This invention claims priority from U.S. patent application Ser. No. 60/233,825, filed Sep. 19, 2000.

BACKGROUND OF THE INVENTION

1. Technical Field

This invention relates, generally, to data display systems and, more particularly, to a system and method for graphical interaction with an aircraft information display system.

2. Background Information

Aircraft flight displays continue to advance in sophistication, achieving increasingly higher levels of information density and, consequently, presenting a greater amount of visual information to be perceived and understood by the operator. In many applications, it is important that visual displays provide a proper cognitive mapping between what the operator is trying to achieve and the information available to accomplish the task. As a result, such systems increasingly utilize human-factor design principles in order to build instrumentation and controls that work cooperatively with human operators. Accordingly, the Federal Aviation Administration (FAA) has promulgated a number of standards and advisory circulars relating to flight instrumentation. More particularly, Title 14 of the U.S. Code of Federal Regulations, Federal Aviation Regulations (FAR) Part 25, Sec. 25.1321 et seq. provides guidelines for arrangement and visibility of instruments, warning lights, indicators, and the like. Similarly, detailed guidelines related to electronics displays can be found in FAA Advisory circular 20-88A,

Guidelines on the Marking of Aircraft Powerplant Instruments

(September 1985).

One area in particular that has not profited in advances in graphical user interfaces is the field of aircraft flight management systems. Specifically, in current generation aircraft, flight plan entry and editing continues to be performed using cumbersome, text-based techniques that have not changed significantly in the last decade. As a result, flight crews frequently complain that current flight management systems (FMS) are non-intuitive, difficult to interpret, and require too much heads-down time. Indeed, due to the high cockpit workload involved, many flight crews abandon the FMS altogether, choosing instead to fly the aircraft using the autopilot.

Systems and methods are therefore desired to overcome these and other limitations of the prior art. Specifically, there is a long felt need for an interface to flight management systems that is intuitive and easy to use, and which enables multiple flight crew members to concurrently interact with the FMS.

BRIEF SUMMARY OF THE INVENTION

The present invention provides systems and methods for an integrated graphical user interface that facilitates the display and editing of aircraft data with improved cursor management. In accordance with various aspects of the present invention, one or more users (e.g., a pilot and a co-pilot) located within the aircraft provide input to a processor through one or more cursor control devices and receive visual feedback via an electronic display. The display includes various graphical elements associated with the lateral position, vertical position, flight plan and/or other indicia of the aircraft's operational state as determined from avionics data and/or various data sources. Through use of one or more cursor control devices, one or more users may view, modify, or otherwise interact with the displayed flight plan and/or other such indicia graphically in accordance with feedback provided by the display.

An aircraft display and control system in accordance with the present invention generally includes a processor, a cursor control and selection device, an aeronautical information database, a geographic database, and a plurality of display devices. Users, such as an aircraft pilot and copilot, can perform flight plan entry and modification by manipulating graphical information on the display devices using cursor control. In one embodiment, the present invention allows multiple members of an aircraft crew to share control of common flight information display areas, aids the crew's situational awareness by providing software-implemented dynamic symbology and highlighting to indicate cursor location, current panel of entry, and current focus for keyboard and cursor events.

BRIEF DESCRIPTION OF THE DRAWINGS

A more complete understanding of the present invention may be derived by referring to the following detailed description and claims when considered in connection with the following illustrative figures.

FIG. 1

is a schematic overview of a user interface in accordance with one embodiment of the present invention;

FIG. 2

is a schematic overview of a display arrangement in accordance with one aspect of the present invention;

FIG. 3

is a schematic overview of a flight deck which embodies certain aspects of the present invention;

FIG. 4

is a schematic diagram of the components of a prior art flight deck;

FIG. 5

is a representation of an exemplary display device in accordance with certain aspects of the present invention;

FIG. 6

is a diagram showing the configuration of different cursor symbols displayed on multi-function display units of the flight deck of FIG.

3

.

FIG. 7

illustrates a different configuration of a cursor symbol in an “inactivated” state; and

FIG. 8

is a schematic representation of the dynamic highlighting feature embodied in one aspect of the present invention.

DETAILED DESCRIPTION OF EXEMPLARY EMBODIMENTS

Systems and methods in accordance with various aspects of the present invention facilitate one or more users' graphical interaction with an aircraft information display. In this regard, the present invention may be described herein in terms of functional block components and various process steps. It should be appreciated that such functional blocks may be realized by any number of hardware, firmware, and/or software components configured to perform the various specified functions. For example, the present invention may employ various integrated circuit components, such as, for example, memory elements, digital signal procession elements, look-up tables, and the lich, which may carry out a variety of functions under the control of one or more microprocessors or other control devices. Such general techniques and components that are known to those skilled in the art are not described in detail herein.

Referring now to

FIG. 1

, a system in accordance with various aspects of the present invention includes a processor

106

configured to communicate with an associated monitor (or monitors)

112

, one or more data sources

108

, one or more cursor control devices

104

, and avionics data

110

. In general, one or more users

102

, such as, for example, a pilot and/or a co-pilot, located within an aircraft (not shown), provide input to processor

106

through cursor control device (or devices)

104

, and receive visual feedback via a display

114

produced by monitor

112

. Display

114

includes various data elements associated with the lateral position, vertical position, flight plan and/or other indicia of the aircraft's operational state as determined from avionics data

110

and/or data sources

108

. Through use of cursor control device(s)

104

, user(s)

102

may interact with the data elements graphically in accordance with feedback provided by display

114

.

Cursor control device

104

includes any device suitable to accept input from user

102

and to convert that input to a graphical position on display

114

. Various joysticks, mice, trackballs, and the like are suitable for this purpose. In one embodiment, cursor control device

104

includes a touch-pad interface device with a thumb actuation switch on the side. In this embodiment, the user rests his or her hand on a built-in palm rest to stabilize the hand, position the fingertip for pointing, and position the thumb for clicking. In an alternate embodiment, cursor control device

104

is a trackball device coupled with one or more keys or push-buttons used to select data captured by the cursor.

Monitor

112

may include any display monitor suitable for displaying the various symbols and information detailed herein. Many conventional monitors are suitable for this task, including, for example, various cathode ray tube (CRT), liquid crystal display (LCD), Heads Up Displays (HUDs), Helmet Mounted Displays (HMDs) and other electronic display systems.

Processor

106

encompasses one or more functional blocks used to provide flight management and control, to interface with cursor control device

104

, and to drive monitor

112

. In this regard, processor

106

may include any number of individual microprocessors, memories, storage devices, interface cards, and other conventional components known in the art.

Avionics data

110

includes aeronautical information related to the state of the aircraft derived from an aeronautical information database. Data sources

108

include various types of data required by the system, such as, for example, flight plan data, data related to airways, navigational aids (Navaids), symbol textures, navigational data, obstructions, font textures, taxi registration, Special Use Airspace, political boundaries, COM frequencies (en route and airports), approach information, and the like. Typically, for example, a geographical information database is included within data sources

108

.

Referring now to

FIG. 2

, a display

114

in accordance with various exemplary aspects of the present invention includes a lateral view

202

, a vertical profile view (or “vertical profile”)

204

, and a hot-map view (or simply “hot-map”)

206

.

Vertical profile

204

suitably includes a side-view aircraft symbol

208

(

b

), one or more waypoint symbols

212

(

b

) (or constraint symbols, described in detail below), line segments

209

(

a

) connecting waypoint symbols

212

(

b

), a first axis

218

representing lateral position and/or time, and a second axis

216

designating altitude. As with the lateral view

202

, the system is preferably configured such that the user may modify the flight plan and trajectory via graphical manipulation of symbols

212

(

b

) using cursor symbol

210

.

In one embodiment, the various areas of display

114

may be expanded to facilitate display and editing of the flight plan. For example, when the user clicks cursor

210

within vertical profile

204

of display

114

, that region expands to fill a larger area of the total display area of display

114

.

Referring further to

FIG. 2

, lateral view

202

suitable includes various graphical elements (“symbols”) representing, among other things, the lateral position of the aircraft with respect to the ground. Lateral view

202

may also include various map features, including terrain, political boundaries, and the like. In the illustrated embodiment, lateral view

202

includes a top view aircraft symbol

208

(

a

), one or more waypoint symbols

212

(

a

), and line segments

209

(

a

) connecting waypoint symbols

212

(

a

), wherein waypoint symbols

212

(

a

) are associated with the current flight path of the aircraft. Display

114

may also include one or more cursor symbols

210

positioned in accordance with input from one or more users

102

(see

FIG. 1

) received via one or more cursor control devices

104

(see FIG.

1

). While the details of the user's interaction with lateral view

202

will be discussed further below, in general, cursor

210

is suitable positioned by the user in order to select and graphically edit data elements appearing on display

114

, such as, for example, the flight plan associated with waypoints

212

(

a

).

As briefly mentioned above, in addition to lateral view

202

and vertical profile

204

, an embodiment of the present invention includes a hot-map region which encompasses a larger albeit simplified lateral area than that shown in lateral view

202

. A rectangular or square outline corresponding to the region shown in lateral view

202

may be displayed in hot map.

FIG. 3

is a representation of certain features of an aircraft cockpit display layout in accordance with one aspect of the present invention. Displays

302

,

304

,

306

, and

308

are included on an instrumental panel

312

of a flight deck

300

and generally comprise four display devices (such as display devices

114

in FIG.

1

), such as, for example, color flat-panel LCD screens. Outboard displays

302

and

308

are each constitute a Primary Flight Display (PFD). All flight information and short-range information is located on displays

302

and

308

. Inboard displays

304

and

306

each constitute a Multi-Function Display (MFD). Displays

304

and

306

can be used by more than one person, requiring only coordinated management. Instrument panel

312

also includes standby instruments (not shown). The standby instruments may be of conventional type, such as an altimeter, airspeed indicator, attitude indicator, and instrument landing system (ILS) glide slope/localizer indicator. Alternatively, they could be implemented as flat panel electronic instruments. Regardless of whether conventional or flat panel electronic instruments are utilized, these instruments are generally meant only as a back-up to displays

302

,

304

,

306

, and

308

.

Thus, in the cockpit of

FIG. 3

, one user (e.g., a pilot) may be present at the left side of the cockpit, in front of display

302

and adjacent to displays

304

,

306

, while another user (e.g., a co-pilot) may be present at the right side of the cockpit, in front of display

306

and adjacent to displays

304

,

306

. Displays

302

,

304

,

306

, and

308

need not be coplanar. Indeed, in a typical aircraft cockpit, displays

302

,

304

, and

306

may be substantially coplanar, with display

308

located on a separate console between the pilot and co-pilot. It should also be noted that displays

302

,

304

,

306

, and

308

need not be identically or substantially identically sized and are not shown to scale, as each display may have a different aspect ratio than that shown.

Displays

302

,

304

,

306

and

308

provide a functionality that formerly was provided by a plurality of gauges on an instrumentation panel. In the past, a cockpit generally would contain separate gauges to indicate, inter alia, attitude, altitude, airspeed and vertical speed. This is illustrated in

FIG. 4

, which is a graphical representation of an exemplary prior art cockpit. Illustrated in

FIG. 4

are, inter alia, airspeed indicator

402

, attitude indicator

404

, radio compass

406

, horizontal situation indicator

408

, and altimeter

410

.

The individual gauges illustrated in

FIG. 4

have in recent years been replaced by various display units. For example,

FIG. 5

illustrates an exemplary display

500

. Display

500

is a single CRT or LCD display unit in which graphical representations of an attitude indicator, airspeed indicator, altimeter, and horizontal situation indicator have been rendered in separate areas of display

500

by a computer. Specifically, area

502

contains a rendering of an attitude indicator, area

504

displays the airspeed, altimeter

506

displays the altitude, and heading source indicator (HSI)

508

shows the heading of the aircraft.

Referring back to

FIG. 3

, in typical usage, display

302

and display

308

will show substantially identical information, such that the pilot and the co-pilot have access to the same information. Typically displays

302

and

308

will be configured in a manner similar to that shown in

FIG. 5

, such that the attitude, altitude, airspeed, and heading are displayed. Display

304

may be configured, for example, to display navigational information, such as an indication of the current heading of the aircraft and data regarding the surrounding area.

Displays

304

and

306

are used for managing the flight plan, carrying out flight path modification, and monitoring aircraft systems and sensors availability. The corresponding procedures involve extensive use of cursor control and multifunction keyboard. Alternatively, the functions of the keyboard and/or cursor control could be performed by other suitable conventional means, such as direct voice input.

One aspect of the design of displays

304

and

306

is the ability for both pilot and copilot to access both displays from each seat, using a distinctive cursor, as shown in FIG.

6

. Both displays provide the same options and are coupled to synchronized FMS processors. Both displays are synchronized such that, for example, when the pilot is working on, for example, an en route high altitude chart on display

304

, the copilot can work on the same chart on display

306

, using a different range scale or type of format. The pilot and copilot can also work together on the same panel, on the same display, each one using a separate multifunction keyboard and a separate cursor control device to interact with the display system. One further aspect of joint access to displays

304

and

306

is that only one cursor and keyboard may be active within a given “panel” or window at a time.

Access to and between displays

304

and

306

is implemented by a “cursor skip” function, which selectively permits each cursor to move about each display. In one embodiment, this cursor skip function is selectively implemented by cursor control velocity. For example, if a pilot slowly operates the cursor control device to move the cursor to the bottom of display

304

, the cursor will stop at the bottom edge of display

304

to prevent the cursor from inadvertently “skipping” to display

306

. Subsequent slow movement of the cursor control device downward will not result in further downward movement of the cursor. Rapid operation of the cursor control, however, will cause the cursor to “skip over” to display

306

. The pilot can then use the cursor and related buttons, knobs, and/or keys to implement any feature available on display

306

. Similarly, this cursor skip function may be implemented to control movement of the cursor between and among displays

302

,

304

,.and

306

and between and among displays

304

,

306

, and

308

. The cursor skip function could, of course, be implemented using a selector other than cursor control velocity. For example, a dedicated button or key could be provided, operation of which would be required to permit “cursor skip” to an adjacent display.

The following functions are redundantly included in both displays

304

and

306

to permit a flight to depart even if one display is inoperable: display engine parameters and warning/caution messages; display all aircraft electrical, fuel, air conditioning, hydraulics systems; display horizontal situation and vertical profile; manage FMS and AFIS; manage normal and abnormal checklists; and display general maintenance items in flight that can be easily understood by the crew.

In various embodiments, the cursor control devices and multifunction keyboards are the primary means of interacting with the MFDs. Operation of the cursor involves the actions of cursor “capture” and “selection,” commonly know in the personal computer world as “point and click.” For example, when a pilot is interacting with horizontal situation indicator, the cursor is movably superimposed upon points on the map by action of the cursor control device. Certain of these points on the map constitute special positions recognized by the system: RNAV points, routes, airports, and the like. When the cursor is superimposed on one of such points, the point is “captured,” that is, the background around the captured point changes color, and the cursor is displayed behind this background. To “select” the captured point, an action button on the cursor control device is operated. This causes data stored for this point in system memory to appear as an information window displayed at the cursor location. The pilot can then begin modification of the parameter displayed in the window, using the multifunction keyboard, for instance. It is also possible and may be beneficial to designate soft keys and labels, which will cause the corresponding function or option to be selected.

In various embodiments, there may be no priority given to either pilot in interacting with displays

304

and

306

. Each pilot can work with his or her cursor on both displays, and both pilots can also work together on the same display, or on the same function on different displays. In the latter case, the system accounts for the chronological order of actions. One possible exception, however, may be that if one pilot has already begun a modification, the other pilot cannot interfere with this parameter as long as the procedure is not terminated. However, the second pilot can modify another parameter on the same display. Hence, it is possible to get both cursors on the same display. The cursors for each pilot may be graphically different, as shown, for example, in FIG.

6

. In

FIG. 6

, the cursors differ in their geometric configuration. In other practical applications of the present invention, the cursors may be distinguished by color, size, shape, or other suitable configuration.

In one aspect of the present invention, when both cursors are present in the same panel of the same display and action is being taken by one pilot with regard to the cursor, the other pilot's cursor changes configuration as shown in FIG.

7

. Cursor configuration

702

indicates that the cursor is inactivated. Once the first pilot's modifications are completed, terminated, or otherwise “timed-out,” the first pilot's cursor will change to configuration

702

and the second pilot's cursor will return to its normal state. In this way, each pilot may ascertain at a glance whether their intended modifications may be made at any point in time. If the cursors are positioned such that their actions will not interfere with one another, it is not necessary for one cursor to be inactivated, and hence the cursor configurations will remain in their normal state (as illustrated, for example, in FIG.

6

).

The MFDs are configured to allow the pilots to modify selected parameters displayed as a window. When a cursor is positioned over a particular parameter, its background changes color and a modification can be effectuated by entering a new value with a keyboard, “dialing” a new value with a knob, or by any other means configured to perform such entries. While being modified, the parameter may be displayed cyan with cyan framing, or with any other format or color. When the modification is completed, the pilot presses the “ENT” or “Enter” key on the keyboard, or clicks the button on the cursor control device. If the pilot presses “ENT” or clicks without entering new data, the cursor automatically skips to the following parameter field. In one aspect of the invention, it is possible to exit the modification process by double-clicking the button of the cursor control device, so that the system returns to the previous status.

If a displayed cursor remains inactive for a given period of time—that is, if its position is not altered using the cursor control device or if no other action is taken—the cursor may be configured to “time out” and to disappear from the display panel until further action is taken. Once the cursor is timed out and removed from view, no further modification of displayed parameters is made until the cursor is refreshed. The cursor may be refreshed—that is, once again made visible-by simply moving the cursor control device even slightly or by operating a button or key so configured to restore the cursor to the display area. In one aspect of the invention, the cursor is highlighted upon restoration to the display and comes back in the same position as when it was timed out. This highlighting may take the form of a brightly-colored “halo” around the cursor and a highlighting of the panel frame, such that the cursor may be found quickly and easily by the pilot during operation of the aircraft. This highlighting effect is maintained briefly, giving the pilot adequate time to locate the cursor, but then fades away such that it does not interfere with the display graphics. In one embodiment, as illustrated in

FIG. 8

, a light-colored yellow halo

802

(

a

) is displayed around a cursor

804

at the moment it is restored, and the gray frame outlining the display panel at which the cursor lies is highlighted in cyan. Through a time period of about 1-3 seconds, the light-colored yellow halo gradually decreases in size and intensity (see

802

(

b

),

802

(

c

)) until cursor

804

has been restored to its normal state.

As mentioned briefly above, systems in accordance with the present invention provide the ability to graphically modify and/or enter flight-plan information via the cursor-control device. It should be understood that the exemplary methods illustrated may include more or less steps or may be performed in the context of a larger process scheme. Furthermore, the various flowcharts presented in the drawing figures are not to be construed as limiting the order in which the individual process steps may be performed.

Thus it is apparent that there has been provided herein a system and a method for aircraft information display and control that fully meets the needs set forth above. Although the invention has been described and illustrated with reference to certain illustrative examples, it is not intended that the invention be limited to these illustrative embodiments. Those of skill in the art will recognized that various modifications and alternatives are possible without departing from the spirit of the invention. For example, although reference has been made throughout to “aircraft,” it is intended that the invention also be applicable to vehicles that are on the ground or in space. Accordingly, it is intended that the invention include all such modifications and alternatives as fall within the scope of the appended claims.