Real-Time Simulation of Point System Having Multidirectional Points as Viewed by a Moving Observer

This invention relates to real-time digital image generation of a gaming area as viewed from a maneuverable viewpoint, and more particularly to such image generation of directional point structures displayed as points of light.

Heretofore, digital image generation (DIG) has been used in architecture and mathematics to display three-dimensional objects. The viewer could maneuver the display to obtain different perspective views, helpful in building the objects or understanding the relationship between parts thereof. However, these systems were basically nondynamic and lacked the realism of real-time maneuvering.

Directional points in these systems have been processed by software. They were treated as separate light for each distinguishable orientation and color. Airport centerline lights are visible in red or green depending on the direction of the approaching aircraft. These lights were software processed as two lights occupying the same position: one red and black light, and one black and green light. For a string of similarly colored lights, the software would compute the relative position of the pilot to the light string and from this divide the light string into two separate strings, of different color, if the relative position required that two colors be presented.

It is therefore an object of this invention to:

PROVIDE A REAL-TIME, REALISTIC DIG display system which processes directional point data rapidly and efficiently;

PROVIDE DIG display system with directional point capability which is simpler, less expensive, more compact and more reliable;

PROVIDE A DIG display system employing a data base including directional points and hardware for determining the visible aspects of the directional points in the perspective of the viewer;

Provide a DIG display system which may be expanded to provide a plurality of window displays having related fields of vision;

provide a DIG display system in which the image data is formatted to colors (including black) for each distinguishable direction;

provide a highly realistic night visual aircraft simulation system which simulates directional lights prominate during night flying conditions;

provide a DIG system in which all of the object data are processed each frame without preselection as a function of the orientation of the observer.

Further objects and advantages of the present invention, and the operation of the night visual system, will become apparent from the following detailed description taken in conjunction with the drawings, in which:

FIG. 1 is a block diagram of the night visual system and peripheral equipment showing data flow relationships;

FIG. 2 is a logic circuit of the translation stage wherein delta data (.DELTA.X, .DELTA.Y, .DELTA.Z) is translated into light source vectors (Vis);

FIG. 3 is a logic circuit of the rotation stage wherein the Vls is multiplied by a rotation matrix in response to the aircraft attitude to provide channel vectors (Vc);

FIG. 4 is a logic circuit of the projection stage wherein Xc and Yc are divided by Zc to project Vc into the X-Y plane to form deflection vector (Vd);

FIG. 5 is a logic circuit of the input logic control which activates the translation stage;

FIG. 6 is a logic circuit of the deflection stage which generates X and Y deflection voltages in response to Vd (Xd, Yd);

FIG. 7 is a pictorial view of a landing field showing the directional lights responsive to each axis; and

FIG. 8 is a detailed logic circuit for directional light logic shown in FIG. 2.

FIG. 1 shows a flight simulation system 10 with night visual capabilities provided by a night visual (NV) system 12. A simulated aircraft 14 is linked to flight simulation computer 16 and NV system 12 through computer linkage 18. Flight simulation computer 16 controls motion system 20 and instrument system 22 of aircraft 14 in response to the pilot's maneuvering action at aircraft controls 24. Additionally, instructors at instructor panel 26 and NV panel 28 may create useful training situations such as engine failure, disabled landing gear, etc. which affect the handling of aircraft 14. NV system 12 is formed by general purpose computer 40 such as Digital Equipment Corporation PDP 11/35, image processor 42, image generator 44, and interface controller 46. Interface controller 46 is provided to control image data flow from GP computer 40 to image processor 42 via a data buffer, to process instructor data from panel 28 to GP computer 40, and to process flight data from aircraft 14 to image processor 42.

GP computer 40 receives flight data, such as aircraft position, aircraft attitude (roll, pitch and yaw), etc. from computer 16. GP computer 40 additionally receives night-time earth data from data base 48 such as landing lights, light strings, environmental lights, beacons, etc., preferably including the intensity, color and size of each light source. Preferably, the aircraft position data is an aircraft position vector Vp extending from the simulated position of aircraft 14 to the origin of the earth coordinate system. In order to simplify conception and data organization, the origin is preferably located proximate the touchdown area of the runway and X axis of data base 48 is coincident to the runway centerline. An updated Vp is supplied each display frame by flight simulation computer 16 as the flight parameters of aircraft 14 change. GP computer 40 combines Vp and the position of certain key light sources (i.e. the first light in each string) from data base 48 for providing a series of initialization vectors Vi to image processor 42. The earth data also includes the relative position of other light sources (delta data) including the rest of the light string (string data). Translator stage 60 in image processor 42 combines the delta data with the appropriate Vi to provide a light source vector Vis for each remaining light source. Rotation stages 62 rotate each Vis by combining it with aircraft attitude data (a 3.times.3 rotation matrix). A different rotation is required for each channel or viewing axis from aircraft 14. Rotation stages 62 provide channel vectors Vc to projection stages 64 which project the three-dimensional Vc into two-dimensional display coordinates or vectors Vd. The data flow through image processor 42 and the mode of operation is controlled by input control logic 66, translation control logic 68 and rotation-projection control logic 70.

Deflection stage 72 within image generator 44 receives the positional portion of the processed image data from image processor 42 and provides analog deflection voltages to CRT display devices 82. Intensity stage 74 receives the color, intrinsic intensity and size portion of the data for controlling the CRT beam voltage, current and focus, The CRT in device 82 is preferably a beam penetration, random deflection tube which allows precise control of spot position, continuous control of spot focus and diameter, and provides at least two phosphors of different colors. Texture stage 76 receives texture portion of the data for controlling the painting by electron beam scanning within display devices 82 and is described in more detail in U.S. patent application Ser. No. 557,543 entitled "Real-Time Simulation of a Point System Having Textured Areas as Viewed by a Moving Observer" filed herewith by Robert L. Peters and assigned to the present assignee.

GP computer 40 has an in-core, buffer memory which contains all the image data required by the current frame. In the present example the in-core buffer is 16 bit by 1024 boards and contains all of the light points in data base 48. Software clipping may be employed for narrowing the software field of view and eliminating points not visible to the pilot due to aircraft orientation. In the present example, logic clipping is employed in projection stage 64. Image data is identified by code bits and by location in the buffer format. Fixed data such as Vi, delta data, string data, most CIF data, is entered into the proper address and bit place within the core buffer immediately from data base 48. Flight data (Vp and rotation matrix) is entered from flight simulation computer 16. Time-dependent data such as revolving bicolor airport beacons, hazard beacons, blinking obstruction lights, landing approach strobe, fog and cloud effects, are calculated by computer 40 and entered into the incore buffer. Other special training effects such as ground traffic, other airborne traffic, air-to-air refueling, mobile emergency equipment, or simulation of an aircraft carrier landing site may be programmed in via GP computer 40 or manually entered through instructor panels 26 and 28.

When the in-core buffer is completed, the entire contents are transferred to a 16.times. 1024 storage medium such as a hardware RAM buffer 204 in interface controller 46. Controller 46 processes the 1024 sixteen bit words sequentially to image processor 42 and GP computer 40 simultaneously assembles an in-core buffer of the next frame. RAM buffer 204 may be formed by sixteen 1 bit by 1024 bits random access memory (93415 Fairchild).

Initialization of each initial point requires four words for each dimension X, Y and Z, a first transfer code word, a 16 bit data word, and second transfer code word and an 8 bit data word. Twelve words are required to process an initial to 24 bits of resolution (23 data bits plus a sign bit). The LSB is 3/4 of an inch to eliminate detectable jumping of the scene from frame to frame. A new Vp is calculated by FS computer 16 each frame and the round-off error in the LSB of Vp causes the entire earth coordinate system to jump a ground distance equal to the LSB. This interframe displacement is minimized and rendered undetectable to the pilot by providing initial point resolution to the 3/4 inch level. The MSB of initialization data is 524288 feet. The gaming area of data base 48 is a cubic volume +524288 feet on an edge.

A single word of CIF data is processed to establish the light source characteristics of the first point, and then delta data is processed point by point. Delta data for each set of noninitial points is formatted in RAM buffer 204 to minimize data changes between points. Many lights in a set have common CIF data (color, intrinsic intensity. These delta light points may be processed sequentially without a CIF updating word. A string of horizontal lights parallel to the X axis of identical color and intensity may be processed by a single word of delta data for each light to define the change in position along the X axis (delta Y being zero). In, in addition, the lights are equally spaced along the X axis, then the entire string of lights may be processed by a single word of string data defining the number of lights in the string. The image data may be formatted in this manner to minimize data processing time. Further, optimum formatting will minimize the cumulative ballastic response time required for each frame. That is, sequential points are adjacent rather than remote to minimize electron beam traversing time; and lights of the same color, intensity and size are processed together because of the time required to change the penetration, current and focus of the electron beam.

Each 16 bit word in the RAM buffer has three code bits followed by 13 data bits. The code bits control the next operation of image processor 42. The data bits contain X, Y or Z initialization data, delta data, transfer data, scale color and intensity data, or the number of lights in a string. There are two exceptions to the three MSB code format: (1) Each data word containing a transfer code is followed by a 16 bit data word (no code bits) and (2) nine rotational matrix components are transferred in a block.

The following is a list of code descriptions for bits 15-13 and the data content for bits 12-0 for the data format in RAM buffer 204 of controller 46. ##STR1##

The code (000) causes the X increment (delta X) to be loaded into the delta X register 210 of translation stage 60. ##STR2##

The code (001) causes the X increment (delta X) to be loaded into the delta X register 210 and also starts the operation of translation stage 60. ##STR3##

Similar to INX. An IZC can be provided with a larger code base. However, in a night visual airport application, vertically stacked lights (delta X= delta Y= 0) are unusual. ##STR4##

Defines the number of lights in a string of uniformly spaced lights of the same color and intrinsix intensity. The spacing between lights in a string is defined by the delta X, delta Y, and delta Z codes immediately following the STG code. ##STR5##

Defines the color (c) and intrinsic intensity (i) of the light source.

c= color codes, positive and negative relative position for bidirectional light sources which are disclosed in more detail in the Section titled "Preferred Embodiment of Directional Light".

i= intensity code

f= options control code ##STR6##

Code (111) transfers the next data word to the window or channel specified by cn (three bits) and the data register specified by the data address field, d (three bits). The word following a transfer code is an initialization data without any code bits.

cn= The window channel to which the data is being directed.

d= Destination of data transfer. The source is the data word immediately following the XFR. i= Initialization Flag. A 1-bit in this bit position indicates a data transfer for initialization, as shown in the following table.

c= Channel flag. A 1-bit in this bit position indicates that the data transfer is channel-dependent, thus requiring channel select specification in cn.

Each stage of NV computer 12 is shown in detail in FIGS. 2 through 6. Preferred embodiments are diclosured at the detailed logic level. Each component is described by function, input-output characters, or conventional nomenclature to enable one skilled in the arts of simulation, digital design, and computer programming to practice the invention. The components are additionally designated by the manufacturer's IC type number from the following integrated circuits data books:

Texas Instruments Incorporated, "The TTL Data Book for Design Engineers," First Edition, Copyright 1973.

National Semiconductor Corporation, "Digital Integrated Circuits," January 1974.

Advanced Micro Devices Inc., "Advanced Micro Devices Data Book," Copyright 1974.

unless otherwise specified. Further, many inverters are employed throughout NV system 10 for buffering signals with multiple loads. These buffer inverters are type 74S04 unless otherwise stated.

FIG. 2 shows translation stage 60 of image processor 42 and a portion of controller 46. Controller 46 receives image data in sequential order from computer 40 at an input 202 of a random access memory 204. The image data is arranged by frame in data blocks M bits wide and N words long. In this embodiment the frame block is 16 bits X, a multiple of 1024 words, and generates about 2000 light points making up the scene content of a single 1/30 second frame of CRT device 82. RAM 204 handshakes with a core memory in GP computer 40 to reproduce each frame of data. Image data is sequentially transfered from RAM 204 through a buffer register 206 to a light point data bus 207 and a texture data bus 208 in response to load pulses from interface controller 46.

RAM 204 may be formed by 16 1024 bit RAMS (93415 Fairchild) connected in parallel for holding the frame data. Register 206 may be formed by four 4 bit registers (74S175).

Frame data is coded as described in section II to enable one of six input registers 210, 220, 240, 250, 260 or 270 connected to light source data bus 207. X coordinate data for light sources in data base 48 is coded either INX(000) or IXC(010) and is loaded into a delta X input register 210 in response to load pulses from input control logic 66, preferably in concert with clock signals from a sync clock gate. Initialization vector data (Vi) follows a code XFR (111) and loads into X-Mux/Reg 211 on select from translation control logic 68. Initialization vectors load through bypass lead 212 to avoid delta X adder 213.

Initialization vectors position land mark points in data base 48 such as the beginning of light strings. After X-Mux 211 has been initialized, the delta X data of subsequent points in the string is loaded into input register 210 and passes through X adder 213 where each delta X is added to the X coordinate of the previous light point in the string generating the Xls portion of the vector Vis (Xls, Yls, Zls) for each light source. Mux register 211 holds these previous coordinates and cycles them back to adder 213 on lead 215 for updating.

A normalization register 216 loads the updated X coordinate data, and left shifts leading zeros or ones for negative numbers in response to translation control logic 68. The first difference between most- and second-most-significant bit in normalization register 216 generates a normalization complete signal back to translation control logic 68 on lead 217. Normalization complete in any of the X, Y or Z normalization registers 216, 226 or 246 stops the normalization process of all the registers insuring that the normalized points maintain consistent dimension units and remain on the same line of vision as viewed on display 82. Normalization has the advantage of reducing the 24 bit initialization data into 16 bits of normalized data by eliminating either leading zeros or ones for negative numbers. The data load is reduced to 66% with negligible loss in position resolution. Logic control 68 then loads the normalized data into an output buffer register 218 which temporarily holds the data while X data for the next light point is accumulated.

Input register 210 may be formed by two 6 bit buffer registers (74S174) and one 4 bit buffer register (74S175) for accommodating the 13 remaining data bits. The three MSB of the 16 bit input on bus 207 was consumed by input code. These three bit places are now used in register 210 to propagate the sign bit to fill the 24 bit places of adder 213 input. Delta X data is a short distance for which 13 bits have been allotted, while initialization data is generally a greater distance and has been allotted 24 bits. Adder 213 may be formed by six 4 bit binary full adder (74283). X-Mux 211 may be formed by six quadruple 2 input multiplexer with storage (74298). Normalization register 216 may be formed by three 8 bit shift registers (74199). Buffer 218 may be formed by four TRI STATE quad D flip-flops (DM 8551 National).

Y coordinate data is coded INY(010) or IYC(011) for loading into delta Y input register 220. Y data is processed through delta Y adder 223 and Y-Mux 221 as described above with respect to X. Y data is left shifted in normalizer 226 and loaded into Y buffer 228. Z coordinate data is coded INZ(100) and is processed through the corresponding components 240, 243, 241, 246 and loads into Z output buffer 248. Preferably, both Y and Z components are constructed and operate identically to the X components to provide the Yls and Zls components of Vls.

Output buffers 218, 228 and 248 operate in a TRI STATE configuration to output light source vectors (Vls) on lead 249 to rotation stage 62 in response to an output enable signal from translation logic control 68. Only one output buffer may be enabled at one time which prevents mixing of X, Y and Z data.

Data on bus 207 concerning the number of light points in a string is coded STG(101) and through input logic control 66 enables a string counter 250 to load. The string data is held in counter 250 until a count pulse is received from logic control 68. Counter 250 then counts down through a zero detect circuit 252 providing a string complete signal back to translation logic control 68. Counter 250 may be formed by two down counters (74193). Zero detect 252 may be formed by two NOR gates (7425) and one NAND gate (74S00) as shown.

Data on bus 207 concerning color, intensity and flags is coded CIF(110) and through logic control 66 enables a CIF register 260 to load the CIF data. Register 260 holds the CIF data while coordinate data is processed on line 262 through translation stage 60 and rotation stage 62. Register 260 then loads into another CIF register (460 in FIG. 4) which holds the CIF data while coordinate data is processed through projection stage 64. The CIF data is then forwarded to image generator 44. CIF register 260 may be formed by two 6 bit registers (74S174) and one 1 bit flip-flop (74S74).

The 13 bits following code XFR(111) are additional code bits for identifying initialization vectors, rotation data, and texture data which are contained in the subsequent words. The XFR additional code is loaded into a transfer register 270 and processed into input control logic 66 to control the flow of light point data on subsequent word. Register 270 may be formed by two 6-bit registers (74S174) and one 1-bit flip-flop (74S74).

Texture data on bus 208 specifies painted (or greater-than-light-source-size) areas which are colored by electron beam scanning in the CRT displays.

The channel flat bit (XFR code 111, bit 11) indicates the window or viewing axis of the data. Each view axis or perspective requires a separate rotation stage 62, projection stage 64, image generator 44. However, the two front windows of aircraft 14 have very similar perspectives and may share a common channel which inputs to both devices 82 left and 82 right. Device 82, if implemented, requires a separate channel which is identified by the flag bits.

FIG. 3 shows rotation stage 62 of image processor 42 which multiplies the Vls at input 249 by a rotation matrix H provided on data bus 207 to produce the rotated vector or channel vector Vc (XcYcZc): y

The rotation matrix H is developed from yaw (.psi., left), pitch (.theta., down) and roll (.phi., right) motions. Assuming that the order of rotation is .psi. followed by .theta. followed by .phi., the matrices for the separate rotations from translated to rotated pilot eye or channel coordinates are as follows: ##EQU1## The composite matrix H describing this rotation is given by the matrix product

the aircraft attitude matrix H is constant for each frame and is therefore computed only once per frame for each channel.

A multiplier multiplexer 310 receives 16 bit Xls, Yls or Zls data on lead 249 and sequentially outputs the data in four 4 bit parts (plus one carry place) to a multiplier register 320 in response to select signals from control logic 70. Register 320 receives the multiplexed 5 bit data in response to load signals from control logic 70, and simultaneously outputs to a flow-through multiplier array 330. The nine elements of rotation matrix data (H) from bus 207 load into a 16 word X 16 bit/word RAM 340 in response to control logic 68. As required during the rotation calculation, control logic 70 addresses RAM 340 and loads particular elements into a multiplicand register 350 which simultaneously outputs to array 330. Array 330 is a 16 bit by 4 bit multiplier and outputs to a product register 360 the product of a given matrix element times one of the 5 bit parts from register 320. Feedback line 362 causes the 16 MSB of these partial products to be combined to form the product of one element-coordinate product to product register 360. Four multiplication cycles are required for each position input data from 249. Accumulator register 380 holds the first element-coordinate product (18 bits) and adds the remaining two through adder 370 on feedback line 382 (18 MSB) as the remaining products become available from product register 360. Three cycles of accumulator 380 are required to form a single rotated coordinate coefficient (16 bits) at rotation stage output 384.

Multiplier MUX 310 may be three dual 4-1 MUX (75S153) connection parallel with one 4 bit input surplus. Multiplier register 320 may be one 6 bit register (74S174). Multiplier array 330 is eight flow-through multipliers (Am25505 Advanced Micro Devices) in 16 bit.times. 4 bit configuration. RAM 340 may be four 16 word memories (74S189) with 5 words surplus. Multiplicand register 350 may be two 6-bit registers (74S174) and one 4-bit register (74S175) connected in parallel. Product register 360 may be three 6-bit registers (74S174) connected in parallel. Adder 370 may be four 4-bit binary full adders (74283). Accumulation register 380 may be three 6-bit registers (74S174).

FIG. 4 shows projection and clipping stage 64 of image processor 42 which projects three-dimensional vectors Vc (Xc Yc Zc) from stage 62 into a two-dimensional deflection vector Vd containing deflection data Xd and Yd used by image generator 44 for positioning the electron beam in CRT displays. This projection is accomplished by dividing Xc and Yc by Zc through the binary division nonrestoring technique (described in "Digital Arithmetic-- I" by Y. Chu, pages 39-43). Z/2 register 410 loads the divisor Zc/ 2 and Mux/Register 420 selects and loads the dividend Xc/ 2 or Yc 2 in response to control logic 70. The inputs to registers 410 and 420 are right-shifted by one digit to divide the Vc data on line 394 by two. Arithmetic logic unit ALU 430 then receives the dividend through a shift return loop 432 and adds or subtracts Zc 2 thereto in response to a.+-. function from logic 70. The dividend.+-. Zc 2 term is loaded into Mux 420, returned to ALU 430, and then combined with another.+-. Z/2. The 16 bit output of ALU 430 is slew wired with respect to the 17 bit input to Mux 420 causing a division by two right shift. The binary division by Zc requires 12 cycles for each X projection and each Y projection. The Xc/Zc and Yc/Zc quotients are generated one bit at a time, MSB first, by comparing the sign bit (MSB) of Zc with the sign bit of the partial remainder with Mux 420 through sign gate 436. The quotient bits individually enter quotient register 440 and are left-shifted by control logic 70. Zc is loaded into renormalization register 450 and is right-shifted by control logic 68 the same number of places as were left-shifted in normalization 246 in translation stage 60. Color, intensity, and flag data on line 262 is loaded into CIF register 460 in response to control logic 68.

The contents of registers 440, 450 and 460 plus texture data on line 208 pass through multiplexer 470 and appear on output 472 in response to select signals from control logic 70. Data on line 472 is serially loaded into format registers 474a-p by decoder 476 in response to LOAD FORMAT REGISTER and FORMAT ADDRESS from control logic 68. Output 472 may interface with a remotely positioned image generator 44, preferably through suitable line driver devices such as DM8830s. Clipping circuit 480 compares the sign bits of Zc/ 2, (Xc or Xc )/2, and the contents of ALU 430 to determine if the light point being processed is within the field of view of the associated window or channel. The field of view may be logic clipped to any desired size; however, a square field of vision (53.14 degrees by 53.14 degrees) along the X and Y dimension is preferred because the arc cotangent of 26.57 degrees is two. Thus, if (Xc or (Xc)/Zc is less than two as determined by gate 482 and 484, the light point is within the logic field of view and enable flip-flop 486 provides a Load Enable signal to new point register 490 through new point gate 492 which, in junction with LOAD NEW DATA POINT from control 70, forwards the content of register 490 to image generator 44.

Gate 482 compares the sign bit of (Xc or Yc)/ 2 initially in register 420 to the sign bit of (/Xc/ or /Yc/)+ Zc /2 initially in register 420 to the sign bit of (/Xc/ or /Yc/)+ Zc 2 initially in register 430 to determine if (Xc or Yc) is greater or less than -Zc/ 2. All points having Xc or Yc data greater than -Zc/ 2 are outside the field of view and are not forwarded to image generator 44. The output of gate 482 is inverted and compared with the sign of Zc/ 2 by gate 484 to inhibit all -Zc data. Gate 484 also inhibits all data within a given distance from aircraft 14 through one detector 488 which monitors the ten MSBs of Zc to inhibit all data with a Zc value of five places or less.

Z register 410 may be three 6-bit registers (74S174). Mux/Register 420 may be five quadruple, 2-input multiplexers (74298) with storage. ALU 430 may be four 4-bit flowthrough arithmetic logic units (74S181). Sign gate 436 may be an exclusive OR gate (74S86). Gate 484 may be a three-input NOR gate (7427) with output inverted by a three-input NOR gate (7427) having two unused inputs grounded. Enable flip-flop 486 may be a JK flip-flop (74S112) with presetting and resetting gating circuitry responsive to control logic 70. One detector 488 may be two 5-input NOR gates (74S260) and one 2-input AND gate (74S08) having a high level output in the absence of ones. Register 474 and 490 may each be twenty-eight 6-bit registers (74174) operated in twelve pairs. Decoder 476 may be a 4-to-16 decoder (74154) with two surplus outputs. Gate 492 may be an AND gate (74S 08).

The field of view cross-section is determined by the shape of each simulated window and may be controlled in many ways, i.e. software clipping by GP computer 40, logic clipping by image processor 42, electronic clipping by analog circuits in image generator 44, or optically clipped in CRT device 82. Alternatively, the dimensions of the effective display may depend on more than one form of clipping. In the present case a square pyramid of vision is established clipping circuit 480; however, a cone of vision may be established by providing a round CRT.

FIG. 5 shows the detailed logic circuitry for input control logic 66. Image data bus 207 supplies a three bit decoder 510 with the three MSB of codes 15, 14, and 13 which are decoded into the eight code outputs for loading the six input registers of translation stage 60. The codes are described in more detail in Section VI, Data Format. Output zero INX(000) and output one IXC(001) are ORed through NAND gate 520 for loading X coordinate data into delta X input register 210. Output two INY(010) and output three IYC(011) are ORed through AND gate 522 for loading Y coordinate data into delta Y input register 220. Output one IXC and output three IYC are ORed through NAND gate 524 to set a compute flip flop 526 into the compute mode. Compute flip flop 526 outputs to translation control logic 68 to initiate a compute operation. Output four INZ(100) loads Z coordinate data into delta Z input register 240. Output five STG(101) loads string length data into string counter 250. Output six CIF(110) loads color-intensity-flag data into CIF input register 260. Output seven XFR(111) loads additional code data into transfer register 270 and sets XFR flip flop 528 into the XFR mode. Flip flop 528 outputs to translation control logic 68 to indicate additional decoding is required. Sync gates 530 are preferably provided for syncing the loading pulses to translation stage 60. A Set and Decode Enable signal from translation control logic 68 clocks flip flop 526 and 528 through a NAND gate 540 and strobes three bit decoder 510 to initiate operation of input control logic 66 after each operation of translation control logic 68. A Clear Enable signal from translation control logic 68 clears flip flops 528 and 528 through a NAND gate 542 at the end of each operation. Flip flops 527 and 528 are synced by clock pulses through gates 540 and 542.

Input control logic 66 additionally decodes bits 12-4 from transfer register 270. Initialization bit 12 and channel bit 11 output into a gate network to provide:

Matrix Data signal to translation control logic 68 through AND gate 550 when bit 12 and bit 11 are true.

Enable All (-) signal to channel gates 570 through AND gate 552 when channel bit 11 is false.

Format Data signal to translation control logic 68 through AND gate 554 when bit 12 is false and bit 11 is true.

Load Format Register signal to projection stage 64 through NAND gate 556 when bit 12 is false, bit 11 is true, and an Enable Format signal from translation control logic 68 is false.

Destination Enable signal to destination decoder 572 through AND gate 558 and NAND gate 560 when bit 12 is true, bit 11 is false, and the Enable Format signal is false.

Channel data bits 10, 9, and 8 from transfer register 270 are additionally decoded into one of eight window perspectives or channels by a channel decoder 574. Decoder 574 outputs into eight channel gate 570 which are ORed with Enable All from gate 552. When Enable All is true, a single gate 570 is enabled by channel data to process rotation matrix data unique to that channel. When Enable All is false all gates 570 are enabled to process image data required by all channels. Channel data bits 7, 6, and 5 from transfer register 270 are additionally decoded by destination decoder 572 to one of six destination gates 576 during initialization operation for providing load signals to the appropriate translation accumulator 214, 224, or 244. An Enable All signal from translation control logic 68 enables all translation accumulators to load simultaneously during delta data or light point operation.

Decoders 510, 572, and 574 may be three-dual, two-line to four-line decoder (74155) connected in a three-line to eight-line configuration. AND gates 520, 522, 550, 552, 558, and 576 may be two input AND gates (74S08). NAND gates 524, 530, 540, 542, and 570 may be two input NAND gates (74S00). NAND gates 556 and 560 may be three input NAND gates (74S10). AND gate 554 may be a three input AND gate (74S11). Flip flops 526 and 528 may be one-half of a four bit register (74S175).

The following flow chart description discloses the operation of input/translation control logic 68. The operation includes STEPS 0-34 which are clocked in the order listed, and DECISIONS A-O. Control logic has three internal phases of operation (I, II, III) which occur as indicated. Numerous hardware circuits could be designed to perform these sequences generating the desired control signals to translation stage 60 and control logic 70.

The following flow chart description discloses the operation of rotation-projection control logic 70 similar in approach to Section XII.

FIG. 6 shows X deflection generator 604, Y deflection generator 606 and CRT unblanking circuit 608 which receive digital deflection data Xd and Yd from projection stage 64 and generate analog X and Y deflection voltages and unblank periods for CRT display devices 82. In deflection generator 604, Xd data from new point register 490h enters X A/D converter 610.

The MSB of Xd is inverted from the 2's complement format of register 474h into the binary format. Operational amplifier 620 receives the analog output of A/D 610 which is summed with X VECTOR GENERATOR signal. Amplifier 620 also receives X OFFSET signal through scaling resistors 622 for positioning the CRT display within the rotated data window of stage 72. The analog output of amplifier 620 is preferably limited to .+-. 5 volts by clipping network 630 which defines the X dimension of the CRT display. The .+-. 5 ma output of amplifier 620 is preferably increased to .+-. 100 ma by power driver 640. X deflection voltage at output 642 drives the deflection circuits of display device 82. Y deflection generator 606 is identical in structure and operation to X generator 604.

A/D converter 610 may be a 12 bit binary unipolar device (AD562 KD-BIN) from Analog Devices which provides a feedback resistor in feedback line 624. Amplifier 620 may be a feedback operational amplifier (NE531) from Signetics in summing configuration. Resistors 622 are preferably 10,000 ohms each. Clipping network 630 may be two 5.1 volt zenor diodes (1N751A) connected in reverse polarity and in back-to-back configuration with two switching diodes (1N914). Power driver 640 may be a suitable output amplifier capable of driving .+-. 5 volts at a load current of .+-. 200 ma at a maximum full output frequency of 3 MHz, such as power driver (model 9824) by Optical Electronics Incorporated.

Unblanking circuit 608 generates CRT UNBLANK to CRT devices 82 causing the electron beam to strike the CRT phosphor simulating a light point in data base 48. A CRT blank period or beam stabilization increment between each point activation is determined for each new light point and is sufficient to permit acceleration, movement and deceleration of the electron beam. First, Xd and Yd load into increment decoder 650. Decoder 650 retains the previous data point Xd and Yd, and by systematic comparison to the new light point Xd and Yd, identifies which is greater, delta Xd or delta Yd. Then decoder 650 enters a "1" into timing register 680 along one of eight outputs in accordance with the magnitude of the identified delta. Clock 682 then progressively left shifts the "1" to the MSB activating unblank timer 684. The number of clock pulses required is greater for larger deltas allowing time for the electron beam to move to the new light source position. Unblank timer 684 determines the exposure time during which the electron beam activates the CRT phosphor. Potentiometer 686 is provided for adjusting the unblank period to accommodate the video gain of CRT device 82 and for particular CRT phosphors. A five microsecond unblank period is preferred for the Kratos 25" beam penetration display CM 325S1. Unblank logic 686 combines the output of unblank timer 684 with DEFLECTION ENABLE from control logic 70 to provide CRT UNBLANK to CRT device 82.

Busy logic 688 inhibit data processing through new point register 490 by a BUSY signal to control logic 70 between the loading of each new point into image generator 44 and the termination of the CRT UNBLANK period for that new point. BUSY also inhibits clock 682 during the same period.

Deflection clear circuit 690 limits the time period during which the deflection coils in CRT device 82 will be required to maintain any electron beam position. After expiration of the maximum deflection period, which in the present case is about eight milliseconds, clear circuit 690 provides DEFLECTION CLEAR to control logic 70. Clear circuit 690 prevents damage to the deflection coils during startup, shutdown, or system malfunction which might otherwise cause maximum deflection current to needlessly flow through the coils beyond the ratings of the coils.

Increment decoder 650 and the operation of BUSY is shown in more detail in patent application Ser. No. 642,645 entitled "Real-Time Simulation of a Point System Having Coordinated Data Flow as Viewed by a Moving Observer" and filed on Dec. 19, 1975 by R. G. Nielsen and assigned to the present assignee.

Timing register 680 may be an 8-bit register (74199) with J and K inputs at + 5 volts and clock-inhibit grounded.

Clock 682 may be any oscillator having a three-dimensional period.

Unblank timer 684 may be a oneshot (74121) using the A1 and A2 inputs and an external 20K ohm timing resistor.

Unblank logic 686 may be an AND gate (7410) and a 50 ohm driver (7440) connected in series therewith.

Busy logic 688 may be a flip-flop (7474) set by LD NEW DATA PT and clocked by the inverted output of timer 684, with D input grounded.

FIG. 7 shows an airport runway 710 positioned within a stationary XYZ coordinate system 730 with a string of centerline lights 720M marking the midportion of runway 710, bidirectional lights 720TD marking the touchdown portion of runway 710, and bidirectional lights 720E marking the end of runway 710. Centerline light string 720 is coincident with axis 730X of coordinant system 730; and each bidirectional light is orientated traversely of axis 730X establishing a color threshold plane X=C perpendicular to axis 730X. C is the X coordinate of the bidirectional light. Lights 720TD and 720E and X axis responsive. Simulated aircraft 740 is shown approaching runway 710 with the cockpit at the origin of moving XYZ coordinate system 742. During a normal approach axis 742X, 742Y and 742Z of moving coordinate system 742 are generally parallel to axis 730X, 730Y and 730Z respectively of stationary coordinate system 730. During the approach of aircraft 740 directional centerline lights 720TD are visible as green lights in the front display 82 of craft 740, lights 720M are visible as white lights, and lights 720E are visible as red. Lights 720TD and 720E are bidirectional and are visible in the reverse color pattern to accommodate aircraft landing in the opposite direction on runway 710. As lights 720TD pass directly under aircraft 740 their visible color changes to red; lights 720M do not change color, and lights 720E change from red to green. That is, when Xls. coordinate of each bidirectional light (in aircraft coordinate system 742) is positive that light is green and when Xls is negative, that light is red. In the case of aircraft 740 lights 720TD and 720E are clipped from the field of view by projection stage 64 just prior to changing color. However, lights 720 may be visible from the side display of aircraft 740, especially if aircraft 740 lands to one side of the centerline axis 730X.

A second aircraft 750 is shown taxiing along adjacent runway 752 which is at an angle with respect to center axis 730X of runway 710. The coordinate system 754 for aircraft 750 is translated from ground coordinate system 730 by position vector Vp of aircraft 750 without rotation. The axes of moving system 754 are generally parallel to the corresponding axes of ground system 730. The color of each directional light is a function of the sign of the X coordinate Xls. When Xls is positive that light is green; when Xls is negative that light is red. Centerline lights 720 are visible in the front display of aircraft 750, and lights 720TD and 720E still appear as green or red, and will change color as the origin of translated moving coordinate system 754 passes through the color threshold plane for each light. By orientating the X axis of stationary coordinate system 730 to be coincident to, or merely parallel with, centerline lights 720, the color of each light 720TD and 720E is determined by the sign of the X coordinate of that light as translated into the moving coordinate system by translation stage 60 prior to rotation by rotation stage 62.

Y responsive bidirectional light strings 760 are shown on runway 762 parallel to axis 730Y. Lights 760 establish a Y=C color threshold plane, and their color is dependent on the sign of Yls in translated unrotated coordinate system 750. Light 780 on top of building 782 is one color responsive, and establishes a color threshold plane Z= height of building 782 (assuming light 770 to be mounted at roof level). Light 780 changes from on (any color) to off (black) as viewed from descending aircraft passing through the height Z plane.

FIG. 8 shows XY directional logic 264a for converting the sign bit of Xls of lights 720TD and 720E and Yls of lights 760 into one of two colors C- or C+. XY Mux 810 receives both SIGNX and SIGNY from the MSB of X Mux 211 and Y Mux 221, respectively, and selects either X or Y as the color sensitive axis in response to XY Flag bit, a "0" or "1" in the MSB of CIF register 260. CIF register 260 contains 3 bits of C- and three bits of color C+ provide a selection of eight colors (or shades of colors) including black for each side of the color threshold plane. The proper color C is selected by color Mux 820 in response to a select signal from XY Mux 810. The selected color C is loaded into CIF register 460 in response to a load signal from control logic 68.

Z directional logic 264b is responsive to SIGNZ of light 780 from Mux 241 (which is loaded into the MSB of CIF register 460) and Z Flag from the second MSB of registers 260 and 460. Z code indicates whether or not the light being processed is Z axis responsive. Z gate 830 combines SIGNZ with Flag Z and outputs to three intensity gates 840. Three bits intensity data input to intensity gate 840 to provide eight intensity levels out to intensity stage 74. Zero intensity (black) may be introduced by the "000" code of the intensity code bits. Black may also be introduced by a "0" from SIGNZ and Z code for a light which is black in one direction.

XY Mux 810 may be three NAND gates (74S00) connected in multiplexer configuration using the Q and Q bar outputs of the flip-flop forming the MSB of CIF register 260. Color Mux 820 may be three sections of one Quad two input Mux (74S157). Gate 830 may be a NAND gate (7400) and gates 840 may be AND gates (7408).

Multiaxis directional lights responsive to XZ or YZ such as bidirectional landing lights on the deck of an aircraft carrier may be processed by logic 264. An XYZ responsive light requires a Flag bit for each axis and, if desired, a color data for Z. An XYZ light has a selection of colors separately activated for each quarter hemisphere by XYZ sign data.

Runway 790 which is not parallel to either axis 730X or 730Y may incorporate bidirectional effects by a data rotation operation performed by software in GP computer 40 or additional hardware in image processor 42.

It will be apparent to one skilled in the art that the objects of this invention have been accomplished by processing image data, including directional point data, through the system to a display device. Directional flag bits are provided to define the character (color, intensity, etc.) and orientation (X, Y or Z responsive) of each directional point.

The foregoing specification is for illustrative purposes only and modifications may be made in the disclosed embodiment without departing from the scope of the invention. For example, an entire face of an object may have directional characteristics which are defined by the directional data and painted into the CRT display. The reflective properties of a surface or the nature of the illumination may create directionally dependent shading. Further, the directional characteristic may relate to color, intensity, on-off, occulting or other considerations.