31 results about "Required navigation performance" patented technology

Methods and apparatus are provided for indicating safe or potentially hazardous operating conditions of an aircraft in a required navigational performance (RNP) environment. The apparatus comprises a course deviation display field with first and second markers defining outer boundaries of the RNP width and a central marker indicating the desired course within the RNP width, an aircraft estimated position uncertainty (EPU) marker in the display field whose size corresponds to the EPU relative to the RNP and a current aircraft position marker coupled to the EPU marker and moving therewith as the aircraft position changes with respect to the RNP width. The display desirably changes color and/or flashes to alert a pilot to a potentially hazardous condition when an outer boundary of the EPU marker approaches to within a predetermined guard-band distance of or overlaps either of the first or second markers. An audible warning can be included.

The present invention is a flight deck system for promoting accurate navigation of an aircraft. The system includes a memory configured for storing position information for the aircraft. The system further includes a processor which is configured for being communicatively coupled with the memory, the processor also being configured for receiving the aircraft position information stored in the memory. The system also includes a display which is configured for being communicatively coupled with the processor. The display is further configured for displaying a scaled indicator, the scaled indicator having been output to the display by the processor, the scaled indicator being based upon the received aircraft position information. The scaled indicator includes: a current position indicator for indicating an estimated current position of the aircraft, a desired position indicator for indicating a desired navigational position for the aircraft, and an allowable Flight Technical Error (FTE) indicator for indicating allowable Flight Technical Error (FTE) for the aircraft. Further, the current position indicator, the desired position indicator, and the FTE indicator are suitable for use by a pilot of the aircraft in maintaining the aircraft within established navigational boundaries.

A monitor on-board an aircraft which uses radio altitude measurements as the basic observable altitude during runway approach. The basic concept utilizes the aircraft's navigation system, which includes means to store and retrieve radio altitude thresholds as a function of the distance along the desired path from the runway thresholds. These threshold functions are determined in advance based on a radio altitude reference which is defined as the expected radio altimeter measurement that would be made if the airplane were exactly on the desired reference path. Vertical containment monitoring is achieved by comparing the radio altitude measurement to computed thresholds for both too high and too low. During the approach, an annunciation message can be generated if the radio altitude measurement is above or below the threshold limits. Using this monitor ensures that the total system error for the aircraft is contained within a bound called the Vertical Containment Level of the desired reference path in space with a probability that is specified.

The invention discloses an optimum navigational parameter fusion method based on three-level filtering under redundant sensor configuration. According to the invention, aiming at the characteristics of information redundancy of a navigation sensor, a three-level filtering framework for the navigation sensor is designed; through local estimation of a first-level kalman filter, the global estimation of a second-level federated filter and the optimum global estimation of a third-level filter, the optimum global estimation of the navigational parameter of a flight management system can be performed by fully using redundant navigation sensor information. The method disclosed by the invention is beneficial to full utilization of the redundant navigation sensor information, meanwhile, improves the accuracy of navigational parameter estimation, and is such a method that facilitating engineering realization. The method has an important practical application significance on meeting navigation performance requirements required by all legs for large aircrafts flying in civilian areas.

The invention belongs to the technical field of satellite navigation positioning, and particularly relates to an integrity risk probability distribution method supporting a satellite navigation positioning reliability requirement. The method comprises steps of according to navigation performance required in different navigation applications, establishing fault tree modules for integrity risk sources in different applications; according to the Bayes rule, finishing an optimal distribution scheme of the integrity risk probability; establishing an one order Markov switching module for each main integrity risk source, according to a specific integrity risk source, setting an initial condition and prior information of the module, and finally determining the P<md>; and determining a sigma expansion coefficient subset according to counting features on positioning errors imposed by specific integrity risk sources in different applications. According to the invention, an improved sigma expansion algorithm based on the expansion coefficient set is provided and expansion coefficients are determined, so theoretical basis is provided for ideal error hypothesis required by integrity monitoring; and a minimal protection level is finally designed, so the requirement of high reliability of satellite navigation positioning is met.

A method is provided for calculating the prediction of required navigation performance for a trajectory associated with a list of segments of a flight plan. A method is also provided for displaying the navigation performance as a corridor trajectory and adapted to guarantee compliance with the navigation performance requirements while offering immediate viewing of the navigation latitude in a corridor.

The invention provides a method for displaying RNP (Required Navigation Performance) parameters of an aircraft. The method comprises the following steps: computing the estimated position, transverse RNP value and vertical RNP value, transverse NSE (Navigation System Error) real-time value and vertical NSE real-time value as well as transverse FTE (Flight Technical Error) limit value and vertical FTE limit value of the aircraft at the current time, and displaying an aircraft icon, a cross ruler for representing the RNP values as well as an FTE limit frame for representing the FTE limit values, wherein the transverse side length of the FTE limit frame corresponds to the transverse FTE limit value, and the vertical side length of the FTE limit frame corresponds to the vertical FTE limit value. The invention also provides a method for replacing the cross ruler by using a rectangular frame. The invention also discloses a corresponding system for displaying the RNP parameters of the aircraft as well as the aircraft comprising the system. The method and system provided by the invention can be used for visually monitoring the RNP running state of the aircraft in the three-dimensional space.

The invention aims to a satellite ephemeris fault monitoring method based on short-base-line multi-reference receiver and having high monitoring efficiency. The satellite ephemeris fault monitoring method comprises the steps that 1, the test statistic amount of ephemeris fault detection is constructed; 2, ambiguity is calculated; 3, false alarm errors are controlled; 4, leak detection errors are controlled. Navigational satellite signals are synchronously received and processed through the multi-reference receiver under short-base-line configuration, multi-reference consistency monitoring of satellite ephemeris faults is carried out through carrier wave phase differential positioning of the multi-reference receiver, and integrity monitoring is carried out according to preset required navigation performance. Compared with a single-reference receiver, more permissive detection threshold values can be obtained by the multi-reference receive and are conductive to the continuity risk in integrity monitoring. In addition, the influence of atmospheric propagation errors of an ionized layer, a troposphere and the like on the satellite ephemeris fault monitoring performance can be avoided by adopting the multi-reference receiver, and the monitoring efficiency is improved.

The invention discloses a Beidou non-motorized broadcast ephemeris fault real-time monitoring method, which comprises the steps of selecting broadcast ephemeris parameter extrapolation time, and analyzing statistical distribution characteristics of broadcast ephemeris parameter differences; based on sensitivity analysis of satellite positions on broadcast ephemeris parameter changes, obtaining the influence of the broadcast ephemeris parameter changes on the satellite positions, wherein broadcast ephemeris parameters with large influence on the satellite positions adopt a high-order extrapolation mode, and broadcast ephemeris parameters with small influence on the satellite positions adopt a low-order extrapolation mode; and obtaining a threshold value meeting the system requirement according to the required navigation performance requirement, and comparing the threshold value with the test statistic so as to realize the real-time monitoring of the Beidou non-motorized broadcast ephemeris fault. According to the invention, a high-order polynomial and low-order polynomial mixed extrapolation mode is adopted for broadcast ephemeris parameters, so that the low calculation amount is guaranteed while higher-precision satellite position deviation can be obtained, Beidou non-maneuvering broadcast ephemeris faults are effectively monitored, and reference is provided for Beidou broadcast ephemeris fault monitoring.

The embodiment of the invention provides a flight assistance method and device, electronic equipment and a readable storage medium, and relates to the technical field of flight navigation. According to the embodiment of the invention, after the navigation performance data of a target aircraft is obtained, the predicted navigation performance of the current remaining flight plan of the target aircraft is calculated according to the navigation performance data, and then the predicted navigation performance is compared with the navigation performance required by the current remaining flight plan to obtain a target comparison result of the predicted navigation performance and the required navigation performance, and after the target comparison result is obtained, the target comparison result and a target flight prompt corresponding to the target comparison result can be output. Therefore, by calculating the predicted navigation performance of the current remaining flight plan of the target aircraft and outputting the flight prompt according to the comparison result of the predicted navigation performance and the required navigation performance, the flight safety and reliability can be improved, and the flight efficiency is ensured.

The device aids the management of air operations, such as operations under Required Navigation Performance with Authorization Required maneuvers. The device includes a guidance system including a plurality of stages for calculating parameters, each of the stages including an architecture having at least three pieces of equipment, which calculate the parameters and implement monitorings to determine the status of the equipment. The device uses these monitored statuses to determine a global status that indicates if the aircraft is able to carry out the air operations with required performance.