raw GPS data and determines location, speed, flight path direction, and altitude. The software engine conditions the GPS data for display on a cockpit display panel. The conditioned data orients the display with the heading, speed, and altitude data of the host system aircraft. A transceiver section provides data transmission to other airborne receiving units within the approximately forty mile range of the airborne network. The transceiver transmits data packets including reconditioned location (track), altitude, and an aircraft class identifier to other aircraft in the network. The transceiver receives data from other airborne vehicles equipped with the system within the network range. Once the computations of positional data for other aircraft are performed, the positional data is sent to the display processing section for appropriate cockpit display. The software engine develops a set of projections that are compared to the relative speed, flight path direction and altitude of the all other units in the airborne network. These projections determine the threat levels of converging flight paths with limits that provide warning data to the pilot of any pending flight path conflict situation.

The invention provides an advanced integrated aviation electric simulation system and a simulation method thereof. An integrated radio frequency system simulator, an integrated photoelectric system simulator, an integrated aerocraft management system simulator, and an external stores system simulator of the system simulate operation process of airborne equipment and generate stimulus information of the system; and aviation electric uniform network simulator of the system is responsible for the information flow of a transmission system, an integrated core process simulator is used for realizing the integration of received data and the calculation of received tasks, and a cockpit simulator is used for realizing the integrated display of the status of an aircraft, receiving a control direction from a pilot and monitoring display equipment to display the simulation process in the form of an image. The operation process of an aviation electric system is simulated by organically integrating the sub-systems, and quantitative simulation analysis of the aviation electric system is further completed. The method can simulate different airborne network topological structures, thereby having very good universality.

This invention relates to an Open Wireless Architecture (OWA) unified airborne and terrestrial communications architecture providing optimal high-speed connections with open radio transmission technologies (RTTs) between aircrafts and ground cells, and between different aircrafts in Ad-Hoc or Mesh network group, to construct the multi-dimensional unified information delivery platform across the airborne networks and the terrestrial networks wherein the same OWA mobile device or OWA mobile computer can be used seamlessly and continuously both in the aircrafts and on the ground.

The invention discloses an on-board network system and a backbone node message processing method thereof. In the system, a mixed layered network structure of combining a ratio Mesh backbone network and a heterogeneous access network is adopted, and the interconnection of various access networks is realized through an on-board backbone network, thereby the flexibility and the expandability of the system are improved. Meanwhile, a backbone node message processing method is adopted in the comprehensive message processing system of backbone network nodes. The method realizes the transformation of heterogeneous messages between a core network and an edge network, and a publishment / subscription mechanism based information distribution service is adopted, thereby the resource utilization ratio and the information access efficiency in complicated network environment are improved. The invention has military and civil values and particularly has wide application prospects in the fields of airborne command collaborative constellation of military integration information grids, civil aviation networked communication, navigation, monitoring, and the like.

An on-board network system is presented. The on-board network system sends a sleep-entered message to a communication bus. The sleep-entered message is sent under a condition that a sleep condition is satisfied on a basis that a network management (NM) message is ceased during state transition process in which node's state transfers from a normal state to a power-saving state. A monitoring ECU corresponding to a master performs an abnormality detection process. In the abnormality detection process, the monitoring ECU detects an abnormality state of the state transition process based on whether or not the sleep-entered message is sent from any one of nodes, thereby it is possible to detect the abnormality state not only during each node is a normal state but also during a bus-sleep state.

The invention discloses a satellite based one-to-many data transmission system, and method. According to the bandwidth of data generated by each task load and the number of corresponding receiving points, a network protocol is selected for the data generated by each task load, and the network data of the task load is packaged according to the selected network protocol and is sent to an assigned network interface of an airborne network switch; large bandwidth data is transmitted through a user datagram protocol (UDP) multicast protocol, and small bandwidth data is transmitted through a transmission control protocol / internet protocol (TCP / IP) or UDP point-to-point dissemination protocol; and when the UDP multicast protocol data and point-to-point dissemination protocol data coexist, virtual local area network (VLAN) division is performed. Due to use of the virtual network and flexible selection of the network protocol, a plurality of data receiving ends can receive signals, and data occupied bandwidth is reduced when air-ground communications is carried out in data generation ends like an unmanned plane and so on by use of a satellite communications link.

The invention relates to an architecture of a propulsion system of a multi-engine helicopter, comprising turboshaft engines (1, 2) that are connected to a power transmission gearbox (3), and comprising a low DC voltage onboard network (7) for supplying helicopter equipment during flight, characterised in that it comprises: a hybrid turboshaft engine (1) that is capable of operating in at least one standby mode during a stable flight of the helicopter; an electrotechnical pack (20) for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a mode in which it provides mechanical power, said restart pack (20) being connected to said onboard network (7); and at least two sources (4, 16, 18) of electrical power for said onboard network (7).

The invention discloses an airborne collision avoidance and ground proximity warning monitoring system which comprises a set of four-channel L band antennas and a system host machine. The system host machine is formed by a data processing module, an RF module, a baseband module, and a power module. The four-channel L band antennas are connected with the RF module through coaxial cables. The RF module is connected with the data processing module through the baseband module. The system host machine obtains aircraft body state information through the connection of an avionics full duplex switched Ethernet (AFDX) or a self-bring interface unit. The system has the advantages that the most reasonable monitoring and alarm information and avoidance advice are provided for a pilot, the working pressure of a pilot is reduced, an man-made error determination is avoided, and the flying safety of an airplane is increased; the reuse of resources is realized, the weight, volume, power consumption and cost of airplane monitoring equipment are reduced, and the reliability and scalability of the equipment are improved.

A data message decoder for high-speed serial bus applications includes a sync pattern decoder that is operated in parallel and simultaneously with a message bit decoder. By operating the sync pattern decoder and the message bit decoder in parallel and simultaneously a true sync pattern following a valid looking sync pattern may be identified and the decoding of the bit message following the valid looking sync pattern may be aborted once the true sync pattern is detected. The data message decoder is robust and tolerant of bus anomalies that are typical when using high frequency signaling on a multipoint serial bus. The robust data message decoder is suitable for, but not limited to, applications in the aerospace industry, such as onboard network systems for advanced commercial and military aircraft.

A telephone system apparatus and method adapted for use on an aircraft seatback which provides an electrical connection point (i.e., jack) formed on a housing of the telephone system. The connection point permits coupling of a user's laptop computer to an on-board network, while the housing also provides the electrical connection point for a telephone handset. In one embodiment a pair of additional electrical connection points are provided for allowing more than one individual to couple his / her laptop computer to phone system, and thus gain access to the network. The telephone system eliminates the need to attach independent jacks at various locations on the seats and efficiently uses the housing of the telephone system for this purpose.

The invention provides a method for controlling multi-stage access to avionic data by a civil onboard network service system. The avionic system data can be prevented from being illegally accessed by application software from the onboard network service system, and therefore the safety of an avionic system is guaranteed. The method for controlling the multi-stage access comprises an application authorization process, an application operation request process and an avionic data authentication process, and the application authorization process and the avionic data authentication process are independent execution processes. The complete execution of the application operation request process comprises the two premises that 1), the application providing an operation application acquires access authorization, that is, the application passes through the application authorization process, and correct authorization proof can be provided in the operation application process; 2), operation data meet the authentication rules of the avionic data, and data authentication can succeed in the avionic data authentication process. The method has the advantages of being high in safety, strong in practicality and low in coupling performance.

The invention discloses an airborne networking radar radiation parameter joint optimization method based on radio frequency stealth, which belongs to the technical field of radar signal processing. For an airborne networking radar system composed of a plurality of airborne radar transmitters and a plurality of airborne receivers, the airborne networking radar radiation parameter joint optimizationmethod is characterized by acquiring a target RCS and a distance from the target RCS to each receiver relative to each radar transmitter, regarding minimization of an airborne networking radar radiofrequency stealth performance characteristic index as a target, regarding target tracking errors, detection performance and radar radiation parameters as constraint conditions, establishing an airborne networking radar radiation parameter optimization model based on radio frequency stealth, performing joint optimization on radiation parameters such as selection, sampling interval, dwell time and transmission power of the radar transmitters, and effectively improving the radio frequency stealth performance of the airborne networking radar system in a target tracking mode by means of the optimalradar radiation parameters obtained by utilizing the model established according to the method under the condition of satisfying certain target tracking precision and target detection performance.

This invention relates to an Open Wireless Architecture (OWA) unified airborne and terrestrial communications architecture providing optimal high-speed connections with open radio transmission technologies (RTTs) between aircrafts and ground cells, and between different aircrafts in Ad-Hoc or Mesh network group, to construct the multi-dimensional unified information delivery platform across the airborne networks and the terrestrial networks wherein the same OWA mobile device or OWA mobile computer can be used seamlessly and continuously both in the aircrafts and on the ground.

The invention discloses an onboard network entertainment system. The system comprises a server assembly, a management control assembly, an external communication assembly, an internal communication assembly and a seat entertainment terminal; the server assembly is connected with the internal communication assembly and is connected with the seat entertainment terminal through a wireless signal; the server assembly communicates with a satellite through the external communication assembly so as to achieve the connection of the onboard network entertainment system and the internet; the management control assembly is used for monitoring the flight state of an airplane so as to control the operation state of the onboard network entertainment system; a user can play with other players in the same cabin or players in the internet through the seat entertainment terminal.

The invention generally pertains to onboard systems for passengers such as In-Flight Entertainment (IFE) Systems. The invention more particularly relates to a system and a method for accessing a personal computer device onboard an aircraft and to an aircraft including such a system. The system includes an onboard network to which is connected at least one interface at a passenger's seat, connection means for connecting said personal computer device to the onboard network, and the system is arranged so that said interface and said personal computer device interact via the transmission of data on said onboard network.

The invention discloses a method for constructing a dynamic relevant fault management system of an airborne network, and belongs to the technical field of electronic information. The method comprises the following steps: firstly, for a static physical structure of an airborne network system in a certain comprehensive test, constructing a product tree and a topological graph for a texted structure part; then, for a dynamic test process of the airborne network system in the comprehensive test, constructing a test item tree for the texted structure part; establishing a data model RI of the fault management system according to the product tree, the topological graph and the test item tree; then, for arbitrary two fault cases fi and fj in the data model RI, judging and determining the dynamic association information between the two fault cases fi and fj; and finally performing brightness display and storage on the topological graph. By adoption of the method disclosed by the invention, reference is provided for engineering technicians to intuitively discover weak links causing relevant faults easily and belonging business logic paths in the design and troubleshooting of avionics systems, and reference is also provided for purposeful reinforcement and improvement of the system.

Methods and systems for communicating data between an aircraft and an off-board network are provided. The method includes pre-loading data for the aircraft onto a secure power unit, communicatively coupling the aircraft to the secure power unit, validating the aircraft at the secure power unit based on air traffic management information, absolute (GMT) time, and aircraft location data, and transferring data between the aircraft and the secure power unit based on the validation.

The present invention relates to an airborne WIFI system architecture. The airborne WIFI system architecture is designed to allow users in an aircraft cabin to access a WIFI network on the aircraft by using a mobile terminal to enjoy services such as audio and video, games, news and internet. The airborne WIFI system architecture comprises an airborne router, an airborne network server, a cabin access point, a WIFI antenna and a 3G / 4G antenna. The airborne router is connected with the 3G / 4G antenna by using a radio frequency cable and can access a 3G / 4G network of a base station of a nearby operator so as to communicate with a ground operation center. The airborne network server is connected with the airborne router by using the Ethernet and is connected with the cabin access point by using the Ethernet. The cabin access point is connected with the WIFI antenna by using the radio frequency cable. A first control switch and two relays are arranged between the airborne router and a power supply system. One relay receives a turn-on signal of an aircraft anti-collision lamp, and the other relay receives a turn-off signal of an aircraft cabin door. A second control switch is arranged between the cabin access point and the power supply system and is used for controlling on and off of power supply of the cabin access point.

The invention relates to a method and a system for integration of portable devices with flight deck displays. The method for integration of a portable electronic device (PED) with a flight deck display in some embodiments includes providing an onboard network coupled to a flight-deck-installed, multi-function display and coupling the PED to the onboard network. The method may also include receiving information from a PED hosted application in the PED, routing information through a gateway and / or a plurality of firewalls, and displaying information on the flight-deck-installed, multi-function display. In some embodiments, a pilot control interface is coupled to the PED through the onboard network, and a plurality of functions on the PED is controlled via the pilot control interface. An airplane in some embodiments includes a fuselage portion, a wing portion, and a system that carries out the method, possibly through use of computer readable storage medium with stored instructions.

The invention relates to the field of communication technology, and particularly relates to a method and system for synchronizing multi-link switching with a gateway based on air-ground communication. The method comprises the following steps: enabling an airborne communication server to switch a communication link with a ground network system; enabling the airborne communication server to send link switching information to the ground network system; and changing an air gateway of the ground network system according to the link switching information parsed by the ground network system. According to the method and system disclosed by the invention, the synchronization between the airborne network to ground gateway and the ground to air gateway can be realized, and the phenomenon that the same communication link is always used in two-way communication can be ensured; and compared with the prior art, the communication link used by a ground network is almost synchronously consistent with the communication link of an engine room network, and thus the two-way communication between an airborne network and the ground network can be implemented.

The invention discloses a data transmission method and equipment. The data is encapsulated as a data frame according to a specific frame format so as to be transmitted, wherein the specific format comprises a constant field, a message control field, a source address, a destination address, a destination port field, a data frame character field, a command character field, and check field. Compared with three onboard network interconnection bus standards in the prior art, the data transmission method based on the specific frame format disclosed by the invention improves the bus effective bandwidth and lowers the delay time of the single command since the effective packet header length is greatly reduced.

The invention provides a time-triggered Ethernet fault diagnosis method based on time synchronization state monitoring, and belongs to the field of airborne network communication technology, which is characterized in that a fault state is diagnosed by using a time deviation among communication nodes as a judgment condition in combination with a global unified time reference established by the time-triggered Ethernet. All end nodes and switches send local time reference information to adjacent switches, the switches correct and compare the received time reference information, judge the operation states of the adjacent nodes through the magnitude of the time deviation and feed back judgment results to the corresponding end nodes or switches. In the process, the physic communication links between adjacent devices, data sending and receiving modules of the both parties and communication software can be verified, the time-triggered Ethernet fault diagnosis method has the advantages of being simple and practical, easy to realize and high in reliability, and can be used for solving the problem that the existing dual redundancy communication system cannot effectively judge the fault at the same time.

The object of the present invention is to provide an over-the-horizon communication system comprising at least two end nodes, the end nodes being configured to receive and transmit communication signals, and providing communication between the at least two end nodes. The system further comprises at least two, in the troposphere and / or stratosphere airborne, network extension nodes that are communicatively connected to the end nodes and wherein the end nodes are arranged for bidirectional or uni-directional communication with the network extension nodes and the network extension nodes are arranged for bidirectional or uni-directional communication between the individual network extension nodes and bidirectional or unidirectional communication with the end nodes.

The invention belongs to airborne network communication technologies, and relates to an improved method for a traditional GJB289A bus communication management and scheduling strategy. The invention relates to a method for increasing transmission processing and scheduling of emergent events and messages on the basis of the traditional GJB289A bus communication management. The enhanced GJB289A bus communication management and scheduling method has the following advantages: bus load real-time dynamic regulation, which means that the realization of bus load real-time dynamic regulation is providedwith basis through real-time management and control of the emergent messages; reduction of transmission delay and jitter, which means that the transmission delay and the accumulation jitter can be effectively reduced through real-time and dynamic adjustment of bus load; guarantee of consistency of a split data transfer sequence, which means that the consistency of the data sending and receiving sequence can be guaranteed for split transmission of big data; and flexibility and high effectiveness, which means that an effective processing mechanism can be provided for application layer softwareto process the emergent events.

The invention belongs to the technology of airborne network test, and discloses an AFDX (Avionics Full Duplex Switched Ethernet) photoelectric conversion time delay test method. According to the method, an AFDX end system is used as a test apparatus, the test of AFDX photoelectric conversion time delay is converted into a test of time delay between transmitting an enable signal TX_EN and receiving a useful signal RF_DV by the AFDX end system, test of photoelectric conversion time delay of ns grade is realized, and consequently, high-precision test of the AFDX photoelectric conversion time delay is realized.