Rendering of Skyveil on the Avionics Primary Flight Display

Abstract

The avionics display software for the aircraft (2) - a display device (3) coupled to receive image rendering display commands and to responsively display a rendered image; - a terrain data source (4) that outputs terrain data representative of the terrain within the field of view of the pilot (13) of the aircraft (2); - an avionics flight data source (10) that outputs avionics data representative of the flight conditions of the aircraft (2), including the roll angle of the aircraft (2); and - a computational resource (6) coupled to the terrain data source (4) to receive terrain data from the terrain data source (4), coupled to the avionics flight data source (10) to receive avionics data from the avionics flight data source (10), and coupled to the display device (3) to provide image rendering display commands to the display device (3) based on the received terrain data and avionics data. The avionics display software is executable by the computational resource (6) and, when executed, programs the computational resource (6) to cause the display device (3) to display a rendered image representing a view outside an operator's window of the aircraft (2). The rendered image includes one or both of a rendered terrain (RT) and a rendered sky (RS), which represent real-world terrain and sky outside the aircraft (2) and whose positions and orientations depend on their relative position and orientation with respect to the aircraft (2). The rendered image further includes a rendered sky veil (SV). A sky veil (SV) is an overlapping graphical representation that is rendered at least partially transparent in such a way that (i) the parts of the rendered sky veil (SV) that (eventually) overlap with the rendered sky (RS) are indistinguishable from the rendered sky (RS) and (ii) the rendered terrain (RT) is visible through the transparent parts of the sky veil (SV) that overlap with the rendered terrain (RT). The sky veil (SV) is rendered as a stationary band in the rendered image during the roll of the aircraft (2). The sky veil (SV) is rendered at least partially transparent along its width (W) such that the width (WR, WL) of the transparent area of ​​the sky veil (SV) depends on the roll angle of the aircraft (2).

Description

[Technical field]

[0001] (CROSS REFERENCE TO RELATED APPLICATIONS) This patent application claims priority to European Patent Application No. 21425066.4, filed December 15, 2021, the entire disclosure of which is incorporated herein by reference.

[0002] The present invention relates generally to avionics display systems, and more particularly to synthetically rendering a sky veil on an avionics primary flight display (PFD) to improve pilot situational awareness in certain flight conditions that result in a so-called brown-over-brown display condition, where terrain is rendered on the primary flight display while little or no sky is rendered, and thus the pilot feels the need to see the location of the sky relative to the rendered terrain. [Background technology]

[0003] As we all know, in recent times, the increasing complexity of aircraft such as airplanes and helicopters has significantly increased the crew workload required for safe flight. To assist the crew in operating in safe conditions and performing their ultimate tasks, various avionics systems have been developed. In particular, pilot situational awareness has become crucial.

[0004] As such, various display systems and methods have been developed to improve pilot situational awareness. One particular type of system developed to increase flight crew situational awareness is called a synthetic vision system, which is a computer-mediated reality system for aircraft that uses three-dimensional synthetic image rendering to give the pilot a clear and intuitive understanding of the flight environment. Synthetic vision systems are designed to render a three-dimensional representation of the view outside the pilot's window on the primary flight display as a background to the primary flight display on which all flight symbology is displayed.

[0005] Certain flight situations, for example when the aircraft is flying near certain terrain such as mountains or landing, may result in the aforementioned brown-over-brown display condition, which may be partial or full, where a partial brown-over-brown display condition is meant to refer to a flight condition where only a portion of the sky is rendered on the primary flight display, and a full brown-over-brown display condition is meant to refer to a flight condition where no sky is rendered at all on the primary flight display.

[0006] A brown-over-brown indication condition is a safety-critical situation because it can cause confusion and / or disorientation to aircraft pilots, who are under pressure to know exactly where the sky is in relation to the rendered terrain.

[0007] To address this need, U.S. Patent No. 5,399,633 discloses an aircraft display system in which a sky veil is rendered on an at least partially transparent flight display such that the rendered terrain can be viewed through portions of the sky veil that overlap the terrain in a manner such that the portions of the sky veil that overlap the rendered sky are not discernible. The sky veil is rendered perpendicular to the pitch tape and parallel to the zero pitch reference line, and extends a predetermined distance from the skyward edge of the flight display measured along a line parallel to the pitch tape. [Prior art documents] [Patent documents]

[0008] [Patent Document 1] European Patent Application Publication No. 2602765 Summary of the Invention [Problem to be solved by the invention]

[0009] The applicant has recognized a need to improve upon existing technology to further improve pilot situational awareness. [Means for solving the problem]

[0010] According to the present invention there is provided aviation electronics display software as set out in the accompanying claims. [Brief description of the drawings]

[0011] [Figure 1] FIG. 1 illustrates a functional block diagram of one embodiment of an aircraft. [Diagram 2] FIG. 2 illustrates an image rendered by avionics display software according to one embodiment of the present invention. [Diagram 3] FIG. 3 illustrates an image rendered by avionics display software according to one embodiment of the present invention. [Figure 4]FIG. 4 illustrates an image rendered by avionics display software according to one embodiment of the present invention. [Diagram 5] FIG. 5 illustrates an image rendered by avionics display software in accordance with another embodiment of the present invention. [Figure 6] FIG. 6 illustrates an image rendered by avionics display software in accordance with another embodiment of the present invention. [Figure 7] FIG. 7 illustrates an image rendered by avionics display software in accordance with another embodiment of the present invention. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0012] The present invention will now be described in detail with reference to the accompanying drawings so that those skilled in the art can make and use it. Various modifications to the described embodiments will be readily apparent to those skilled in the art, and the general principles described may be applied to other embodiments and applications without departing from the scope of the invention as defined in the appended claims. Thus, the present invention should not be limited to the embodiments described and illustrated herein, but should be accorded the widest scope of protection consistent with the features described and claimed.

[0013] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly used by those having ordinary skill in the art related to the present invention. In case of conflict, the present specification, including the definitions provided, is binding. Furthermore, the examples are provided for illustrative purposes only and should not be considered as limiting.

[0014] In particular, the block diagrams contained in the accompanying drawings and described below are not intended to represent structural features or configurational limitations, but should be interpreted as representing functional features, i.e. essential characteristics, of devices for preserving similar functionality (ability to function), defined by the effect or functional limitations obtained, and which may be implemented in various ways.

[0015] To facilitate an understanding of the embodiments described herein, reference will be made to certain specific embodiments and specific terminology will be used to describe the same. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the scope of the present invention.

[0016] FIGURE 1 illustrates an avionics display system 1 of an aircraft 2 (shown in FIGS. 3 and 6) that includes avionics display software in accordance with the present invention. The aircraft 2, and in particular the avionics display system 1, - a display device 3 coupled to receive image rendering display commands and to responsively display the rendered image; - a terrain data source 4 outputting terrain data representative of the terrain in the field of view of the pilot 13 of the aircraft 2; - an avionics flight data source 10 that outputs avionics data representative of the avionics state of the aircraft 2, including its roll angle; and - a computational resource 6 coupled to the terrain data source 4 to receive terrain data from the terrain data source 4, coupled to the avionics flight data source 10 to receive avionics data from the avionics flight data source 10, and coupled to the display device 3 to provide image rendering display commands to the display device 3 based on the received terrain data and avionics data; Includes.

[0017] In particular, the avionics display software is executable by the computing resources 6 and, when executed, programs the computing resources 6 to cause the display device 3 to display a rendered image representative of the operator's view outside the window of the aircraft 2.

[0018] In one embodiment, the terrain data source 4 includes a database of terrain data configured to store terrain data representative of terrain within the field of view of a pilot of the aircraft 2. The database of terrain data is thus a three-dimensional map of the terrain as a function of altitude, i.e. a matrix that includes data relating to the altitude of the terrain.

[0019] According to a further embodiment of the present invention, not described in detail below, the terrain data in the database of terrain data is determined by a sensory system (not shown) on board the aircraft 2 and is therefore determined during the flight of the aircraft 2.

[0020] The avionics display system 1 further includes an avionics graphic data source 5 including graphic elements symbolizing real-world items and symbols used to represent avionic quantities of the aircraft 2, such as attitude, altitude, heading, and speed (e.g., ground speed, airspeed, vertical speed, etc.) indicative of the status of the aircraft 2, and outputs avionics data indicative of the sensed avionic quantities.

[0021] According to another embodiment of the invention, the avionics flight data source 10 is in the form of an external inertial navigation system 10, which is a system including motion sensors, such as accelerometers, rotational sensors, such as gyroscopes, and a dedicated electronic control unit (not shown) designed to calculate the position, orientation and velocity of the aircraft 2, such as by dead reckoning, and generate corresponding data.

[0022] Computational resource 6 is - an electronic control unit 7 designed to communicate with the terrain data source 4 and the avionics graphic data source 5, to receive and process data from the terrain data source 4 and the avionics graphic data source 5 and to generate data on display commands; - a memory 8 (here a SATA memory) designed to communicate with the electronic control unit 7 and to receive and store data from the terrain data source 4 and the avionics graphic data source 5; - an input / output (I / O) board 9 designed to communicate with the electronic control unit 7 and with an external inertial navigation system 10 of the aircraft 2, the input / output (I / O) board 9 being designed to receive data from the external inertial navigation system 10 and to transmit them to the electronic control unit 7; - a graphic control unit GPU 11 designed to communicate with the electronic control unit 7 and to receive and process data relating to display commands in order to display them on the display device 3; and - a video board 12 designed to communicate with the electronic control unit 7, the GPU 11 and the display device 3, to receive data regarding display commands and to display them on the display device 3; Further includes:

[0023] Figures 2-4 show a composite image displayed on pilot 13 rendered on display device 3 according to one embodiment of the invention, hereinafter referred to as a sloshing embodiment or mode, while Figures 5-7 show a composite image rendered on display device 3 according to another embodiment of the invention, hereinafter referred to as a multi-strip embodiment or mode.

[0024] According to one aspect of the present invention, the avionics display software, when executed, is designed to cause the computational resources 6 to, among other things, allow the pilot 13 to select either the sloshing mode or the multi-strip mode by rendering an interface on the display device 3 with which the pilot 13 can interact to select the desired mode of the composite image.

[0025] In both embodiments, the rendered image advantageously has a generally rectangular shape with a width W taken along a first direction (here parallel to the x-axis of the Cartesian reference system xyz) and a height H taken along a second direction (here parallel to the y-axis of the Cartesian reference system xyz) and represents the view out the pilot's window of the aircraft 2. The rendered image also has a skyward edge, which is an edge that defines the location of the sky in the rendered image. As will also be explained in more detail below, the skyward edge may change its position depending on the position of the aircraft 2, in particular in terms of roll angle.

[0026] The rendered image includes one or both of a rendered terrain RT and a rendered sky RS, which represent the terrain and sky in the real world outside the aircraft 2 and whose position and orientation depend on the relative position and orientation of the aircraft 2. The terrain is preferably rendered using various shades of a first color, particularly an earth color such as brown / green, while the sky is preferably rendered in a single shade of a second color different from the first color, such as blue.

[0027] In both embodiments, the rendered image further includes rendered flight-related information including a rendered zero pitch reference line RL (see FIGS. 3 and 6). The rendered flight-related information further includes a rendered pitch tape or rudder PT. In particular, the pitch tape or rudder PT provides an indication of the pitch of the aircraft, while the rendered zero pitch reference line RL is an imaginary reference line that is parallel to the surface of the Earth originating from the aircraft 2 and thus indicates what is above and below the aircraft 2.

[0028] In both embodiments, the rendered image may further include additional flight related information (not shown), such as altitude, vertical speed, flight plan, roll pointer, flight path vector, flight path predictor, etc.

[0029] In both embodiments, the rendered image further includes a rendered skyveil SV. In particular, the skyveil SV is an overlapping graphical representation within the rendered image having attributes described below with reference to Figures 2-6, some of which are common to the sloshing and multi-strip embodiments, while others are different.

[0030] In both embodiments, the Skyveil SV is conveniently rendered continuously, sequentially or selectively based on unique rendering criteria.

[0031] In particular, in both embodiments, the sky veil SV is an overlapping graphical representation that is rendered at least partially transparently in such a way that (i) the portions of the rendered sky veil SV that (eventually) overlap the rendered sky RS are indistinguishable from the rendered sky RS, and (ii) the rendered terrain RT is visible through the transparent portions of the sky veil SV that overlap the rendered terrain RT.

[0032] In both embodiments, the Skyveil SV has a respective width W SV and their respective heights H SV In particular, the width W of Skyveil SV SV is defined as the distance between the side edges of the sky veil SV parallel to the second direction (i.e., parallel to the direction of the height H of the rendered image), and the height H of the sky veil SV SV is defined as the distance between the top and bottom edges of the sky veil SV parallel to the first direction (i.e. parallel to the direction of the width W of the rendered image).

[0033] Additionally, the Skyveil SV is rendered to exhibit one or more of the following characteristics: a) Extends parallel to the skyward edge of the rendered image; b) spanning the full width W of the skyward edge of the rendered image; c) Functions of the height H of the rendered image, specifically height H as a percentageSV , which extends from the skyward edge of the rendered image; d) Its overall width W SV A substantially constant height H SV having; and e) has the same color as the rendered sky RS.

[0034] According to a preferred aspect of the invention, in both embodiments, the sky veil SV is represented as an independent graphic layer that overlaps with the rest of the representation on the rendered image. The sky veil SV is, for example, drawn in the same color as the composite sky so that parts of the sky that overlap with the rendered sky cannot be identified. In this way, even in brown-over-brown situations, a minimum part of the sky is always represented, and a transparent zone provides visibility of the parts of the terrain that overlap with the sky veil SV. This mechanism allows the pilot to know the location of the sky with an appropriate increase in situational awareness.

[0035] Furthermore, in both embodiments, and according to a preferred aspect of the invention, the sky veil SV is advantageously a function of the height H of the rendered image, in particular a height H which is a percentage. SV , which is rendered to extend from the skyward edge of the rendered image, and conveniently spans the full width W of the rendered image. In other words, the width W of the sky veil SV SV is equal to the width W of the rendered image.

[0036] In the sloshing embodiment shown in Figures 2-4, the sky veil SV is rendered as a band that is stationary in the rendered image during a roll of the aircraft 2, and in particular as a straight band (i.e., a band that extends along the direction of the width W of the rendered image without curving or bending). Furthermore, the sky veil SV is rendered in such a way that the width of the transparent area of ​​the sky veil SV depends on the roll angle of the aircraft 2. SV More specifically, the sky veil SV is rendered at least partially transparent along its width W SVSubstantially the same height H throughout SV and is rendered as a single long, narrow stripe or band of the same color as the rendered sky RS. Sky Veil SV is rendered to remain in a stationary position within the rendered image regardless of the flight attitude of aircraft 2, i.e. regardless of pitch, roll and yaw angles.

[0037] The rendered sky veil SV comprises two side or lateral portions or regions L, R, each having a width and a transparency, and a middle or central or central portion or region C. In particular, the side regions L, R are at least partially transparent, and the central region C is opaque.

[0038] According to the embodiment shown in FIGS. 3 and 4, the width W C is invariant with the roll angle of the aircraft 2. More specifically, the width W C is a function of the width W of the rendered image, in particular a percentage, conveniently 60% for example. Furthermore, the width W of the central region C C is invariant with the pitch angle of aircraft 2.

[0039] Furthermore, the side regions L, R have a width W which varies with the roll angle of the aircraft 2. L , W R That is, when the roll angle is different from 0°, the width W L , W R More specifically, the width W of the side regions L, R is fixed. L , W R The rendered sky veil SV has a constant width W SV The widths W of the side regions L and R vary in the opposite direction to the roll angle of the aircraft 2 within their respective ranges of variation. L , W R varies with roll angle and is invariant with pitch angle of the aircraft 2. In particular, the width W of the side regions L, R L , W Rvaries discretely with the roll angle of the aircraft 2 in corresponding variation steps as the roll angle of the aircraft 2 varies discretely with the corresponding variation steps, and in particular varies discretely with the roll angle of the aircraft 2 within a variation range having a positive or negative variation step for each positive or negative variation step of the roll angle. L , W R varies from a percentage which is the initial value of the width W of the rendered image, conveniently for example 20%, to a percentage which is the final value of the width W of the rendered image, conveniently for example 40%, by a percentage which is the variation step of the width W of the rendered image, conveniently for example 1%, as the roll angle of the aircraft 2 varies from an initial value of zero to a final value, conveniently for example a final value of ±20°, conveniently in variation steps of for example ±1°.

[0040] The central region C has a width W C , being invariant with the roll angle of the aircraft 2, advantageously being, for example, 0% or close thereto, and thus being substantially completely opaque. Moreover, due to the fact of being opaque, the central region C has the same color as the rendered sky, regardless of the roll angle of the aircraft 2. Moreover, the side regions L, R have a transparency that increases outwards, i.e. from their respective inner edges adjacent to the central portion C towards their respective outer edges of the sky veil SV (i.e. towards the edge of the rendered image). Thus, the side regions L, R become increasingly transparent when moving from the central region C of the sky veil SV towards its edge. More specifically, the transparency of the side regions L, R increases from their inner edges towards their outer edges, i.e. for example from a minimum of 0% to a maximum of 60%. In particular, referring to FIG. 4, in particular FIG. 4a) and FIG. 4c), by way of example, it can be seen that, when the roll angle is equal to -20° (FIG. 4a), the width W of the side regions L is 100%. L is a function of the width W of the rendered image, in particular a percentage, conveniently equal to a value of, for example, 40%. Furthermore, the width W of the side region R Ris a function of the width W of the rendered image, in particular a percentage, conveniently equal to a value of, for example, 0%. Furthermore, when the roll angle is equal to +20° (c in FIG. 4), the width W L is a function of the width of the rendered image, in particular a percentage, conveniently equal to a value of, for example, 0%. Furthermore, the width W R is a function of the width W of the rendered image, in particular a percentage, conveniently equal to a value of, for example, 40%.

[0041] It should be noted that the values ​​given above for width, height and transparency of regions C, L and R can be changed and adjusted, for example, according to the needs of the Pilot 13 or other visualization criteria.

[0042] In this configuration shown in Figures 2-4, the overall width W SV , i.e. there is a displacement of opaque and transparent areas along the width W of the rendered image. This graphic effect is intended to enhance the pilot's perception of the position of the maximum part of the sky as a function of the aircraft's power.

[0043] In the multi-strip embodiment shown in Figures 5-7, the sky veil SV moves in the rendered image as a function of the roll angle of the aircraft 2 during its roll, and is advantageously rendered as a band with an oblique movement, in particular a straight band (i.e. extending along the direction of the width W of the rendered image without curvature or bending). More specifically, the sky veil SV is rendered as a band of multiple, here three, parallel and spaced apart sub-bands B 1 -B 3 In particular, subband B 1 -B 3 is represented as a single elongated stripe or band of the same color as the rendered sky RS.

[0044] According to the embodiment of Figures 5-7, the sky veil SV is rendered at least partially transparent along its height. In this way, even in brown-over-brown situations, parts of the sky veil SV are always rendered, and the transparent areas of the rendered sky veil SV provide visibility of the rendered terrain RT that overlaps with the rendered sky veil SV. This allows the pilot of the aircraft 2 to know his position in the sky in any flight situation, thereby improving his situational awareness.

[0045] In particular, the sky veil SV is rendered to be specifically tilted or inclined in solidarity with the roll angle, i.e. tilted or inclined relative to an axis longitudinal to the aircraft 2, here the rolling axis (i.e. the axis about which the roll angle is measured, i.e. the axis about which the aircraft 2 rolls). The sky veil SV is thus parallel to the artificial horizon, i.e. the rendered zero pitch reference line RL, providing the pilot 13 with a sense of movement of the synthetic representation. Furthermore, the sky veil SV is rendered to be visible even at high attitude angles (e.g. greater than 90°).

[0046] The sky veil SV is rendered to move, advantageously tilt or lean, in the rendered image depending on the flight attitude of the aircraft 2, advantageously as a function of the roll angle. In particular, the sky veil SV is rendered to lean perpendicular to the direction in which the aircraft 2 leans as a result of the change in the roll angle. As also shown in FIG. 5, when the value of the roll angle is equal to 0° (i.e. the aircraft 2 does not lean), the sky veil SV is rendered in a stationary position in the rendered image (a). When the value of the roll angle varies up to ±20° (i.e. the aircraft 2 leans according to the roll angle; see FIGS. 5b) and 5c) respectively), the sky veil SV is rendered to lean at an angle having a maximum value of minus plus 20° in the rendered image. The tilt of the sky veil SV causes the subband B 1 -B 3 is conveniently only partially visible at upper angles in the rendered image.

[0047] 7, in the multi-strip embodiment, the sky veil SV is rendered parallel to the rendered zero-pitch reference line RL, with a distance D therefrom that depends on the roll angle of the aircraft 2. More specifically, the distance D is determined by the distance between the rendered zero-pitch reference line RL and the bottom-most sub-band of the sky veil SV, i.e., the sub-band of the sky veil SV that is closer to the rendered zero-pitch reference line RL (here sub-band B 3 ) is defined as the distance between

[0048] Furthermore, if the roll angle satisfies the first condition, the distance D satisfies a first relationship with the roll angle, and if the roll angle satisfies the second condition, the distance D satisfies a second relationship with the roll angle. In particular, if the roll angle satisfies the first condition, the roll angle advantageously has a value within a first range from 0° to ±45°. Furthermore, if the roll angle satisfies the second condition, the roll angle advantageously has a value within a second range from 45° to 90° or from −45° to −90°. Furthermore, if the distance D satisfies the first relationship with the roll angle, the distance D increases proportionally with the value of the roll angle (see a) to c) of FIG. 6 and FIG. 7 . The latter has a value x at angles of 0°, 27.5°, and 45°. 1 , x 2 , and x 3 Let D be the assumed distance, and x 3 x 2 Greater than x 2 x 1 Furthermore, if the distance D satisfies the second relationship with the roll angle, then the distance D decreases proportionally to the value of the roll angle (at angles of 45°, 67.5°, and 90°, the value x 4 , x 5 , and x 6 See d) to f) of Figure 7, which shows the assumed distance D. 6 x 5 Less than x 5 x 4 less than).

[0049] Furthermore, the values ​​of the distance D when the roll angle is equal to 0° and ±90° are equal (hence the value x 1 and x 6 Note that the distance D is equal to ±45°. Furthermore, the value of the distance D is maximum when the roll angle is equal to ±45°.

[0050] Subband B 1 -B 3 is subband B 1 -B 3 A gradually decreasing height H taken along a second direction perpendicular to 1 -H 3 and increasing intervals d taken along the second direction 1 , d 2 The height H 1 -H 3 and interval d 1 , d 2 changes, but the height H 1 -H 3 and interval d 1 , d 2 The height H of the sky veil SV is given as the sum of SV Note that is constant. Furthermore, in subband B 1 -B 3 Height H 1 -H 3 and interval d 1 , d 2 is invariant with the roll angle of aircraft 2.

[0051] Subband B 1 -B 3 Height H 1 -H 3 is the percentage of the height H of the rendered image, and the spacing d of subbands B1-B3 1 , d 2 is a percentage of the height of the rendered image.

[0052] According to the embodiment shown in FIGS. 1 The value of is the height H 2 is larger than the value of 3According to the embodiment shown in FIG. 1 -H 3 is a function of the height H of the rendered image, in particular a percentage, conveniently 5%, 3%, and 2%, for example, and is invariant to the pitch and roll angles of the aircraft 2. Furthermore, band B 1 and B. 2 is a function of the height H of the rendered image, specifically the interval d which is a percentage, conveniently 1% 1 Band B 2 and B. 3 is the interval d in terms of absolute value 1 Larger interval d 2 , in particular a function of the height H of the rendered image, in particular a percentage, conveniently 3% for example.

[0053] Subband B 1 -B 3 have transparency that is constant along their width and invariant with the roll angle of the aircraft 2. In particular, according to the embodiment of Figures 5-7, subband B 1 -B 3 The width is the width W of Skyveil SV SV , and thus equal to the width W of the rendered image. In particular, the first band B 1 The transparency of subband B is advantageously 0% or close to it, so that it is substantially completely opaque, while the transparency of other subbands B 2 , B 3 The transparency of the first band B 1 More specifically, subband B 1 The transparency of subband B is advantageously, for example, 0% or close to it, and is therefore substantially completely opaque, regardless of the roll angle of the aircraft 2. 2 and B. 3 The transparency of band B has a fixed value, conveniently 20% and 40%, respectively. Therefore, regardless of the roll angle, the transparency of band B 1 -B 3 The transparency of remains constant throughout the entire flight of aircraft 2.

[0054] Subband B 1 -B 3 It should be noted that the values ​​given above for width, height, and transparency can be changed and adjusted, for example, depending on the needs of Pilot 13 or other visualization criteria.

[0055] The sky veil SV according to the sloshing and multi-strip embodiments may, according to one aspect of the invention, include a border that is opaque, or at least substantially opaque, and rendered in a second color. Thus, those portions of the border of the sky veil SV that overlap the rendered sky are also indistinguishable. Furthermore, the rendered terrain cannot be seen through the border. Also note that, according to one aspect of the invention, the edges of the border are preferably faded to give a soft appearance and to avoid appearing like a horizon. Furthermore, the sky veil SV may, in some embodiments, be rendered without a border.

[0056] The avionics display system 1 is configured such that the sky veil SV is rendered in the same color as any rendered sky. Thus, according to one embodiment of the present invention, there is no trigger mechanism or event that renders the sky veil SV; rather, the latter is rendered continuously. According to a further embodiment of the present invention, the sky veil SV is selectively rendered in response to a trigger mechanism or event. It is noted that in normal blue-over-brown display situations, the sky veil SV is indistinguishable from the rendered sky and does not pose a potential distraction to the pilot.

[0057] From the above, the advantages of the system according to the present invention are clear.

[0058] In particular, the avionics display system 1 is designed to assist the flight crew in difficult situations, such as brown-over-brown situations, where the sky is not always visible, by displaying the location of the sky through a veil rendered during flight, i.e., sky veil SV. Additionally, as also described above with respect to the above modes, the avionics display system 1 is designed to enable better situational awareness of the pilot, and the flight crew in general, thereby reducing the presence of situations that cause confusion and / or disorientation to the flight crew.

[0059] It is evident that modifications can be made to the described system and method without going beyond the scope of protection defined in the claims.

[0060] For example, the vehicle display system 1 may be used in any type of vehicle and achieve the same benefits, although it should be noted that in such cases, the aviation electronics display system 1 must be adapted based on the particular application.

Claims

1. The avionics display software for an aircraft (2) comprises: - a display device (3) coupled to receive image rendering and displaying commands and to display rendered images in response; a terrain data source (4) for outputting terrain data representative of the terrain in the field of view of a pilot (13) of said aircraft (2); an avionics flight data source (10) for outputting avionics data representative of the flight conditions of said aircraft (2), including the roll angle of said aircraft (2); and a computational resource (6) coupled to said terrain data source (4) to receive terrain data from said terrain data source (4), coupled to said avionics flight data source (10) to receive avionics data from said avionics flight data source (10), and coupled to said display device (3) to provide image rendering display commands to said display device (3) based on the received terrain data and avionics data; Equipped with the aviation electronics display software is executable by the computational resource (6), and when executed, the computational resource (6) is programmed to cause the display device (3) to display a rendered image representative of the operator's view out of a window of the aircraft (2); the rendered image includes one or both of a rendered terrain (RT) and a rendered sky (RS) representing real-world terrain and sky external to said aircraft (2), the positions and orientations of which depend on the relative position and orientation with respect to said aircraft (2); The rendered image further includes a rendered sky veil (SV); said sky veil (SV) being an overlapping graphical representation that is at least partially rendered transparently in such a way that (i) the portions of said rendered sky veil (SV) that (eventually) overlap with said rendered sky (RS) are indistinguishable from said rendered sky (RS) and (ii) said rendered terrain (RT) is visible through the transparent portions of said sky veil (SV) that overlap with said rendered terrain (RT); said sky veil (SV) being rendered as a stationary band in said rendered image during a roll of said aircraft (2); Aviation electronics display software, wherein the sky veil (SV) is rendered at least partially transparent along its width (W) such that a width (WR, WL) of a transparent area of ​​the sky veil (SV) depends on the roll angle of the aircraft (2).

2. The Sky Veil (SV) is a) extending parallel to a skyward edge of the rendered image; b) spanning the full width (W) of the skyward edge of the rendered image; c) a function of the height (H) of the rendered image, in particular a height (H) that is a percentage ＳＶ ) extending from the skyward edge of the rendered image; d) Its overall width (W ＳＶ ) over a substantially constant height (H ＳＶ ) and e) having the same color as the rendered sky (RS); The aviation electronics display software (1) of claim 1, rendered to show one or more of the features.

3. said rendered sky veil (SV) comprising two at least partially transparent side regions (L, R) and an opaque central region (C); The side regions (L, R) have a width (W Ｌ , W Ｒ 2. The aviation electronics display software (1) of claim 1, further comprising:

4. The width of the side regions (L,R) is such that the rendered sky veil (SV) has a constant width (W ＳＶ 4. The aviation electronics display software of claim 3, wherein the roll angle of the aircraft varies inversely to the roll angle of the aircraft within a respective range of variation so as to have a roll angle of the aircraft relative to the roll angle of the aircraft.

5. The width (W Ｌ , W Ｒ 5. The aviation electronics display software (1) of claim 3 or 4, wherein the roll angle (r) varies in discrete steps as the roll angle of the aircraft (2) varies in corresponding discrete steps.

6. 6. The aviation electronics display software (1) of claim 4 or 5, wherein the widths (WL, WR) of the side regions (L, R) vary in variation steps (conveniently ±1° variation steps) from a percentage (conveniently 20%) of an initial value of the width (W) of the rendered image to a percentage (conveniently 40%) of a final value of the width (W) of the rendered image.

7. The central region (C) has a width (W Ｃ 7. The aviation electronics display software (1) according to any one of claims 1 to 6, further comprising:

8. The width (W Ｃ 8. The aviation electronics display software of claim 7, wherein the width of the rendered image is preferably 60%.

9. The central region (C) has a width (W Ｃ ) and invariant with the roll angle of the aircraft (2), advantageously at or near 0%, The aviation electronics display software (1) according to any one of claims 1 to 8, wherein the side regions (L, R) have a gradually increasing transparency towards the outside.

10. The avionics display software for an aircraft (2) comprises: - a display device (3) coupled to receive image rendering and displaying commands and to display rendered images in response; a terrain data source (4) for outputting terrain data representative of the terrain in the field of view of a pilot (13) of said aircraft (2); an avionics flight data source (10) for outputting avionics data representative of flight conditions of said aircraft (2), including the roll angle of said aircraft (2); and a computational resource (6) coupled to said terrain data source (4) to receive terrain data from said terrain data source (4), coupled to said avionics flight data source (10) to receive avionics data from said avionics flight data source (10), and coupled to said display device (3) to provide image rendering display commands to said display device (3) based on the received terrain data and avionics data; It is equipped with the aviation electronics display software is executable by the computational resource (6), and when executed, the computational resource (6) is programmed to cause the display device (3) to display a rendered image representative of the operator's view out of a window of the aircraft (2); the rendered image includes one or both of a rendered terrain (RT) and a rendered sky (RS) representing real-world terrain and sky external to said aircraft (2), the positions and orientations of which depend on the relative position and orientation with respect to said aircraft (2); The rendered image further includes a rendered sky veil (SV); said sky veil (SV) being an overlapping graphical representation that is at least partially rendered transparently in such a way that (i) the portions of said rendered sky veil (SV) that (eventually) overlap with said rendered sky (RS) are indistinguishable from said rendered sky (RS) and (ii) said rendered terrain (RT) is visible through the transparent portions of said sky veil (SV) that overlap with said rendered terrain (RT); the sky veil (SV) being rendered as a moving band in the rendered image during a roll of the aircraft (2) as a function of its roll angle; The Skyveil (SV) is made up of a number of parallel and spaced apart sub-bands (B １ -B ３ ), and The avionics display software, wherein the Sky Veil (SV) is rendered at least partially transparent along its elevation.

11. 11. The aviation electronics display software of claim 10, wherein the rendered image further includes rendered flight related information including a rendered zero pitch reference line (RL), and the sky veil (SV) is rendered parallel to the rendered zero pitch reference line (RL) at a distance (D) therefrom that is dependent on the roll angle of the aircraft (2).

12. 12. The aviation electronics display software of claim 11, wherein the distance (D) satisfies a first relationship with the roll angle when the roll angle satisfies a first condition, and wherein the distance (D) satisfies a second relationship with the roll angle when the roll angle satisfies a second condition.

13. 13. The aviation electronics display software (1) of claim 12, wherein if the roll angle satisfies the first condition, the roll angle has a value within a first range, preferably from 0° to ±45°, and if the roll angle satisfies the second condition, the roll angle has a value within a second range, preferably from 45° to 90° or from −45° to −90°.

14. 14. The aviation electronics display software of claim 12 or 13, wherein said distance (D) increases in proportion to said roll angle if said distance (D) satisfies said first relationship with said roll angle, and wherein said distance (D) decreases in proportion to said roll angle if said distance (D) satisfies said second relationship with said roll angle.

15. The Sky Veil (SV) is a) extending parallel to a skyward edge of the rendered image; b) spanning the full width (W) of the skyward edge of the rendered image; c) a height (HSV) that is a function of the height (H) of the rendered image, in particular a percentage, extending from the skyward edge of the rendered image; d) having a substantially constant height (HSV) across its total width (WSV); and e) having the same color as the rendered sky (RS); The aviation electronics display software (1) of claim 14, rendered to show one or more of the features.

16. The subband (B １ -B ３ ) is the subband (B １ -B ３ ) in a direction perpendicular to the １ -H ３ ) and gradually increasing intervals (d １ , d ２ 16. The aviation electronics display software (1) of claim 15, further comprising:

17. The subband (B １ -B ３ The height (H １ -H ３ ) and spacing (d １ , d ２ 17. The aviation electronics display software (1) of claim 10, wherein:

18. The subband (B １ -B ３ The height (H １ -H ３ ) is a percentage of the height of the rendered image, and the subband (B １ -B ３ ) the interval (d １ , d ２ 18. The aviation electronics display software (1) of claim 16 or 17, wherein:

19. The subband (B １ -B ３ ) are their widths (W ＳＶ 20. The aviation electronics display software (1) of claim 10, wherein the transparency is constant along the roll angle of the aircraft (2) and invariant with the roll angle of the aircraft (2).

20. The first band (B １ ) is advantageously 0% or close to it, so that it is substantially completely opaque, and the other sub-bands (B ２ , B ３ The transparency of the first band (B １ 20. The aviation electronics display software (1) of claim 18 or 19, wherein the aviation electronics display software (1) has a constant value higher than

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