Patent Publication Number: US-2021166570-A1

Title: Aircraft display system and method

Description:
CROSS-REFERENCE TO RELATED APPLICATION AND CLAIM OF PRIORITY 
     The present application claims priority to U.S. Provisional Patent Application Ser. No. 62/941,984 filed Nov. 29, 2019, the entire contents of which are hereby incorporated by reference. 
    
    
     TECHNICAL FIELD 
     The disclosure relates generally to aircraft, and more particularly to aircraft display systems. 
     BACKGROUND 
     An electronic primary flight display (PFD) of an aircraft is used to display primary flight information and can include an airspeed indicator, turn coordinator, altimeter and a vertical speed indicator for example. A PFD can also be used to display other awareness-type information. The presentation of primary flight information and awareness-type information on the PFD can be distracting and require significant effort from the pilot to interpret the information presented. 
     SUMMARY 
     In one aspect, the disclosure describes a primary flight display system for an aircraft. The system comprises: 
     a display device; 
     one or more processors operatively connected to the display device; and 
     non-transitory machine-readable memory operatively connected to the one or more processors, storing instructions executable by the one or more processors and configured to cause the one or more processors to: 
     using data associated with an operation of the aircraft, cause a primary flight display representation to be displayed on the display device, the primary flight display representation including a first textual object having a first font size; and 
     cause the primary flight display representation on the display device to include a second textual object having a second font size, the second font size being 2.5 or more times larger than the first font size. 
     The second font size may be three or more times larger than the first font size. 
     The second font size may be about four times larger than the first font size. 
     The second font size may be about five times larger than the first font size. 
     The second font size may be between 2.5 and ten times larger than the first font size. 
     The second font size may be between three and six times larger than the first font size. 
     The second textual object may be an alert flag. 
     The second textual object may have a transparent background. 
     The second textual object may have a color that is commensurate with an alert level associated with the second textual object. 
     The second textual object may have a transparency level that is commensurate with the or an alert level associated with the second textual object. 
     The second font size of the second textual object may be commensurate with the or an alert level associated with the second textual object. 
     The second textual object may define an axis scale. 
     The second textual object may define a heading scale. 
     The first and second textual objects may be collocated. 
     The first and second textual objects may be at least partially superimposed. 
     One or more characters of the second textual object may be partially transparent. 
     The instructions may be configured to cause the one or more processors to cause the second textual object to be displayed on an attitude indicator of the primary flight display representation. 
     The second textual object may be collocated with a graphical object. 
     The instructions may be configured to cause the one or more processors to cause a position of the second textual object to be selected based on a current phase of flight of the aircraft. 
     Embodiments can include combinations of the above features. 
     In another aspect, the disclosure describes a computer-implemented method for controlling a display device of an aircraft. The method comprises: 
     using data associated with an operation of the aircraft, causing a primary flight display representation to be displayed on the display device, the primary flight display representation including a first textual object having a first font size; and 
     causing the primary flight display representation on the display device to include a second textual object having a second font size, the second font size being 2.5 or more times larger than the first font size. 
     The second font size may be three or more times larger than the first font size. 
     The second font size may be about four times larger than the first font size. 
     The second font size may be about five times larger than the first font size. 
     The second font size may be between 2.5 and ten times larger than the first font size. 
     The second font size may be between three and six times larger than the first font size. 
     The second textual object may be an alert flag. 
     The second textual object may have a transparent background. 
     The second textual object may have a color that is commensurate with an alert level associated with the second textual object. 
     The second textual object may have a transparency level that is commensurate with the or an alert level associated with the second textual object. 
     The second font size of the second textual object may be commensurate with the or an alert level associated with the second textual object. 
     The second textual object may define an axis scale. 
     The second textual object may define a heading scale. 
     The first and second textual objects may be collocated. 
     The first and second textual objects may be at least partially superimposed. 
     One or more characters of the second textual object may be partially transparent. 
     The method may comprise causing the second textual object to be displayed on an attitude indicator of the primary flight display representation. 
     The second textual object may be collocated with a graphical object. 
     The method may comprise causing a position of the second textual object to be selected based on a current phase of flight of the aircraft. 
     Embodiments can include combinations of the above features. 
     In another aspect, the disclosure describes a computer program product for a method for controlling a display device of an aircraft, the computer program product comprising a non-transitory computer readable storage medium containing program code, the program code being readable/executable by a computer, processor or logic circuit to perform a method as disclosed herein. 
     In another aspect, the disclosure describes an aircraft comprising the system as disclosed herein. 
     Further details of these and other aspects of the subject matter of this application will be apparent from the detailed description included below and the drawings. 
    
    
     
       DESCRIPTION OF THE DRAWINGS 
       Reference is now made to the accompanying drawings, in which: 
         FIG. 1  shows an exemplary aircraft flight deck and a corresponding exemplary aircraft including the flight deck; 
         FIG. 2  shows a schematic representation of an exemplary display system of the aircraft of  FIG. 1 ; 
         FIG. 3  shows an exemplary primary flight display representation generated using the system of  FIG. 2 ; 
         FIG. 4  shows another exemplary primary flight display representation generated using the system of  FIG. 2 ; 
         FIG. 5  shows another exemplary primary flight display representation generated using the system of  FIG. 2 ; and 
         FIG. 6  is a flowchart of a method for controlling a display device of an aircraft. 
     
    
    
     DETAILED DESCRIPTION 
     Systems and methods for assisting a pilot during flight of an aircraft are disclosed herein. In various embodiments, the systems and methods disclosed herein can improve the operation of an aircraft flight deck by providing visualization techniques to display textual objects in a manner that reduces interference with traditional display characters and symbology used on a primary flight display (PFD) or other types of aircraft displays. In some embodiments, the systems and methods disclosed herein can enable high saliency to be achieved for textual objects associated with immediate action flags while limiting the distraction of a pilot prior to or during escape maneuvers requiring significant pilot attention for example. In some embodiments, the systems and methods disclosed herein can permit the saliency of textual objects to be commensurate with associated alert levels. In some embodiments, the systems and methods disclosed herein can permit the simultaneous display of textual and/or graphical objects in a superimposed yet clear and effective manner. 
     In some embodiments, the systems and methods disclosed herein can enhance the situational awareness of the pilot during phases of flight of relatively high workload. Such enhancement in situational awareness can improve flight safety by helping reduce the potential for pilot error. The systems and methods disclosed herein can be used during various phases of operation (e.g., flight) of aircraft. 
     Aspects of various embodiments are described through reference to the drawings. 
       FIG. 1  shows an exemplary aircraft  10  and a partial schematic representation of flight deck  12  which can be part of aircraft  10 . Aircraft  10  can be a corporate, private, commercial or any other type of aircraft. For example, aircraft  10  can be a fixed-wing or rotary-wing aircraft. In some embodiments, aircraft  10  can be a narrow-body, twin engine jet airliner or an (e.g., ultra-long-range) business jet. Aircraft  10  can be a drone controlled remotely. Flight deck  12  can include additional or fewer elements than those shown and described herein. Flight deck  12  can include left portion  12 A intended to be used by a pilot (sometimes referred as “captain”) of aircraft  10  and right portion  12 B intended to be used by a co-pilot (sometimes referred as “first officer”) of aircraft  10 . As referenced herein, the term “pilot” is intended to encompass an individual responsible for the operation of aircraft  10  during flight either onboard aircraft  10  or off of aircraft  10 . Left portion  12 A and right portion  12 B can have functionally identical components so that at least some operational redundancy can be provided between left portion  12 A and right portion  12 B of flight deck  12 . 
     Flight deck  12  can include one or more display devices  14 A,  14 B (referred generally herein as “display device  14 ”) providing respective display areas. In the exemplary configuration of flight deck  12  shown in  FIG. 1 , left portion  12 A and right portion  12 B can each include two head-down display devices  14 A (referred hereinafter in the singular as “HDD  14 A”) and an additional HDD  14 A can be provided in pedestal region  16  of flight deck  12 . HDD  14 A provided in pedestal region  16  can be shared by the two pilots during normal operation of aircraft  10 . HDDs  14 A can include one or more cathode-ray tubes (CRTs), liquid crystal displays (LCDs), plasma displays, light-emitting diode (LED) based displays or any type of display device suitable for use in flight deck  12 . HDDs  14 A can be configured to dynamically display (e.g., real-time) information about various systems of aircraft  10 , information related to flight/mission planning, maps and any other information that can be useful to the pilot during the operation of aircraft  10 . HDDs  14 A can facilitate dialog between the pilot and various systems of aircraft  10  via suitable graphical user interfaces. Flight deck  12  can include one or more data input devices such as, for example, one or more cursor control devices  18 , one or more multi-function keypads  20  that permit data entry by the pilot. In some embodiments, one or more HDDs  14 A could have touch sensitive display area(s) to permit user input by way of the pilot touching the applicable display area(s). 
     Flight deck  12  can also include one or more head-up display devices  14 B (referred hereinafter in the singular as “HUD  14 B”) which can be transparent displays that can present data without requiring the pilot to look away from his/her usual point out the windshield of aircraft  10 . HUD  14 B can present information to the pilot while the pilot&#39;s head is positioned “up” and looking forward, instead of angled down looking at lower instruments or displays such as HDDs  14 A. In various embodiments, right and left portions  12 A,  12 B of flight deck  12  can each have a HUD  14 B or, alternatively, flight deck  12  can include only one HUD  14 B disposed in left portion  12 A of flight deck  12  for example. HUDs  14 A can either be fix-mounted displays or head-mounted displays (including helmet-mounted displays). In various embodiments, HUD  14 B can include a CRT configured to generate an image on a phosphor screen, a solid state light source such as a LED that is modulated by an LCD screen to display an image, optical waveguides that produce an image directly in a combiner, or a scanning laser configured to display an image on a transparent medium. 
     It is understood that aspects of this disclosure, including the display of textual objects, are not limited to one or more display devices  14  that are part of flight deck  12  or that are onboard aircraft  10 . For example, the display of textual objects and associated steps could, alternatively or in addition, be performed off of aircraft  10  using a system and/or display device  14  that are located off of aircraft  10  and are used to control aircraft  10  remotely. For example, relevant information could be transmitted between aircraft  10  and a location remote from aircraft  10  (e.g., ground station) in order to be used by an operator (i.e., pilot) controlling/flying aircraft  10  remotely. 
       FIG. 2  shows a schematic representation of an exemplary system  22  which can be part of aircraft  10  or off of aircraft  10  and which can assist a pilot during flight of aircraft  10  by providing enhanced situational awareness to the pilot with reduced distraction. System  22  can be integrated with flight deck  12 . System  22  can include one or more computers  24  (referred hereinafter in the singular) operatively connected to one or more display devices  14  (e.g., HDD  14 A and/or HUD  14 B) of flight deck  12 . Computer  24  can be configured to control at least some of the information/content displayed on display device  14 . System  22  and methods disclosed herein can be used with one or more display devices  14  operating as PFDs. Accordingly, the textual objects defined herein can be displayed on one or more PFDs. 
     Computer  24  can include one or more data processors  26  (referred hereinafter in the singular) and one or more computer-readable memories  28  (referred hereinafter in the singular) storing machine-readable instructions  30  executable by data processor  26  and configured to cause data processor  26  to generate one or more outputs including one or more signals for causing display device  14  of aircraft  10  to display one or more textual objects  32 A,  32 B and optionally other textual or graphical (i.e., non-textual) objects. 
     Computer  24  can receive input(s)  34  in the form of data or information that can be processed by data processor  26  according to instructions  30  in order to generate suitable output for controlling display device  14 . Input  34  can include information (data) associated with the operation of aircraft  10 . Input  34  can be received via manual entry by the pilot using one or more pilot input devices such as cursor control device  18  and/or multi-function keypad  20  for example. Alternatively or in addition, input  34  can be received automatically from one or more data sources (e.g., aircraft systems  36 ) operatively connected to computer  24  such as a navigation system, a flight management system, an air data system and/or a (e.g., radar) altimeter for example. Input  34  can include operating parameters of aircraft  10  measured via suitable sensors or derived from data acquired via such sensors. Input  34  can include data indicative of a substantially real-time status of aircraft  10 . The term “substantially” as used herein may be applied to modify any quantitative representation which could permissibly vary without resulting in a change in the basic function to which it is related. 
     Computer  24  can be part of an avionics suite of aircraft  10  and be operatively integrated with avionic components of aircraft  10 . For example, in some embodiments, computer  24  can be configured to carry out additional functions than those described herein including the management of one or more graphic user interfaces of flight deck  12  and/or other part(s) of aircraft  10 . The methods disclosed herein (or part(s) thereof) could be performed using a plurality of computers  24  or data processors  26 , or, alternatively, be performed entirely using a single computer  24  or data processor  26 . In some embodiments, computer  24  could be physically integrated with (e.g., embedded in) display device  14 . 
     Data processor  26  can include any suitable device(s) configured to cause a series of steps to be performed by computer  24  so as to implement a computer-implemented process such that instructions  30 , when executed by computer  24 , can cause the functions/acts specified in the methods described herein to be executed. Data processor  26  can include, for example, any type of general-purpose microprocessor or microcontroller, a digital signal processing (DSP) processor, an integrated circuit, a field programmable gate array (FPGA), a reconfigurable processor, other suitably programmed or programmable logic circuits, or any combination thereof. 
     Memory  28  can include any suitable known or other machine-readable storage medium. Memory  28  can include non-transitory computer readable storage medium such as, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any suitable combination of the foregoing. Memory  28  can include a suitable combination of any type of computer memory that is located either internally or externally to computer  24 . Memory  28  can include any storage means (e.g. devices) suitable for retrievably storing machine-readable instructions  30  executable by data processor  26 . 
       FIG. 3  shows an exemplary representation of a PFD displayed on display device  14  using system  22 . In various embodiments, the PFD representation shown on display device  14  can include one or more of the following: airspeed indicator  38 , attitude indicator  40  sometimes referred to as “ADI”, side slip indicator  42 , altimeter  44 , vertical speed indicator  46 , turn indicator  48 , horizontal situation indicator (not shown), flight path vector (not shown) and flight director (not shown). The area of display device  14  that is typically used as attitude indicator  40  can inform the pilot of the pitch and roll characteristics of aircraft  10  and the orientation of aircraft  10  with respect to the horizon substantially in real time. Attitude indicator  40  can be located generally centrally in the PFD representation. 
     The information presented in various areas and indicators of display device  14  can be based on real-time data associated with the operation of aircraft and received as input  34 . The information can be presented using graphical objects (e.g., lines, symbols or other non-textual objects) and/or textual objects. In some embodiments, system  22  can be configured to present one or more first textual objects  32 A in the PFD representation in one or more “regular” first font sizes and one or more second textual objects  32 B in the same PFD representation in one or more significantly larger second font sizes compared to the first font sizes of any first textual objects  32 A that are displayed in the PFD representation simultaneously with second textual objects  32 B. The significantly large difference in font sizes between first and second textual objects  32 A,  32 B (and optionally other visual characteristics disclosed herein) can help the pilot distinguish between different types of information presented by offering a relatively clear visual grouping between the types of information. In some embodiments, first textual objects  32 A of the first font size can be associated with primary flight information which can include a pitch scale, flight path vector, flight director and a speed indication and an altitude indication. The primary flight information may be defined as basic flight parameters that are known to a person skilled in the art as being common to all PFDs, and comprises at least one of airspeed, vertical speed, attitude and altitude. 
     In some embodiments, second textual objects  32 B of the second font size can be associated with awareness-type of information which can include alert messages and numerical values along a scale for example. Awareness-type information can be defined as information that is not (i.e., other than) primary flight information. 
     The font size as referenced herein is intended to represent the overall size (generally height) of a font shown on display device  14 . The font size can be measured in a point (pt) size, which is the vertical measurement of the lettering where 72 points is equal to one inch (25.4 mm). In some embodiments, the second font size(s) of second textual object(s)  32 B can be at least 2.5 times larger than the first font size(s) of first textual object(s)  32 A. In some embodiments, the second font size(s) of second textual object(s)  32 B can be three or more times larger than the first font size(s) of first textual object(s)  32 A. In some embodiments, the second font size(s) of second textual object(s)  32 B can be four or more times larger than the first font size(s) of first textual object(s)  32 A. In some embodiments, the second font size(s) of second textual object(s)  32 B can be five or more times larger than the first font size(s) of first textual object(s)  32 A. In some embodiments, the second font size(s) of second textual object(s)  32 B can be up to ten times larger than the first font size(s) of first textual object(s)  32 A. In some embodiments, the second font size(s) of second textual object(s)  32 B can be between  2 . 5  and ten times larger than the first font size(s) of first textual object(s)  32 A. In some embodiments, the second font size(s) of second textual object(s)  32 B can be between 2.5 and eight times larger than the first font size(s) of first textual object(s)  32 A. In some embodiments, the second font size(s) of second textual object(s)  32 B can be between three and six times larger than the first font size(s) of first textual object(s)  32 A. In some embodiments, the second font size(s) of second textual object(s)  32 B can be between 2.5 and five times larger than the first font size(s) of first textual object(s)  32 A. In various embodiments, the second font size(s) of second textual object(s)  32 B can be about 2.5, about three, about four, about five, about six, about seven, about eight, about nine or about ten times larger than the first font size(s) of first textual object(s)  32 A. 
     In addition to font size, other characteristics of second textual object(s)  32 B can also be used to achieve the desired visual effect. For example, the characteristics of second textual object(s)  32 B can be selected so that the primary flight information is not overly obscured (e.g., masked or covered) by second textual object(s)  32 B and the pilot&#39;s eye scan pattern is also not overly disrupted. For example, the characteristics of second textual object(s)  32 B can be selected to provide an appropriate level of saliency and prominence to make second textual object(s)  32 B distinguishable from its surroundings. In some embodiments, the characteristics of second textual object(s)  32 B can be selected to achieve a visual effect that is not overly bold or striking and also does not capture the pilot&#39;s eye scanning pattern for too long. The characteristics of second textual object(s)  32 B can also be selected so as not to create a false image when combined with other graphical or textual objects that can be collocated with textual object(s)  32 B. 
     Characteristics of second textual object(s)  32 B can include one or more of the following: location within the display area of display device  14 , font size, font style, use of bold characters, use of filled or hollow characters, color, shading, transparency level of characters, flashing, blinking, contrast, dynamic variation of color saturation, fading animation to introduce and remove second textual object(s)  32 B from display device  14  and superimposition with other textual or graphical objects shown on display device  14 . Shading can include graphical overlays both patterned and solid, whether opaque or partially transparent. During operation of system  22 , commands for displaying second textual objects  32 B on displayed device  14  generated by computer  24  can be representative of a string of textual characters, their position(s) within the display area of display device  14  and one or more properties that specify visual characteristics corresponding to the desired visual effect. 
     In reference to  FIG. 3 , second textual objects  32 B can be numerical values such as “27”, “30” and “33” that define a heading scale along a horizon line displayed in the PFD representation. Second textual objects  32 B can be displayed in a display area that also includes attitude indicator  40 . The visual characteristics of second textual objects  32 B can be selected to exhibit a level of saliency that is commensurate with a level of alert (urgency) associated with the information represented by second textual objects  32 B. In this embodiment, second textual objects  32 B have a relatively high transparency level and have a color (e.g., white) selected to correspond to a relatively low level of alert. While second textual objects  32 B effectively convey the intended information to the pilot, they are not overly distracting to the pilot and also do not significantly obscure other primary flight information displayed on display device  14 . 
     Second textual objects  32 B can be positioned within the PFD representation and in a superimposed relationship with other textual objects (e.g., first textual objects  32 A) and/or graphical objects (e.g., lines and symbols) displayed in the same display area. In other words, one or more second textual objects  32 B can be collocated with one or more first textual objects  32 A or other object(s). Accordingly, the message represented by second textual objects  32 B does not need to be presented in a region of the display area that is free of other objects. In the example shown, numerical value “30” is in a superimposed relationship with horizontal lines that are part of a pitch scale of attitude indicator  40 . In various embodiments, second textual objects  32 B can displayed to overlay other objects or be under other objects. In some embodiments first and second textual objects  32 A,  32 B can be at least partially superimposed. Second textual objects  32 B can have a transparent background area so as not to obstruct the underlying display around and between the characters of second textual objects  32 B. 
       FIG. 4  shows another exemplary representation of a PFD displayed on display device  14  using system  22 . Second textual objects  32 B can include numerical values “27”, “30” and “33” from  FIG. 3  and, alternatively or in addition, an alert flag displaying the message “STALL”. The alert flag can be displayed in a display area that also includes attitude indicator  40 . For example, the alert flag can be displayed in a central region of the PFD representation and may overlay part of attitude indicator  40 . 
     The alert flag can be associated with a miscompare error, failure or other time-critical event. The visual characteristics of the alert flag can be selected to exhibit a level of saliency that is commensurate with the level of alert associated with the information represented by the alert flag. In this embodiment, the alert flag has a lower transparency level, has a larger font size than the numerical values “27”, “30” and “33”, and has a color (e.g., red) selected to correspond to a relatively high level of alert. In various embodiments colors such as white, amber and red can be used for low, medium (caution) and high (warning) alert levels respectively. While the “STALL” alert flag effectively conveys the intended message and the corresponding alert level to the pilot, the alert flag does not significantly obscure other primary flight information displayed on display device  14  and does not pull the pilot&#39;s gaze away from the primary flight information, which can be helpful to the pilot when dealing with the situation associated with the alert flag. 
     The alert flag can be positioned within the PFD representation of display device  14  and in a superimposed relationship with other textual objects (e.g., first textual objects  32 A) and/or graphical objects (e.g., lines and symbols) displayed in the same display area. In some embodiments, corresponding haptic and/or audible alert(s) can be generated in conjunction with the alert flag displayed in the PFD representation. 
       FIG. 5  shows another exemplary representation of a PFD displayed on display device  14  using system  22 . Second textual objects  32 B can include numerical values “27”, “30” and “33” from  FIG. 3  and, alternatively or in addition, also another alert flag displaying the message “PULL UP”. The alert flag can be displayed in the PFD representation and may overlay part of attitude indicator  40 . The visual characteristics of the alert flag can be selected to exhibit a level of saliency that is commensurate with the level of alert associated with the information represented by the alert flag. In this embodiment, the alert flag has a lower transparency level and has a larger font size than the numerical values “27”, “30” and “33” selected to correspond to a relatively high level of alert. While the “PULL UP” alert message effectively conveys the intended message and the corresponding alert level to the pilot, the alert flag does not significantly obscure other primary flight information displayed on display device  14  and does not pull the pilot&#39;s gaze away from the primary flight information, which can be helpful to the pilot when dealing with the situation of aircraft  10  associated with the alert flag. 
     The position of the alert flag can be linked to a particular phase of operation (e.g., flight) of aircraft  10 . For example, an alert flag displayed during an approach phase of flight could be displayed at a lower position on the display area compared to the same or other alert flag being displayed during another phase of flight. In some embodiments, the position of second textual object  32 B can depend on the content of second textual object  32 B. 
       FIG. 6  is a flowchart of method  100  for controlling a (e.g., primary flight) display device of aircraft  10 . Method  100  can be computer-implemented and performed using system  22  described herein or other suitable system. Accordingly, the functionality of system  22  disclosed herein is also applicable to method  100  and is not repeated below in relation to method  100 . Method  100  can comprise: 
     using data (e.g., input  34  in  FIG. 2 ) associated with an operation of aircraft  10 , causing a PFD representation to be displayed on display device  14 , the PFD representation including first textual object  32 A having a first font size (see block  102 ); and 
     causing the PFD representation on the display device  14  to include second textual object  32 B having a second font size that is 2.5 or more times larger than the first font size (see block  104 ). 
     The above description is meant to be exemplary only, and one skilled in the relevant arts will recognize that changes may be made to the embodiments described without departing from the scope of the invention disclosed. The present disclosure may be embodied in other specific forms without departing from the subject matter of the claims. The present disclosure is intended to cover and embrace all suitable changes in technology. Modifications which fall within the scope of the present invention will be apparent to those skilled in the art, in light of a review of this disclosure, and such modifications are intended to fall within the appended claims. Also, the scope of the claims should not be limited by the preferred embodiments set forth in the examples, but should be given the broadest interpretation consistent with the description as a whole.