• 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 contributing to the securing of a synthetic vision display of an aircraft (10) for displaying on a display means (2,6) an at least partial perspective view (8) of the environment of said aircraft (10) and control symbology (9). During this process, at least one control point (P1, P2, P3) located in said environment is defined and forming with a reference point (Pr) of said aircraft (10) a first line (DP). Next, a display function F1 calculates the display coordinates (a1, b1), (a2, b2), (a3, b3) of each control point (P1, P2, P3) on said control means. visualization (2,6), then the inverse (F2) -1 of a second display function F2 is calculated and from the said display coordinates (a1, b1), (a2, b2), (a3 , b3) a second straight line (Ds) passing through said reference point (Pr). Finally, comparing said first and second lines (DP, Ds) corresponding to a same control point (P1, P2, P3) to define whether said synthetic vision display is integral.
    公开号:FR3021771A1
    申请号:FR1401230
    申请日:2014-05-28
    公开日:2015-12-04
    发明作者:Adrien Ott
    申请人:Airbus Helicopters SAS；
    IPC主号:
    专利说明:

    [0001] 1 Contributing method of securing a synthetic graphic representation of the external view of an aircraft. The present invention is located in the field of aircraft avionics and in particular visual devices for steering assistance and navigation. The present invention relates to a method contributing to the securing of a synthetic graphic representation of the external view of an aircraft and a synthetic vision device provided with such a method contributing to securing.
    [0002] Aircraft avionics provides extensive information to the pilot and / or co-pilot on both aircraft parameters and flight conditions as well as navigation. Recent developments in the field of avionics include displaying on a visualization means, such as a screen fixed in the cockpit of the aircraft or a head-up display system integrated for example the helmet of the pilot of the aircraft, a synthetic graphic representation of the external view of this aircraft. Such a synthetic graphical representation of the external view of this aircraft may be in perspective and is generally constructed from mathematical functions as well as software means such as a perspective plot software. This graphical representation is based on one hand on at least one database of the environment of the aircraft and on the other hand on the known position of the aircraft in this environment.
    [0003] Each database of the environment of the aircraft can comprise in particular information on the terrain and the terrain surrounding the aircraft as well as the positions in this environment of different particular elements such as obstacles and landing zones for example . The position of the aircraft can be obtained, inter alia, by a satellite tracking device of which the aircraft is equipped. In addition, this synthetic graphical representation can take into account the aircraft's route, that is to say the direction in which the aircraft flies, as well as its heading, which defines the orientation of the aircraft by example report to the magnetic north, and its attitude, which corresponds to its inclination around the axes of roll, pitch and yaw of the aircraft. This synthetic graphical representation is then oriented on the visualization means to be consistent with the actual view of the pilot of the aircraft, in accordance with the heading and attitude information of the aircraft. The axes of roll, pitch and yaw are characteristic axes of an aircraft. The roll axis is in a longitudinal direction extending from the front of the aircraft towards the rear of the aircraft, the yaw axis is in a direction of elevation extending from bottom to top perpendicular to the longitudinal direction and the pitch axis is in a transverse direction extending from right to left perpendicular to the longitudinal and elevation directions. This heading and attitude information is, for example, provided by a means for determining heading and attitude known by the acronym AHRS corresponding to the English designation "Attitude and Heading Reference System".
    [0004] The synthetic graphic representation of the exterior view of an aircraft is generally designated by the acronym SVS designating in English "Synthetic Vision System". Moreover, it may be superimposed on this synthetic graphical representation additional pilotage information often referred to by the term "pilotage symbology". This control symbology notably comprises an attitude symbology representing attitude and inclination references such as a skyline symbol, a scale of attitude on either side of the skyline. and an inclination scale thus representing the pitch and the roll of the aircraft. This attitude information is generally provided by AHRS type heading and attitude determining means and graphically transcribed on the display means using a dedicated display function. The control symbology may also comprise particular landmarks corresponding, for example, to the position of land or landing zones located in the environment of the aircraft. For example, US 7352292 discloses a synthetic graphical representation system from a database and sensor information present on the aircraft. This graphical representation is a combination of data from the sensors and information from the database. The database is also updated during the 20 flights of the aircraft with the data from the sensors. In addition, the display of the synthetic graphical representation and / or control symbology can be monitored to ensure the validity of the displayed information. This monitoring can be done in different ways.
    [0005] For example, the securing of a display can be provided by a feedback mechanism, i.e. the initial data generated by this display are computed from the displayed information and the results of this display are compared. calculation with the initial data. Such a feedback mechanism may also be referred to by its terminology in English "feedback".
    [0006] The document FR2670591 describes such a system for securing information for piloting an aircraft. This security system performs a retroactive calculation of the navigation parameters from the information displayed and compares the information thus obtained with the data directly from the sensors of the aircraft. An alarm is then issued if a difference greater than a predefined threshold is reached. The calculation of the information initially displayed and the retroactive calculation of the navigation parameters are performed by the same function.
    [0007] It is also possible to implement two dissimilar and parallel graphical generation channels in order to secure such a display. We can then compare these two graphical representations generated parallel possibly by two separate calculation means.
    [0008] US 7342512 discloses a display system for an aircraft having a comparison computer for controlling this display. This comparison calculator performs a calculation independently of the display device of a selection of points actually displayed from the corresponding information provided by the sensors used by the display device and compares the results with the points actually displayed. If a significant discrepancy exists, an error message is displayed. In addition, document US7212715 describes a system 25 comparing the information displayed on a display screen and data of the aircraft. If this information displayed and the data of the aircraft are different, no information is displayed on this display screen. In addition, EP1875439 discloses a graphical generation device including means for monitoring the display of this graphical generation. These monitoring means make it possible to prohibit the use of certain functions that can generate the display of recurring symbols. These monitoring means also make it possible to generate and control images dedicated to the surveillance as well as to monitor certain state variables internal to the graphical generation device. Document US8243098 discloses a display device for an authoritative image composed in fact of several sub-images 10 combined with one another. The authoritative image can be compared with an original image to validate this original image. Finally, the document FR2963690 describes a mechanism for securing a client / server computer system making it possible on the one hand to prevent the accidental triggering of a function and, on the other hand, to guarantee the integrity of the functions and the coherence of the functions. information exchanged between the client and the server. This security mechanism uses computer signatures and the establishment of feedback circuits. Furthermore, in the field of aircraft, standards 20 set the safety conditions applicable to the various systems and devices used, for example avionics systems, including the effects of a defect on such a system. Five levels of criticality of a system, designated by the acronym DAL corresponding to the English designation "Design Assurance Level" are thus defined by the aeronautical standard "ARP4754A" and used for example in the standard "DO-254" . DAL level A is the most critical level, a defect that can cause a catastrophic problem that may result in an aircraft crash. On the other hand, the level DAL E is the level 3021771 6 less critical, a defect can then cause a problem without effect on the safety of the flight of the aircraft. In fact, the avionics systems of criticality level DAL A are intact and designed to limit the risk of occurrence of defects. Such systems generally include control and security devices to detect the occurrence of defects. The avionics systems of criticality level DAL A are then the safest and most reliable of the aircraft. The display of the control symbology generally has a criticality level DAL A, the knowledge of the attitude of the aircraft being important, or even essential, for the control of the flight of the aircraft and, consequently, the realization a safe flight. The display of the control symbology thus meets the requirements of integrity and dependability necessary for its use as an aid to the piloting and navigation of the aircraft. On the other hand, the synthetic graphic representation of the external view of an aircraft does not today have a criticality level DAL A. In particular, the orientation of the perspective representation on the visualization means of the aircraft , which takes into account the heading and attitude of the aircraft, is not monitored. As a result, its good positioning vis-à-vis the heading and the trim of the aircraft is not guaranteed. In fact, this synthetic graphical representation does not meet the requirements of reliability, integrity and dependability necessary for its use as a steering and navigation aid. In this way, the synthetic graphical representation of the external view of an aircraft must be taken into account as simple information provided to the pilot of the aircraft, without being used as piloting and navigation aids. Such a synthetic graphical representation is generally now in accordance with a criticality level DAL C. The object of the present invention is therefore to propose a method that contributes to securing a synthetic graphic representation of the external view of a aircraft, the common use of which with other processes or other complementary independent means makes it possible to claim conformity of the display at a criticality level DAL A or DAL B. This synthetic graphic representation thus has a 10 level of reliability, integrity and operational safety sufficient to be used as a flight and navigation aid. These additional independent methods or means for claiming conformity of the display at such a criticality level are, for example, a method or means for satellite positioning of the aircraft, a method or means for determining the heading and the attitude, such as an AHRS type means, as well as a database of the environment of the aircraft. Such a database of the environment of the aircraft can be a database of terrain, navigation or obstacles. The subject of the present invention is a method that contributes to securing a synthetic graphical representation of the external view of an aircraft, this aircraft comprising at least one display means on which a view at least one view can be displayed. partial perspective of the environment of the aircraft and secondly a steering symbology. The aircraft is characterized by three privileged directions, the axes of roll, pitch and yaw. The roll axis is in a longitudinal direction extending from the front of the aircraft towards the rear of the aircraft, the yaw axis is in a direction of elevation extending from below. at the top perpendicular to the longitudinal direction and the pitch axis is in a transverse direction extending from right to left perpendicular to the longitudinal and elevation directions. In addition, the heading of the aircraft corresponds to the roll axis of the aircraft. During this method, which contributes to securing a synthetic graphic representation of the external view of an aircraft, at least the heading and the attitude of the aircraft and a reference point Pr of the aircraft characterized by first coordinates in a terrestrial reference, at least one control point P1, P2, P3 located in the environment of the aircraft is defined, the position of a first line Dp1, Dp2, Dp3 passing through each point of P1, P2, P3 control and the reference point Pr of the aircraft being known with respect to roll axes, pitch and yaw of the aircraft, is calculated by a first display function F1 the 20 coordinates of display (a1, b1), (a2, b2), (a3, b3) of each control point P1, P2, P3 on the display means, - the inverse (F2) -1 of a second is calculated display function F2 and from the display coordinates (a1, b1), (a2, b2), (a3, b3) corresponding to each control point P1, P2, P3 a second straight line Dsi, Ds2, Ds3 passing through the reference point Pr of the aircraft, the first display function F1 and the second display function F2 being distinct, - comparing each first line Dp1 , Dp2, Dp3 and each second second line Ds1, Ds2, Ds3 corresponding to the same control point P1, P2, P3, and it is defined that the at least partial perspective view of the environment of the aircraft is integrates if the first and second straight lines Dp, Ds corresponding to the same control point P1, P2, P3 have an angular difference less than or equal to a predetermined margin. Under these conditions, the aircraft comprises a synthetic vision display device of a synthetic graphic representation of the external view of an aircraft. This synthetic graphic representation of the external view of an aircraft is displayed on at least one visualization means that the aircraft comprises and represents, among other things, an at least partial perspective view of the external environment of the aircraft placed behind. of a steering symbology. This at least partial perspective view of the external environment of the aircraft 15 consists of a representation of the surrounding relief with possibly particular elements such as land or landing zones, buildings. This at least partial perspective view of the external environment of the aircraft is oriented taking into account the heading and attitude of the aircraft to be representative for example of the direct vision of the environment that to the pilot of the aircraft through a transparent windshield of the aircraft. In another representation used in particular flight phases of the aircraft, the display reference may be the instantaneous route followed by the aircraft instead of its heading. This display means may be for example a screen or a head-up display device. The method according to the invention uses the heading and the attitude of the aircraft, which are necessary information for the pilot of the aircraft in order to control the aircraft efficiently and serenely. The heading and the attitude of the aircraft are for example provided by an instrument of the AHRS type embedded in the aircraft. The course is generally characterized by a direction in a terrestrial reference and the attitude by angles with respect to roll, pitch and yaw axes of the aircraft. The directions of these axes of roll, pitch and yaw generally form a local coordinate system 5 linked to the aircraft and are also known in the terrestrial reference, for example by means of the AHRS type instrument and a satellite positioning means. embedded in the aircraft. Indeed, thanks to this means for determining the heading and attitude of the AHRS type and to this satellite positioning means, the position and the orientation of the local coordinate system linked to the aircraft are known in the terrestrial reference. As a result, it is possible to transpose the coordinates of any point from one marker to another. The heading and attitude of the aircraft are therefore known in the landmark.
    [0009] The reference point Pr of the aircraft is a fixed point of the aircraft which can be any point of the aircraft or a particular point of the aircraft such as its center of gravity, the position of the aircraft head. an occupant and the driver in particular or the center of the display device used. This reference point Pr 20 is preferably used as a reference for displaying the synthetic graphic representation of the external view of the aircraft. This reference point Pr being a fixed point of the aircraft is known in a local coordinate system related to the aircraft. This reference point Pr can moreover be the center of this local reference linked to the aircraft and formed for example by the roll, pitch and yaw axes of the aircraft. The position of this reference point Pr can also be calculated in the terrestrial reference and characterized by first coordinates in this terrestrial reference. The method according to the invention also uses at least one control point P1, P2, P3, each control point P1, P2, P3 corresponding to a point situated in the environment of the aircraft.
    [0010] Each control point P1, P2, P3 is used to verify the reliability and accuracy of the at least partial perspective view of the external environment of the aircraft. Each control point P1, P2, P3 forms with the reference point Pr a first straight line Dp1, Dp2, Dp3. The position and the orientation of each first line Dp1, Dp2, Dp3 can be known in the local coordinate system linked to the aircraft. Similarly, the position of each control point Pt, P2, P3 can be known in the local coordinate system related to the aircraft. In addition, the position of each control point P1, P2, P3 and the position 10 and the orientation of each first line Dp1, Dp2, Dp3 can be calculated in the terrestrial reference. Each control point P1, P2, P3 may be a known point of a database stored in a memory embedded in the aircraft, for example a database of terrain, navigation or obstacles. This memory can be integrated or connected to a navigation device or to the synthetic vision display device. The second coordinates of each control point P1, P2, P3 are then known in the terrestrial reference through this database. Each control point P1, P2, P3 thus forms with the reference point Pr a first straight line Dp1, Dp2, Dp3. Each first line Dp1, Dp2, Dp3 is then determined from the first coordinates of the reference point Pr and the second coordinates of each control point P1, P2, P3 in the terrestrial reference frame. As a result, the position and the orientation of each first line Dp are known relative to the heading of the aircraft in the terrestrial frame. In addition, the position of each control point P1, P2, P3 as well as the position and orientation of each first line Dp1, Dp2, Dp3 can also be determined in the local coordinate system linked to the aircraft.
    [0011] Each checkpoint P1, P2, P3 can also be defined by a first line Dp1, DP2, DP3 positioned relative to the heading of the aircraft in the local coordinate system linked to the aircraft and passing through the reference point Pr of the aircraft as well as a distance L from the reference point Pr. In fact, each line Dp can be characterized by an angle along the direction of the heading of the aircraft. The first coordinates of the reference point Pr and the position of the heading of the aircraft being known in the local coordinate system related to the aircraft, the second coordinates of each control point P1, P2, P3, respectively located on each line Dp1 , Dp2, Dp3 at a distance L from the reference point Pr, can be determined in this local coordinate system linked to the aircraft. The distance L is preferably the same according to each first line Dp, although a specific distance L 1 can be defined for each first line Dp1, DP2, DP3. Furthermore, the position and orientation of each first line Dp1, Dp2, Dp3 and the position of each control point P1, P2, P3 can also be calculated in the terrestrial reference.
    [0012] Preferably, the first straight lines Dpj, Dp2, Dp3 are defined in the field of the at least partial perspective view of the environment of the aircraft displayed on the display means which generally also corresponds to the pilot's field of view. The term "at least partial field of view in perspective of the environment of the aircraft" means the zone of the environment of the aircraft which is displayed on the display means. Indeed, to display such a view at In view of the environment of the aircraft, a calculator is generally limited to this field of at least partial perspective view of the environment in order to limit the calculation times. This is particularly the case for a synthetic graphic representation of the SVS type. In this way, only coordinates present in this field of this at least partial perspective view can be used by the method according to the invention.
    [0013] The method according to the invention then makes it possible to calculate the display coordinates (ai, b1), (a2, b2), (a3, b3) of each control point P1, P2, P3 on the display means intermediate of a first display function F1. Each display means is generally a display of a given size and generally comprises pixels distributed in horizontal lines and in vertical columns. In fact, any element represented on this display can be characterized by display coordinates (x, y) in a fixed reference linked to this display, where x is for example a column number and y is a line number.
    [0014] As a result, each pair of display coordinates (ai, b1), (a2, b2), (a3, b3) respectively represents the control points P1, P2, P3 displayed on the display means taking into account the heading and attitude of the aircraft. The first display function F1 makes it possible, for example, to display on the display means a graphical representation of the terrain surrounding the aircraft and / or of particular elements such as an airfield from their known positions in the reference mark. earthly. The first display function F1 can also make it possible to display a control symbology on the display means. This first display function F1 takes into account the heading and the attitude of the aircraft to display this graphic representation of the terrain surrounding the aircraft in order to be representative of the vision of the pilot. When the reference point Pr is the reference of the display of the synthetic graphical representation of the external view of the aircraft, the display coordinates (a1, b1), (a2, b2), (a3, b3) of each control point P1, P2, P3 respectively correspond to the point of intersection between each first straight line Dpi, Dp2, Dp3 and the synthetic external scene 5 represented on the display means. We can then calculate via the inverse (F2) -1 of a second display function F2 and from the display coordinates (ai, b1), (a2, b2), (a3, b3 ) of each control point P1, P2, P3 a second straight line Ds for each control point 10 Pi, P2, P3. Indeed, the second display function F2 makes it possible to display, for example on the display means, a control symbology. This second display function F2 also takes into account the heading and the attitude of the aircraft to display this steering symbology. As a result, the inverse (F2) -1 of the second display function F2 can, from a point C1 displayed on the known display means, for example by its display coordinates (x, y), make it possible to know at least the straight line Dc passing through the reference point Pr and the point C2 of the environment of the aircraft corresponding to this point C1 displayed on the display means. Moreover, if we know the distance between the point C2 and the reference point Pr, then the position of this point C2 can be precisely defined on this line Dc.
    [0015] Furthermore, when the reference point Pr is the reference of the display of the synthetic graphic representation of the external view of the aircraft, the straight line Dc passes directly through the reference point Pr and through the point C1 displayed on the medium of visualization.
    [0016] Thus, each second straight line Dsi, Ds2, Ds3 passes through the reference point Pr of the aircraft and must also pass through a control point P1, P2, P3 corresponding to a pair of display coordinates (ai, b1). ), (a2, b2), (a3, b3) on the display means. In fact, the position and the orientation of each second line Ds are known in the terrestrial frame thanks to this second display function F2. As a result, each second straight line Ds can then be positioned relative to the heading of the aircraft, the coordinates of the reference point Pr and the orientation of the heading of the aircraft 10 being known in the terrestrial reference. In this way, with the second display function F2, a calculation is performed that is inverse to that performed by the first display function F1. In addition, the position and orientation of each second straight line Ds can also be calculated in the local coordinate system related to the aircraft. Then, the method according to the invention makes it possible to compare the first and second straight lines Dp, Ds passing through the same control point P1, P2, P3. Indeed, the first straight line Dp and the second straight line Ds passing through the same control point P1, P2, P3 are theoretically confounded, since they both pass through the reference point Pr and by the same point among the points of reference. control P1, P2, P3. On the other hand, these lines are actually close, but distinct following the different approximations made during the calculation steps for determining the display coordinates (a1, b1), (a2, b2), (a3, b3) of the control P1, P2, P3, then the second straight Ds 1, DS2, DS3. In addition, the purpose of the method which contributes to securing according to the invention is to constitute an element contributing to the validation of the synthetic graphic representation of the external view of an aircraft in order to make it possible to reach in association with Other independent independent means a level of reliability, integrity and dependability sufficient for this synthetic graphical representation to be used as a steering and navigation aid. In fact, the first and second display functions F1, F2 are distinct so as to have a dissimilarity in these display functions F1, F2. As a result, the computations made by the first display function F1, then by the second display function F2 make it possible to have a level of reliability and integrity greater than the use of a single function of FIG. F1 display, common F2. In this way, the two display functions F1, F2 being distinct, these may have slightly different results, following formulas, calculation modes and / or possible approximations according to each display function F1, F2 although the results provided by these two display functions F1, F2 are correct. Consequently, an angular difference can exist between the first and second straight lines Dp, Ds corresponding to the same control point P1, P2, P3, this angular difference being characterized by an angle between the first line Dp and the second line Ds. It can then be determined that if this angular difference is less than or equal to a predetermined margin, the two display functions F1, F2 provide consistent results. On the other hand, when this angular difference is greater than this predetermined margin, the two display functions F1, F2 provide inconsistent results. The predetermined margin is determined to be the maximum angular difference considered acceptable on the basis of the respective mathematical approximations of the two display functions F1, F2 and their respective latency times to consider the first and second straight lines. Dp, Ds are merged. The predetermined margin has for example a value of one degree (1 °). Moreover, the two display functions F1, F2 may have different security levels, one of the display functions F2 having a security level higher than the other display function F1. We can then consider, if the two display functions F1, F2 are coherent, that is to say if the angular difference between the first and second straight lines Dp, Ds 10 corresponding to the same control point P1, P2 , P3 is less than or equal to the predetermined margin, that the display function F2 is a contributing element to the improvement of the integrity of the function F1. Associated with other independent complementary means, the two display functions F1, F2 can advantageously be considered as having the highest level of security of these two display functions F1, F2, the display function F2 having for example the highest security level validating the other display function F1.
    [0017] As a result, when the first and second straight lines Dp, Ds passing through the same control point P1, P2, P3 are coherent, that is to say if they have between them an angular difference less than or equal to a predetermined margin it can then be defined that the at least partial perspective view of the environment of the aircraft 25 is correct. In addition, according to the highest level of security achieved by one of the display functions F1, F2, the at least partial perspective view of the environment of the aircraft can be defined as integrated and reliable. Preferably, only one of said display functions F1, F2 has a criticality level DAL A or DAL B. Advantageously, and as mentioned above, it can then be considered that the two display functions F1, F2 have a criticality level DAL A or DAL B and deduce that the method contributing to the securing of a synthetic graphic representation of the external view of an aircraft according to the invention contributes to a criticality level DAL A or else DAL B As a result, associated with other complementary independent means, this synthetic graphic representation of the external view of an aircraft can then be used as an aid for the piloting and navigation of the aircraft, levels of reliability, 10 of sufficient integrity and dependability being achieved by the securing method of the invention. According to a first embodiment of this method, which contributes to securing a synthetic graphic representation of the external view of an aircraft, the first display function F1 is a function for displaying the at least partial perspective view. the environment of the aircraft on the display means and the second display function F2 is a display function of the control symbology on the display means.
    [0018] The first display function F1 then makes it possible to calculate the display coordinates (x, y) on the display means of all points of the environment according to the information contained in at least one database. This first display function F1 performs this calculation of the display coordinates (x, y) taking into account on the one hand a viewing angle from the reference point of the display of the synthetic graphic representation of the view. the aircraft, which is preferably the reference point Pr and secondly the heading and attitude of the aircraft. This first display function F1 thus enables the pilot of the aircraft to have on the visualization means a synthetic graphic representation of the external view of the aircraft coherent with the real view that it can have through the transparent windshield of the aircraft. The second display function F2, on the other hand, makes it possible to display on the display means a control symbology 5 comprising in particular an attitude symbology representing the angles of attitude and inclination of the aircraft obtained by a determination means. AHRS type heading and attitude as well as control symbologies, such as for example a speed vector of the aircraft.
    [0019] According to a second embodiment of this method contributing to securing according to the invention, the first display function F1 is a display function of the control symbology on the display means and the second display function F2. is a function for displaying the at least partial perspective view of the environment of the aircraft on the display means. According to a preferred embodiment of this method, which contributes to securing a synthetic graphic representation of the external view of an aircraft, the first display function F1 is a function for displaying the at least partial perspective view. of the environment of the aircraft on the criticality level display means DAL C while the second display function F2 is a display function of the control symbology on the criticality level display means DAL A. Finally, when the at least partial perspective view of the environment outside the aircraft is not integral, that is to say if the angular difference between the first and second straight lines Dp, Ds is greater than at the predetermined margin, the display of the at least partial perspective view is changed on the display means. This modification thus indicates to the pilot of the aircraft that the at least partial perspective view of the environment outside the aircraft can not be used as a flight and navigation aid. For example, the at least partial perspective view of the external environment may be grayed out or darkened or even not displayed. This view can then be replaced by a conventional artificial horizon type separation or a "wide field" artificial horizon. On the other hand, when the at least partial perspective view of the environment outside the aircraft is intact, that is to say if the angular difference between the first and second straight lines Dp, Ds is less than or equal to the predetermined margin, it displays the at least partial perspective view on the display means. The pilot of the aircraft can then use the at least partial view in perspective of the environment outside the aircraft as piloting and navigation aids. Moreover, it is possible to use, during the method of contributing security of the invention, one or more control points P1, P2, P3 in order to check the integrity of the view at least partially in perspective of the environment. outside the aircraft. Indeed, the use of a single control point P1 makes it possible to control the reliability and the accuracy of the display of this control point P1 of the environment on the at least partial view in perspective of the environment of the environment. the aircraft. If the result of this check is positive, then we can assume that all the points of the environment of the aircraft located on this first line Dp1 formed by this control point P1 and the reference point Pr is also represented by reliably and accurately on the at least partial perspective view of the environment of the aircraft.
    [0020] The use of several control points P1, P2, P3 makes it possible to control the reliability and the accuracy of the display of these control points P1, P2, P3 of the environment on the at least partial perspective view of the environment of the aircraft. If the result of this check is positive for all of these checkpoints P1, P2, P3, then we can assume that all the points of the environment of the aircraft located on the first straight lines Dp1, Dp2 , Dp3 formed by each control point P1, P2, P3 and the reference point Pr is also reliably and accurately shown in the at least partial perspective view of the environment of the aircraft. These control points P1, P2, P3 generally forming with the reference point Pr of the first non-coplanar straight lines, it is then possible to extend this result to all the points of the environment of the aircraft.
    [0021] However, the increase in this number of control points P1, P2, P3 is accompanied by an increase in the calculation time necessary for this control as well as by the use of calculation means which may possibly be detrimental to other functions also requiring calculation means 20 more or less important. Preferably, three control points P1, P2, P3 are selected in the field of the at least partial perspective view of the environment of the aircraft thus forming with the reference point Pr three first straight lines Dp1, Dp2, Non-coplanar Dp3.
    [0022] The contributive method of securing a synthetic graphic representation of the external view of an aircraft then constitutes a contributing element in improving the integrity of this synthetic graphic representation of the external view of the aircraft. These three control points P1, P2, P3 can be chosen randomly in this field of the at least partial perspective view of the environment of the aircraft or according to three predefined first lines Dp1, Dp2, Dp3. According to an example in which three control points P1, P2, P3 form, with the reference point Pr, three first non-coplanar straight lines Dp1, Dp2, Dp3, a first control point P1 is situated on a first line Dp1 situated in a plane containing the roll and pitch axes of the aircraft and oriented at an angle of -10 ° with respect to the roll axis in this plane. A second control point P2 is defined by a first line Dp2 located in this same plane and oriented at an angle of + 10 ° with respect to the roll axis. A third control point P3 is defined by a first line Dp3 located in a plane containing the roll and yaw axes of the aircraft and oriented at an angle of -10 ° with respect to the roll axis in this plane. These three points P1, P2, P3 are located at a distance L from the reference point Pr. The distance L has a value of 10 nautical miles (10 Nm). Furthermore, the method according to the invention may comprise a control phase during which the control points P1, P2, P3 are successively selected in order to scan the whole of the at least partial perspective view of the environment. of the aircraft. This control phase makes it possible to verify that this at least partial view in perspective is integral in its entirety. The control points P1, P2, P3 scan the whole of the at least partial view in perspective in a given time interval which is limited, this given time interval having for example a duration of one second (1s) . The present invention also relates to a device for displaying synthetic vision of an aircraft. This synthetic vision display device comprises at least one visualization means, at least one memory and at least one calculating means. The memory stores calculation instructions and at least a database of the aircraft environment such as a terrain, navigation and / or obstacle database. The synthetic vision display device is capable of being connected to at least one positioning means of the aircraft making it possible in particular to determine at least the heading and attitude of the aircraft and a reference point Pr of the aircraft. This aircraft may in particular comprise satellite positioning means and / or means for determining the heading and the attitude of the AHRS type.
    [0023] The synthetic vision display device then makes it possible to display on at least one visualization means on the one hand an at least partial perspective view of the environment of the aircraft and on the other hand a steering symbology. The synthetic vision display device is furthermore capable of implementing the method that contributes to securing a synthetic graphic representation of the exterior view of an aircraft previously described in order to secure the display of the view at least partial perspective of the environment of the aircraft. In combination with other complementary independent means, the synthetic vision display device and more particularly the at least partial perspective view of the aircraft environment can then be used as piloting and flight control aids. the navigation of the aircraft. A display means of this synthetic vision display device may be a screen disposed on an aircraft instrument panel or a head-up display device. Such a head-up display device is, for example, integrated into the pilot's helmet of the aircraft, the display means then being a clear viewfinder fixed in the cockpit, or the pilot's visor, or an optical element arranged in front of at least one one of the pilot's eyes.
    [0024] The present invention also relates to an aircraft comprising such a synthetic vision display device and at least one positioning means. The invention and its advantages will become more apparent in the following description with exemplary embodiments given by way of illustration with reference to the appended figures which represent: FIG. 1, an aircraft equipped with a device for synthetic vision display; FIG. 2, a synthetic vision display device; FIG. 3, a synthetic graphic representation of the external view of an aircraft; FIG. 4, a view of the aircraft; 5, a block diagram of a method contributing to the securing of a synthetic graphic representation of the external view of an aircraft and FIGS. 6 and 7, two views of the visualization means and the surrounding terrain; display means of a variant of the invention.
    [0025] The elements present in several separate figures are assigned a single reference. FIG. 1 shows a rotary wing aircraft 10 comprising, in addition to a fuselage 11, a main rotor 12 and a rear rotor 13, a synthetic vision display device 1. A pilot 20 is installed on board this aircraft 10, and more precisely to a cockpit of this aircraft 10 and can look at the external environment of the aircraft 10 through a transparent windshield. Such a synthetic vision display device 1 is shown in more detail in FIG. 2. This synthetic vision display device 1 comprises several display means including a main screen 2 and a secondary screen 6. This main screen 2 is positioned on a dashboard 7 of the aircraft 10 while the secondary screen 6 is positioned opposite the pilot's head 20 and thus constitutes a head-up device. The pilot 20 can thus see the information displayed on this secondary screen 6 without turning his head and thus without taking his eyes off the external environment of the aircraft 10 through the windshield 15. This synthetic vision display device 1 also comprises a memory 3, a calculation means 4 and a positioning means 5. The memory 3 makes it possible to store one or more data bases of the external environment of the aircraft 10 as well as calculation instructions. These calculation instructions may be in the form of a computer program and are used by the calculating means 4. The positioning means 5 comprises a satellite positioning means and a means for determining the heading and the attitude of the satellite. type AHRS. FIG. 3 represents an exemplary display of the display means 2,6 on which the pilot 20 of the aircraft 10 can see on the one hand an at least partial perspective view 8 of the external environment of the aircraft 10 and on the other hand a control symbology 9 of the aircraft 10. The at least partial perspective view 8 of the external environment of the aircraft 10 consists of a representation of the surrounding relief with possibly particular elements such as land or 30 landing zones, buildings. The pilot 20 can also see in this display example various flight and navigation information 7 such as the altitude of the aircraft 10 and its heading 16. The at least partial perspective view 8 of the external environment of the aircraft 10 takes into account the heading 5 and the attitude of the aircraft 10, the heading 16 being the axis of roll of the aircraft 10 and its attitude corresponding to its inclination around its roll axes, pitching and yawning. In addition, this at least partial perspective view 8 uses a reference point Pr corresponding to the reference of the display of this view. This reference point Pr is located at the pilot's head 20 of the aircraft 10 as shown in FIG. 1. Thus, the at least partial perspective view 8 is representative of the pilot's direct vision. the external environment of the aircraft 10 through the windshield 15.
    [0026] FIG. 4 represents a perspective view of the aircraft 10, the visualization means 2.6 and the relief 30 surrounding the aircraft 10 and located more particularly in front of the aircraft 10. A terrestrial reference (X, Y, Z) is attached to the relief 30. A local coordinate system (Xio, Yio, Zio) attached to the aircraft 10 is furthermore formed by the directions of the roll axes X10, pitch Y10 and yaw Zlo of the aircraft 10 FIG. 5 represents a block diagram of a method contributing to the securing of a synthetic graphic representation of the external view of the aircraft 10. This method contributing to securing allows, in association with other complementary independent means. , to verify the integrity of the synthetic graphic representation displayed by the synthetic vision display device 1 and comprises six successive steps.
    [0027] These complementary independent means are, for example, the satellite positioning means and the means for determining the heading and attitude of the AHRS type that comprise the positioning means 5 as well as the database or databases 5 of the environment. 10 of the aircraft stored in the memory 3. During a first step 21, the heading 16 and the attitude of the aircraft 10 are determined by means of the heading and attitude determination means. of the AHRS type and the reference point Pr via the satellite positioning means. The heading 16, the attitude of the aircraft 10 and the reference point Pr are therefore known both in the local coordinate system (X1o, Y10, Z1o) of the aircraft 10 and in the terrestrial reference (X, Y, Z ) by means of positioning 5.
    [0028] Indeed, thanks to the positioning means 5, the position and orientation of the local coordinate system (Xio, Yio, Zio) in the terrestrial reference (X, Y, Z) are known. It is then possible to transpose the coordinates of any point from one marker to another. During a second step 22, three control points P1, P2, P3 are defined in the environment of the aircraft 10. Each control point P1, P2, P3 is located on a first straight line Dp1 respectively. Dp2, Dp3 passing through the reference point Pr. The position of each first straight line Dp1, Dp2, Dp3 is known with respect to heading 16 in the local coordinate system (Xio, Yio, Zio). For example, the first straight lines Dp1, Dp3 are located in a horizontal plane of the local coordinate system (Xio, Yio, Zio), respectively forming an angle a1, a3 with the direction of the heading 16, and the first straight line DP2 is located in a vertical plane of the local coordinate system (X1o, Y10, Z1o) passing through the direction of heading 16, forming an angle a2 with this direction of heading 16. The first three straight lines Dp1, Dp2, Dp3 are non-coplanar. As a result, the three control points P1, P2, P3 are known in the local coordinate system (Xio, Yio, Zio). Similarly, each first straight line Dpi, Dp2, Dp3, and each control point P1, P2, P3 can also be transposed and characterized in the terrestrial frame (X, Y, Z). Preferably, the first straight lines Dp1, DP2, Dp3 are in the field of the at least partial perspective view 8.
    [0029] However, the control points P1, P2, P3 may be points derived from a database stored in the memory 3 and thus known in the terrestrial frame (X, Y, Z). Each first line Dp1, DP2, DP3, passing through the reference point Pr and respectively a control point P1, P2, P3, can then be characterized in the terrestrial frame (X, Y, Z). During a third step 23, a display function F1 calculates the display coordinates (a1, b1), (a2, b2), (a3, b3) of each control point P1, P2, P3 on the visualization means 2,6. The first display function F1 is a display function of the at least partial perspective view 8 of the environment of the aircraft 10 on the display means 2,6. During a fourth step 24, the inverse (F2) -1 of a second display function F2 is calculated and from the display coordinates (a1, b1), (a2, b2), (a3, b3) three second straight lines Dsi, Ds2, Ds3 passing through said reference point Pr and respectively by a control point P1, P2, P3. The second display function F2 is a display function of the control symbology 9 on the display means 2,6. In addition, the first display function F1 and the second display function F2 are separate display functions in order to have a dissimilarity in these display functions F1, F2. On the other hand, the first display function F1 has a criticality level 5 DAL C while the second display function F2 has a criticality level DAL A. During a fifth step 25, the first straight line Dra1 is compared , Dp2, Dp3 and the second straight line Dsi, Ds2, Ds3 passing through the same control point P1, P2, P3, in order to check whether the angular difference between this first straight line Dp1, Dp2, Dp3 and this second straight line Ds1, Ds2, Ds3 is greater than a predetermined margin. Indeed, following different calculation approximations and the use of two distinct display functions F1, F2, a first straight line Dpi, Dp2, Dp3 and a second straight line Ds1, Ds2, Ds3 15 passing theoretically through the same point of view. control P1, P2, P3 and by the reference point Pr can not be confused. The predetermined margin then takes into account these different approximations of calculation and the use of two distinct display functions F1, F2.
    [0030] Finally, during a sixth step 26, it is defined that the at least partial perspective view 8 of the environment of the aircraft 10 is integral if the first straight line Dp1, Dp2, Dp3 and the second straight line Dsi, Ds2 , Ds3 passing through the same control point P1, P2, P3 have an angular difference less than or equal to this predetermined margin.
    [0031] Indeed, in this case, the first straight line Dp1, Dp2, Dp3 and the second straight line Ds1, Ds2, Ds3 passing through the same control point P1, P2, P3 can be considered as merged. As a result, it is deduced that the two display functions F1, F2 provide consistent results. Thus, the second display function F2 which has a criticality level DAL A constitutes a factor 3021771 contributing to the conformity of the first display function F1 with the criticality level DAL A, although its criticality level is lower. . In this way, the at least partial perspective view 8 of the environment of the aircraft 10 determined by the first display function F1 is validated by the second display function F2 which has a criticality level DAL A. It can then be considered, in association with other independent complementary means, that the at least partial perspective view 8 of the environment of the aircraft 10 has a criticality level DAL A and can be used as a piloting aid. and navigation by the pilot 20. The at least partial perspective view 8 is thus normally displayed on the display means 2,6. The pilot 20 of the aircraft 10 then knows that he can use this at least partial perspective view 8 of the outside environment to the aircraft 10 as a piloting aid and navigation. On the other hand, when the at least partial perspective view 8 of the environment outside the aircraft 10 is not integral, that is to say if the angular difference between a first straight line Dpi, Dp2, Dp3 and a second straight line Dsi, Ds2, Ds3 passing through the same control point P1, P2, P3 is greater than the predetermined margin, the display of the at least partial perspective view 8 on the display means 2,6 is modified to inform the pilot 20.
    [0032] For example, the at least partial perspective view 8 of the external environment may be grayed out or darkened or even not displayed. Figures 6 and 7 are shown displays on a display means 2.6 of a variant of the invention. According to this variant, the display functions F1, F2 make it possible to simultaneously display twice the same elements representing an artificial horizon line 17, 27, attitude markers 18, 28 and heading markers 19 , 29 on each artificial horizon 17,27. These elements are oriented with respect to the heading 16 and attitude of the aircraft 10 and are displayed with a specific color. In this variant, the control points P1, P2, P3 are particular points. Indeed, a first control point P1 is located on the heading of the aircraft 10, that is to say its axis of roll X10 in the local coordinate system (Xio, Yio, Zio) linked to the aircraft 10 then that two other control points P2, P3 are located on an artificial horizon line in the local coordinate system (X1o, Y10, Z1o), i.e., the pitch axis Y10. In fact, the control points P1, P2, P3 are known in this local coordinate system (Xio, Yio, Zio) and can be transposed in the terrestrial frame (X, Y, Z). These control points P1, P2, P3 are located at a first distance L1 any predetermined predefined Pr reference point. The first display function F1 then makes it possible to determine the display coordinates (ai, b1), (a2 , b2), (a3, b3) of each control point P1, P2, P3 on the display means 2.6. The first artificial horizon line 17, the first attitude markers 18 and the first heading markers 19 can then be displayed. The first artificial horizon 17 is a segment passing through the display coordinates (a2, b2), (a3, b3) corresponding to the two control points P2, P3, the first attitude markers 18 being equidistant and parallel to this first artificial horizon line 17. The first heading markers 19 are equidistant segments parallel to a direction perpendicular to the first artificial horizon line 17 and 30 passing through the display coordinates (ai, b1) of the first control point P1.
    [0033] The inverse (F2) -1 of the second display function F2 then makes it possible to first determine lines Dsi, Ds2, Ds3 passing through the reference point Pr and respectively the display coordinates (ai, b1), (a2, b2), (a3, b3) corresponding to each control point P1, P2, P3. Then, complementary points P'1, P'2, P'3 respectively located on each line Ds1, Ds2, Ds3 at a second distance L2 any predefined but of the reference point Pr are determined, the position of these complementary P'1 , P'2, P'3 are known both in the local coordinate system (X10, Y10, Z10) and in the terrestrial frame (X, Y, Z). This second distance can be equal to first distance. Finally, the display function F1 makes it possible to determine the complementary display coordinates (a'1, b'1), (e'2, W2), (a13, b'3) of each complementary point P'1, P'2, P'3 on the display means 2,6. The second artificial horizon 27, the second attitude markers 28 and the second heading markers 29 can then be displayed. The second artificial horizon 27 is a segment passing through the complementary display coordinates 20 (a'2, b'2), (a'3, b'3) corresponding to the two complementary points P'2, P ' 3, the second attitude markers 28 being equidistant and parallel to this second artificial horizon line 27. The second heading markers 29 are equidistant segments parallel to a direction perpendicular to the second artificial horizon line 27 and passing through the complementary display coordinates (a'1, b'1) of the first complementary point P'1. Thus, by comparing the first and second artificial horizon lines 17,27, the first and second attitude landmarks 18,28 and the first and second landmarks 19,29, it is possible to check the consistency of the functions. display F1, F2 and, consequently, to deduce that the two display functions F1, F2 have a criticality level which is the highest criticality level of these two display functions F1, F2. In FIG. 6, the display means 2.6 displays elements 17, 18, 19 originating from the display function F1 and elements 27, 28, 29 coming from the display function F2 which are distinct. In fact, the results of the display functions F1, F2 are not coherent with each other. In FIG. 7, the elements 17, 18, 19 originating from the display function F1 and the elements 27, 28, 29 coming from the display function F2 are merged, meaning that in this case the functions of FIG. F1, F2 display are well consistent with each other because they give identical results. In addition, the elements 27,28,29 from the display function F2 are shown with thicker lines. Thus, the elements 27, 28, 29 coming from the display function F2 constitute a trimming of the elements 17, 18, 19 displayed by the other display function F1 when these two display functions F1, F2 are coherent. . Naturally, the present invention is subject to many variations as to its implementation. Although several embodiments have been described, it is well understood that it is not conceivable to exhaustively identify all the possible modes. It is of course conceivable to replace a means described by equivalent means without departing from the scope of the present invention. For example, the display functions F1, F2 can be inverted, the first display function F1 being a display function of the control symbology 9 and the second display function F2 being a display function of the control. view at least partially in perspective 8 of the environment of the aircraft 10 on the display means 2,6. Likewise, the criticality levels of each display function F1, F2 can be inverted and / or different. 5
    权利要求:
    Claims (16)
    [0001]
    REVENDICATIONS1. A method contributing to the securing of a synthetic graphic representation of the external view of an aircraft (10), said aircraft (10) comprising at least one display means (2,6) on which can be displayed on the one hand a at least partial perspective view (8) of the environment of said aircraft (10) and secondly a control symbology (9) of said aircraft (10), a roll axis (X10) extending from the front said aircraft (10) to the rear of said aircraft (10), a yaw axis (Z1o) extending from bottom to top perpendicular to said roll axis (X10) and a pitch axis (Y10) extending from right to the left perpendicular to said roll axes (X10) and yaw axis (Z10), forming a local coordinate system (Xio, Yio, Zio) connected to said aircraft (10), characterized in that, in which - at least the heading and attitude of said aircraft (10) and a reference point (Pr) of said aircraft (10), - at least one control point (P) is defined 1, P2, P3) located in said environment of said aircraft (10), the position of a first straight line (Dpi, Dp2, Dp3) passing through each control point (P1, P2, P3) and said reference point (Pr ) of said aircraft (10) being known in said local coordinate system linked to said aircraft (10), - it calculates by a first display function (F1) the display coordinates (ai, b1), (a2, b2), ( a3, b3) of each control point (P1, P2, P3) on said display means (2,6), the inverse (F2) -1 of a second display function (F2) is calculated and from said display coordinates (ai, b1), (a2, b2), (a3, b3) a second straight line (Dsi, Ds2, Ds3) for each control point (P1, P2, P3), each second right (Dsi, Ds2, Ds3) passing through said reference point (Pr) of said aircraft (10), said first display function (F1) and said second display function (F2) being distinct, - said comparator is compared first line (Dp1, Dp2, Dp3) and said second line (Dsi, Ds2, Ds3) passing through the same control point (P1, P2, P3), it is defined that said at least partial perspective view (8) of the environment of said aircraft (10) is integral if said first and second straight lines Dp, Ds passing by the same control point (P1, P2, P3) have an angular deviation less than or equal to a predetermined margin.
    [0002]
    2. Method according to claim 1, characterized in that each control point (P1, P2, P3) is defined in said local coordinate system (Xio, Yio, Zio), then the position of each control point (P1, P2, P3) in a terrestrial reference (X, Y, Z).
    [0003]
    3. Method according to any one of claims 1 to 2, characterized in that one defines three control points (P1, P2, P3) forming with said reference point (Pr) three first straight lines (Dp1, Dp2, Dp3) not coplanar.
    [0004]
    4. Method according to any one of claims 1 to 3, characterized in that each control point (P1, P2, P3) is characterized by said first straight line (Dp1, Dp2, Dp3) positioned relative to said longitudinal axis of roll (X10) and passing through said reference point (Pr) and a distance L from said reference point (Pr).
    [0005]
    5. Method according to any one of claims 1 to 3, characterized in that said reference point (Pr) is characterized by first coordinates in a terrestrial reference (X, Y, Z) and each control point ( P1, P2, P3) is a known point of a database whose second coordinates are known in said terrestrial reference (X, Y, Z), said first line (Dp1, Dp2, Dp3) corresponding to a point of control (P1, P2, P3) being determined from said first coordinates of said reference point (Pr) and said second coordinates of said control point (P1 P25 P3). 10
    [0006]
    6. Method according to any one of claims 1 to 5, characterized in that said control points (P1, P2, P3) are selected from the field of said at least partial perspective view (8).
    [0007]
    7. Method according to any one of claims 1 to 2, characterized in that said control points (P1, P2, P3) are chosen successively in order to scan said at least partial perspective view (8) in an interval given time.
    [0008]
    8. Method according to any one of claims 1 to 7, characterized in that, when said at least partial perspective view (8) is not integral, the display of said at least partial perspective view is modified. (8) on said display means (2,6) for informing a pilot of said aircraft (10).
    [0009]
    9. Method according to any one of claims 1 to 8, characterized in that said first display function F1 is a display function of said at least partial perspective view (8) of said environment of said aircraft (10) on said display means (2,6) and said display function F2 is a function of displaying said control symbology (9) on said display means (2,6).
    [0010]
    10. Method according to any one of claims 1 to 8, characterized in that said first display function (F1) is a display function of said control symbology (9) on said display means (2, 6) and said display function (F2) is a display function of said at least partial perspective view (8) of said environment of said aircraft (10) on said display means (2,6). 10
    [0011]
    11. Method according to any one of claims 1 to 10, characterized in that one of said display functions (F1, F2) has a higher security level than the other display function (F1, F2). 15
    [0012]
    12. Method according to any one of claims 1 to 11, characterized in that one of said display functions (F1, F2) has a criticality level indifferently DAL A or DAL B.
    [0013]
    13. Method according to any one of claims 1 to 12, characterized in that said reference point (Pr) is the reference point of said display of said synthetic graphical representation of said external view of said aircraft (10).
    [0014]
    14. A method according to claim 3, characterized in that said first control point P1 being located on said roll axis of said aircraft (10) and said control points P2, P3 being located on said pitch axis (Y10 ) at a first distance L1 from said reference point Pr, - displaying a first artificial horizon line 17, first attitude markers 18 and first heading markers 19 on said viewing means (2,6) to from said display coordinates (a1, b1), (a2, b2), (a3, b3) of each control point P1, P2, P3, said first artificial horizon line 17 passing through said display coordinates ( a2, b2), (a3, b3) corresponding to said control points P2, P3, said first attitude markers 18 being equidistant and parallel to said first artificial horizon line 17 and said first heading landmarks 19 being segments equidistant and parallel to a perpendicular direction at said first artificial horizon line 17 and passing through said display coordinates (ai, b1) of said first control point P1, additional points P'1, P'2, P'3 are determined via the inverse (F2) -1 of said second display function F2, said complementary points P'1, P'2, P'3 being on said straight lines (Dsi, Ds2, Ds3) at a second distance L2 of said reference point Pr, - complementary display coordinates (a'1, b'1), (a'2, b'2), (a'3, b'3) of each complementary point P 'are determined. 1, P'2, P'3 on the display means (2,6) by said display function F1, and - a second artificial horizon line 27, second attitude markers 28 and second cap marks 29 on said display means (2,6) from said complementary display coordinates (a'1, b'1), (a'2, b'2), 30 (a'3, b '3), said second artificial horizon 27 passing through said display coordinates complementary ages (a'2, b'2), (a'3, b'3) corresponding to said complementary points P'2, P'3, said second attitude markers 28 being equidistant and parallel to said second line; artificial horizon 27, said second heading markers 29 being segments parallel to a direction perpendicular to said second artificial horizon line 27 and passing through said complementary display coordinates (a'i, b'i) of said first complementary point P'1.
    [0015]
    15. Device for displaying synthetic vision (1) of an aircraft (10), said synthetic vision display device (1) comprising at least one display means (2,6), at least one memory ( 3) and at least one calculation means (4), said memory (3) storing at least one database of the environment of said aircraft (10) and calculation instructions, said synthetic vision display device (1) ) for displaying on at least one display means (2,6) on the one hand an at least partial perspective view (8) of the environment of said aircraft (10) and on the other hand a steering symbology (9), said synthetic vision display device (1) being able to be connected to at least one positioning means (5) of said aircraft (10) making it possible to determine at least the heading and the attitude of said aircraft ( 10) and a reference point (Pr) of said aircraft (10), a roll axis (X10) extending from the front of said aircraft (10) the rear of said aircraft (10), a yaw axis (Z10) extending from bottom to top perpendicular to said roll axis (X10) and a pitch axis (Y10) extending from right to left perpendicular to said roll axis (X10) and yaw axis (Z1o), forming a local coordinate system (Xio, Yio, Zio) linked to said aircraft (10), characterized in that said synthetic vision display device (1) is capable of setting implementing the method contributing to the securing of a synthetic graphic representation of the external view of an aircraft (10) according to claims 1 to 14 in order to secure the display of said at least partial perspective view (8). ) of the environment of said aircraft (10).
    [0016]
    An aircraft (10) comprising a synthetic vision display device (1) and at least one positioning means (5), characterized in that said synthetic vision display device (1) is according to claim 15 .
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    同族专利:
    公开号 | 公开日
    US9489758B2|2016-11-08|
    FR3021771B1|2016-06-10|
    EP2950049B1|2016-12-07|
    EP2950049A1|2015-12-02|
    US20150348299A1|2015-12-03|
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    法律状态:
    2015-04-22| PLFP| Fee payment|Year of fee payment: 2 |
    2015-12-04| PLSC| Search report ready|Effective date: 20151204 |
    2015-12-04| EXTE| Extension to a french territory|Extension state: PF |
    2016-05-20| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-23| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1401230A|FR3021771B1|2014-05-28|2014-05-28|METHOD OF CONTRIBUTING THE SECURITY OF A SYNTHETIC GRAPHIC REPRESENTATION OF THE OUTER VIEW OF AN AIRCRAFT|FR1401230A| FR3021771B1|2014-05-28|2014-05-28|METHOD OF CONTRIBUTING THE SECURITY OF A SYNTHETIC GRAPHIC REPRESENTATION OF THE OUTER VIEW OF AN AIRCRAFT|
    EP15168827.2A| EP2950049B1|2014-05-28|2015-05-22|A method contributing to the integrity monitoring of a synthetic graphic representation of the outside view of an aircraft|
    US14/723,694| US9489758B2|2014-05-28|2015-05-28|Method contributing to making safe a synthetic graphics representation of the view outside an aircraft|
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