US20070244933A1 - Display system for airplane cockpit or other vehicle - Google Patents

Abstract

A display system for an airplane or other vehicle is disclosed. A rear projection LCD is used to allow for a maximum amount of screen area to be used in displaying operator pertinent data.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS
• This application is a continuation of U.S. patent application Ser. No. 11/294,046, filed Dec. 5, 2005, entitled “Display System For Airplane Cockpit Or Other Vehicle,” which is a continuation of U.S. patent application Ser. No. 10/760,620, filed on Jan. 20, 2004, entitled “Display System for Airplane Cockpit Or Other Vehicle,” now U.S. Pat. No. 6,972,695, which is a continuation of U.S. patent application Ser. No. 09/863,140, filed on May 22, 2001, entitled “Display System for Airplane Cockpit or Other Vehicle,” now U.S. Pat. No. 6,750,788, which is a divisional of U.S. patent application Ser. No. 08/934,825, filed on Sep. 22, 1997, entitled “Display System for Airplane Cockpit or Other Vehicle”, now U.S. Pat. No. 6,259,378. The entire disclosure of each prior application is incorporated herein by reference.
BACKGROUND OF THE INVENTION
• 1. Field of the Invention
• The present invention relates generally to display systems for airplane cockpits or other vehicles, and more particularly, to a rear projection digital display system which allows a high level of information to be selectively displayed regarding such data as travel path, travel conditions, vehicle condition, geographical conditions, and hazard or obstruction warnings.
• 2. Description of the Related Art
• The layouts of cockpits for airplanes are regulated by the FAA in the United States. The SAE (Society of Automotive Engineers), which acts as a standards writing/recommending body to the FAA, has issued standards for aircraft instruments which are adhered to in aircraft construction. For example, the 3ATI slot standard, which is an ARINC (Aeronautical Radio, Inc.) standard, has been complied with in the vast majority of all aircraft in use today. This standard was developed when electro-mechanical display devices, such as HIS (Horizontal Situation Indicator), were the norm, and only allows a panel area of 3“.times.3” in dimension.
• With the advance of digital technology, there has been a need in the industry to replace these displays with digital versions, to provide increased reliability, accuracy and more functionality. However, the planes cannot be easily retrofited with digital equipment that require a bigger screen, and the required 3.times.3 panel has conventionally proven to be too small for digital displays. The 3“.times.3” display has been a major impediment to the development of such a digital display.
• First, standard direct view LCDs are not mass produced in this size, and therefore a specially made LCD for 3“.times.3” can cost as much as $10,000 each to produce. Furthermore, due to the construction of the direct view LCD, the outer perimeter of the device cannot be used to display information, as it is used by the drive electronics. As a result, the 3“.times.3” LCD typically produces a display area of only 2.3“.times.2.3”. This reduced display area impedes the ability to put enough information on the display for it to be useable for many functions.
• A second problem addressed by the invention is the growing demand in the avionics industry for more sophisticated “situational awareness for safety” (SAS) technology. This refers to technology which provides the pilot with more easily understandable and more comprehensive information about the immediate surroundings, and any hazards which may be present.
• For example, in 1996, there were 246 general aviation airplane crashes in the United States. Of these crashes, 42 were controlled flight into terrain (CFIT). That is, situations in which the airplane was flown into an obstruction such as a mountain, an antenna or the ground under control of the pilot. Typically these instances occur when visibility is very low and the pilot is off course. As a result, the pilot is unaware of the natural obstructions in the flight path because the display devices only provide information on the desired flight course.
• It is believed that if the present invention had been available for these planes, a large number of these accidents would have been prevented, and hundreds of lives saved. Thus, there is a need in the industry for (1) technology to effectively collect data on surrounding structures even when the pilot is off path, and (2) hardware to display this information in a simple and direct manner to the pilot, preferably using digital instruments.
SUMMARY OF THE INVENTION
• Accordingly, it is an object of the present invention to overcome the above-noted deficiencies in the prior art.
• In particular, in certain aspects of the invention, an avionics display device may include a rear projection LCD system which obtains maximum display area in a 3ATI display slot.
• In addition, in the present invention the microprocessor may receive G.P.S. (“Global Positioning System”) data as an input, and may also have a memory which stores topographical map data (e.g., Defense Mapping Agency topographical information of North America or other geographical area) in database form. The device correlates the G.P.S. and topographical data to determine the location of the aircraft, and any obstacles in the flight path or surrounding area. Other navigational devices (e.g. VOR) may also be used to determine position. In addition, data from the flux gate and gyro may be used to aid in the determining the flight path of the aircraft. From this information, upcoming obstacles are determined from the DOD topographical data and are displayed to the pilot.
• In certain embodiments of the invention, different types of information are selectively displayable on the system. To avoid clutter and ease of understanding, user inputs are provided to allow the pilot to selectively turn on or off the display of certain information. For example, as the pilot is approaching the runway for a landing, and is within visible range of the runway, the pilot may turn off the rearward view or navigational aids not associated with the approach to the runway.
• In addition, it should be noted that while the present invention is a well-suited for use in the avionics cockpit display, it is equally applicable to other vehicles.
BRIEF DESCRIPTION OF THE DRAWINGS
• FIG. 1 is block diagram of the components of one embodiment of the present invention.
• FIG. 2 is a cross section of one embodiment of the invention.
• FIG. 3A is a block diagram of one embodiment of the video display system of the invention.
• FIG. 3B is a more detailed block diagram of the mirror and LCD system of an embodiment of the invention.
• FIG. 4 is a block diagram of one embodiment of the sensor input system of the invention.
• FIG. 5 is a program flow chart of the operation of one embodiment of the invention.
• FIG. 6 is a flow chart of a subroutine for use in the program flow ofFIG. 5.
• FIGS. 7A and 7B are representative display screens of one embodiment of the invention.
• FIGS. 8A and 8B illustrate an embodiment of the invention for use in a 3ATI slot.
DETAILED DESCRIPTION
• FIG. 1 is a block diagram of the overall system. The entire system is run by amicroprocessor100 which may be the MPC821 manufactured by Motorola. As will be explained more fully below,microprocessor100 receives a plurality of thesensor inputs200 which may include, for example, G.P.S. information, flux gate data, gyro data, etc. Thesensor inputs200 are sampled and input toprocessor100 in sync withclock sync signal300. Themicroprocessor100 receivesclock sync signal300 and regenerates and supplies it to the attached devices.Microprocessor100 is also associated with anon-volatile memory410, which may be a flash memory such as model 208F800 manufactured by Intel. This memory is used to store operational software, database information, and repetitive screen data as explained more fully below.Microprocessor100 is also associated withvolatile memory420, such as DRAM, for storing information used during operation, and graphical information for driving the display system. Typically,memories410 and420 each will have at least 4 M bytes of storage space.
• Microprocessor100 also controlsrear projection system500, which includes alight source510,LCD driver system520, and arear projection LCD530, which displays data onscreen540. TheLCD driver system520 receives the graphical information frommemory420, which is programmed by themicroprocessor100.
• Microprocessor100 programs the graphical data intomemory420 based on the data received fromsensor inputs200, and the user input conditions received from auser input device600.
• As is shown inFIG. 2, the entire device may be fitted into a 3ATI box. As shown, user input device600 (FIG. 1) includes a plurality ofbuttons900 and at least oneknob910 which are selectively positioned so as not to obstruct screen540 (not shown). Referring toFIGS. 1 and 2, these devices are positioned within the instrument so as to avoid crossing the light path betweenlight source510,LCD530 and the image path between theLCD530 andscreen540. The mechanical aspects of the present invention to achieve such a compact and unobstructed design will be explained more fully hereinafter.
• Rear Projection LCD Display System
• FIG. 3A is a more detailed block diagram ofrear projection system500 which includeslight source510,mirror system532,LCD530,LCD driver522,serializer524 andscreen540. A commercially available TFT (Thin Film Transistor) type LCD may be used for the image projection, although any suitable projection LCD system may be used.LCD530 andmirror system532 make up a filterless microlens type rear projection LCD. An example of such device is the Sony model no. LCXO19. The LCXO19 has a substantially rectangular image generation area (active area) of 26.9 mm.times.20.1 mm, which provides an approximately 4:3 aspect-ratio. The device may operate as follows:Light source510 emanates white light, andmirror system532 breaks up the light into three components, R, G, B, respectively along a first axis R, a second axis G, and a third axis B, all three of which are at an angle to one another. The light rays R, G, B impinge upon individual pixels ofLCD530 at discreet angles. In accordance with electrical signals received fromLCD driver522 andserializer524, which are formulated in response to data frommicroprocessor100 and the graphical data frommemory420, the individual pixels ofLCD530 are adjusted so as to collectively form a color image which is projected along optical axis X and on toscreen540. TheLCD530 may be updated at any desired rate viadriver520, but preferably is updated at 30 frames per second. The operation of the LCD driver is described below.
• A more detailed description of the light system of one embodiment of the invention is provided with reference toFIG. 3B. Lamp or otherlight source510 generates white light which is reflected off afirst mirror5322 and passed through acondenser lens5323 so as to form a collimated light beam which is then presented to adichroic lens system5324. The system includes awedge5324 which has atop surface5324A coated with a dichroic material which reflects red light and passes all other colors. The reflected red is direct to the LCD at 7 degrees above the line normal to the LCD. The second surface5324B of thewedge5324 reflects blue at 0 degrees to the normal and passes all other colors. Beneath thewedge5324 is amirror5325, which reflects the remaining green light −7 degrees with respect to the normal. For sake of simplicity, this is illustrated inFIG. 3B with respect to only one ray of light. Of course, in operation all light presented to thewedge5324 andmirror5325 will undergo similar separation. R, G and B light beams are then impinged uponLCD530. Following theLCD530, the formed image is passed through a projection lens system, includinglenses5326A and5326B and projected on the screen.
• It should be noted that instead of awedge5324, two separate mirror plates could be used. However, the wedge arrangement achieves the same results as a mirror system, while avoiding the necessity of light passing through up to four additional surfaces (e.g., the green light would have to go through two extra surfaces on the way down and two extra surfaces on the way up). This allows for greater display intensity.
• TheLCD driver system520 includes a digital to analog converter. The analog data is then input to theserializer524, which is then input toLCD530. TheLCD driver522 is refreshed from a graphics buffer which is inmemory420. This is done in hardware. Ifprocessor100 stops updating the screen memory, theLCD driver522 will still continue to pull the screen data in bursts from the graphics buffer inmemory420, and keep the LCD image updated. This means thatprocessor100 does not have to update the screen graphics data at a constant speed in order to eliminate flicker.
• The screen data is updated in “push-pull” graphics buffers. This means that while a first buffer is used for LCD refresh, the processor software updates a second buffer. When the processor is done with the new update, it sets a “ready” flag and changes the start address for theLCD driver522. This is called a “handoff” of the new buffer. When theLCD driver522 is at the end of the current screen refresh period, it will automatically use the new buffer address, placing the newly updated graphics data on the screen. TheLCD driver522 also generates an interrupt inprocessor100 which indicates “handoff complete” by resetting the “ready” flag and setting the address of the next update buffer. This flag/address indicates the free buffer and will be used by the main program loop for the next update.
• A three buffer system may be used to accomplish this result.
• 1. Buffer currently displayed (read-only until hand-off to next buffer).
• 2. Buffer being painted (will become next displayed).
• 3. Buffer being cleared (will become next painted).
• The use of a three buffer scheme allows the buffer clear operation to be done by direct memory access (DMA) which improves processor efficiency by allowing processor software execution to occur simultaneously with screen buffer clearing.
• In order to increase system speed, repetitively displayed graphics, e.g. background graphics such as a compass pattern, are written only once and stored as background scenes. Thus, instead of the buffer being cleared to black, the appropriate repetitive scene is copied via DMA into the buffer. This allows the paint procedures to add only the appropriate graphics on top of the repetitive scene.
• Thus, the process of reading and writing three buffers, (buffer0,buffer1, and buffer2) is as follows:
• 1. Refresh the LCD screen with data from buffer0.
• 2.Processor100 andmemory420 cooperate to store a new graphic intobuffer1.
• 3.Processor100 andmemory420 cooperate to store repetitive scene data inbuffer2.
• 4. Refresh the LCD screen with data frombuffer1.
• 5. Write new scene data intobuffer2 to overlay repetitive scene data already inbuffer2.
• 6. Store repetitive scene data in buffer0.
• 7. Refresh the LCD screen with data inbuffer2.
• It will be recognized that the above description is merely one example of how the LCD reading and writing and driving functions may be performed. It will be clear to those of ordinary skill in the art that many other types of memory and program architecture are possible to achieve similar results.
• Sensor Inputs
• The present invention receives a plurality of sense signals, which are used byprocessor100 to calculate various parameters such as current heading, height off ground, longitude and latitude positions, attitude of the aircraft, etc. As shown inFIG. 4, a plurality ofsignals210 may be received from various sensors in the aircraft. Thesignals210 may be fed intosignal conditioning circuits220 which in turn are fed into a 48channel multiplexor230. Themultiplexor230 also receives aclock control signal240. In one embodiment, the clockcontrol sync signal240 is the A/C power supply of the aircraft which is 400 Hz. Use of the aircraft power supply of the clock signal is advantageous to sync multiplexor sampling to the A/C sensors, as sensors throughout the aircraft may be synched withprocessor100 and themultiplexor230 without the need for a separate clock signal to be run throughout the aircraft. The use of asingle multiplexor230 also allows use of asingle AID converter250 which inputs tomicroprocessor100.Signal inputs210 include signals from the flux gate, the directional gyro, the G.P.S. receiver, the ILS receiver (instructional landing system) which provides for precision approach guidance and landing. As shown inFIG. 1, some inputs may be directly coupled to themicroprocessor100 byserial input250. For example, GPS data may be serial input from a GPS receiver. Or, data from the radar altimeter, which indicates the height of aircraft above the ground may be input by serial input. Depending on the priority level of the data, some of the inputs may be sampled once per cycle while others may be sampled multiple times per cycle through themultiplexor230.
• In some embodiments a 1600 Hz sync signal is generated by “synching” off the peak voltages and zero crossings of the 400 Hz power supply signal. This allows faster sampling.
• In addition to the above-described sensors, additional sensors such as a lightening sensor may be used. Indeed any navigational or other flight data sensor may be used.
• In certain embodiments of the invention,nonvolatile memory410 will store a database corresponding to a topographical map illustrating different obstacles throughout a given sector of the world based on longitudinal and latitudinal locations. The sensor data which provides the plane's location such as a G.P.S. receiver, or a similar type system will be reviewed by themicroprocessor100 and correlated via a look-up table with the topographical data. As a result,microprocessor100 will be able to determine if any obstacles are within the flight path of the aircraft or within the vicinity of the aircraft. This data, as explained below, can then be displayed to the pilot in a succinct manner so as to alert him of the possibility of hitting the obstacle.
• Memory410 also stores other database information, such as airport location, runway data, magnetic north data, etc.
• The present invention also provides a unique method of updating the database information stored inmemory410.
• As is well known in the art, database information such as airport location, magnetic data, etc., is updated on a regular basis. However, when these databases are updated, they have an effective date in which they will become applicable.
• Databases are updated by a regular maintenance procedure on the airplane. In particular, a maintenance computer is attached to the onboard microprocessor by, for example, a serial port. The maintenance computer updates the database to include the effective data. However, the problem is where the maintenance on the airplane is performed prior to the effective date of the new data. In such situations, the airplane has conventionally been forced to store both the “old” database information as well as the soon to be effective database information, thereby doubling the amount of memory required. However, according to the present invention, the database is updated such that only the changed information of database is written into the memory. These changed information points are written into a portion of the memory referred to as continuation data. Using the database,microprocessor100 will first read the anticipated data from the regular portion of the database, and then it will check the conditional memory section to see if any changes have been made in data currently being polled. If a change has been made,microprocessor100 determines whether the new effective date has taken place, and if it has, it uses the new data in the conditional memory; otherwise, it uses the old data. That is, the maintenance computer determines the contents of the database of the onboard computer and determines what data has changed. It only uploads the changed data. For example, in one embodiment the onboard memory contains data indicating the date of the last update. The maintenance computer checks this date and from this can determine what data to add. It should be noted that multiple changes may be made to a particular data point, with each change stored in the continuation memory. Of course, if desired the extra main memory may be re-updated and the continuation memory cleared.
• This system has two main benefits. First, it reduces the amount of onboard memory that is required, thereby reducing the cost of the device, and second, it speeds up the maintenance process of uploading the new data to the airplane as it is only necessary to upload the changed data.
• Mechanical Improvements
• As explained above, one of the aspects of the invention concerns maximizing the displayable area of the LCD screen. In one embodiment of the invention directed to a 3ATI avionics slot, any blockage of the 3“.times.3” screen can result in a useable display area which is too small for practical purposes. Accordingly, one aspect of the invention is directed to the optimization of the placement of the user input devices, i.e., the user buttons and knobs which allow the pilot to control the symbolage displayed on the device. According toFIG. 2, a plurality ofpush buttons900 are arranged along the outer perimeter of the display device. In addition, at least oneturn knob910 is set in the bottom corner of the display device, to avoid conflict with the viewing area.Knob910 is then connected via auniversal joint920 to arotary encoder930. Alternatively, a flexible shaft could be used instead of a joint arrangement. The use of the universal joints solves two problems. First, it allows the placement of the knobs to be substantially parallel and proximate to the outer casing of the device. Second, it allows the shafts of the knobs to be placed out of the optical path of the LCD.
• The system of the present invention allows 8.4 square inches of a 3ATI panel, which has 9.56 square inches of possible space, to be used for video display. Thus, about 88% of the screen is utilized. According to the invention, preferably at least 70% (e.g., for a 3ATI panel slot about 6.7 square inches) of the screen is used. More preferably, 75-88% (e.g., for a 3ATI panel slot about 7.2 to 8.4 square inches) is used, or at least 75% (e.g., for a 3ATI panel slot about 7.2 square inches). Even greater advantages are achieved by using at least 80% (e.g., for a 3ATI panel slot about 7.6 square inches) of the screen, or at least 85% (e.g., for a 3ATI panel slot about 8.5 square inches). Accordingly, one embodiment utilizes in the range of about 80% of the screen.
• Operation
• Referring toFIG. 5, the program flow of the present invention will be described. In step700, theprocessor100 receives the sensor signals fromsensor inputs210. This is done as the multiplexor steps through each of the inputs. In step710, themicroprocessor100 polls the user input buttons, to determine the symbolage and various data to be displayed on the screen. In step720,processor100 calculates the required display parameters, e.g., attitude of the plane, compass direction, and other such data based upon the sensed signals and the particular graphical modes selected by the user controls. Insteps730 to750,processor100 calculates any “emergency” parameters, even if they were not selected by the user in step720.
• An example of such a subroutine is illustrated inFIG. 6. For example, assuming the user had the terrain data and G.P.S. and topographical data functions of the device turned off, instep810, the processor would review the sensed G.P.S. data. Instep820, it would receive the flux gate and gyro data. Instep830 it would use the data fromstep810 and820 to calculate the current location and attitude of the plane and its present flight path. Instep840 it would look up the topographical data inmemory410 associated with the location and flight path calculated instep830 and determine the location of any obstacles. Instep850 the processor would determine if any obstacles are in the current flight path. If yes, it would write emergency graphical data to the next buffer to be displayed by the LCD. If no, it would proceed to step860 and determine if any obstacles are located within a predetermined distance of the plane's current location or flight path. If yes, warning data would be written into the graphical buffer to next be painted on to the LCD. For example, if instep850 an obstacle is found to be within the flight path, it may be written to the buffer so as to show up in bright red and flashing on the next screen. If instep860 an obstacle is found within the predetermined location of the aircraft, but not directly within the flight path, a yellow or amber symbol may be displayed on the screen so as to advise the pilot to closely monitor the location of that obstacle.
• In determining whether an obstacle is within the flight path, the system considers the altitude of the obstacle and the plane, as well as the current flight path. For example, if an obstacle is located at 1200 feet elevation, and the plane is currently flying at 6000 feet, a warning would not be issued, unless the plane was in a descending course that would put it on course with the obstacle.
• Referring again to the main program flow ofFIG. 5, instep760 the processor will write the graphical data to the next buffer inmemory420 and instep770 repetitive data is written in thenext plus 1 buffer. Instep780, thenext plus 2 buffer is cleared and instep790 the process is looped back to the beginning and repeated.
• Display Screens
• FIGS. 7A and 7B illustrate representative screens which may be displayed using the present system.FIG. 7A illustrates a 360 degree view with graphical representations of man made obstacles, as well as natural terrain obstacles. The current location of the plane is illustrated by aplane icon1000. The current heading is illustrated as 240 degrees byicon1100 and the current flight course is illustrated byline1200. A natural terrain obstacle is illustrated asicon1300.Natural obstacle1300 has an elevation of 1670 feet, which may be considered dangerously close to the plane's current elevation of 1220 feet. Furthermore, the current flight course may be considered dangerously close to thenatural terrain object1300, therefore an alert would be generated. As a result, for example,alert icon1400, as well asicon1300 itself, may flash in red or amber. In addition, an audible alarm may be sounded. Referring to the same figure, man madeobstacles1500 are represented by inverted “V's” on the screen.
• FIG. 7B is similar toFIG. 7A described above, except it is in “arc” or 90 degree view, thereby only providing the pilot with a forward looking perspective. In addition, other graphical images may be presented on the display. For example, inFIG. 7B anondirectional beacon1600 is illustrated on the display.
• As may be well appreciated by those of ordinary skill in the art any type of navigational display may be presented on the display of the present invention. Accordingly, the above described examples are to be recognized merely as illustrative and not exhaustive of the scope of the invention.
• Construction
• FIG. 8A illustrates an example of an embodiment of the invention for use in a 3ATI slot as used in the invention.FIG. 8B is a partial breakaway of the housing of the embodiment for use with a 3ATI slot with the rear projection system of the invention disposed therein. For simplicity, other components are not shown in the figure.
• While the invention has been described above with particular reference to an avionics display system, it will be appreciated that it may be used in any vehicle display system. In particular, it is extremely well-suited for freight and commercial trains as well as high-speed bullet train systems. Moreover, while the Avionics display has been disclosed with reference to the 3ATI system, it is clearly understood that it may be used in other slot sizes and its applicability is clearly pertinent thereto.

Claims (1)

1. A method of updating a database with data having a predetermined effective date, comprising: (a) providing a computer having a storage media for storing the database; (b) dividing the storage media into at least two sections including a main data portion and a continuation portion; (c) storing initial database data in the main area; (d) during updates, interfacing a maintenance computer with the storage media; (e) using the maintenance computer to compare the new data to be updated with previously stored data in the storage media and determine the differences; (f) only writing the differences into the continuation portion of the storage media, with an associated effective date wherein the computer in operation searches both the main and continuation data and uses the continuation data in lieu of the main data if the effective date has passed.

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