DE102007061273A1 - Flight information e.g. flight height information, displaying method for aircraft, involves transforming image into another image by partial non-planar projection and visualizing latter image in two-dimensional display plane of display unit - Google Patents

Abstract

The method involves generating a synthetic image as a partial non-planar projection of a surrounding of an aircraft. The image is visualized in a two-dimensional display plane of a display (50) of a display device and/or is transformed into another image (52) by the partial non-planar projection. The image (52) is visualized in the two-dimensional display plane of the display unit. The projection is projected with another projection on a non-planar image plane to produce a third image, which is transformed into the image (52) by a third projection. An independent claim is also included for a display device of an aircraft for displaying flight information.

Description

The The present invention relates to a method for the preparation of Flight information by means of at least one display instrument of a Aircraft, wherein at least a first synthetic image of a Environment of the aircraft is generated, as well as a display instrument for an aircraft, in particular adapted for use in a method according to the invention, comprising at least one display device for visualizing flight information in a substantially two-dimensional representation plane, where at by means of the display device at least a first synthetic Image of the environment of the aircraft is displayed.

Out The prior art are various gauges for a cockpit of an aircraft known. In addition to indicating instruments, like altimeters, artificial horizons, or Speedometers or combination displays, the different Display parameters of the aircraft, keep so-called synthetic Vision systems (Synthetic Vision Systems (SVS)) are increasingly being introduced into Cockpits.

In A synthetic vision system uses database content of methods of graphic data processing on a visual system This is a realistic representation of the real environment of the aircraft. This is especially true ensure safe flight in poor visibility conditions.

A generic method and a generic display instrument, for example, in the article SPIE Vol. 5802, pp. 219-230, Enhanced and Synthetic Vision 2005, May 2005 Edition "Synthetic vision systems for improving unmanned aerial vehicle operator situation awareness" , described. In this synthetic vision system, it is proposed, in particular, that a video image of the surroundings of an aircraft, which is surrounded by a synthetically generated image of the surroundings of the aircraft, be displayed on a screen in a central area. Thus, on a primary flight guidance display used in an unmanned aerial operator station on the ground, a perspective, three-dimensional view is taken in the direction of a longitudinal axis of the aircraft to simulate a pilot's view of the cockpit. In this implementation of a synthetic vision system, the virtual image is created by a planar perspective projection on a planar surface.

The Use of such a synthetic vision system as a substitute for A real view from a cockpit is for a pilot but very getting used to. So is the natural one peripheral viewing area severely limited, as in known Systems comparatively low horizontal viewing angle in the range from about 30 ° to about 90 °, d. H. in an angular range from -15 ° to + 15 ° or -45 ° to + 45 ° from a center of the image. larger Viewing angle (but usually to the detriment of that the larger the viewing angle becomes, increasingly larger longitudinal distortions occur. While information in an image center is getting stronger be downsized, information in an outdoor area a picture more and more stretched. The distance between the same real angle ranges is not very linear in planar projections. An enlargement the viewing angle range in a known synthetic vision system over a range of 120 °, d. H. a range of -60 ° to + 60 ° out from an image center, leads to such strong distortions that it leads to misinterpretations the picture of the synthetic vision system can come, in particular Obstacles in a center of the image are considered too far away become.

Before will be discussed in detail in the following First, the theoretical foundations of a projection and their properties explained.

Under a projection becomes the mapping of points of the three - dimensional Understood space on points of a given area. is this plane is called a planar projection. As so-called projection beams are the connecting lines a camera or eye point of the viewer with the points in the understood three-dimensional space. The cut of the projection rays with a projection surface or image plane defines the Pixel in the planar projection.

In a planar perspective projection is a camera point 1 , as in 1 illustrated, in the end. This creates a beam emanating from the camera projection beam 3 , Different from an image plane 5 lying objects (A, B) of the same size are in this projection on an image plane 5 different sizes shown as pictures A ', B'.

In 2 is a perspective projection using the example of an equilateral hexahedron 7 with the kan tenlänge 1 shown.

Apart from lines in the projection surface or image plane, all distances are distorted in the perspective projection. Parallel routes run to a vanishing point 9 to, wherein this is parallel to a projection surface or image plane at infinity at distances. In the primary flight guidance display (PFD), in particular, a perspective projection is stimulus for the three-dimensional perception of a synthetic view.

A The demand for a synthetic view is, as mentioned earlier, the relevant information on a limited display area to compress and thereby a loss of information or an information corruption to avoid or minimize. The demand for representation the largest possible field of vision and after of sufficient recognizability on a limited display surface in opposite directions. The choice of the distance of a projection surface scale from a camera point and the resulting viewing angle directly these two factors. The setting of a viewing angle (Field of View, FOV) is at the perspective projection in a display instrument usually a fixed size. A change in the angle of view during the flight can namely by changing proportions lead to serious irritation. Such is the depth effect especially a terrain view from a viewing angle dependent. Accordingly, appears by the compression of the figure the environment flatter with increasing viewing angle. The pilot sees Although a larger environment, the distances to objects in the synthetic view, however, appear larger, because they are smaller because of the distortions that occur become. For small viewing angles, however, the distortions are hardly noticeable; the relations of representation appear realistic. In contrast, small viewing angles make only a narrow Range around the projection normal, making the visual field unrealistic compared to a usual view involving of a peripheral field of view.

These effects identified for the terrain the selection of the viewing angle are in a perspective flight path representation of additional relevance, since the distance to three-dimensional Elements of the flight path (except for a landing) clearly less than to a terrain.

3a to 3c show the perspective projection of a flight path, which is represented by tunnel elements, as a function of a viewing angle in known from the prior art synthetic vision systems. In 3a the viewing angle is 30 °, in 3b 60 ° and in 3c 120 °. All objects are in the same position. While at a viewing angle of 30 °, ie from -15 ° to + 15 °, the next tunnel elements 11 . 11 ' seemingly be flown through immediately and a curve 12 reached in a short time, seem the tunnel elements 11 . 11 ' corresponding tunnel elements 13 . 13 ' at a viewing angle of 60 ° ( 3b ), farther away and at a viewing angle of 120 °, they seem to be the tunnel elements 11 . 11 ' corresponding tunnel elements 15 . 15 ' to be much further away. Thus, with a larger viewing angle, a longer part of the future course of the desired trajectory or desired flight path can be recognized. Furthermore, the distortion leads to larger viewing angles that relative movements in the center of the representation are barely recognizable. However, towards the edges, the elements seem to accelerate and move at higher speeds.

4a shows the geometric dependence of a minimum visibility d _{i of} a flight path of the width b of a selected viewing angle α _i . Provided there is no vertical or horizontal deviation to a desired path and a direction of projection corresponds to the direction of a flight path of an aircraft 17 , the following relationship results:

The diagram in 4b represents the course of the minimum visibility d at variable viewing angle α and different widths b of the flight path display. Clearly recognizable is the strong increase in the minimum visibility with small viewing angles. For that in the 3a to 3c Example shown apply to a width of the flight path of b = 100 m, the minimum visibility 186.6 m (30 ° viewing angle), 86.6 m (60 ° viewing angle) and 28.9 m (120 ° viewing angle). At an airspeed of V = 100 m / s (~ 200 kts), the time periods in which an element of the flight path leaves the field of vision vary between approximately 2 s and 0.3 s. A too small viewing angle can therefore lead to a pilot flying more "in the future", thus initiating directional or slope changes of the flight path too early Elements remain visible until just before they pass, but the disadvantage is the minimization of information onsgehaltes of the future to fly through elements.

Furthermore, from the prior art display devices for simulators are known. So revealed the DE 691 03 734 T2 a collimated display device with external, axial, spherical mirrors for a simulator. A projection device is intended to project a virtual image onto a spherical screen via a spherical mirror. This is intended to present a visual representation of an environment to a user of the simulator.

Furthermore, the disclosure DE 34 17 058 A1 a similarly constructed visual simulator. An external projector projects a virtual image onto a dome-shaped screen. A user of the simulator arranged on the inside of the dome should thus be given an impression of a simulation environment.

task The present invention is the generic Method and the generic display instrument to further develop that the disadvantages of the state overcome the technique, in particular a method and a display instrument providing a representation a synthetic environment image or first image with enlarged Allow viewing angle ranges, but at the same time a misinterpretation of the surrounding image is largely avoided.

The The object concerning the method according to the invention is characterized solved that the first image as at least partially non-planar projection of the environment is generated and in at least a two-dimensional display plane of at least one display device the display instrument is visualized and / or the first image by means of at least a first, at least partially non-planar Projection is transformed into at least a second image and the second image in the two - dimensional representation plane of the Display device is visualized.

there may be provided in particular that in the first projection the first image by means of at least one second projection first projected onto a non-planar image plane becomes a third image generate and then by means of at least a third Projection transformed the third image into the second image becomes.

at the two aforementioned alternative embodiments can be provided that the first image in dependence at least one position, at least one orientation and / or at least an attitude of the aircraft based on at least one Database, in particular at least one storage device, filed Environmental data, such as a terrain shape and / or surface shape an environmental landscape, at least one position and at least a geometrical dimension of at least one stationary obstacle, as a building, and / or at least one position and / or at least a geometric dimension of at least one relative to the environment the aircraft movable obstacle, as at least one other Aircraft, at least one land vehicle and / or at least one watercraft, and / or based on at least one surface scanning system of the aircraft, such as a radar system and / or at least one Sonar system, generated data is generated.

at the aforementioned embodiments of the invention is with the invention further proposed that the position, the Alignment and / or attitude of the aircraft based on Data from at least one satellite navigation system, such as GPS and / or Galileo, and / or at least one Attitude / Heading reference system (AHRS) is determined.

One The method according to the invention can further be characterized be characterized in that the generation of the first image, the first projection, the second projection and / or the third Projection at least one computational projection, in particular at least one conversion of image information of the first image in image information of the second image and / or the third image and / or image information of the third image in image information the second image, preferably by means of graphic data processing, comprises

Also it is preferred that the generation of the first image, the first projection, the second projection and / or the third Projection at least one optical projection, in particular at least an optical transmission of image information of the first Image in Bildin formations of the second image and / or the third image and / or image information of the third image in image information of the second image.

Farther is proposed by the invention that during the generation of the first image, during the first Projection and / or during the third projection at least an orthographic azimuthal projection and / or at least one equidistant and / or medium-distance azimuthal projection performed becomes.

Also is provided in a particularly preferred embodiment, that during the generation of the first image, during the first projection and / or during the second projection profiled at least one at least partially, in particular spherical, elliptical, parabolic, wavy, jagged, pyramidal, conical and / or curved image plane is used.

developments of the method according to the invention can characterized in that by means of the first image, at least one of the second image and the third image virtual representation of the environment of the aircraft, in particular in the form of at least one grid representation and / or at least a full-surface shape representation is displayed.

The Invention also proposes that by means of first image, the second image and / or the third image at least a virtual representation of the environment of the aircraft from at least one cockpit position towards the front of the aircraft and / or in a direction of movement and / or direction of flight of the aircraft is shown.

Farther is preferred that by means of the first image, the second Image and / or the third image, a viewing angle range of -30 ° to + 30 °, more preferably from -60 ° to + 60 °, still more preferably from -90 ° to + 90 °, even more more preferably from -120 ° to + 120 ° and / or most preferably from -180 ° to + 180 ° of Visualized environment of the aircraft.

After all is for the inventive method suggested that in the first image, the second image and / or the third image, additional flight data of the aircraft, in particular at least one altitude information, at least position information, such as at least one satellite navigation position, at least one directional information, as at least one compass heading and / or at least one satellite navigation course, at least one Location information, such as at least one inclination angle and / or at least one Rollage, preferably in the form of at least one artificial Horizons, at least operating information at least one drive unit of the aircraft, as at least an operating temperature, at least a fuel consumption, at least a tank content and / or at least one speed, at least one speed information, and / or at least one planned and / or future flight path is displayed or will be.

The the display instrument concerned task is solved, that the first image is a non-planar projection of the environment of the aircraft and can be visualized in the presentation plane is or the first image using at least a first at least partially non-planar projection in the presentation plane as at least a second image can be visualized.

One inventive display instrument can thereby be characterized in that the display device at least a tube screen, at least a liquid crystal screen (LCD), at least thin-film transistor (TFT) screen, at least one surface-conduction electron emitter screen (SED), at least one plasma screen, comprising at least one screen at least one organic light-emitting diode (OLED) and / or at least an optical projection device for visualizing the image at least one at least for example planar projection surface includes.

at This embodiment is particularly preferred that the Display device, in particular the presentation plane a round, elliptical and / or rectangular format, in particular the ratio of a width to a height of Representation level is substantially 1: 1, 4: 3 and / or 16: 9.

Especially preferably has a display instrument according to the invention to at least one graphical data processing unit for implementation the first, the second and / or the third projection.

Farther can be characterized a display instrument according to the invention be by at least memory device, in particular for storage and / or retrieving environmental data, including at least one Data carrier reading device and / or data medium writing device, like at least a DVD drive and / or CD drive, and / or at least a, preferably removable mass storage, as at least a hard disk and / or at least a memory stick.

After all is for the display instrument according to the invention proposed that the indicating instrument be used as a cockpit instrument, Head-up display, projection display, especially for at least a cockpit screen and / or a helmet visor, and / or head-down display is designed.

Of the Invention is therefore based on the surprising finding that a misinterpretation of on a display instrument Illustrations of an environment such as in particular by length distortions in a representation with large viewing angles, by use a non-planar projection can be avoided. For example a spherical projection can be performed So a projection on a spherical surface. Through this Non-planar projection makes it possible to have aspect ratios close to reality and also large viewing angles, even beyond 180 °, make sense, without causing misinterpretations of the environmental image represented by a pilot can come, at least the possibility of Misinterpretation is reduced. Furthermore, as well Viewing angle beyond 180 ° possible are, elements of the peripheral field of view are shown what especially for the display of spatially close elements, such as B. terrain formations and / or airways is of great use.

Before detailed to the technical teaching of the present invention it is appropriate, first to explain the theoretical basics, based on which in the known from the prior art methods or indicating instruments the disadvantages described above occur. So is the present Invention just based on the knowledge that the previously described disadvantages to the use of a planar projection are attributed.

before already became properties of perspective projection and their effects on the perspective flight path display mentioned. Due to the limitation of the viewing angle in a planar perspective Projection leave cross-sectional elements for a period of time actually reaching the field of view, causing inaccuracies can lead to the timing of control inputs. Also in the curve arise due to the limitation of the minimum Visibility visual imperfections, the faulty Control inputs can cause. Theoretically, that would be a viewing angle of 180 ° desirable so the time at which a cross member, i. H. an element which enters a peripheral, not shown, viewing area, the Ad leaves with the actual Time of flying through this element matches. But as shown in the following, is in a planar projection a viewing angle of 180 ° can not be realized. Size Viewing angles reduce the minimum visibility, but produce increasing distortions in the central and peripheral areas of the picture. This distortion is to be quantified below.

5 makes line of sight 16 from a camera point 17 in an angle difference of Δα = 10 ° in the range of -90 ° to + 90 °. In 5 are image planes 19 . 19 ' . 19 '' a planar projection at viewing angles of αi = 60 ° (image plane 19 ), 120 ° (image plane 19 ' ) or 160 ° (image plane 19 '' ). The picture levels 19 . 19 ' . 19 '' have the same lengths L and are at a distance d _i from the camera point 17 away. Thus, the range of the viewing angle of ε _i = 1 ° around the viewing direction is mapped to a length l _ii on the image plane according to equation (2): l ii = 2d i tan (ε i / 2) (2)

The range of the viewing angle of ε _ai = 1 ° at the outermost edge of the respective image plane 19 . 19 ' . 19 '' is projected to a length l _ai according to the following relationship: l ai = d i (Tan (α i / 2) - tan (α i / 2 - ε ai )). (4)

pro Winkel ε_i ergeben sich folgende normierte Längen im Innen- und Außenbereich:

By substituting (2) and (3) into equation (4) and the reference to the average length

for each angle ε _i , the following normalized lengths result in the interior and exterior:

The diagrams in 6a and 6b show the development of normalized lengths in the interior and exterior of the image planes 19 . 19 ' . 19 '' depending on the viewing angle. The inner length decreases similar to a quadratic function; the outside length grows strongly similar to an exponential function from a viewing angle of about 90 °. Thus, with a viewing angle of 60 °, the projected inner length only has a length of about 91% compared to the undistorted inner length, the projected outer length is about 120% of the undistorted outer length. With a viewing angle of 160 °, these tendencies increase to about 25% inside and about 743% outside. These distortions are also in 5 at the 160 ° image plane 19 '' clearly recognizable: the same angular difference forms at one edge of the image plane 19 '' to a much greater length than indoors. As a result, a viewing angle of 180 ° is impossible using a planar projection because the imaging length would be infinite.

embodiments The invention will be described below with reference to the aforementioned and further figures explained. This results Further features and advantages of the invention from the following Description in which embodiments of an inventive Device explained by way of example with reference to several drawings become.

there shows

1 schematically the implementation of a perspective projection;

2 the result of a perspective projection using the example of a hexahedron;

3a to 3c perspective projections of a flight path profile at different viewing angle ranges;

4a schematically the relationship between a minimum visibility and different viewing angles;

4b a graphical representation of the relationship between a viewing angle and a minimum visibility for different widths of a flight path;

5 the geometric relationships between different viewing angles, respective image planes and projection lengths of objects;

6a and 6b graphical plots of a projection length in the interior of an image and in the exterior of an image as a function of the respective viewing angles;

7 the geometric relationships of 5 when using spherical image planes;

8a in a planar representation, the schematic sequence of an orthographic azimuthal projection;

8b in a planar representation, the schematic sequence of an equidistant azimuthal projection;

9 the display of a display instrument according to the invention in which a spherical projection with an extended viewing angle is used to represent a synthetic view;

10a the display of a display instrument according to the invention, in which a non-planar projection is visualized by means of an equidistant azimuthal image on the display plane;

10b the display of a display instrument according to the invention, in which a non-planar Projection is visualized by means of an orthographic azimuthal image on a presentation plane;

11a the display of a prior art indicating instrument using a planar projection with a first viewing angle; and

11b the display of a display instrument the 10a at an extended viewing angle.

According to the invention, the described problems of the prior art, in particular to allow large viewing angles, are overcome by the use of a non-planar image plane in a projection. 7 As an example of a non-planar projection, the top view represents the same situation as in 5 with the difference that now on non-planar image planes in the form of spherical image planes 21 . 21 ' . 21 '' . 21 ''' on a camera point 23 projected. Non-planar image planes can also be used other than spherically shaped image planes, such as elliptical or pillow-shaped image planes. The length of the image planes 21 . 21 ' . 21 '' . 21 ''' is also L. The planar image planes 19 . 19 ' . 19 '' with corresponding viewing angle are also in comparison for 7 shown. Out 7 will be seen that lengths on the image planes 21 . 21 ' . 21 '' . 21 ''' not distorted even with large viewing angles. The normalized lengths l _{ii, n} and l _{ai, n} are constant in the spherical projection 1 ,

In addition, it becomes clear that viewing angles of 180 ° or more can be reproduced with the non-planar projection. The picture plane 21 '' For example, it represents a viewing angle of 360 °.

The image planes of the spherical projection are spherical segments. In order to transfer a non-planar image resulting from the non-planar projection onto a two-dimensional display plane of a display device, for example the rectangular format of a standard screen in order to visualize the image in this display plane, at least one additional projection can be performed. The first non-planar projection for imaging the first synthetic image of the surroundings of the aircraft as a second image on a display unit having a two-dimensional representation plane can therefore be a second projection in accordance with FIG 7 , and another third projection to transform the in the image planes 21 . 21 ' . 21 '' . 21 ''' comprise a third image generated by a second projection. Alternatively, however, the first image can be directly generated as a non-planar projection of the environment, for example by means of ray tracing, and visualized in the presentation plane.

For the implementation, in particular the third projection, there are different methods. In the 8a presented method, a non-planar image plane 25 , here by way of example a spherical image plane, in a representation plane 27 , for example, a display plane of a rectangular screen, is called an orthographic azimuthal projection. This method leads to the avoidance of longitudinal distortions in the outer area of the image plane 25 and to upsets in a border area of the presentation plane 27 , The compressions in the central area or inner area of the display plane 27 are smaller, so that in this area an almost distortion-free visualization in the presentation level 27 is possible. In the outdoor area or edge area, however, the lengths are shown shortened. The result is thus a characteristic that is reversed to a planar projection: in the central region, the lengths are not reduced, but stretched or enlarged, as in the case of the planar projection, while lengths in the outer region, similar to an image in a curved exterior mirror of a motor vehicle, are reduced.

At the in 8b The method shown becomes an image plane 29 in a sense, in a representation plane 31 "Unrolled", which causes the lengths of the lines to a 0 ° line of sight 32 to be cut, to be imaged lengthways. This equidistant or pitch-accurate azimuthal projection allows viewing angles of 360 ° and theoretically even more.

In the following, the theoretical principles for the implementation, in particular the third projection are explained:
A point P (α, γ) in a relative to the aircraft fixed, polar spherical coordinate system with the radius r = 1 on the image plane 25 becomes in the equidistant azimuthal projection according to the following equations in polar coordinates P '(r, φ) on the representation plane 27 displayed: r = π 2 - α (7) φ = γ. (8th)

The projection of the spherical image plane 29 on the planar representation level 31 takes place during the orthographic azimuthal projection according to the following regulations: r = cos (α) (9) φ = γ. (10)

The Performing a non-planar, in particular spherical, Projection, for example, with a viewing angle of 180 ° leads to the following effects: While the lengths hardly distorted, it comes in marginal areas of the projected image to ever larger angle distortions. One too a viewing direction orthogonal line below a camera point is shown as a circle segment. In a perspective Flight path representation is therefore when using the non-planar projection a transverse element that one approaches, starting from one almost rectangular representation with increasingly curved Lines are shown. When flying through the element is this then look at a viewing angle of 180 ° as a circle. The element leaves the viewing area with it exactly the moment the aircraft passes through the element emotional. The display instrument can thus also represent elements which are perpendicular to the line of sight.

The following are now based on the 9 to 11b Further advantages of the method and the display device according to the invention explained using the example of a display of a synthetic vision system.

In 9 is an ad 50 a synthetic vision system shown. The ad 50 represents a synthetic image 52 In this case, terrain formations are visualized in the vicinity of the aircraft in a full-surface shape representation and the synthetic image of the environment is visualized on a planar, ie two-dimensional display plane of a display instrument. Next to the image 52 the environment of the aircraft contains the indication 50 further flight information. So gives a compass indicator 54 Information about a direction of flight of the aircraft, an altitude indication 56 Information about an altitude of the aircraft, a speedometer 58 Information about an airspeed of the aircraft and an artificial horizon 60 Information about an inclination angle or a rolling position of the aircraft. The in the ads 54 . 56 . 58 . 60 The information presented may be determined by physical sensors or determined based on output data from a satellite navigation system, such as a GPS system or a Galileo system. In particular, positional determinations are made by the satellite navigation system. Preferably, alternatively or additionally, an orientation of the aircraft is determined by recording measurement data in the inertial system of the aircraft as a reference system, for example by means of gyro sensors.

To create the image 52 The environment of the aircraft may first be a first synthetic image of the environment based on stored in a database, which is in particular of the display device according to the invention, stored data based on position information, such as are supplied by a satellite navigation system. In the display instrument according to the invention, the virtual image thus generated, which in particular includes information about the terrain shape and / or the surface shape of the surroundings of the aircraft, but may also contain further information about stationary or movable obstacles, such as buildings or other vehicles, generated.

Subsequently, this synthetic first image can be transformed into the second image by means of a first non-planar projection 52 be transferred. This is done first, as it is for example in 7 is shown, converted by means of a second projection, the first image in a third image to a third projection, as shown for example in 8a and 8b is shown in the second image 52 to be convicted. The image 52 represents a representation of the environment of the aircraft with an extended viewing angle of 150 °. This representation is a realistic image of the environment is generated, and in particular distortions that can lead to misinterpretation by a pilot of the aircraft can be avoided. This is how the representation of the image corresponds 52 essentially the experience of the pilot when looking out of the cockpit, so that the distance to obstacles is correctly estimated and maneuvers can be initiated at the right time. In addition, the image contains 52 also information about the environment, in particular a terrain shape of the aircraft in a peripheral field of vision of the pilot, so that also obstacles that in a peripheral edge region of the figure 52 lie on the display 50 are displayed. As already mentioned, other than spherically shaped image planes for a non-planar projection can be used, for example, to mitigate angular distortion in the peripheral areas of a display.

In an alternative embodiment of the invention, the first image can be generated directly as a non-planar projection of the surroundings of the aircraft, for example by means of ray tracing, as an image 52 to be visualized in a two-dimensional representation plane.

In 10a is an ad 150 shown in which an image 152 an environment of the aircraft is shown. Elements of the ad 150 , those of the ad 50 in 9 correspond, bear the same reference numerals, but increased by 100. The image 152 is visualized by a non-planar projection with a viewing angle of 150 °. To visualize the environment of the aircraft on the display 150 The non-planar projection of the environment, which is generated either directly based on data from a database or generated by performing a non-planar projection from a planar image of the environment of the aircraft, using an equidistant, azimuthal two-dimensional image as an image 152 on the display 150 shown. In contrast, in 10b the same in 10a represented environment of the aircraft on a display 150 ' in the form of an image 152 ' shown. Those elements of the ad 150 ' , those of the ad 150 correspond, bear the same reference numerals, but simply deleted. Unlike the in 10a displayed display 150 will appear in the ad 150 ' a visualization of the non-planar mapping of the environment by means of an orthographic, azimuthal two-dimensional mapping performed. It is good from the 10a and 10b to recognize that the images 152 . 152 ' create a visual impression comparable to the normal field of view of a pilot.

In 11a is an ad 50 ' shown in which an image 52 ' the environment of the aircraft is shown. Elements of the ad 50 ' , those of the ad 50 in 9 correspond, bear the same reference numerals, but simply deleted. In 11a is in comparison to the ad 50 in 9 the image 52 ' visualized by a planar perspective projection with a standard viewing angle of 60 °. It can be clearly seen that obstacles that lie in the peripheral field of view of the pilot, and in the image 52 displayed at the image 52 ' not be displayed. The initiation of a flight by a pilot could thus lead to a collision of the aircraft with one of the laterally existing obstacles, in particular terrain formations.

However, if the viewing angle is increased in the planar projection, for example, to a viewing angle of 150 °, the results in 11b displayed display 50 '' , Elements of the ad 50 '' , those of the ad 50 ' correspond, bear the same reference numerals, but deleted twice. As can be seen from a comparison of the ad 50 '' with the ad 50 ' results in the display 50 '' through the image 52 '' The aircraft's surroundings present an obstacle in the pilot's peripheral field of vision, but obstacles appear in the central area of the figure 52 '' , ie in the direction of flight of the aircraft, are significantly smaller, so that the distance to these obstacles can easily be overestimated by a pilot. This can lead to maneuvers being initiated too late and a collision with an obstacle or a terrain formation can no longer be avoided.

By comparing the ad 50 '' with the ad 50 it follows that the in the 9 used non-planar projection according to the invention just avoids this disadvantage, since a realistic representation of the environment in the display 50 in particular, the distance to the aircraft in the direction of flight obstacles is represented in a manner that correspond to the experience of the pilot in a direct view from the cockpit of the aircraft in the direction of flight.

Consequently The invention contributes to the problem of line distortion large viewing angles in cockpit vision systems, such as from the State of the art are known, overcome. With the sen cockpit vision systems based on planar perspective projections, especially synthetic vision systems, it comes with large Viewing angles, in particular from about 90 °, to such strong longitudinal distortions, so that a pictured image is no longer the visual Experiences or the visual impression of a pilot at a sight correspond from a cockpit of the aircraft. The present Invention is based on the recognition that the differences between the representation of the virtual environment image and the normal visual impression of the pilot when looking out of a cockpit of the aircraft on the use of planar perspective Projections is based. By replacing this planar perspective Projection through a non-planar projection will accomplish that as well at large viewing angles for the pilot one A visual impression is created on the aircraft, which is its usual visual experience when looking out of a cockpit of the aircraft correspond.

A Getting used to comparatively larger ones Angular distortions in the border area of a display of a virtual Visual system, however, is easier to do than habituation to the reductions present in planar perspective projections of information in the central area of an ad at large Viewing angles. In particular, the use of the invention in synthetic Visual systems in which large area displays be used, leads to a significant improvement the ability to interpret the by the synthetic Visual system supplied information.

The in the above description, in the drawings and in the Claims disclosed features can both individually or in any combination for the realization be essential to the invention.

1

camera point

3

Projection beam

5

image plane

7

Hexaeder

9

vanishing point

11 11 '

tunnel element

12

Curve

13 13 '

tunnel element

15 15 '

tunnel element

16

line of sight

17

camera point

19 19 ', 19' '

image plane

21 21 ', 21' ', 21' ''

image plane

23

camera point

25

image plane

27

presentation layer

29

image plane

31

presentation layer

32

line of sight

50, 50 ', 50' '

display

52 52 ', 52' '

image

54 54 ', 54' '

direction indicator

56 56 ', 56' '

height indicator

58 58 ', 58' '

speedometer

60 60 ', 60' '

artificial horizon

150 150 '

display

152 152 '

image

154 154 '

direction indicator

156 156 '

height indicator

158 158 '

speedometer

160 160 '

artificial horizon

QUOTES INCLUDE IN THE DESCRIPTION

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Cited patent literature

• - DE 69103734 T2 [0016]
• - DE 3417058 A1 [0017]

Cited non-patent literature

• SPIE Vol. 5802, pp. 219-230, Enhanced and Synthetic Vision 2005, May 2005 edition [0004] "Synthetic vision systems for improving unmanned aerial vehicle Operator Situation Awareness".

Claims (18)

Method for displaying flight information ( 54 . 56 . 58 . 60 . 154 . 156 . 158 . 160 . 154 ' . 156 ' . 158 ' . 160 ' ) by means of at least one indicating instrument of an aircraft, wherein at least one first synthetic image ( 52 ' . 52 '' ) of an environment of the aircraft, characterized in that the first image is generated as an at least partially non-planar projection of the environment and is visualized in at least one two-dimensional representation plane of at least one display device of the display instrument and / or the first image ( 52 ' . 52 '' ) by means of at least one first, at least partially non-planar projection into at least one second image ( 52 . 152 . 152 ' ) and the second image ( 52 . 152 . 152 ' ) in the two-dimensional representation plane ( 27 . 31 ) of the display device ( 50 . 150 . 150 ' ) is visualized. Method according to Claim 1, characterized in that, in the first projection, the first image is first projected onto a non-planar image plane by means of at least one second projection ( 21 . 21 ' . 21 '' . 21 ''' ) is projected to produce a third image and then the third image is transformed into the second image by means of at least one third projection. Method according to claim 1 or 2, characterized that the first image depending at least a position, at least one orientation and / or at least one Attitude of the aircraft based on at least one database, in particular at least one storage device, stored environmental data, like a terrain shape and / or surface shape an environmental landscape, at least one position and at least a geometrical dimension of at least one stationary obstacle, as a building, and / or at least one position and / or at least a geometric dimension of at least one relative to the environment the aircraft movable obstacle, as at least one other Aircraft, at least one land vehicle and / or at least one Watercraft, and / or based on at least one Oberflächenabtastsystem of the aircraft, such as a radar system and / or at least one Sonar system, generated data is generated. Method according to claim 3, characterized that the position, the orientation and / or the attitude of the aircraft based on data from at least one satellite navigation system, like GPS and / or Galileo and / or at least one Attitude / Heading Reference Systems (AHRS), is or will be determined. Method according to one of the preceding claims, characterized in that the generation of the first image, the first projection, the second projection and / or the third projection at least one computational projection, in particular at least a conversion of image information of the first image in image information of the second image ( 52 . 152 . 152 ' ) and / or the third image and / or image information of the third image in image information of the second image ( 52 . 152 . 152 ' ), preferably by graphic data processing. Method according to one of the preceding claims, characterized in that the generation of the first image, the first projection, the second projection and / or the third projection at least one optical projection, in particular at least one optical transmission of image information of the first image in image information of the second image ( 52 . 152 . 152 ' ) and / or the third image and / or image information of the third image in image information of the second image ( 52 . 152 . 152 ' ). Method according to one of the preceding claims, characterized in that during the generation the first image, during the first projection and / or during the third projection at least one orthographic azimuthal projection and / or at least one equidistant and / or medium-distance azimuthal projection performed becomes. Method according to one of the preceding claims, characterized in that during the generation of the first image, during the first projection and / or during the second projection at least one at least partially profiled, in particular spherical, elliptical, parabolic, corrugated, serrated, pyramidal, conical and / or curved image plane ( 21 . 21 ' . 21 '' . 21 ''' ) is used. Method according to one of the preceding claims, characterized in that by means of the first image, the second image ( 52 . 152 . 152 ' ) and / or the third image, at least one virtual representation of the surroundings of the aircraft, in particular in the form of at least one grid network representation and / or at least one full-surface shape representation is mapped. Method according to one of the preceding claims, characterized in that by means of the first image, the second image ( 52 . 152 . 152 ' ) and / or the third image at least a virtual representation of the environment of the aircraft from at least one cockpit position in the forward direction of the aircraft and / or in a direction of movement and / or direction of flight of the aircraft is mapped. Method according to one of the preceding claims, characterized in that by means of the first image, the second image ( 52 . 152 . 152 ' ) and / or the third image, a viewing angle range of -30 ° to + 30 °, more preferably -60 ° to + 60 °, even more preferably -90 ° to + 90 °, even more preferably -120 ° to + 120 ° and / or most preferably from -180 ° to + 180 ° of the environment of the aircraft. Method according to one of the preceding claims, characterized in that in the first image, the second image ( 52 . 152 . 152 ' ) and / or the third image additional flight data of the aircraft, in particular at least one flight altitude information ( 56 . 156 . 156 ' ), at least one position information, such as at least one satellite navigation position, at least one direction information ( 54 . 154 . 154 ' ), such as at least one compass heading and / or at least one satellite navigation course, at least one position information, such as at least one inclination angle and / or at least one rollage, preferably in the form of at least one artificial horizon ( 60 . 160 . 160 ' ), at least one operating information relating to at least one drive unit of the aircraft, such as at least one operating temperature, at least one fuel consumption, at least one tank content and / or at least one rotational speed, at least one speed information ( 58 . 158 . 158 ' ), and / or at least one planned and / or future flight path ( 11 . 13 . 15 ) is displayed. Display instrument for an aircraft, in particular adapted for use in a method according to one of the preceding claims, comprising at least one display device ( 50 . 150 . 150 ' ) for visualizing flight information in a substantially two-dimensional representation plane ( 27 . 31 ), wherein by means of the display device ( 50 . 150 . 150 ' ) at least a first synthetic image of the surroundings of the aircraft can be represented, characterized in that the first image is a non-planar projection of the surroundings of the aircraft and in the representation plane ( 27 . 31 ) is visualizable or the first image using at least a first at least partially non-planar projection in the representation plane ( 27 . 31 ) as at least a second image ( 52 . 152 . 152 ' ) is visualizable. Indicating instrument according to Claim 13, characterized in that the display device has at least one tube screen, at least one liquid crystal display (LCD), at least Thin-film transistor (TFT) screen, at least one Surface-conduction electron emitter screen (SED), at least a plasma display, at least one screen comprising at least an organic light emitting diode (OLED) and / or at least one optical Projection device for visualizing the image on at least an at least for example planar projection surface includes. Indicating instrument according to Claim 14, characterized that the display device, in particular the display plane has a round, elliptical and / or rectangular format, in particular the ratio of a width to a height the display plane is substantially 1: 1, 4: 3 and / or 16: 9. Indicating instrument according to one of the claims 13 to 15, characterized by at least graphic data processing unit for performing the first, the second and / or the third Projection. Indicating instrument according to one of the claims 13 to 16, characterized by at least memory device, in particular for storing and / or retrieving environmental data at least one data carrier reading device and / or data medium writing device, like at least a DVD drive and / or CD drive, and / or at least a, preferably removable mass storage, as at least a hard disk and / or at least a memory stick. Indicating instrument according to one of the claims 13 to 17, characterized in that the indicating instrument as a cockpit instrument, head-up display, projection display, in particular for at least one cockpit screen and / or a helmet visor, and / or head-down display is configured.