6 results about "Required navigation performance" patented technology

This disclosure relates to improved techniques for upgrading legacy flight management systems (FMSs) installed in an aircraft. In certain embodiments, an integrated guidance system (IGS) can be installed in an aircraft having a legacy FMS to provide enhance flight functionalities, such as required navigation performance (RNP), localizer performance with vertical guidance (LPV), and automatic dependent surveillance-broadcast (ADS-B), capabilities. Additionally, the IGS described can include, inter alia, a navigator system that receives and processes information from an ADS-B system to implement a variety of automated following options, each of which can provide an automated mechanism for controlling a flight path of the aircraft relative to another aircraft that is being tracked by an ADS-B system.

The application discloses a kind of satellite clock orbit correction product integrity information coding precision and update cycle determination method and device, belong to satellite navigation technical field.The method receives the real-time observation data of integrity monitoring station network and satellite clock orbit correction product integrity information by PPP-RTK cloud master station, constructs protection level prediction model based on the required navigation performance of user, and the sensitivity analysis is carried out to the protection level change caused by integrity information change, determines coding precision and average failure duration.Combining average failure duration constructs update cycle determination model, finally forms the coding and broadcast scheme of satellite clock orbit correction product integrity information.The application significantly improves the reliability of broadcast data and the integrity of PPP-RTK real-time positioning, and provides important support for intelligent, unmanned application of high-precision, high-integrity space-time information demand.

The invention particularly relates to a flight guiding method for high plateau airport terminal operation. The method comprises the steps that the real-time position, flight state parameter information and a flight plan of an aircraft are loaded; calculating a horizontal guide parameter, namely a lateral offset distance, by considering leg type characteristics; calculating a vertical guide parameter, namely a leg gradient, by considering leg type features; generating a horizontal guide instruction, namely an expected roll angle, based on the lateral offset distance; generating a vertical guidance instruction, namely an expected pitch angle, based on the leg gradient; and based on the expected roll angle and pitch angle, a control plane deflection instruction is generated by using a fractional order PID controller with phase compensation, and the aircraft is controlled to fly according to a predetermined flight path according to the control plane deflection instruction. According to the method, high-precision three-dimensional flight guidance meeting the RNP AR requirement of the navigation performance required by special authorization can be realized, and the method is of great significance in improving the flight guidance function of a civil aircraft flight management system and guaranteeing the flight safety of a civil aircraft in a high plateau airport environment.

The invention discloses a method for constructing a navigation performance path required by a flight management system for executing point turning, and the flight management system aims at the flight plan condition of the point turning. Four transition path construction methods of point turning including initial point turning, continuous point turning, bypass-considered point turning and bypass-prohibited point turning and bypass detection processing are provided, so that the problem that the precision, the reliability, the repeatability and the predictability of point turning performed for a waypoint by a traditional method cannot be ensured is solved; the continuous and smooth reference track can be provided for a pilot, flight guidance and / or flight guidance, continuous and smooth required navigation performance monitoring can be provided for the pilot, the reliability, repeatability and predictability of the flight path of an aircraft are enhanced, and the flight safety in a specified airspace is further improved.

The invention discloses a method for determining an advanced turning parameter of a path for executing required navigation performance by a transport plane flight management system, and the method comprises the steps: determining an index requirement of an FMS executing an RNP path in a system demand confirmation process by an FMS supplier, and designing and calculating a t phi function in a system design process according to a turning rate; the function is composed of a scheduling frequency of the rolling instruction calculation task, a gain ks of time overhead of the rolling instruction calculation task, a time gain k [delta] psi of a task calculation time-consuming turning rate of the rolling instruction calculation task, and a rolling angle variable quantity [delta] phi for tracking a nonlinear path; and taking the k delta psi as a configurable parameter, and if the FMS executes turning guidance of the RNP path tracking nonlinear path and enters a steady state after leg switching and does not meet the index requirement, adjusting the k delta psi. The problems that a traditional method is high in cost, the iteration process is low in efficiency, and under some conditions, results are unstable or poor due to the fact that experiment conditions are non-repeatable are solved.

The invention relates to a method for generating a navigation performance path required by a waiting leg of a flight management system, which comprises the following steps of: judging updating conditions of the navigation performance path required by the waiting leg by the flight management system; and calculating waiting leg parameters, a waiting entry path, a waiting operation path and a waiting exit path according to the updating condition of the navigation performance path required by the waiting leg. According to the invention, different stages of waiting programs of all flight plans are processed respectively, and the continuity of flight capability of a reference path is ensured by providing a waiting path in the whole course; compared with the traditional method that the precision, reliability, repeatability and predictability cannot be ensured by switching the entry segment, the exit segment and the next segment waiting for operation, the method provided by the invention can provide a continuous and smooth reference track, and supports to provide continuous and smooth required navigation performance monitoring for a pilot; the reliability, repeatability and predictability of the flight path of the aircraft are enhanced, and the flight safety in a specified airspace is improved.