• 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 system (10) for displaying a cockpit (3) of an aircraft (1) comprises: a display device (20) configured to be carried integral with a user's head in the cockpit of the aircraft; . an orientation sensor (16) of the user's head (50); and. a display computer (18) configured for: - controlling the display of information relating to the flight of the aircraft on the display device (20), - acquiring orientation information of the user's head ; determining an angular difference value between a direction (52) corresponding to the orientation information of the user's head and a longitudinal axis (5) of the aircraft; - evaluating a condition according to said angular difference value; and - control the display on the display device according to: a first display mode when said condition is verified, this first display mode corresponding to a display comprising at least one symbol (38, 40) to aid the piloting of the aircraft displayed in a compliant manner; and. another display mode when said condition is not verified.
    公开号:FR3052553A1
    申请号:FR1655438
    申请日:2016-06-13
    公开日:2017-12-15
    发明作者:Cedric Descheemaeker；Sanchez Javier Manjon
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    System and method for displaying an aircraft The invention relates to the display of flight control information in an aircraft cockpit. Modern aircraft, in particular transport aircraft, generally include a system for displaying piloting information in their cockpit. Such a system, for example of the CDS type ("Control and Display System" in English) controls the display of information on screens, said head down, the cockpit: to view this information, the user, usually a driver or a co-pilot of the aircraft, must lower his head to look at the screens. He can not see at the same time the environment of the aircraft through a windshield of the cockpit. To allow the user to see this information while monitoring the environment of the aircraft, some aircraft are now equipped with a head-up display, commonly called HUD for "Head Up Display" in English. A HUD device comprises a projector and a semi-reflecting glass ("combine" in English) disposed between the windshield of the aircraft and a position corresponding to the position of the head of a pilot or co-pilot when the one It is installed in the cockpit to fly the aircraft. The projector projects information on the semi-reflective glass and the user can thus view this information in superposition of the environment of the aircraft visible through the windshield. Some information may be displayed in a consistent manner. In the remainder of the description, the term "compliant" relates to the display of an information or a symbol on a display or a transparent screen, such that this information or this symbol is visible to the user in superposition. from the outside environment of the aircraft, to a position consistent with the meaning of the information or symbol. For example, a symbol representing an airstrip, when displayed in a compliant manner, is superimposed on the position of the actual airstrip visible to the user through the windshield of the aircraft. . Such a HUD device is generally of a high cost. In addition, its installation in an aircraft can be complex and expensive, especially if this installation was not planned during the design of the aircraft. Moreover, the HUD device is not visible to the user, or only partially visible, if the user is required to turn his head to monitor the lateral environment of the aircraft: the information displayed on the HUD is not visible. then not visible, or only partially visible, by the user.
    The inventors of the present invention have considered a solution to these problems, which could be to use a display device configured to be attached to the head of a user, in particular a pilot, in the cockpit of an aircraft. Such a device is commonly called HMD for "Head Mounted Display". It is sometimes also called HWD for "Head Worn Display" in English. It generally comprises a display mounted integral glasses or a helmet, so that the user can see the information displayed on the display when wearing these glasses or helmet. In the remainder of the description, the term HMD denotes both an HMD device and an HWD device. HMD devices comprising a helmet are for example used in military aircraft to help perform shooting operations on a target. HMD devices comprising glasses are for example used to produce displays in augmented reality. The display is preferably transparent so that the user can view the information displayed, actually increased, superimposed the environment. Such a solution can only be acceptable if the display of information on the HMD device is adequately controlled according to the orientation of the user's head. Thus, for example, the information can not be displayed on the HMD device in the same way regardless of the orientation of the driver's head, because then some information might not be displayed in a manner consistent with the external environment of the aircraft visible to the user. This would be the case in particular of information intended to be displayed in a manner consistent with the environment. On the other hand, there would be no point in displaying this information in such a way that it seems to be displayed in a fixed way in the cockpit when the user turns his head (in the same way as for the information displayed on a HUD ): indeed, in such a case, the user would face the same problem as with a HUD device, namely that the information would not be visible to the user, or only partially visible, if the user is brought to turn his head to monitor the lateral environment of the aircraft. SUMMARY OF THE INVENTION
    The present invention is intended to provide a solution to these problems. It relates to a cockpit display system of an aircraft comprising: a display device configured to be carried integral with the head of a user in the cockpit of the aircraft; an orientation sensor of the user's head of the display device; and a display calculator configured to control the display of information relating to the flight of the aircraft on the display device.
    The system is notable in that the display computer is configured to: - acquire orientation information from the user's head, provided by the sensor; determining at least one angular difference value between, on the one hand, a direction corresponding to said orientation information of the user's head and, on the other hand, a longitudinal axis of the aircraft; to evaluate at least one functional condition at least of said angular difference value; and - control the display on the display device according to: a first display mode when said condition is verified, this first display mode corresponding to a display comprising at least one aircraft piloting aid symbol displayed in a compliant manner; and. another display mode when said condition is not verified.
    Thus, the display system adapts the display mode of the information according to the value of the angular difference between the direction corresponding to the orientation information of the user's head and the longitudinal axis of the user. 'aircraft. This makes it possible to display the information appropriately for the user according to the orientation of the user's head, in particular with regard to the at least one symbol displayed in accordance with the first mode of the user. display.
    Advantageously, the at least one flight aid symbol is chosen from among the following symbols: a speed vector symbol of the aircraft; and an aircraft reference symbol.
    The first display mode advantageously corresponds to a display similar to that of a HUD.
    In a first embodiment, the angular deviation value comprises a lateral angular deviation and said condition includes at least a first elementary condition which is satisfied when the lateral angular deviation is between a predetermined negative threshold of lateral angular deviation and a predetermined positive threshold of lateral angular deviation. In particular, said condition further includes a second elementary condition which is verified when the value of a second lateral angular difference between on the one hand the direction corresponding to the orientation of the head of the user and on the other hand the velocity vector of the aircraft is between a second predetermined negative threshold of lateral angular deviation and a second predetermined positive threshold of lateral angular deviation.
    Advantageously, the other display mode corresponds to a second display mode in which the at least one aircraft piloting aid symbol is displayed in a non-conforming manner. In particular, the at least one symbol is a speed vector symbol of the aircraft and the display further comprises a symbol representative of a skyline, the aircraft speed vector symbol and the representative symbol. of the horizon line being displayed relative to each other so as to indicate a climb movement or a descent movement of the aircraft.
    Advantageously, the at least one aircraft piloting aid symbol is displayed in a non-conforming manner to a position characteristic of a direction towards which the user can orient his head to obtain a display conforming to the minus one symbol in the first display mode.
    In particular, in the second display mode, the display further comprises a symbol representative of the roll of the aircraft, shown associated with the at least one symbol.
    Still in a particular way, in the second display mode, the display comprises a reduced number of information with respect to the display corresponding to the first display mode.
    In a second embodiment, the angular difference value comprises a vertical angular difference and said condition includes at least one elementary condition which is satisfied when the vertical angular difference is between a predetermined negative threshold of vertical angular difference and a positive predetermined threshold of vertical angular difference. In particular, the other display mode corresponds to a third display mode in which the display corresponding to the first display mode is at least partially masked.
    In a particular embodiment, in the first display mode, the display comprises at least a portion of a trim scale and, where appropriate, this trim scale is laterally expanded depending on the orientation of the trim. the head of the user, to allow the display of said at least a portion of the trim scale.
    In another particular embodiment, in the first display mode, the display further comprises a speed scale and / or an altitude scale and the display computer controls the display on the display device. in such a way that the speed scale and / or the altitude scale are displayed vertically in a reference linked to the aircraft. The invention also relates to a method of displaying in a cockpit of an aircraft, the aircraft comprising a display system comprising: a display device configured to be carried integral with the head of a user in a the cockpit of the aircraft; a sensor for orienting the head of a user of the display device; and a display calculator configured to control the display of information relating to the flight of the aircraft on the display device.
    The method is remarkable in that it comprises the following steps implemented by the display computer: - acquiring orientation information from the user's head, provided by the sensor; determining at least one angular difference value between, on the one hand, a direction corresponding to said orientation information of the user's head and, on the other hand, a longitudinal axis of the aircraft; to evaluate at least one functional condition at least of said angular difference value; and - control the display on the display device according to: a first display mode when said condition is verified, this first display mode corresponding to a display comprising at least one aircraft piloting aid symbol displayed in a compliant manner; and. another display mode when said condition is not verified. The invention also relates to an aircraft comprising a display system as mentioned above. DETAILED DESCRIPTION: The invention will be better understood on reading the description which follows and on examining the appended figures.
    Figure 1 schematically illustrates an aircraft with a cockpit.
    Figure 2 schematically illustrates a display system of a cockpit of an aircraft according to an embodiment of the invention.
    Figures 3a, 3b and 3c illustrate the orientation of a user's head of the display system, respectively in top view, in side view and in rear view.
    Figures 4a, 5a, 6a, 7a, 8a, 9a and 10a illustrate display examples, on an HMD display device, according to embodiments of the invention.
    FIGS. 4b, 5b, 6b, 7b, 8b, 9b and 10b represent orientations of the head of a user of the display device HMD, respectively corresponding to the displays of FIGS. 4a, 5a, 6a, 7a, 8a, 9a and 10a.
    Figures 7c, 7d and 7e illustrate several display examples similar to the display shown in Figure 7a.
    FIG. 11 represents, in a vertical plane perpendicular to a longitudinal axis of the aircraft, zones corresponding to different display modes according to embodiments of the invention, as a function of the orientation of the head of a user of the HMD display device.
    Figure 12 shows, in top view, areas according to an embodiment of the invention, corresponding to different display modes according to the orientation of the head of a user of the HMD display device.
    Fig. 13 shows, in side view, areas according to an embodiment of the invention, corresponding to different display modes according to the orientation of the head of a user of the HMD display device. The aircraft 1 represented in FIG. 1 comprises a cockpit 3 in a front part of said aircraft. It comprises a longitudinal axis 5, corresponding to a rolling axis of the aircraft. This longitudinal axis is substantially horizontal when the aircraft is parked on the ground. The aircraft also comprises a yaw axis (not shown), substantially vertical when the aircraft is parked on the ground. By convention, in the remainder of the description, the horizontal term designates a straight line or a substantially horizontal plane when the aircraft is parked on the ground, such that this line or plane is perpendicular to the yaw axis of the aircraft. Similarly, the vertical term designates a straight line or a substantially vertical plane when the aircraft is parked on the ground, such that this line or plane is parallel to (or contains) the yaw axis of the aircraft.
    The display system 10 shown in Figure 2 comprises a display computer 18 including a processing unit (labeled PROC in the figure). This processing unit can in particular correspond to a processor or a microprocessor of the display computer. According to various embodiments, the display computer 18 is a common display computer controlling several display devices of the aircraft or a dedicated computer to the display system 10. In a particular embodiment, this calculator corresponds to a modular avionics-type computer IMA ("Integrated Modular avionics" in English) also supporting functions other than the display. The display system 10 further comprises a display device 20 configured to be carried integral with the head of a user in the cockpit of the aircraft. This display device corresponds to an HMD (or HWD) display device as mentioned above. It is connected to the display computer 18 by a link 19. The display system 10 also comprises a sensor 16 for orienting the head of a user of the display device, in particular a driver of the aircraft. This sensor 16 is connected at the output to the display computer 18 by a link 17. In a particular embodiment, the sensor 16 is mounted integral with the display device 20, as symbolized by the arrow 21 in broken lines. It then corresponds, for example, to a set of inertial sensors integrated in the display device 20. In another particular embodiment, the sensor 16 is mounted integral with the cockpit 3 of the aircraft. It then corresponds, for example, to a camera arranged to automatically monitor the head of a user of the display device 20. The display computer 18 is connected to at least one avionic computer 12 of the aircraft. In the particular example shown in FIG. 2, the display computer is connected to several avionic computers 12 via a link 15 of a communication network 14 (labeled "Net" in the figure) to which these avionics computers are also connected. . The avionic computers 12 are for example located in an avionics bay 2 of the aircraft.
    In operation, the display computer 18 is configured to control the display of information relating to the flight of the aircraft on the display device 20. This information relating to the flight of the aircraft is derived from the at least one an avionic computer 12 or determined by the display computer 18 as a function of information received from the at least one avionic computer 12. The sensor 16 outputs, on the link 17, orientation information of the control head. the user. This information is received by the display computer 18 which acquires it.
    In an advantageous embodiment, the orientation information of the user's head corresponds to at least one of a set of angles, as illustrated by FIGS. 3a, 3b and 3c. In these figures, the orientation of the head 50 of the user is represented by a line 52. In an exemplary embodiment, this straight line 52 corresponds to a theoretical direction of the user's gaze when he looks ahead without turning his eyes neither to the right nor to the left and without raising or lowering his eyes. Other definitions of the orientation of the head of the user are however possible without departing from the scope of the invention. In said advantageous embodiment, the orientation information of the head of the user corresponds to at least one angle among a yaw angle ψ, a pitch angle Θ and a roll angle φ respectively illustrated by FIGS. , 3b and 3c. These angles are defined in a reference linked to the aircraft. Thus, the yaw angle ψ is an angle, defined in projection in a horizontal plane, between a straight line 5 'parallel to the longitudinal axis 5 of the aircraft and the line 52 representing the orientation of the head of the aircraft. user. The pitch angle Θ is an angle, defined in projection in a vertical plane parallel to the longitudinal axis 5 of the aircraft, between a straight line 5 "parallel to the longitudinal axis 5 of the aircraft and the line 52 representing the angle of roll φ is a defined angle in projection in a vertical plane perpendicular to the longitudinal axis 5 of the aircraft, between a vertical line 56 and an axis the user's head orientation information acquired by the display computer 18 corresponds to at least one of the angles ψ, Θ and φ. the orientation information of the user's head, the display computer 18 determines at least one angular difference value between on the one hand a direction corresponding to said orientation information of the head of the user and on the other hand a longitudinal axis The display computer 18 evaluates at least one condition based on at least said angular difference value and controls the display on the display device 20 according to: a first display mode when the condition is verified, this first display mode corresponding to a display comprising at least one aircraft piloting aid symbol displayed in a compliant manner; and. another display mode when the condition is not verified.
    Advantageously, the at least one flight aid symbol of the aircraft is selected from the group comprising: a speed vector symbol of the aircraft; and an aircraft reference symbol.
    An example of a display on a display 8 of the display device 20 comprising these two symbols displayed in conformity is shown in FIG. 4a. The aircraft reference symbol 38 (or "aircraft reference") corresponds to the longitudinal axis 5 of the aircraft. FIG. 4b illustrates, in plan view, the orientation of the user's head corresponding to the display shown in FIG. 4a, in the cockpit of the aircraft comprising a windshield 4. In the example, the line 52 representing the orientation of the head 50 of the user is parallel to the longitudinal axis 5 of the aircraft, in projection in a horizontal plane. In such a case, the aircraft reference symbol 38 is displayed in conformity with the center of the display, from a lateral (or horizontal) point of view, on the display 8, as represented in FIG. 4a. The vertical position of the symbol 38 depends in particular on the value of a pitch angle of the aircraft. In this display example, the speed vector 41 of the aircraft is parallel to the longitudinal axis 5 of the aircraft and to the line 52 representing the orientation of the head 50 of the user, projected in a plane horizontal. Therefore, the aircraft speed vector symbol 40 is also centered laterally. In the example shown, in addition to the symbols 38 and 40 displayed in conformity, the display on the display 8 comprises an altitude scale 32, a speed scale 30 and a roll scale 34 of the aircraft. These different scales are improperly displayed on the display 8. They are displayed at respective positions on the display 8 independent of the yaw angle and the pitch angle of the user's head. The display on the display 8 further comprises a scale 36 of attitude of the aircraft, which is displayed in a compliant manner: its position on the display 8 depends on the pitch angle of the user's head .
    In another example illustrated by FIGS. 5a and 5b, the speed vector 41 is no longer parallel to the longitudinal axis 5 of the aircraft and to the line 52 representing the orientation of the head 50 of the user. The velocity vector 41 is oriented towards the left front of the aircraft. As a result, the speed vector symbol 40 is displayed in accordance with a position shifted to the left (with respect to FIG. 4a), close to the speed scale.
    In yet another example illustrated by FIGS. 6a and 6b, the speed vector 41 is also oriented towards the left front of the aircraft. However, unlike the previous example, the head of the user is also oriented towards the left front of the aircraft, so that the line 52 representing the orientation of the head of the user is parallel to the velocity vector 41. Accordingly, the velocity vector symbol 40 is suitably displayed, centered laterally on the display 8. In this example, it is considered that the velocity vector of the aircraft and the head of the user are oriented too far to the left of the aircraft to allow the display of the aircraft reference symbol 38 on the display 8 to be correctly displayed: in order to be displayed in conformity, the symbol 38 should be placed at an external position on display 8, to the right of it. Therefore, the symbol 38 is not displayed on the display. Furthermore, advantageously, the plate scale 36 is expanded laterally (or horizontally) so as to allow the display of a portion of said plate scale on the display 8. A trim plate normally has a left portion and a right portion displayed on either side of the aircraft reference symbol 38, as in the examples of FIGS. 4a and 5a. In the example of Figure 6a, the right part, normally located to the right of the symbol 38 is not displayed since this symbol 38 can not be displayed. In the absence of dilation of the scale 36, the left part could also not have been displayed: its position would be either on the right of the display 8 or superimposed on the altitude scale 32, which would prevent its display for readability reasons. The lateral dilation of the scale 36 makes it possible to display here its left part, to the left of the altitude scale 32. The user can thus see the position of the speed vector symbol 40 of the aircraft relative to the scale of the attitude scale, which allows it to deduce the slope of the aircraft.
    The examples represented in FIGS. 4a, 5a and 6a correspond to the first display mode in which at least one aircraft piloting aid symbol, among the aircraft reference symbol 38 and the speed vector symbol 40, is displayed in the display 8. The display on the display 8 corresponds to an augmented reality display. superimposed on the environment of the aircraft visible to the user through the transparent display 8 and the windshield of the aircraft. As indicated above, in order to determine whether to select this first display mode or another display mode, the display computer 18 determines at least one angular difference value between on the one hand a direction corresponding to the other. guidance information of the user's head and secondly the longitudinal axis of the aircraft. In a first embodiment, the display computer 18 determines a lateral angular deviation. The term lateral angular difference here denotes an angular difference considered in projection in a horizontal plane. For example, in FIGS. 5b and 6b shown in a view from above and therefore corresponding to a projection in a horizontal plane, the lateral angular deviation corresponds to the angle formed between the longitudinal axis 5 of the aircraft and the straight line. 52. This lateral angular deviation varies according to the yaw angle ψ of the head 50 of the user. A variation of the angle of yaw, and thus of the angular difference, induces a lateral displacement of the symbols 38 and / or 40 displayed in conformity on the display 8, hence the use of the side qualifier to designate this angular difference. To determine the display mode to be selected, the display computer 18 evaluates at least one condition based on the value of the lateral angular deviation. This condition includes at least a first elementary condition which is satisfied when the lateral angular deviation is between a negative predetermined threshold of lateral angular deviation and a positive predetermined threshold of lateral angular deviation. In an example illustrated in FIG. 12, representing a space 58 located at the front of the user's head 50 in the cockpit of the aircraft, the line 5 'is parallel to the longitudinal axis 5 of the aircraft . Two straight lines 5'a and 5'b each forming an absolute value angle Δ1 with the line 5 ', illustrate the predetermined positive and negative thresholds of lateral angular deviation. In this particular example, these two thresholds are equal in absolute value. Thus, the first elementary condition is verified when the straight line 52 (not shown in FIG. 12), corresponding to the orientation of the user's head, is located between the two straight lines 5'a and 5'b. The value of the angle Δ1 is chosen such that the aircraft reference symbol 38 can be displayed in conformity on the display 8, in particular between the right and left edges of the display, when the absolute value of the Lateral angular deviation is less than or equal to Δ1. Advantageously, the condition evaluated by the display computer 18 includes a second elementary condition which is verified when a second lateral angular difference between the speed vector 41 and the line 52 (corresponding to the orientation of the user's head) is between a second negative predetermined threshold of lateral angular deviation and a second predetermined positive threshold of lateral angular deviation. In FIG. 12, two lines 41a and 41b each forming an absolute value angle Δ2 with the velocity vector 41, illustrate the second predetermined positive and negative lateral angular difference thresholds. In this particular example, these two thresholds are equal in absolute value. Thus, the second elementary condition is verified when the line 52, corresponding to the orientation of the head of the user, is located between the two straight lines 41a and 41b. The value of the angle Δ2 is chosen such that the speed vector symbol 40 can be displayed in conformity on the display 8, in particular between the speed scale 30 and the altitude scale 32, when the absolute value of the second lateral angular difference is less than or equal to Δ2. In the example shown in FIG. 12, at least one of the first elementary condition and the second elementary condition is verified when the line 52, corresponding to the orientation of the user's head, is situated between the two straight lines 41a and 5'a. The condition evaluated by the display computer 18 is then checked and the display computer controls the display, on the display device 20, according to the first display mode. When the line 52 is located outside the lines 41a and 5'a, in one of the hatched areas 53a and 53b, neither of the two elementary conditions is verified. The condition evaluated by the display computer 18 is then not verified and the display computer controls the display, on the display device 20, according to a second display mode. The condition evaluated by the display computer 18 is therefore equivalent to a logic OR of the first elementary condition and the second elementary condition. Thus, this condition is verified as long as at least one of the aircraft reference symbols 38 or 40 speed vector can be displayed in conformity on the display 8. Advantageously again, a time delay is initialized when the condition is not satisfied. not checked and the display computer only activates the second display mode at the end of said delay if the condition has remained unchecked for the duration of the delay. This makes it possible to avoid inadvertent passages from the first display mode to the second display mode and then to the first display mode when the user is required to turn his head briefly to look at one side of the cockpit, before bringing his head back. in its initial orientation. This is also advantageous when turbulence induces brief movements of the user's head. The value of the timer is for example chosen in an interval of 1 to 2 seconds. Preferably, the transition from the second display mode to the first display mode is immediate when the condition is checked again, which allows the user to immediately access a consistent display of the at least one symbol. In particular, the transition from the first display mode to the second display mode, and vice versa, is carried out progressively for a predetermined duration, for example equal to 1 second, using in particular a cross-fade technique.
    Figures 7a and 7b illustrate an example of display according to the second display mode. As shown in FIG. 7b, the velocity vector 41 is parallel to the longitudinal axis 5 of the aircraft. The head 50 of the user is oriented towards the left front of the aircraft, so that the line 52 forms an angle with the longitudinal axis of the aircraft (as well as with the speed vector 41) higher than the absolute value at Δ1 and Δ2. Consequently, the condition evaluated by the display computer 18 is not verified and the display computer therefore controls the display according to the second display mode. The display on the display 8, illustrated in FIG. 7a, then comprises a speed vector symbol 40a displayed in a non-compliant manner, that is to say whose position on the display is not representative of the orientation of the speed vector of the aircraft relative to the external environment of the aircraft visible through the display 8. The symbol 40a is represented inside a circle 35. The display further comprises a symbol 42a corresponding to a chord of circle 35 and representative of a horizon line, this symbol also being displayed in a non-compliant manner. Advantageously, the symbols 40a and 42a are displayed in broken lines to warn the user that they are displayed in a non-conforming manner. Advantageously, the display also comprises a sector 42 of the circle 35, between the symbol 42a and the perimeter of the circle 35, below the symbol 42a. This sector 42, which symbolizes the space below the horizon at the front of the aircraft, is colored so as to improve the user's situational awareness. The aircraft velocity vector symbol 40a and the symbol 42a representative of the horizon line are displayed relative to one another so as to indicate a climb movement or a descent movement of the aircraft. : when the symbol 40a is displayed under the symbol 42a, this makes it possible to inform the user that the aircraft is descending and when the symbol 40a is displayed above the symbol 42a, this makes it possible to inform the user that the aircraft mounts. As shown in FIG. 7a, the symbol 42a, representative of the horizon line, is preferably inclined with respect to a horizontal direction as a function of the roll angle of the aircraft. This inclination of the symbol 42a allows the user to become aware of the roll angle of the aircraft. In a particular embodiment shown in Figure 7a, the circle 35 has an open portion 34o between two lines 34a and 34b and the display comprises a mark 34c. The position, relative to the circle 35, of the open portion 34o and the two lines 34a and 34b, is a function of the roll angle of the aircraft. The spacing between the lines 34a and 34b is chosen such that the mark 34c is displayed between these two lines when the roll angle of the aircraft is situated in a range of acceptable roll angles with respect to the flight of the aircraft. This helps the user to properly control the roll angle of the aircraft. Advantageously, the symbol 40a is displayed in a non-conforming manner at a position characteristic of a direction towards which the user can orient his head to obtain a conformal display of the at least one symbol in the first display mode: thus the symbol 40a is displayed near the right edge of the display 8 so as to indicate to the user that he can orient his head to the right to obtain a consistent display of the symbol 40 of speed vector, according to the first mode display. Similarly, when the head of the user is oriented towards the right front of the aircraft so that the condition evaluated by the display computer 18 is not verified, the display computer controls accordingly the display according to the second display mode and the symbol 40a is displayed near the left edge of the display 8. This indicates to the user that he can turn his head to the left to obtain a corresponding display of the symbol 40 speed vector, according to the first display mode. On the other hand, in this second display mode, the altitude and speed scales are respectively replaced by displays 32a of a current altitude value and 30a of a current speed value.
    In the second display mode, the display thus comprises a reduced number of information with respect to the display corresponding to the first display mode. This helps to make the user aware that the display corresponds to this second display mode. However, the user has at his disposal most of the information required for piloting the aircraft, even if no information is displayed in a consistent manner. In addition, if it deems it necessary to have piloting aid information displayed in a correct manner, the display indicates in which direction it can turn its head to obtain a consistent display in the first display mode. Other display examples according to the second display mode are shown in FIGS. 7c, 7d and 7e. In these figures, the symbol 42a is shown horizontal, corresponding to a zero roll angle. The marker 34c is then substantially centered between the lines 34a and 34b. In FIG. 7c, the speed vector symbol 40a is located above the symbol 42a: the aircraft is therefore uphill. FIG. 7d corresponds to a situation in which the aircraft is also climbing, with an attitude angle greater than that corresponding to FIG. 7c, since the symbol 42a is represented at a position lower than its position in FIG. 7c. The display of FIG. 7d also corresponds to a lower position of the symbol 42a: indeed, even if the attitude angle of the aircraft continues to increase, the symbol 42a remains displayed at this position so that the user can see this symbol in any situation. Similarly, in FIG. 7e, the symbol 42a is displayed at a higher position: even if the attitude angle of the aircraft continues to decrease, the symbol 42a remains displayed at this position so that the user can see this symbol in any situation. In this FIG. 7e, the symbol 40a is situated below the symbol 42a, which corresponds to a situation of descent of the aircraft.
    In a second embodiment, the display computer 18 determines a vertical angular difference. The term vertical angular difference here denotes an angular difference considered in projection in a vertical plane.
    For example, in FIGS. 9b and 10b shown in side view and therefore corresponding to a projection in a vertical plane, the vertical angular difference corresponds to the angle θ formed between a parallel line 5 "(projected in the plane vertical) to the longitudinal axis of the aircraft and the line 52. This vertical angular difference corresponds to the pitch angle of the user's head 50. A variation of the pitch angle, and therefore of the angular difference, induces a vertical displacement of the symbols 38 and / or 40 displayed in conformity on the display 8 in the first display mode, hence the use of the vertical qualifier to designate this angular difference. the display computer 18 evaluates at least one condition based on the value of the vertical angular difference, which condition includes at least one elementary condition which is verified e when the vertical angle is between a negative predetermined threshold of vertical angular deviation and a positive predetermined threshold of vertical angular difference. An example illustrated in FIG. 13 represents a space 58 located at the front of the user's head 50 in the cockpit of the aircraft, in side view and in projection in a vertical plane. Two straight lines 5'v and 5'x respectively forming angles of value A3a and A3b with the straight line 5 ", illustrate the predetermined positive and negative thresholds of vertical angular deviation Thus, the elementary condition is verified when the line 52 (no shown in Figure 13), corresponding to the orientation of the user's head, is located between the two lines 5'v and 5'x.The values of the angles A3a and A3b are preferably chosen such that, when the line 52 is located between the two lines 5'v and 5'x, the display on the display 8 is an augmented reality display, superimposed on the external environment of the aircraft visible through the windshield Advantageously, two straight lines 5'y and 5'z form angles A3c and A3d with the line 5 ", corresponding to a second positive threshold and a second negative threshold of vertical angular difference. The lines 5'v and 5'y define an area 53c of the space 58, corresponding to pitch angles of the user's head between A3a and A3c. The lines 5'x and 5'z delimit an area 53d of the space 58, corresponding to pitch angles of the user's head between A3b and A3d. An area 53e corresponds to pitch angles greater than A3c and a zone 53f corresponds to pitch angles less than A3d. When the orientation of the head of the user is such that the straight line 52 is situated between the straight lines 5'v and 5'x (the pitch angle of the head of the user is between the predetermined negative threshold of vertical angular difference A3b and the predetermined positive threshold of vertical angular difference A3a), the elementary condition is verified and the display computer 18 controls the display according to the first display mode. When the elementary condition is not satisfied, the display computer 18 controls the display according to a third display mode in which the display corresponding to the first display mode is at least partially masked. Advantageously, this display is partially hidden when the orientation of the head of the user is such that the line 52 is located in one of the zones 53c or 53d and, the display is completely hidden when the orientation of the head of the user is such that the line 52 is located in one of the zones 53e or 53f. The values of the angles A3a and A3b being chosen as indicated above, when the display computer 18 controls the display according to the first display mode, this display is visible to the user in superposition of the environment of the aircraft visible through the windshield of the cockpit. The user can therefore see the symbol or symbols displayed in conformity in superposition of said environment. When the pitch angle of the user's head is such that the straight line 52 is located in one of the zones 53c or 53d, the environment visible to the user through the display 8 of the display device 20 corresponds partly to the external environment of the aircraft (through the windshield of the cockpit) and partly inside the cockpit. For example, in the zone 53c, the environment visible to the user through an upper part of the display 8 corresponds to buttons panels of the ceiling of the cockpit. In zone 53d, the environment visible to the user through a lower part of the display 8 corresponds to a part of the cockpit located under the windshield, for example a control module FCU ("Flight Control Unit" in English) and possibly cockpit head-down display screens. In the third display mode, the display on the display 8 is then partially hidden so as to display information on the display 8 only in a part of the display 8 such that this information is visible to the user. user in superposition of the external environment of the aircraft. The display is hidden in the part of the display (high or low depending on the situation) for which the environment visible to the user through this part of the display corresponds to the interior of the cockpit.
    Fig. 9a shows a partially masked display on the display 8, corresponding to an orientation of the user's head 50 as shown in Fig. 9b. The pitch angle Θ of the user's head lies between the positive threshold of vertical angular difference A3a and the second positive threshold of vertical angular difference Δ3α. Therefore, the environment visible to the user through the the upper part of the display 8 corresponds to the cockpit ceiling, in particular the cockpit control panel panels. The display is partially hidden in such a way that no information is displayed in the upper part of the display 8. Preferably, the information displayed in a non-conforming manner, in particular the roll scales 34, of altitude 32 and speed 30, are shifted down on the display 8 relative to their respective positions in the first display mode. These scales are all the more offset towards the bottom of the display 8 that the user raises the head towards the ceiling of the cockpit (and that the pitch angle Θ is high). When their display is possible, the aircraft reference symbol 38 and / or the speed vector symbol 40 are displayed in accordance, as in the first display mode.
    Similarly, Figure 10a shows a partially masked display on the display 8, corresponding to an orientation of the head 50 of the user as shown in Figure 10b. The pitch angle Θ of the user's head is between the vertical angular difference negative threshold A3b and the second negative vertical angular difference threshold A3d. The environment visible to the user through the lower part of the display 8 corresponds in particular to the FCU control module of the cockpit. The display is partially hidden in such a way that no information is displayed in the lower part of the display 8. Preferably, the information displayed in a non-conforming manner, in particular the roll scales 34, of altitude 32 and speed 30, are shifted upward on the display 8 relative to their respective positions in the first display mode. As a result, the roll scale 34 is not displayed in the example shown in Fig. 10a. These scales are all the more offset towards the top of the display 8 that the user lowers his head towards the floor of the cockpit (and that the pitch angle Θ is low). When their display is possible, the aircraft reference symbol 38 and / or the speed vector symbol 40 are displayed in accordance, as in the first display mode.
    The values of the second positive and negative thresholds of vertical angular difference A3c and A3d (respectively corresponding to the straight lines 5'y and 5'z) are advantageously chosen so as to correspond to pitch angles of the user's head from of which the external environment of the aircraft visible through the windshield of the cockpit is no longer visible through the display 8. Thus, when the user raises his head towards the ceiling of the cockpit, as long as the angle pitch Θ of its head is less than A3a, the entire environment visible to the user through the display 8 corresponds to the external environment of the aircraft visible through the windshield and the computer of display 18 controls the display according to the first display mode. When the user continues to raise his head towards the ceiling of the cockpit, from the moment when the pitch angle Θ of his head becomes greater than A3a, while remaining lower than A3c, the upper part of the environment visible by the user through the display 8 corresponds to the ceiling of the cockpit and the display is partially hidden as already described. The more the user raises his head, the more non-conforming information displayed, in particular the scales, is shifted downward from the display 8. When the user continues to lift his head towards the ceiling of the cockpit, from from the moment when the pitch angle Θ of its head becomes greater than A3c, the environment visible to the user through the display 8 corresponds entirely to the ceiling of the aircraft and therefore the display on the display 8 is completely hidden. Similarly, when the user lowers his head towards the cockpit floor, as long as the pitch angle Θ of his head is greater than A3b, the entire environment visible to the user through the display 8 corresponds to the external environment of the aircraft visible through the windshield and the display computer 18 controls the display according to the first display mode. When the user continues to lower his head towards the floor of the cockpit, from the moment when the pitch angle Θ of his head becomes less than A3b, while remaining higher than A3d, the lower part of the environment visible by the user through the display 8 corresponds to the FCU control module and possibly to the head-down screens of the cockpit and the display is partially hidden. The more the user lowers his head, the more the non-conforming information displayed, in particular the scales, is shifted upwards of the display 8. When the user continues to lower his head towards the floor of the cockpit, starting from the moment when the pitch angle Θ of its head becomes smaller than A3d, the environment visible to the user through the display 8 corresponds entirely to the control module FCU and to the head-down screens of the cockpit and consequently the display on the display 8 is completely hidden.
    The first embodiment and the second embodiment can be combined with one another. An example of a combination of the two embodiments is illustrated in FIG. 11, which represents a sectional view, in a vertical plane perpendicular to the longitudinal axis of the aircraft, of a space 58 located at the front of the aircraft. head 50 of the user in the cockpit of the aircraft. A zone Z1 corresponds to the display according to the first display mode, when the straight line 52 corresponding to the orientation of the head 50 of the user intersects the vertical plane in this zone Z1. Two zones Z2a and Z2b, located respectively to the left and to the right of Z1, correspond to a display according to the second display mode, when the straight line 52 corresponding to the orientation of the head 50 of the user intersects the vertical plane in one of the zones Z2a or Z2b. These two zones respectively correspond to the zones 53a and 53b already described with reference to FIG. 12. Two zones Z3 and Z4, situated respectively above and below ZI, correspond to a display according to the third display mode, when the line 52 corresponding to the orientation of the head 50 of the user intersects the vertical plane in one of the zones Z3 or Z4. These two zones respectively correspond to the zones 53c and 53e on the one hand and 53d and 53f on the other hand, already described with reference to FIG. 13. As already described with reference to FIGS. 9a, 10a and 13, the zones 53c and 53d and therefore the zone Z3 correspond to a display according to the third display mode. This display is based on that of the first display mode, but is at least partially hidden in an upper portion of the display 8. Two zones Z3a and Z3b are respectively located on the left and right of the zone Z3. These two zones Z3a and Z3b are located respectively above the zones Z2a and Z2b. Therefore, like the latter, they correspond to yaw angle values of the user's head for which line 52 is located in one of the zones 53a or 53b shown in FIG. Z3a and Z3b, the display is at least partially masked, as in area Z3, but instead of being based on the first display mode, it is based on the second display mode. Similarly, two zones Z4a and Z4b are respectively located on the left and right of zone Z4. These two zones Z4a and Z4b are located below zones Z2a and Z2b, respectively. Therefore, like the latter, they correspond to yaw angle values of the user's head for which the line 52 is located in one of the zones 53d or 53f shown in FIG. Z4a and Z4b, the display is at least partially masked, as in the Z4 area, but instead of being based on the first display mode, it is based on the second display mode.
    FIGS. 8a and 8b illustrate a particular embodiment in which the display computer 18 adapts the display on the display 8 as a function of the roll angle of the user's head. FIG. 8b illustrates a situation in which the user's head 50 (rear view) is inclined to the right by a roll angle φ. In such a situation, in the first display mode, the display controlled by the display computer 18 on the display 8 corresponds to that shown in FIG. 8a. On this display, the roll 34, altitude 32 and speed 30 scales, although not in conformity, are rotated by an angle -φ so as to compensate for the inclination of the head of the user. Thus, seen by the user, these scales seem fixed in a reference linked to the aircraft: for example, the altitude scales 32 and 30 speed are permanently displayed vertically in the cockpit. This allows the user to become aware of the fact that he tilts his head relative to the cockpit. The aircraft reference symbol 38 and the speed vector symbol 40 are themselves displayed in a compliant manner when they can be displayed. This particular embodiment is applicable both in the first display mode and in the third display mode when the display is partially hidden, the scales being then at least partially displayed.
    In a particular embodiment, in the third display mode the display computer 18 controls the display of at least one virtual instrument in a part of the display in which the display is hidden. As indicated above, the environment visible to the user through this part of the display preferably corresponds to an interior part of the cockpit of the aircraft, for example the ceiling of the cockpit or a part of the cockpit located under the cover. broken. According to one variant, the virtual instrument corresponds for example to a light or a virtual button of a virtual control panel visible in superposition of the ceiling of the cockpit. According to another variant, which can be combined with the previous one, the virtual instrument corresponds for example to a virtual head-down screen visible in superposition of a part of the cockpit located under the windshield.
    In a particular embodiment, the cockpit of the aircraft comprises a device for adjusting the position of the user in the cockpit. This device corresponds for example to a usual set of 3 balls located near the windshield. When the orientation of the head of the user is such that the line 52 intersects an area surrounding the user's position adjusting device for a duration greater than a predetermined time delay, the display computer controls the user's position. display on the display 8 of a symbol corresponding to the device for adjusting the position of the user. The value of the predetermined time delay is for example chosen equal to 2 seconds. The area surrounding the device for adjusting the position of the user is for example defined in a vertical plane perpendicular to the longitudinal axis of the aircraft. It is for example defined by a margin of yaw angle and a pitch angle margin of the head of the user. These margins are chosen to be sufficient to enable detection by the display computer 18 because the user is looking at the user's position adjustment device while taking into account the fact that the user's head is not visible. perfectly immobile. However, these margins are chosen small enough to avoid inadvertently detecting the fact that the user is looking at the user's position adjustment device, even though he would observe the external environment of the aircraft. The display on the display 8 of the symbol corresponding to the device for adjusting the position of the user enables the user to check whether the position of said symbol, calculated by the display computer 18, is superimposed on the actual device. setting the user's position visible through the display. If this is the case, the user knows that the display system is well aligned and that he can have confidence in the position of the information displayed on the display, in particular the positions of the symbols displayed in conformity. On the other hand, if the position of said symbol, calculated by the display computer 18, is not superimposed on the actual device for adjusting the position of the user visible through the display, the user knows that must not use the display system. A reset of the alignment of the display system must then be performed during an aircraft maintenance operation. A verification as aforesaid of the alignment of the display system may in particular be carried out before any use of said system during an approach procedure for landing on an airstrip of an airport.
    In an advantageous embodiment, the display system further comprises a position sensor of the user's head. According to a first variant, this position sensor is independent of the sensor 16 for orienting the head of the user. According to a second variant, this position sensor is integrated in the sensor 16 for orienting the head of the user. The display computer is then configured to acquire information provided by this position sensor and to determine the angular deviation value as a function of both the orientation of the user's head and the position of the head. of the user. This embodiment is of interest especially when the user is positioned in the cockpit of the aircraft so that the position of his head does not correspond to a theoretical position. This results in a better match between on the one hand the areas 53c, 53e, 53d and 53f and on the other hand the environment visible to the user as a function of the actual position of his head.
    The display system 10 described above can correspond to both a monocular system and a binocular system. In the case of a monocular system, the display device 20 comprises a single display 8. In the case of a binocular system, the display device 20 comprises two displays 8, each dedicated to an eye of the user. .
    权利要求:
    Claims (15)
    [1" id="c-fr-0001]
    A system (10) for displaying a cockpit (3) of an aircraft (1) comprising: - a display device (20) configured to be carried integral with the head of a user in the cockpit of the aircraft; - an orientation sensor (16) of the head (50) of the user of the display device; and - a display computer (18) configured to control the display of information relating to the flight of the aircraft on the display device (20), characterized in that the display computer is configured for: acquire orientation information from the user's head, provided by the sensor; determining at least one angular difference value between firstly a direction corresponding to said orientation information of the user's head and secondly a longitudinal axis of the aircraft; to evaluate at least one functional condition at least of said angular difference value; and - control the display on the display device according to: a first display mode when said condition is verified, this first display mode corresponding to a display comprising at least one symbol (38, 40) to aid the piloting of the aircraft displayed in a compliant manner; and. another display mode when said condition is not verified.
    [2" id="c-fr-0002]
    2. System according to claim 1, characterized in that the at least one flight aid symbol is chosen from among the following symbols: a symbol (40) of the speed vector of the aircraft; and an aircraft reference symbol (38).
    [3" id="c-fr-0003]
    3- System according to one of claims 1 or 2, characterized in that the angular difference value comprises a lateral angular difference and said condition includes at least a first elementary condition which is verified when the lateral angular difference is between a predetermined negative threshold (-Δ1) of lateral angular deviation and a positive predetermined threshold (Δ1) of lateral angular deviation.
    [4" id="c-fr-0004]
    4. The system of claim 3 combined with claim 2, characterized in that said condition further includes a second elementary condition which is verified when the value of a second lateral angular difference between on the one hand the direction (52) corresponding to the orientation of the head of the user and secondly the speed vector (41) of the aircraft is between a second predetermined negative threshold (-Δ2) of lateral angular difference and a second predetermined positive threshold ( Δ2) lateral angular deviation.
    [5" id="c-fr-0005]
    5. System according to one of claims 3 or 4, characterized in that the other display mode corresponds to a second display mode in which the at least one symbol (40a) for driving assistance of the aircraft is displayed incorrectly.
    [6" id="c-fr-0006]
    6. System according to claim 5, characterized in that the at least one symbol is a speed vector symbol (40a) of the aircraft and the display further comprises a symbol (42a) representative of a line of horizon, the aircraft speed vector symbol and the horizon line symbol being displayed relative to each other to indicate a climb movement or a descent movement of the aircraft .
    [7" id="c-fr-0007]
    7- System according to one of claims 5 or 6, characterized in that the at least one symbol (40a) of piloting assistance of the aircraft is displayed non-compliant with a characteristic position of a direction towards which the user can direct his head to obtain a consistent display of the at least one symbol (40) in the first display mode.
    [8" id="c-fr-0008]
    8- System according to any one of claims 5 to 7, characterized in that, in the second display mode, the display further comprises a symbol (42a, 34a, 34b) representative of the roll of the aircraft, represented associated with the at least one symbol (40a).
    [9" id="c-fr-0009]
    9- System according to any one of claims 5 to 8, characterized in that, in the second display mode, the display comprises a reduced number of information with respect to the display corresponding to the first display mode .
    [10" id="c-fr-0010]
    10- System according to any one of the preceding claims, characterized in that the angular difference value comprises a vertical angular difference and said condition includes at least one elementary condition which is verified when the vertical angular difference is between a threshold predetermined negative (A3b) vertical angular difference and a predetermined positive threshold (A3a) vertical angular difference.
    [11" id="c-fr-0011]
    11- System according to claim 10, characterized in that the other display mode corresponds to a third display mode in which the display corresponding to the first display mode is at least partially masked.
    [12" id="c-fr-0012]
    12- System according to any one of the preceding claims, characterized in that, in the first display mode, the display comprises at least a portion of a trim scale (36) and, where appropriate, this scale plate is laterally expanded depending on the orientation of the user's head, to allow the display of said at least a portion of the trim scale.
    [13" id="c-fr-0013]
    13- System according to any one of the preceding claims, characterized in that, in the first display mode, the display further comprises a speed scale (30) and / or an altitude scale (32) and the display computer controls the display on the display device so that the speed scale and / or the altitude scale are displayed vertically in a reference frame linked to the aircraft.
    [14" id="c-fr-0014]
    14- A method of displaying in a cockpit (3) of an aircraft (1), the aircraft comprising a display system (10) comprising: - a display device (20) configured to be carried integral with the head (50) of a user in the cockpit of the aircraft; a sensor (16) for orienting the head of a user of the display device; and a display computer (18) configured to control the display of information relating to the flight of the aircraft on the display device, the method being characterized in that it comprises the following steps implemented by the display computer: - acquiring orientation information from the user's head, provided by the sensor; determining at least one angular difference value between firstly a direction corresponding to said orientation information of the user's head and secondly a longitudinal axis of the aircraft; to evaluate at least one functional condition at least of said angular difference value; and - control the display on the display device according to: a first display mode when said condition is verified, this first display mode corresponding to a display comprising at least one symbol (38, 40) to aid the piloting of the aircraft displayed in a compliant manner; and. another display mode when said condition is not verified.
    [15" id="c-fr-0015]
    15- Aircraft (1) characterized in that it comprises a display system (10) according to one of claims 1 to 13.
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    同族专利:
    公开号 | 公开日
    CN107487449A|2017-12-19|
    CN107487449B|2020-05-05|
    FR3052553B1|2020-11-27|
    US20170358108A1|2017-12-14|
    US10235777B2|2019-03-19|
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    法律状态:
    2017-06-21| PLFP| Fee payment|Year of fee payment: 2 |
    2017-12-15| PLSC| Search report ready|Effective date: 20171215 |
    2018-06-26| PLFP| Fee payment|Year of fee payment: 3 |
    2020-06-19| PLFP| Fee payment|Year of fee payment: 5 |
    2021-06-22| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1655438A|FR3052553B1|2016-06-13|2016-06-13|AIRCRAFT DISPLAY SYSTEM AND METHOD|FR1655438A| FR3052553B1|2016-06-13|2016-06-13|AIRCRAFT DISPLAY SYSTEM AND METHOD|
    US15/616,614| US10235777B2|2016-06-13|2017-06-07|Display System and method for an aircraft|
    CN201710429619.8A| CN107487449B|2016-06-13|2017-06-09|Display system and method for an aircraft|
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