• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The present invention relates to a method for calculating the navigation performance prediction required for a trajectory associated with a list of segments of a flight plan. The invention also provides a method for displaying navigation performance in a corridor path to ensure compliance with navigation performance requirements and providing immediate visualization of navigation latitude in a corridor.
    公开号:FR3053780A1
    申请号:FR1601060
    申请日:2016-07-07
    公开日:2018-01-12
    发明作者:Michel Roger；Christophe Pierre；Herve Gourtelard
    申请人:Thales SA；
    IPC主号:
    专利说明:

    © Publication no .: 3,053,780 (to be used only for reproduction orders)
    ©) National registration number: 16 01060 ® FRENCH REPUBLIC
    NATIONAL INSTITUTE OF INDUSTRIAL PROPERTY
    COURBEVOIE © Int Cl 8 : G 01 C21 / 20 (2017.01), G 01 C 23/00, G 06 F 3/048
    A1 PATENT APPLICATION
    Date of filing: 07.07.16. (© Applicant (s): THALES Société anonyme - FR. © Priority : @ Date of availability of the request: 12.01.18 Bulletin 18/02. @ Inventor (s): ROGER MICHEL, PIERRE CHRISTOPHE and GOURTELARD HERVE. (56) List of documents cited in the preliminary search report: See the end of this brochure References to other related national documents: ©) Holder (s): THALES Société anonyme. o Extension request (s): © Agent (s): MARKS & CLERK FRANCE General partnership.
    DEVICE AND METHOD FOR CALCULATING PREDICTION OF REQUIRED NAVIGATION PERFORMANCE.
    The present invention relates to a method for calculating the navigation performance prediction required for a trajectory associated with a list of segments of a flight plan. The invention also relates to a method making it possible to display the navigation performance in a corridor trajectory making it possible to guarantee compliance with the navigation performance requirements and by providing immediate visualization of the navigation latitude in a corridor.

    DEVICE AND METHOD FOR CALCULATING PREDICTION OF REQUIRED NAVIGATION PERFORMANCE
    Field of the invention
    The invention relates to the field of flight management systems, and more particularly that of assistance in piloting aircraft by calculating in advance navigation performance.
    State of the art
    The so-called Performance Based Navigation (PBN) is a flight method which was defined by the international civil aviation organization ICAO in 1998 in order to optimize the use of navigation. space in front of the permanent growth of its frequentation. The PBN method makes it possible to define conditions to be respected in terms of integrity, availability, functionality, accuracy and continuity. These conditions translate into requirements in terms of Required Navigation Performance (RNP) and in terms of EPE (Estimated Position Error) or EPU (Estimated Position Uncertainty).
    RNP required navigation performance is defined for flight portions. As shown in Figure 1, the RNP varies depending on whether the aircraft is on a portion Oceanic ’or‘ Enroute ’or‘ Terminal Area ’or‘ Approach ’flight portion. So a procedure with a certain required performance refers to a specific block of space. The level of performance required is expressed by the width of a corridor depending on the block of space. For example, a block of ocean space can have a corridor width from 4 to 10Nm where the symbol Nm corresponding to the nautical mile and 1 nautical mile is equal to 1852 m.
    In the approach phase to an airport where many aircraft coexist in a reduced space, the required level of performance translated into the width of the corridor is generally 1 Nm at the start of the approach, drops to 0.5 Nm for non-precision approaches 0.3 Nm for precision approaches and up to 0.1 Nm for special approaches called 'RNP AR'. The variability in the level of performance required makes it possible to define a three-dimensional trajectory composed of straight lines and curves, in an environment with high traffic density, around areas sensitive to noise or through difficult terrain. The required performance level can be defined in a configuration file of the flight management system, manually by the pilot or called from a database present in the flight management system. It can also be defined by default depending on whether the space overflown by the aircraft is of the oceanic type, en route or airport, for example.
    In order to be able to follow the requirements of the RNP procedure, the aircraft's navigation means must be able to calculate the position of the aircraft according to the performance required over the space overflown. Thus, a procedure with a certain required performance means that the navigation systems of the aircraft must be able to guarantee that the position of the aircraft is within a circle of radius xx Nm. For example, for a procedure having an RNP required performance of 5 Nm, the navigation system of the aircraft must be able to calculate the position of the aircraft in a circle of radius 5 Nm. More precisely as illustrated in FIG. 2, the navigation system must guarantee that the aircraft must not leave a corridor of width 10 Nm (2 x RNP: accuracy limit) for 95% of the flight time, and guarantee that the aircraft will never cross the border of a corridor of width 20 Nm (4 x RNP: containment limit).
    The accuracy of the position calculation may vary along the flight. Indeed, external Global Positioning System GPS type satellite navigation devices have different levels of coverage depending on the geographic area considered. It is the same for radio navigation means. As for inertial means, they suffer from the inertial drift problem inherent in these systems.
    Conventionally, the calculation error of the horizontal aircraft position called TSE "Total System Error" represented in FIG. 3 is the quadratic sum of 3 components, expressed by the following equation:
    TSE = <FTEF + (NSE) Ï + (PDEF where:
    - NSE "Navigation System Error" represents the aircraft location error, also called PEE for "Position Estimation Error". This error characterizes the error in the calculation of the aircraft position from radio position, inertial or satellite sensors. It is often depicted as a circle around the plane.
    - PDE "Path Definition Error" represents the aircraft trajectory error. This error is considered negligible because it is associated with an unlikely coding error in the navigation database. This error becomes even smaller for navigation systems using a geodesic reference model of the WGS84 type.
    - FTE for "Flight Test Error" represents the aircraft guidance error, also called PSE for "Path steering Error". This error is related to the guidance mode of the aircraft and has for source, three guidance states classified from the least precise corresponding to the most important error, to the best:
    - manual guidance without help to follow the trajectory,
    - manual guidance with follow-up of flight director orders,
    - automatic guidance with the autopilot engaged to follow the trajectory.
    In FIG. 3, the arrow "DesP" for "desired path" corresponds to the desired trajectory, and the dotted arrow "DefP" for "defined path" corresponds to the calculated trajectory.
    For the TSE, it is a first component (PDE) which in practice is considered negligible, a second component (FTE) which has 3 fixed values and which only applies to the active flight segment, that which the aircraft is following, and a third component (NSE) which is linked to sensor measurements. This last component can vary along the trajectory because it is a function of the performance of the available sensors around the position of the aircraft which is evolving.
    The error in the calculation of the position of the aircraft comes from the systems performing the calculation, in general the navigation system which is designated by the English terminology "Flight Management System" or FMS and which sets the course to follow available to on-board staff and available to other on-board systems. This FMS system also allows navigation aid, by displaying information useful to pilots, or by communicating guidance instructions to an automatic pilot system. On certain aircraft, such as ΙΆ350, it is the ADIRU system that operates the aircraft location function. These systems provide an estimate of the so-called calculation error (EPE) for "Estimation Position Error", sometimes called (EPU) for "Estimation Position Uncertainty", two names that represent the same information. This information is thus representative of an estimated performance level compared to a required performance level. FIG. 4 illustrates according to a known display, the performance prediction estimated under the EPU information variable according to the flight segments. The navigation system must guarantee that the aircraft position is within a circle of radius ‘xx’, this radius characterizing the EPU uncertainty in the calculation of the position. This circle, depending on the speed of the aircraft, takes the form of an ovoid to take account of the possible reduction in tolerance required when switching from one flight segment to the next, at the exit of a transition bend between two flight segments.
    Thus, currently knowledge of the required navigation performance remains limited to the current flight segment, or even near the end of the next segment, while the value of the required navigation performance is variable throughout the flight plan. The pilot does not benefit from the knowledge in advance of a change in the required navigation performance.
    Similarly, the estimated navigation performance is a function of location sensors, the availability of which varies along the flight, and the calculation of the value of the estimated navigation performance is only valid today for the current flight segment. followed by the aircraft. Thus, knowledge of the estimated navigation performance remains limited to the current position of the aircraft and does not allow the pilot to anticipate on the non-compliance with the required performance.
    Thus, the information available to the operator remains the required navigation performance and estimated navigation performance values for the current flight segment as illustrated in Figures 5a and 5b. FIG. 5a represents a page of a screen of a flight management system, a screen which is not accessible by the pilot in “head-up” position and which access requires from the pilot to enter the management system menu to display this page on a screen. In the example on this page, the title "APPROACH" indicates that the information provided relates to an approach phase to an airport, for example. At the bottom left, the term "REQUIRED" is displayed with a numerical value of 1.0 NM which indicates the level of performance required by the RNP procedure. At the bottom right, the term "ESTIMATED" is displayed with a numerical value of 0.60 NM which indicates the estimated level of performance. In the example, the requirement of the RNP procedure is satisfied, the estimated level of navigation performance being lower than the required level of navigation performance. The term "HIGH" combined with the term "ACCUR" represents a qualitative indication of the level of integrity of navigation calculations for the pilot and shows that the level of safety is considered to be high.
    Furthermore, the operator maintains the aircraft on a calculated trajectory which is called the "wire" trajectory as illustrated in FIG. 5b. FIG. 5b represents a page of a navigation screen of the flight management system on board an aircraft which shows the trajectory to be followed by the aircraft, is generally easily accessible in the "head up" position by the pilot of the aircraft, requiring no maneuver to gain access. The current aircraft position is indicated by an aircraft symbol, represented in the center of three concentric circles of increasing radius. The trajectory of the aircraft is indicated by an axis or "wire" passing through the current position of the aircraft, a first and a second waypoint (CI27R, FI27R). The current position and the first waypoint define a first current portion of the trajectory, a portion of the trajectory being commonly called segment or "leg" in English. The first and second waypoints define a second portion of the trajectory.
    The aircraft systems must comply with and not exceed the required navigation performance, which is expressed in width Nm of a corridor. However with the wire display, the operator has no information on the navigation latitude in the corridor which is defined by the required navigation performance, and if an obstacle is in the corridor, the pilot will not see it that at the last moment and the operation will require an emergency authorization request to the ground operator.
    Thus, navigation systems currently deliver a required level of navigation performance and an estimated level of navigation performance which are limited to the current flight segment or at best the next segment for the current position of the aircraft. In addition, known navigation systems do not allow the operator to know the "freedom" to navigate a defined corridor while respecting the RNP procedure.
    An object of the invention is to overcome the drawbacks of known systems.
    Summary of the invention
    An object of the present invention is to provide a device and a method for calculating the navigation performance prediction required for a trajectory associated with a list of segments of a flight plan.
    Another object of the invention is to provide a device and a method for transforming a wire trajectory into a corridor trajectory, making it possible to guarantee compliance with PBN navigation performance requirements as long as the aircraft does not leave the corridor trajectory. .
    Advantageously, the device of the invention provides assistance in piloting an aircraft within the framework of PBN procedures by providing an ability to define the navigation performance required on a list of segments.
    Advantageously, the device of the invention provides simple corridor trajectory information, allowing the operator of the aircraft to better control the trajectory of the aircraft and the expected and available performance, by giving him easy access to the corridor in which performance is guaranteed and to the limits not to be exceeded. By immediately viewing the navigation latitude in a corridor, avoiding an obstacle becomes an easy operation to be carried out by the pilot, without prior authorization request or with a very anticipated request because the operator or the pilot thanks to the knowledge of the estimated performance, respects the safety clearly displayed to it by the corridor trajectory.
    To achieve the desired results, methods, devices and a computer program product are described.
    In particular, a method, operated by an aircraft calculation platform, for calculating the navigation performance prediction required for an aircraft trajectory, comprises the steps of:
    - receive a list of segments of a flight plan;
    - for each segment of the list:
    - identify all the contingencies constituting navigation performance constraints;
    - determine and select the most restrictive contingency for said segment;
    - calculate a required navigation performance prediction, based on data from the contingency selected;
    and
    - update the list of segments with the required navigation performance prediction associated with each segment.
    According to one embodiment, the identification step consists in identifying the contingencies existing in the navigation database and the contingencies defined by an operator. In another embodiment, the determination step consists in determining if a performance contingency given by a regulation is the most restrictive, and selecting it.
    When no navigation performance constraint is identified 4, the calculation of the required navigation performance prediction is made according to default values.
    Advantageously, the method can be operated for a calculation of prediction of required horizontal navigation performance and / or for a calculation of prediction of required vertical navigation performance. Still advantageously, the steps of the method can be re-executed automatically if the flight plan changes.
    The invention also relates to a device for calculating the prediction of navigation performance required for an aircraft trajectory, which comprises:
    - means for receiving a list of segments of a flight plan;
    - means allowing for each segment of the list:
    - to identify all the contingencies constituting navigation performance constraints;
    - to determine and select the most restrictive contingency for said segment;
    - calculate a required navigation performance prediction, based on data from the selected contingency;
    and
    - means for updating the list of segments with the required navigation performance prediction associated with each segment.
    In one embodiment, the device is able to operate all the steps of the claimed process.
    The invention also covers a flight management system (FMS) or an on-board computer of the EFB type which comprises a device for calculating the navigation performance prediction required for an aircraft trajectory as claimed.
    The invention also relates to a computer program product which includes code instructions for performing the steps of the method, when the program is executed on a computer.
    In one embodiment, the method for calculating the predictions of estimated navigation performance can be executed to allow display thereof. The invention also relates to a method for displaying predictions of navigation performance estimated and required for an aircraft trajectory, the method being operated by an aircraft calculation platform and comprises the steps:
    - calculate predictions of estimated navigation performance for a list of segments of a flight plan;
    - calculating for the same list of segments, predictions of required navigation performance according to the steps of the method of calculating predictions of required navigation performance;
    and
    - to represent graphically on a display means said predictions of estimated and required navigation performance.
    In one embodiment, the step of calculating predictions of estimated navigation performance comprises the steps of:
    - receive a list of segments comprising all the segments of a flight plan with a prediction of a passage time associated with each segment;
    - for each segment of the list:
    - identify the positioning systems external to the aircraft available in the geographic area of said segment;
    - determine the performance values of the identified positioning systems and select the external positioning system with the lowest navigation performance calculation error for the position of said segment and said predicted passage time;
    - calculate an estimated navigation performance prediction, from data from the selected external positioning system;
    and
    - update the list of segments with the estimated navigation performance prediction associated with each segment.
    In one embodiment, the graphical representation consists of displaying said predictions of estimated and required navigation performance on a wire trajectory.
    In a variant, before the display step, the method makes it possible, for each segment of the list, to subtract from the required navigation performance predictions, the estimated navigation performance predictions, in order to construct a corridor trajectory, and in which the Graphical representation consists of displaying said predictions of navigation performance estimated and required according to the corridor.
    According to one embodiment, the display step consists in displaying a wire trajectory for the segments having an estimated navigation performance prediction greater than the required navigation performance prediction.
    In a variant, the graphic representation consists in representing the navigation latitude in contrast on the corridor trajectory.
    The invention also covers a device for displaying predictions of navigation performance estimated and required for an aircraft trajectory, the display device comprises a display means and calculation means making it possible to calculate performance predictions. of estimated and required navigation, the predictions of estimated navigation performance are calculated according to the steps of the claimed calculation method, and the device further comprises means for graphically representing on the display means the predictions of estimated and required navigation performance .
    The display means can be an aircraft cockpit screen, such as a "Navigation Display" (ND) or a "Primary Flight Display" (PFD) screen.
    Description of the figures
    Various aspects and advantages of the invention will appear in support of the description of a preferred mode of implementation of the invention but not limiting, with reference to the figures below:
    Figure 1 illustrates RNP required navigation performance for different flight portions;
    Figure 2 illustrates the RNP navigation limits of an aircraft in a corridor;
    Figure 3 illustrates the three components of the aircraft horizontal position calculation error;
    Figures 4a and 4b illustrate different pages of the navigation screen of a flight management system, according to the state of the art;
    FIG. 5 illustrates a display of the predicted navigation performance prediction for a trajectory associated with a list of segments according to an embodiment of the invention;
    FIG. 6 illustrates a display of the navigation performance prediction required for a trajectory associated with a list of segments according to an embodiment of the invention;
    FIG. 7 illustrates a combined display of the predictions of navigation performance required and estimated for a trajectory associated with a list of segments according to an embodiment of the invention;
    FIG. 8 illustrates a combined display of the predictions of navigation performance required and estimated for a trajectory associated with a list of segments according to another embodiment of the invention;
    FIG. 9a illustrates the method for calculating the predictions of navigation performance required for a list of segments in an embodiment of the invention;
    FIG. 9b illustrates a method for calculating predictions of estimated navigation performance for a list of segments in an embodiment of the invention;
    FIG. 9c illustrates the method of constructing a corridor trajectory in an embodiment of the invention;
    FIG. 10 schematically illustrates the structure and the functions of a flight management system of the FMS type making it possible to operate the present invention;
    FIG. 11 illustrates the method for calculating the EPU prediction for a segment in an embodiment of the invention;
    FIG. 12 illustrates the method for calculating the EPU-inertia prediction for a segment in an embodiment of the invention;
    Figure 13 illustrates the type of EPU considered for segments depending on the availability or loss of RAIM functionality;
    Figure 14 illustrates the corridor value (Default, Pilot, Database) taken into account for a segment;
    Figures 15 to 20 illustrate different variants of the display of predictions of required and estimated navigation performance;
    Figure 21 illustrates the three components of the aircraft vertical position calculation error;
    Figures 22 and 23 illustrate variants of the vertical corridor display.
    Detailed description of the invention
    FIG. 5 represents an example of display according to an embodiment of the invention, of the prediction of estimated navigation performance (EPU) for a wire trajectory associated with a list of segments. This display allows the operator to monitor the navigation performance of the aircraft. A list of segments as defined in the description is a continuous sequence of segments (S1, S2, .... Si, ..., Sn), the segments being straight or curved, each segment having a starting point (PDsî ) and an end point (PF S i) respectively defined by their latitude, longitude and altitude. In addition, any segment of a list is associated with an hour or a time of passage on the end point of the segment, and we speak of a dated list of segments. In the example of FIG. 5, five segments (S1 to S5) from a list of segments Sn are represented. The segment S1 which has as its starting point PDsi and its end point PFsi contains the representation of the aircraft in its current position, the segment S2 which has as its starting point PDs2 and its end point PFs2 displays an estimated navigation performance prediction EPU of 0.1 Nm. The segment S5 which begins with PD S5 displays an estimated performance prediction of 0.3 Nm. For reasons of simplification, only the EPUs of two segments are represented.
    FIG. 6 represents an example of display according to an embodiment of the invention, of the navigation performance prediction required for a wire trajectory associated with a list of segments, where the list of segments (S1 to S5) is identical to that of FIG. 5. In this representation, the required performance prediction is displayed in half-width of a corridor corresponding to the corridor within which the aircraft can taxi. This display allows the operator to anticipate a more restrictive required navigation performance requirement. On the S2 segment, this value is 1 Nm signifying that the aircraft must taxi in a corridor of width 2Nm on this flight portion, and for the S5 segment, this value is 0.3 Nm signifying that the aircraft must taxi in a corridor 0.6 Nm wide on this portion of the flight.
    FIGS. 7 and 8 show display examples combining predictions of required and estimated navigation performance for a wire path associated with a list of segments, according to different embodiments of the invention. The display in FIG. 7 can be a representation conforming to the mental representation of an operator with a first corridor relating to the UPR and a second corridor corresponding to the required navigation performance. The display in FIG. 8 allows the operator, even in unmanaged mode (where the automatic trajectory tracking NAV mode is not engaged) to know the relative situation of the aircraft with respect to the regulatory limit (the width "required" corridor).
    FIG. 9a illustrates according to an embodiment of the invention, steps of the method for calculating the predictions of estimated performance for a list of segments of a flight plan.
    The method begins with a step (902) of receiving a dated list of ‘N’ flight segments for a trajectory associated with a flight plan. Each segment of the flight plan is associated with a predicted time of passage of the aircraft on said segment. The list of segments is produced by the flight management system. Flight plan data is generally provided by the flight management system (FMS) which has a current flight plan for the aircraft which includes the different points of the flight plan. FIG. 10 schematically illustrates the structure and the functions of a known flight management system (FMS), making it possible to implement the means able to operate the method of the invention. An FMS type system is installed in an airplane and has a man-machine interface (1220) comprising input means, for example formed by a keyboard, and display means, for example formed by a screen. display, or simply a touch screen display, as well as at least the following functions:
    - Navigation (LOCNAV) (1201), to perform the optimal localization of the aircraft according to geolocation means (1230) such as satellite or GPS positioning, GALILEO, VHF radionavigation beacons, inertial units. The methods and systems described mainly affect or relate to this part of the computer;
    - Flight plan (FPLN) (1202), to enter the geographic elements constituting the skeleton of the route to follow, such as the points imposed by the departure and arrival procedures, waypoints, air corridors, commonly designated airways according to English terminology;
    - Navigation database (NAVDB) (1203), to build geographic routes and procedures from data included in the databases relating to points, beacons, interception or altitude legs, etc .;
    - Performance database, (PERFDB) (1204), containing the aerodynamic and engine parameters of the aircraft;
    - Lateral trajectory (TRAJ) (1205), to build a continuous trajectory from the points of the flight plan, respecting the performance of the aircraft and the confinement constraints (RNP);
    - Predictions (PRED) (1206), to build an optimized vertical profile on the lateral and vertical trajectory and giving the estimates of distance, time, altitude, speed, fuel and wind especially on each point, updated with each change of parameter and calculated to the destination, which will be displayed to the crew. ;
    - Guidance (GUID) (1207), to guide the aircraft in the lateral and vertical planes on its three-dimensional trajectory, while optimizing its speed, using information calculated by the Predictions function (1206). In an aircraft equipped with an automatic piloting device (1210), the latter can exchange information with the guidance module (1207);
    - Digital data link (DATALINK) (1208) for exchanging flight information between the Flight Plan / Predictions functions and the control centers or other aircraft;
    - one or more screens, in particular so-called FMD, ND and VD screens which are: The FMD (“Flight Management Display” in English) is an interface, generally a display screen, which can be interactive (for example a touch screen) , allowing to interact with the FMS. For example, it allows you to define a route and trigger the calculation of the flight plan and the associated trajectory. It also makes it possible to consult the result of the calculation in textual form. The ND ("Navigation display" in English) is an interface, generally a display screen, which can be interactive (for example a touch screen), making it possible to consult the plane's lateral trajectory in two dimensions, seen from above. Different viewing modes are available (pink, map, arc, etc.) as well as on different scales (configurable). The VD (“Vertical Display” in English) is an interface, generally a display screen, which can be interactive (for example a touch screen), making it possible to consult the vertical profile in two dimensions, projection of the trajectory. As for the ND, different scales are possible for the VD.
    In an alternative embodiment, the device of the invention can be implemented at the level of an on-board computer separate from the FMS, of the “Electronic Flight Bag” (EFB) type according to the consecrated Anglicism. The EFB is an electronic information management device that helps flight crews perform flight management tasks. It is a computer platform which can host software applications specially developed to operate functions such as takeoff and centering performance calculations.
    The method then makes it possible (904) to recover the performance values of a set of positioning systems outside the aircraft. The main known positioning systems are radio navigation beacons on the ground (ex: VOR, TACAN, DME, LOC, MLS ...), inertial navigation systems (ex: 1RS, ADIRS, AHRS, etc ...) and satellite-based positioning systems (e.g. GNSS, GPS, GLONASS ...). Each type of positioning system is associated with navigation performance.
    In the next step (906), the method makes it possible to calculate for each segment 'i' of the list, a prediction of estimated navigation performance, taking into account the position of the segment 'i' considered and the time prediction passing through this segment, as well as data from positioning systems through inertial units, navigation beacons and satellite systems. As detailed below with reference to FIG. 11, the calculation of the estimated performance prediction (908) is based on an innovative use of the functionalities of the satellite reception systems on board the aircraft, and of information produced by the different position sensors. Advantageously, the method of the invention makes it possible to compare the information produced by the various positioning systems and to select for the calculation of the estimated performance prediction, that which offers the best navigation performance for each segment 'i', as a function the position of the segment and the predicted passage time.
    The output (910) of the method for calculating the prediction of the estimated navigation performance is the list of 'N' segments for the entire flight plan associated with the trajectory, with for each segment, the prediction for the estimated navigation performance (EPU_PREDIT ) calculated.
    According to one embodiment, the method for calculating the navigation performance prediction estimated over the entire flight plan is carried out at regular intervals, if no automatic restart event has appeared for a certain duration (15 minutes for example), to take into account satellite breakdowns, navigation beacon breakdowns or other events.
    In another embodiment, the method for calculating the estimated navigation performance prediction can be restarted automatically if the predictions of passage time on the segments change significantly, for example due to a change in speed, weather phenomena ( strong winds).
    In another variant, the calculation of the estimated performance prediction can be restarted following a restart of the calculation of the required performance prediction.
    FIG. 9b illustrates according to an embodiment of the invention, steps of the method for calculating the performance predictions required for a list of segments of a flight plan. The method begins with a step (903) of receiving a list of ‘N’ flight segments for a trajectory associated with a flight plan.
    In a following step (905) the method makes it possible to calculate for each segment of the list, a required performance prediction.
    For each segment 'i' in the list, the method makes it possible (907) to identify, via the information in the navigation database and the operator inputs, all of the contingencies giving the required navigation performance constraints, to select ( 909) the most restrictive contingency, and calculate (911) from the data of the selected contingency, a performance prediction required for the segment considered.
    When an operator defines a corridor width value, it is applicable on the current segment and on all the other segments of the entire list. However, if a regulation is associated with navigation performance, it is translated into the value of corridor width through the other options (Data base navigation, flight area) and can be more restrictive than the value entered by the operator. In the state of the art, when the value defined by the operator becomes a value greater than that corresponding to the regulations, the system sends a message to the pilot asking him to lower the value of the corridor to bring it into conformity with the regulations. Advantageously, with the method of the invention, for a given segment 'i', for the calculation of required performance prediction, the system takes the most restrictive contingency, that is to say that giving the value of the half -width of the corridor. The system only takes into account the contingency defined by the operator if the corridor value it defines is lower than that of the regulations. When the corridor is defined for a segment in the database, it corresponds to the performance regulations required for this segment and it is applicable, unless the pilot value is more restrictive. When neither an operator value nor a "Database" value exists for a segment, a default corridor value, determined according to the geographical area of flight (terminal, oceanic route, approach), is applied for this segment. Thus, when the corridor is defined for a segment with the default value, it corresponds to the performance regulations required for this segment and it is applicable unless the pilot value is more restrictive. Figure 14 illustrates which corridor value (Default, Driver, Database) is taken into account for a segment ‘i’.
    The output (913) of the method for calculating the required navigation performance is the list of 'N' segments for the entire flight plan associated with the trajectory, with for each segment, the required navigation performance prediction ( RPN) calculated.
    Thus, the purpose of the system for calculating the prediction of the required navigation performance is to define for each of the segments of the list, the required navigation performance which is applicable, that is to say which is in compliance with the regulations. .
    The calculation of the required navigation performance prediction is not restarted regularly or automatically. The calculation is restarted following a modification by the operator of the list of segments (by adding, deleting segments) or following a modification by the operator of the value of the corridor associated with a segment
    Advantageously, as illustrated in FIG. 9c, the method implemented by the device of the invention also makes it possible to combine the required navigation performance predictions (9020) with calculated estimated navigation performance predictions (9010). for the same list of segments (9000), in order to build (9030) a navigation corridor trajectory.
    Advantageously, two approaches are proposed to construct a corridor from the two types of performance predictions. In a first option, the method makes it possible to subtract the predicted performance from that required, so that it can never exceed the required stress, regardless of the position of the aircraft in this corridor. The advantage of this solution is that if a deterioration in navigation performance occurs, it is progressive and visible to the operator. The display resulting from this approach is illustrated in Figure 18.
    An alternative approach to constructing a corridor is to consider a corridor of width "1 x corridor" when the predicted performance is strictly lower than the required performance. If the predicted performance is greater than or equal to the required performance, the display reverts to a thread. In this case, the guarantee is not to stay inside the corridor but to guarantee never to cross the corridor twice as wide, which is the main safety objective. The advantage of this solution is that the aisle in which the aircraft can fly is wider. The display resulting from this approach is illustrated in Figure 19.
    According to various embodiments, the corridor can be displayed (9040) on request on a screen for the pilot in the form of a so-called “ribbon” trajectory according to different variants illustrated in FIGS. 15 to 20, the ribbon being obtained by a contrasting filling of the width of the corridor corresponding to the navigation latitude.
    The display device can be a conventional cockpit screen such as a “Navigation Display” (ND) or a “Primary Flight Display” (PFD) screen with a “Synthetic Visual System” (SVS) capacity as shown in FIG. 20 For a ground operator, this information can be displayed on a screen of the control station.
    The “ribbon” trajectory is constructed in such a way that it never leaves the contingency (width of the corridor) relative to the reference trajectory corresponding to the list of initial segments of the flight plan, illustrated in FIGS. 15 and 16. In the as a corridor is defined, the only representation of the points of the segments without drawing the wire which joins them is another example of representation proposed in figure 17.
    If on a segment, the predicted performance is higher than the required performance, the corridor becomes again a thread on the segment. Optionally, an alert message can be sent to the operator when this segment will soon become the active segment, in other words when this segment is close to the start of the list of segments.
    Thus, the pilot can choose to display or not:
    - the required navigation performance predictions for the segments;
    - predictions of estimated navigation performance of the segments;
    - the corridor resulting from the combination of the two predictions.
    Optionally, when displaying multiple flight plans, all displays can be temporarily disabled automatically or manually.
    FIG. 11 illustrates the step of calculating the estimated navigation performance prediction EPU for a segment ‘i’ of the list (step 908 of FIG. 9a).
    The method is described here for the calculation of the estimated horizontal navigation performance prediction, however the skilled person will transpose the principles of the method to the calculation of the estimated vertical navigation performance prediction.
    Advantageously, the method uses the functionalities of the satellite reception systems on board the aircraft for monitoring the satellites and detecting the faulty satellites. In particular, the method uses a capacity of these systems to predict the availability of satellites for a given date and place, a feature called "RAIM" for "Reliability, Availability, and Integrity Monitoring". Receivers equipped with RAIM technology are able to predict the integrity of GPS positioning signals received from satellites and able to detect by a function called "FDE" for "Fault Detection and Exclusion" the faulty satellites and exclude them from the calculation the position of the aircraft.
    The estimated navigation performance prediction is related to the number and position of available satellites at a given time or time.
    The process is iterative and operates segment after segment (1102,1124). For a segment ‘i’ (1102), the method makes it possible to determine (1104) if the satellite prediction is precise and available using the RAIM functionality. In the positive case, for any segment where the satellite prediction is precise and available, the method makes it possible to establish the prediction of navigation performance estimated as a function of the value of the predicted satellite performance, called "EPU_SATELLITE" (1110).
    To increase its accuracy, the method makes it possible to combine satellite information (1104) with information (1106) from systems based on inertial units (1RS, AHRS ...), for example to cover cases where the satellite system gives a aberrant aircraft position value (due for example to a transient loss of satellites). The inertial system will then passivate this response. Indeed, the inertial system drifts slowly and the aircraft position of the satellite system which is precise in the long term will passivate this drift by allowing the inertial system to readjust. The satellite system provides the value of its performance (1104) and by the use of the inertial system (1106) the method makes it possible to consolidate this value and calculate a prediction of estimated navigation performance called "EPU_HYBRID" (1108).
    Returning to the initial step (1104), if on a segment 'i' the satellite system is not available or has an inadequate performance compared to the required navigation performance (branch No), the method makes it possible to take into account counts the performance information provided by the other positioning systems - beacons and inertials. The method makes it possible to calculate (1112) the estimated navigation performance called EPUBALISES associated with the types of beacons available around the segment ΐ which do not have satellite information (without RAIM), and makes it possible to calculate (1114) the estimated navigation performance , called EPUJNERTIE, associated with inertial systems, taking into account the inertial drift on the segment 'i' "without RAIM". Then the method makes it possible to compare (1116) the values EPU_BALISES and EPUJNERTIE and take the value (1118, 1120) corresponding to the best performance. As described, the method calculates the EPU BEACONS value (1112) only when the RAIM capacity is not available. To do this, the system searches whether in the geographical area of the segment ‘i’ "without RAIM", radio navigation beacons exist (VOR, TACAN, DME, LOC, ILS, MLS ...). If so, the process calculates the estimated performance associated with the tags based on the available tags. For example, the EPU_BALISES is around 4Nm for VOR tags while it can be around 0.3Nm for DME tags. The EPU_BALISES for the segment ‘i’ is compared (1116) to the EPUJNERTIE of the same segment ‘i’ whose calculation is described below. Similarly, the method only calculates the value of the LOSS (1114) only when the RAIM capacity is not available. Inertial systems (1RS, AHRS) have a variable EPUJNERTIE value over time because of their intrinsic drift which is of the order of 2Nm to 4Nm per hour depending on the performance of the systems and in the absence of registration by the satellite position. When the RAIM capacity becomes unavailable for a first segment ‘i’ (1202), as described with reference to FIG. 12, the method initializes (1204) the EPUJNERTIEJ of this segment with the last value of the EPU_SATELLITE. After a first RAIM unavailability, for the following segments which have a RAIM capacity not available (branch no, 1206), the EPUJNERTIE of the corresponding segment 'i' is the EPUJNERTIE of the segment Ί-Τ increased by the drift of the inertial system which is proportional to the travel time of segment 'i'. The drift can be estimated linearly along the segment. Such an operation can be continued iteratively as long as the value of the segment EPUJNERTIE remains lower than that of the EPU_BALISES.
    Thus for each segment 'i' of the list, the method calculates (1122) an EPU value of the segment 'predicted EPU', and iterates over the next segment 'N + T (1124) so as to generate a list of' N 'segments with an estimated navigation performance prediction calculated for each segment (910).
    In general, the UPR has a value dependent on the positioning systems available. For example, the satellite system achieves EPU_SATELLITE (1110) of the order of 0.1 Nm.
    Advantageously, the method makes it possible to determine whether the length of a segment of the list is too long, with regard to the configuration of the satellites or the presence of ground beacons. In such a case, the method makes it possible to split the segment into several fixed length sub-segments, so as to obtain an adequate predicted performance value. A maximum segment length can be set, such as equal to 100Nm for example. In an alternative, another method for cutting a segment that is too long is to use the RAIM response which in current systems gives the "RAIM" state for -15mn, -5mn, Omn, + 5mn and + 15mn compared to the segment position.
    Figure 13 illustrates the type of EPU considered for several segments according to the availability or not of the RAIM functionality. Before the RAIM loss, the prediction provided is based on the EPU_SATELLITE. After the RAIM loss, at the next end point (PF), the prediction provided is based on the LOCKOUT as long as it is less than the EPU_BALISES and becomes based on the EPU_BALISES after the next end point where it becomes higher.
    Although the methods for calculating the required and estimated navigation performance prediction have been described for a horizontal navigation performance prediction, a corresponding calculation of the navigation performance prediction may be applied to the vertical axis of the trajectory d 'an aircraft.
    As for the horizontal axis, there exists on the vertical axis, the "Total System Error" (TSEz) in z (vertical axis) which represents the error in the calculation of the vertical position, in other words the altitude of an aircraft. This error shown in Figure 21 has three components, and is expressed by the following equation:
    TSE Z = V (FTE Z ) 2 + (HCE) 2 + (ASE) 2 where
    - "Flight Test Error vertical" (FTEz) corresponds to the vertical guidance error of the aircraft in manual or automatic mode;
    - "Horizontal coupling Error" (HCE) corresponds to the error induced by the lateral error (horizontal coupling error); and
    - "Altimetry System Error" (ASE) corresponds to the error of the altimetry system in the calculation of the altitude of the aircraft from radio position, inertial or satellite sensors.
    There are regulatory requirements relating to the deviation between a reference vertical profile and the aircraft, of the order of 250ft at high altitude, and of the order of 150ft at low altitude. These requirements which define the required vertical performance are the inputs to the calculation of the required vertical performance prediction and can be represented as a vertical corridor.
    According to the same principle as for the calculation of the horizontal performance prediction, the method for calculating the vertical performance prediction takes into account the different vertical positioning systems with their associated precision. The main known systems are satellite positioning systems (eg GPS, GLONASS, etc.), systems based on barometric or radio pressure (Air Data Computer ADC, Radio Altimeter RA) and navigation systems based on inertia ( ex: 1RS, ADIRS, AHRS, etc ...). Taking into account the vertical position sensors, an estimate of the vertical performance is established according to the available sensors. This estimate is the basis for calculating the estimated vertical performance prediction.
    The method of calculating the required and estimated performance predictions makes it possible to construct a vertical navigation corridor which can be displayed on request on a screen for the pilot. The vertical "ribbon" profile is constructed so as never to leave the contingency "2 x the width of the corridor" (2 times the deviation tolerance) vertical compared to the vertical reference profile corresponding to the list of segments.
    Figures 22 and 23 illustrate variants of vertical corridor display on a "Vertical display" (VD) or on a "Primary Flight Display" (PFD) having a "Synthetic Visual System 3D" (SVS 3D). The system can display the vertical ribbon profile for the required and estimated predictions based on dotted lines as illustrated in FIG. 21. Another proposal for the display of this ribbon trajectory by the display system is provided in FIG. 22.
    According to an implementation mode, the method for calculating the predictions estimated and required on a list of segments is carried by a specific partition of a hardware platform specific to the avionics but different from that of the FMS. According to another preferred embodiment, this calculation is carried out on the FMS execution platform, by components suitable for the calculations. The advent of integrated modular avionics on recent aircraft has made it possible to define platforms for execution and digital communication between functions. This development has, however, led to an increase in complexity - notably the internal complexity of functions but also the complexity of the process of configuring the avionics system - and the growing need for performance and optimization of resources. In this context, the new hardware platforms are equipped with management (operations, security and maintenance), energy optimization and localization capabilities, which go beyond the standard functions of known platforms. According to another aspect, the invention relates to a computer program product comprising code instructions making it possible to carry out the steps of the method according to the invention. The process can be implemented using hardware and / or software elements. The method may be available as a computer program product on a computer readable medium. The method can be implemented on a system that can use one or more dedicated electronic circuits or a general-purpose circuit. The technique of the method according to the invention can be carried out on a reprogrammable calculation machine (a processor or a microcontroller for example) executing a program comprising a sequence of instructions, or on a dedicated calculation machine (for example a set of doors logic like an FPGA or an ASIC, or any other hardware module). The different modules of the system according to the invention can be implemented on the same processor or on the same circuit, or distributed over several processors or several circuits. The modules of the system according to the invention consist of calculation means including a processor. The reference to a computer program which, when executed, performs any of the functions described above, is not limited to an application program running on a single host computer. On the contrary, the terms computer program and software are used here in a general sense to refer to any type of computer code (for example, application software, firmware, microcode, or any other form of computer instruction) which can be used to program one or more processors to implement aspects of the techniques described here.
    权利要求:
    Claims (18)
    [1" id="c-fr-0001]
    Claims
    1. Method for calculating the navigation performance prediction required for an aircraft trajectory, the method being operated by an aircraft calculation platform and comprising the steps of:
    - receive a list of segments of a flight plan;
    - for each segment of the list:
    - identify all the contingencies constituting navigation performance constraints;
    - determine and select the most restrictive contingency for said segment;
    - calculate a required navigation performance prediction, based on data from the contingency selected;
    and
    - update the list of segments with the required navigation performance prediction associated with each segment.
    [2" id="c-fr-0002]
    2. The method according to claim 1, in which the identification step consists in identifying the contingencies existing in the navigation database and the contingencies defined by an operator.
    [3" id="c-fr-0003]
    3. The method according to claim 2 or 3 in which the determining step consists in determining if a performance quota given by a regulation is the most restrictive, and selecting it.
    [4" id="c-fr-0004]
    4. The method according to any one of claims 1 to 3 wherein the calculation of the required navigation performance prediction is made according to default values when no navigation performance constraint is identified.
    [5" id="c-fr-0005]
    5. The method according to any one of claims 1 to 4 in which the steps are performed for a calculation of prediction of required horizontal navigation performance and / or for a calculation of prediction of required vertical navigation performance.
    [6" id="c-fr-0006]
    6. The method according to any one of claims 1 to 5 wherein the steps are automatically re-executed if the flight plan changes.
    [7" id="c-fr-0007]
    7. A device for calculating navigation performance prediction required for an aircraft trajectory, the device comprising:
    - means for receiving a list of segments of a flight plan;
    - means allowing for each segment of the list:
    - to identify all the contingencies constituting constraints of
    15 navigation performance;
    - to determine and select the most restrictive contingency for said segment;
    - calculate a required navigation performance prediction, based on data from the selected contingency;
    20 and
    - means for updating the list of segments with the required navigation performance prediction associated with each segment.
    [8" id="c-fr-0008]
    8. The device according to claim 7 in which the means are capable of carrying out the steps of the method according to any one of claims 2 to
    6.
    [9" id="c-fr-0009]
    9. Flight management system (FMS) or on-board computer of the EFB type comprising a device for calculating a prediction of navigation performance required for an aircraft trajectory according to claim 7 or 8.
    [10" id="c-fr-0010]
    10. A computer program product, said computer program comprising code instructions making it possible to carry out the steps of the method according to any one of claims 1 to 6, when said program is executed on a computer.
    [11" id="c-fr-0011]
    11. Method for displaying predictions of navigation performance estimated and required for an aircraft trajectory, the method being operated by an aircraft calculation platform and comprising the steps of:
    - calculate predictions of estimated navigation performance for a list of segments of a flight plan;
    - calculate for the same list of segments, predictions of navigation performance required according to the process steps of any one of claims 1 to 6;
    and
    - represent graphically on a display means said predictions of estimated and required navigation performance.
    [12" id="c-fr-0012]
    12. The method according to claim 11 in which the step of calculating predictions of estimated navigation performance comprises the steps of:
    - receive a list of segments comprising all the segments of a flight plan with a prediction of a passage time associated with each segment;
    - for each segment of the list:
    - identify the positioning systems external to the aircraft available in the geographic area of said segment;
    - determine the performance values of the identified positioning systems and select the external positioning system with the lowest navigation performance calculation error for the position of said segment and said predicted passage time;
    - calculate an estimated navigation performance prediction, from data from the selected external positioning system;
    and
    - update the list of segments with the estimated navigation performance prediction associated with each segment.
    [13" id="c-fr-0013]
    13. The method according to claim 11 or 12 wherein the graphical representation consists of displaying, over a wire trajectory, said predictions of estimated and required navigation performance.
    [14" id="c-fr-0014]
    14. The method according to any one of claims 11 to 13 comprising, before the display step, a step consisting for each segment to be subtracted from the required navigation performance predictions, the estimated navigation performance predictions, to construct a corridor trajectory, and in which the graphical representation consists in displaying said predictions of navigation performance estimated and required as a function of the corridor.
    [15" id="c-fr-0015]
    15. The method according to claim 14, in which the display step consists in displaying a wire path for the segments having an estimated navigation performance prediction greater than the required navigation performance prediction.
    [16" id="c-fr-0016]
    16. The method according to claim 14 or 15 in which the graphic representation consists in representing the navigation latitude in contrast on the corridor trajectory.
    [17" id="c-fr-0017]
    17. Device for displaying predictions of estimated navigation performance and required for an aircraft trajectory, the display device comprising a display means and calculation means making it possible to calculate predictions of estimated navigation performance and required, the required navigation performance predictions being calculated according to the method steps of any one of claims 1 to 6, the device further comprising means for graphically representing on said display means said navigation performance predictions estimated and required.
    [18" id="c-fr-0018]
    18. The display device according to claim 17 wherein the display means is a screen of the aircraft cockpit, such as a "Navigation Display" (ND) or a "Primary Flight Display" (PFD) screen.
    1/18
    LL
    I
    2/18
    类似技术:
    公开号 | 公开日 | 专利标题
    EP2573586B1|2014-09-10|Method and system for piloting an aircraft during runway approach
    EP1902276B1|2014-01-08|Device for assisting a vertical guidance approach for aircraft
    CA2457278C|2011-07-12|Process and device to assist the piloting of an aircraft on a non-precision approach during the landing phase
    FR3021107A1|2015-11-20|METHOD FOR AIDING NAVIGATION OF AN AIRCRAFT WITH CORRELATION OF DYNAMIC INFORMATION WITH A 4D FLIGHT TRACK
    FR2940426A1|2010-06-25|DEVICE FOR ASSISTING THE CHOICE OF A DEROUTEMENT AIRPORT
    FR2898972A1|2007-09-28|Aircraft`s minimal flight altitude monitoring method for use in terrain awareness and warning system, involves generating alert message based on relative position of vertical flight profile with respect to minimal vertical flight profile
    FR2906921A1|2008-04-11|Three dimensional emergency path providing method for aircraft, involves updating searched path based on changes in environmental conditions according to information provided by on-board sensors and exterior information
    FR2916840A1|2008-12-05|METHOD AND DEVICE FOR CALCULATING A FLIGHT PLAN
    FR3025920A1|2016-03-18|METHOD FOR REAL-TIME CALCULATION OF A PLANNED TRACK, IN PARTICULAR A FLIGHT PLAN, COMBINING A MISSION, AND A SYSTEM FOR MANAGING SUCH A TRAJECTORY
    EP3244977B1|2021-04-28|Method and system for displaying information relating to an aircraft, device for producing said information and related computer program product
    FR2949897A1|2011-03-11|AIRCRAFT ASSISTING ASSISTANCE METHOD AND CORRESPONDING DEVICE.
    FR3021401A1|2015-11-27|RECONFIGURATION OF THE DISPLAY OF A FLIGHT PLAN FOR THE PILOTAGE OF AN AIRCRAFT
    FR3038750A1|2017-01-13|METHOD FOR INTEGRATING A NEW NAVIGATION SERVICE IN AN OPEN AIR ARCHITECTURE OPEN ARCHITECTURE SYSTEM OF A CLIENT-SERVER TYPE, IN PARTICULAR A FIM MANUFACTURING SERVICE
    FR3053780A1|2018-01-12|APPARATUS AND METHOD FOR CALCULATING NAVIGATION PERFORMANCE PREDICTION
    EP1465136B1|2006-05-17|Method and apparatus for on-board pilot assistance in the absence of air traffic control
    EP1057160A1|2000-12-06|Assistance system for avoiding terrain collision for an aircraft
    EP3267156B1|2019-08-21|Calculation device and method for predicting estimated navigation performance
    FR2904706A1|2008-02-08|Aircraft`s e.g. civil transport aircraft, steering assisting method, involves determining minimal decision height corresponding to arrival instant based on performances of satellite localization unit and arrival characteristics of aircraft
    FR3007545A1|2014-12-26|SYSTEM METHOD AND COMPUTER PROGRAM FOR PROVIDING A MACHINE MAN INTERFACE DATA RELATING TO AN ASPECT OF THE OPERATION OF AN AIRCRAFT
    FR3008818A1|2015-01-23|DEVICE AND METHOD FOR PREDICTING THE PRECISION, THE INTEGRITY AND AVAILABILITY OF THE POSITION OF AN AIRCRAFT ALONG A TRACK.
    FR3030794A1|2016-06-24|METHOD AND SYSTEM FOR GUIDING AN AIRCRAFT
    FR3058555A1|2018-05-11|UNIFORMIZATION OF PLATFORM APPROACHES FOR AIRCRAFT
    FR3026214A1|2016-03-25|METHOD FOR MANAGING ALERTS
    FR2994010A1|2014-01-31|DEVICE AND METHOD FOR MANAGING NAVIGATION POINT JOINT STRATEGY
    EP2369297B1|2013-09-25|Flight assistance device for aircraft
    同族专利:
    公开号 | 公开日
    US20180012503A1|2018-01-11|
    US10866592B2|2020-12-15|
    CN107591032B|2021-06-29|
    FR3053780B1|2018-07-06|
    CN107591032A|2018-01-16|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20040189492A1|2003-03-26|2004-09-30|Selk Louis G.|Graphical display for aircraft navigation|
    US20110301842A1|2010-06-08|2011-12-08|Honeywell International Inc.|Display of navigation limits on an onboard display element of a vehicle|
    DE19614801A1|1996-04-15|1997-10-16|Vdo Luftfahrtgeraete Werk Gmbh|Method and device for displaying flight guidance information|
    US6278965B1|1998-06-04|2001-08-21|The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration|Real-time surface traffic adviser|
    US6389355B1|1999-09-14|2002-05-14|Honeywell International Inc.|Methods and apparatus for graphical display and editing of flight plans|
    US7164383B2|2002-09-25|2007-01-16|The Board Of Regents Of The University Of Oklahoma|Navigation system using locally augmented GPS|
    FR2853978B1|2003-04-16|2006-02-03|Eurocopter France|METHOD AND DEVICE FOR SECURING THE FLIGHT OF AN AIRCRAFT IN FLIGHT CONDITIONS TO INSTRUMENTS OUTSIDE INFRASTRUCTURE OF FLIGHT TO INSTRUMENTS|
    FR2861871B1|2003-11-04|2006-02-03|Thales Sa|METHOD FOR MONITORING THE FLOW OF THE FLIGHT PLAN OF A COOPERATIVE AIRCRAFT|
    IL159893A|2004-01-15|2008-11-26|Rafael Advanced Defense Sys|Method of terrain following|
    FR2870606B1|2004-05-18|2010-10-08|Airbus France|METHOD AND DEVICE FOR SECURING A LOW ALTITUDE FLIGHT OF AN AIRCRAFT|
    US7366591B2|2004-06-21|2008-04-29|Honeywell International, Inc.|System and method for vertical flight planning|
    US7421319B2|2004-10-25|2008-09-02|Arinc Inc.|Systems and methods for preflight planning and inflight execution using portable electronic data storage and display devices|
    FR2881534B1|2005-02-01|2007-04-20|Airbus Sas|METHOD AND DEVICE FOR DETERMINING THE WIDTH OF A SAFETY CORRIDOR FOR AN AIRCRAFT, AND METHOD AND SYSTEM FOR SECURING AUTOMATIC LOW ALTITUDE FLIGHT OF AN AIRCRAFT|
    US7548196B2|2005-02-15|2009-06-16|Fagan John E|Navigation system using external monitoring|
    US7437225B1|2005-07-29|2008-10-14|Rockwell Collins, Inc.|Flight management system|
    US7876238B2|2005-12-22|2011-01-25|The Boeing Company|Methods and systems for displaying procedure information|
    US8164485B2|2006-04-13|2012-04-24|The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration|System and method for aiding pilot preview, rehearsal, review, and real-time visual acquisition of flight mission progress|
    FR2913800B1|2007-03-13|2010-08-20|Thales Sa|DEVICES AND METHODS FOR FILTERING FIELD ANTI-COLLISION ALERTS AND OBSTACLES FOR AN AIRCRAFT|
    US7782229B1|2007-06-28|2010-08-24|Rockwell Collins, Inc.|Required navigation performance scales for indicating permissible flight technical error |
    US9237313B2|2008-04-04|2016-01-12|The Boeing Company|Transverse vertical profile display for aeronautical routes|
    US8155800B2|2008-06-19|2012-04-10|Honeywell International Inc.|System for displaying required navigation performance on a horizontal situation indicator|
    US20100023187A1|2008-07-28|2010-01-28|Honeywell International Inc.,|System and method for displaying constraint information on a graphical aircraft instrument tape element|
    US7965202B1|2008-09-26|2011-06-21|Rockwell Collins, Inc.|System, system, module, and method for presenting an abbreviated pathway on an aircraft display unit|
    US9316506B2|2008-10-16|2016-04-19|The Boeing Company|Method and apparatus for displaying vertical terrain information|
    FR2949897B1|2009-09-04|2012-08-03|Thales Sa|AIRCRAFT ASSISTING ASSISTANCE METHOD AND CORRESPONDING DEVICE.|
    US9494447B2|2010-07-28|2016-11-15|Honeywell International Inc.|Methods and systems for attitude differentiation in enhanced vision images|
    US9558668B2|2010-10-26|2017-01-31|Honeywell International Inc.|Systems and methods for improving an in-trail procedures request|
    FR2968785B1|2010-12-09|2014-07-11|Airbus Operations Sas|METHOD AND DEVICE FOR AUTOMATICALLY MONITORING THE CAPACITY OF AN AIRCRAFT TO FOLLOW A FLIGHT TRACK COMPRISING AT LEAST ONE TURN.|
    EP2530433B1|2011-06-01|2015-04-22|Harman Becker Automotive Systems GmbH|Method of generating a database for a navigation device|
    FR2983598B1|2011-12-06|2013-12-27|Airbus Operations Sas|METHOD FOR AUTOMATIC MONITORING OF AIR OPERATIONS REQUIRING GUARANTEE OF NAVIGATION PERFORMANCE AND GUIDANCE|
    US20130345905A1|2012-06-25|2013-12-26|Honeywell International Inc.|Avionics display system providing enhanced flight-plan management|
    US8798922B2|2012-11-16|2014-08-05|The Boeing Company|Determination of flight path for unmanned aircraft in event of in-flight contingency|
    US9061770B2|2013-01-28|2015-06-23|Honeywell International Inc.|Electronic flight bag systems and methods for verifying correct takeoff performance data entry|
    US9527601B2|2013-02-05|2016-12-27|Honeywell International Inc.|Method and apparatus for generating a virtual inner marker for an aircraft landing approach|
    FR3006049B1|2013-05-24|2016-01-01|Thales Sa|METHOD AND SYSTEM FOR SELECTING AN APPROACH TRACK|
    FR3010807B1|2013-09-13|2015-10-09|Airbus Operations Sas|METHOD AND DEVICE FOR AIDING THE CONTROL OF AN AIRCRAFT DURING AN APPROACH PHASE FOR LANDING.|
    EP2889579B1|2013-12-31|2018-02-14|The Boeing Company|System and method for defining and predicting aircraft trajectories|
    FR3017967B1|2014-02-21|2016-03-04|Thales Sa|METHOD AND SYSTEM FOR FLIGHT MANAGEMENT|
    US10665114B2|2014-03-28|2020-05-26|The Boeing Company|Aircraft fuel optimization analytics|
    CN103927906B|2014-04-29|2016-10-12|北京威胜通达科技有限公司|The method of Big Dipper independent navigation based on Big Dipper short message and 4G communication pattern|
    FR3025920B1|2014-09-15|2016-11-04|Thales Sa|METHOD FOR REAL-TIME CALCULATION OF A PLANNED TRACK, IN PARTICULAR A FLIGHT PLAN, COMBINING A MISSION, AND A SYSTEM FOR MANAGING SUCH A TRAJECTORY|
    US9666084B2|2014-12-19|2017-05-30|Rockwell Collins, Inc.|Display and control of time evolved conditions relative to a vehicle|
    US9524647B2|2015-01-19|2016-12-20|The Aerospace Corporation|Autonomous Nap-Of-the-Earth flight path planning for manned and unmanned rotorcraft|
    US9464901B1|2015-05-28|2016-10-11|Rockwell Collins, Inc.|RNP-scaled waypoint symbology generating system, device, and method|
    GB2529551B|2015-07-22|2016-07-20|Via Tech Ltd|Method for detecting conflicts between aircraft|
    EP3147885A1|2015-09-28|2017-03-29|The Boeing Company|Automated aircraft intent generation process based on specifications expressed in formal languages|
    US10721259B2|2016-03-31|2020-07-21|The Boeing Company|System and method for automatic generation of filter rules|US10140873B2|2016-08-16|2018-11-27|The Boeing Company|Performance-based track variation for aircraft flight management|
    CN110308743B|2019-08-05|2021-11-26|深圳市道通智能航空技术股份有限公司|Aircraft control method and device and aircraft|
    CN112859914A|2021-01-13|2021-05-28|中山大学|Trajectory planning-based hypersonic aircraft reentry safety control method and system|
    法律状态:
    2017-06-28| PLFP| Fee payment|Year of fee payment: 2 |
    2018-01-12| PLSC| Search report ready|Effective date: 20180112 |
    2018-06-28| PLFP| Fee payment|Year of fee payment: 3 |
    2020-06-25| PLFP| Fee payment|Year of fee payment: 5 |
    2021-06-24| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1601060|2016-07-07|
    FR1601060A|FR3053780B1|2016-07-07|2016-07-07|APPARATUS AND METHOD FOR CALCULATING NAVIGATION PERFORMANCE PREDICTION|FR1601060A| FR3053780B1|2016-07-07|2016-07-07|APPARATUS AND METHOD FOR CALCULATING NAVIGATION PERFORMANCE PREDICTION|
    US15/642,248| US10866592B2|2016-07-07|2017-07-05|Device and method for calculating required navigation performance prediction|
    CN201710551735.7A| CN107591032B|2016-07-07|2017-07-07|Apparatus and method for calculating a required navigation performance prediction|
    [返回顶部]