62 results about "Airborne collision avoidance system" patented technology

A multi-dimensional mechanic operating collision avoidance method suitable for an airborne collision avoidance system belongs to the field of air traffic safety technology, and comprises the following steps: monitoring and tracking a native and a target airplane; adopting a protection area model based on a surrounding body to conduct flight conflict detection; adopting a real-time collision detection method to conduct collision threat detection; using a four-dimensional space-time mechanic operating collision avoidance model to calculate and evaluate the manner and the strength of a release advise RA; conducting coordination and decision-making of the release advise RA; displaying and publishing a traffic advise TA and the release advise RA; conducting omnidistance monitoring for collision release effect after adopting a mechanic operating collision avoidance measure of the native; relieving the traffic advise TA and the release advise RA. The method improves the limitation of only being able to provide two release advises of climbing/descending vertically of a conventional airborne collision avoidance system, so as to allow the airborne collision avoidance system to be able to provide six release advises (climbing/descending vertically, speeding up/speeding down horizontally, or turning left/turning right), and has the advantages of more flexible and effective.

The invention relates to the technical field of airborne collision avoidance, and discloses an optimization method for the target monitoring and tracking performance of an airborne collision avoidancesystem. Specifically, the method includes the following processes: judging whether an aircraft is making large maneuvering flight according to the course angle, roll angle and pitch angle informationinput by a carrier aircraft; if the aircraft is making large maneuvering flight, correcting the track angle of current monitoring and tracking according to the evaluated course angle change rate to form a virtual corrected track, and dispatching the launch direction of an inquiry signal according to the azimuth angle of the virtual corrected track to make an inquiry; and if a received response signal satisfies the track updating rule, converting the virtual corrected track into a corrected track and outputting the corrected track to the next processing cycle, and keeping the aircraft in the period of large maneuvering flight. Through the scheme, the influence of the antenna and the installation environment on the azimuth measurement of a target aircraft is eliminated, the accuracy and stability of the track tracking angle are maintained, and the situation awareness ability is improved.

The invention discloses a launch phase real-time calibrating device and a method based on four unit directional antennas. Calibrating source signals are divided into four ways of calibrating signals by a power divider in the device; the calibrating signals are respectively sent to four launch channels; the four launch channels are respectively connected with four transmit-receive switches correspondingly; the four transmit-receive switches are respectively connected to the four unit directional antennas; simultaneously the four transmit-receive switches are respectively connected with a matrix switch through four receiving channels; and the matrix switch is connected with a phase comparator. The method is characterized in that through launching the calibrating source signals by two channels, receiving the calibrating signals by two channels, and comparing the phase difference of two ways of received signals, the phase relationship between two launch channels is obtained. The device and method provided by the invention can be widely used for a system which has real-time calibrating requirements from each port phase in wave beam formation, such as an airborne collision avoidance system and an antenna system with symmetrical property, and the system has the advantages of obvious market prospect and economic benefits.

The invention relates to an airborne autonomous scheduling system and an airborne autonomous scheduling method under an unmanned aerial vehicle and manned aircraft coexistence environment. The airborne autonomous scheduling system comprises a data interface, the airborne autonomous scheduling system realizes data interconnection with an airborne system of an unmanned aerial vehicle or a manned aircraft through the data interface, and the airborne autonomous scheduling system is integrated in the airborne system of the unmanned aerial vehicle or the manned aircraft. The airborne autonomous scheduling system comprises a fusion interface through which the system is effectively fused with an airborne perception avoidance system and an airborne collision avoidance system providing an air interval function. Under an unmanned aerial vehicle and manned aircraft coexistence operating environment, and especially at landing facilities under no direct air traffic control and in the surrounding area thereof, the airborne autonomous scheduling system described by the invention can ensure that all aircrafts land safely and efficiently. The airborne autonomous scheduling system can be expanded to other autonomous scheduling instructions on the basis of the coordinated decision-making mechanism of the distributed system thereof, such as completing a specified flight procedure through formation.

A method for realizing ACAS conflict alert in a blank pipe ATC system is disclosed. A system is supported by a communication data processing server, a monitoring data processing server, a flight data processing server, a seat work station and network equipment. The method comprises the following steps: (1) acquiring real time radar monitoring data; (2) carrying out tracking filtering, smoothing and interpolation to a position of the obtained monitoring data; (3) selecting an aircraft, determining a flight scope and selecting a threat object in the flight scope; (4) selecting a threshold, using a threshold table to obtain the three thresholds of corresponding reserved time, a horizontal spacing and a vertical spacing according to a height of the threat object; (5) calculating a conflict alert parameter, which comprises an approach speed calculation and a reserved time calculation; (6) calculating alarm. In the invention, through the ATC system, ACAS alarm means encountered by a pilot can be know. A relief measure which is not consistent with the ACAS can be timely corrected. Therefore, hidden troubles can be eliminated and security of air traffic can be increased.

The invention relates to the field of application of a secondary radar airborne collision avoidance system and particularly relates to a data recording and analyzing method for the airborne collision avoidance system (ACAS). Aiming at the problems in the prior art, the invention provides the data recording and analyzing method for the airborne collision avoidance system. According to the data recording and analyzing method, output data of an ACAS receiving-transmitting main engine of an ACAS II system is converted into an RS232 format by a data conversion board and is further recorded to be a text document in a TXT (Text file) format; then data analysis is carried out by an upper computer. In a working process of the airborne collision avoidance system, all display data is recorded and analyzed, and data content accuracy and data cycle accuracy are judged. According to the data recording and analyzing method, flight data of a target airplane is collected by the ACAS receiving-transmitting main engine and then the flight data of the target airplane is converted into a bus data format by the conversion board according to an ARINC429 format; the upper computer is used for receiving the flight data of the target airplane in the bus format and analysis operation on the flight data of the airplane or the flight data of the target airplane is carried out.

The invention discloses an airborne collision avoidance system (ACAS) and transponder (XPDR) radio frequency integrated design system and belongs to the field of air traffic control. The ACAS and XPDR radio frequency integrated design system comprises an upper directive antenna, a lower directive antenna, an antenna channel diverter switch, an ACAS receiver, an XPDR receiver, a radio frequency cable and a transmitter. The transmitter is an ACAS/XPDR integral transmitter, the upper directive antenna and the lower directive antenna are respectively connected with the antenna channel diverter switch through the radio frequency cable, and the antenna channel diverter switch is respectively connected with the ACAS receiver, the XPDR receiver and the ACAS/XPDR integral transmitter. The ACAS and XPDR radio frequency integrated design system has the advantage of being capable of replacing a traditional separated ACAS and XPDR radio frequency transceiver system. The ACAS and XPDR radio frequency integrated design system is easy to implement in projects and effectively achieves ACAS and XPDR radio frequency integrated design.

The invention provides an airborne anti-collision system failure recording system and a failure recording decoding system; in the case that an airborne anti-collision system experiences a failure change, the failure change is encoded; the information such as failure code is recorded to a corresponding failure recording file, and the failure code information in the failure recording file is decoded; compared with the prior art, the systems of the invention can determine the information such as failure occurring time, failure content, failure state, failure times and failure types according to the failure recording information of the failure file, can provide quick failure locating and can accurately and specifically describe the failure change process during a whole flight, and maintenance time for TCASII airborne anti-collision system is greatly shortened; great assistance is provided for clearing the failure of the TCASII airborne anti-collision system and analyzing possible potential issues; the problems are solved that the conventional recording approach with failure redundant recordings has no 'failure recovery' recording.

The invention discloses a digital intermediate frequency single pulse orientation method. The method is implemented on the basis of a receiver of an onboard anti-collision system, an antenna of the onboard anti-collision system is the antenna of a four-radar unit, and the four-radar unit is arranged squarely. The method comprises the following steps of: (1) sampling bandpass; (2) performing digital phase discrimination; (3) automatically calibrating phase differences; and (4) mapping phase orientation. By the method, the onboard anti-collision system has correct orientation, high speed, small volume, low power consumption and low cost, has obvious advantages in market competition and can produce high economic benefits.

The invention relates to TCAS airborne collision avoidance system and discloses GPIB bus interface-based collision avoidance system testing equipment which comprises an incoming signal simulating device, an output signal testing device, a controller and a processor, wherein the incoming signal simulating device is connected to a detected device through a GPIB bus input interface, the detected device is connected to the output signal testing device through a GPIB bus output interface, and the controller is connected with the detected device, the incoming signal simulating device and the output signal testing device to complete control of the detected device, the incoming signal simulating device and the output signal testing device, and the processor is connected with the output signal testing device to determine output signals and provide a test result. The invention further provides a GPIB bus interface-based collision avoidance system test method.

The invention discloses a mixed monitoring tracking method of an airborne collision avoidance system. According to the method, with a comprehensive use of active monitoring and passive monitoring, mixed monitoring is achieved. The method includes the following steps of: initially using the active monitoring, determining a potential threat condition, tracking and confirming, shifting from the active monitoring to the passive monitoring, verifying passive monitoring data, determining a mixed threat condition, shifting from the passive monitoring to the active monitoring, and tracking and re-confirming. The above operations are used in a certain order to form the mixed monitoring tracking method; with use of the above method, while a collision avoidance capability of an existing TCAS is maintained, the interrogation frequency of the TCAS is reduced, the active request signals in airspace are reduced, and the signal complexity in the airspace is reduced. The ADS-B technology is used, so that the TCAS with the mixed monitoring function is higher in request efficiency, and the TCAS has the capability to track multiple aircrafts.

The invention discloses an interface adaptation method and a circuit used for an airborne collision avoidance system, relates to an air collision avoidance technology, and aims to provide a data conversion method and a circuit based on an aerialcarrier platform. The technical note of the circuit provided by the invention is as follows: the circuit comprises an atmosphere height acquiring and coding module, a radio altitude acquiring and coding module, and a fly parameter data conversion module, wherein the atmosphere height acquiring and coding module is used for acquiring current atmosphere height value, and the atmosphere height value is changed into an ARINC 429 data format so as to be finally output to the airborne collision avoidance system; the radio altitude acquiring and coding module is used for acquiring current radio altitude value, and the radio altitude value is changed into the ARINC429 data format so as to be finally output to the airborne collision avoidance system; and the fly parameter data conversion module is used for collecting alarm information generated by the airborne collision avoidance system, the alarm information is subjected to digital-analog conversion so as to be finally output to an airplane reference record instrument. By using the method and the circuit provided by the invention, a compatible problem of the existing airplane and digital airborne collision avoidance system following a Russian-made protocol can be solved.

The invention discloses a multifunctional data conversion system based on an airborne collision avoidance system, comprising an atmosphere height conversion unit, a radio height conversion unit, and a flight parameter conversion unit. An aircraft atmosphere data machine and an aircraft radio altimeter are respectively connected with the input ends of the atmosphere height conversion unit and the radio height conversion unit. The flight parameter output end of the airborne collision avoidance system is connected with aircraft flight parameter equipment. The multifunctional data conversion system is easy to implement in engineering, and can complete atmosphere height, radio height and flight parameter signal format conversion between the aircraft equipment and the collision avoidance system according to the requirement of an aircraft platform. An adopted sampling circuit reduces the sampling error of analog data conversion and improves the sampling precision of an analog data conversion system. The function of conversion between RS422 data and ARINC429 data and conversion between high-speed ARINC429 data and low-speed ARINC429 data is added.

The invention provides an airborne collision avoidance system central maintenance system and maintenance method. The central maintenance system includes the following subsystems: a power supply self-checking subsystem, a task monitoring subsystem, a comprehensive self-checking subsystem, a starting self-checking subsystem, and an expansion self-checking subsystem. The comprehensive self-checking subsystem collects all the fault original information reported by the other subsystems of the airborne collision avoidance system and processes the faults comprehensively, and then stores the processed results and reports the results to an integrated avionics system. The integrated avionics system can obtain the self-checking results or the related information of the airborne collision avoidance system by starting the self-checking subsystems. The task monitoring subsystem monitors the task states of the airborne collision avoidance system in real time, monitors the online recovery in real time, and generates a monitoring log. The expansion self-checking subsystem enables the airborne collision avoidance system to realize human-computer interaction, and displays the LRU self-checking result through indicators.

The present invention provides a system and method for improving Arinc 429 communication system reliability. The system comprises a first Arinc 429 communication system and a second Arinc 429 communication system that are independent of each other. The method comprises: monitoring in real time whether a currently used communication system among the two independent Arinc 429 communication systems encounters a fault; if a fault occurs, online recovering the faulty Arinc 429 communication system; if the recovery is successful, terminating the process; and if the recovery is unsuccessful, starting the other Arinc 429 communication system. According to the present invention, the reliability of the Arinc 429 communication system in a traffic alert collision avoidance system II (TCAS II), the problem that after an Arinc 429 communication system encounters a hardware fault and theus the TCAS II communication fails is solved, and further the problem that the TACS loses its normal functions when the configuration region of the Arinc 429 communication system fails in a complicated electromagnetic environment or under the single particle reverse effect is solved.

The invention discloses an MDP (Markov decision process) based airborne collision avoidance system logical unit design method which is characterized by including the steps of 1, building encounter models; 2, modeling for aircraft collision avoidance by means of the MDP; 3, creating a logical table according to the models so as to obtain the logical units. Reliability of the designed logical units can be improved and the logical units can be modified conveniently by application of the method. Therefore, by the method, safety performance of aircraft in flying is improved while the logical units can be modified and reconstructed repeatedly.

The invention discloses an airborne collision avoidance system, which generates a decision alarm based on a decision alarm collaboration module and an ADS-B response target, and realizes alarm collaboration with the ADS-B response target. In addition to the inherent capability of ACAS X, the system is mainly characterized in that when a monitored ADS-B response target generates collision threat, a traffic alarm and a decision alarm can be generated, and an existing ACAS X monitoring and anti-collision alarm method is used for generating a decision alarm (RA) for the ADS-B response target; when a decision alarm is generated, alarm cooperation with an ADS-B response target is realized, compatibility of maneuvering flight avoidance actions is maintained through cooperation, and compatibility, safety and effectiveness of vertical maneuvering flight directions of the ADS-B response target and the ADS-B response target are ensured.