DE2049482A1 - Information display device - Google Patents

Description

Patent attorneys

Dipl. Ing. C. Wallach -8. OCT. 1970

Dipl. Ing. G. Koch
Dr. T. Haibach

8 Munich 2 ₁₂ 87O - Fk / St.

Kiufingeratr. 8, part. 240275

Sperry Rand Corporation, New York / Ü3A

Information presentation device

The invention relates to information display devices for vehicles and in particular on devices for displaying the plug position and the plug heading information for aircraft on a cathode ray tube. The plug location information not only includes information that relate to the longitudinal inclination, the transverse inclination and others, but also on the position of the vehicle in relation to a course over Orund, for example an airway ("path in the sky") or especially on a runway of an approached one Airfield * Bs is absolutely necessary that such position information is always correct to the viewer Perspective is represented. If the representation of such information by a conventional horizontal raster scan, as it is used, for example, in normal television, is to be given, complicated electromechanical elements must be used or a digital computer with memory capabilities can be used to ensure proper perspective if that Vehicle inclinations, bank slopes, and heading changes is subjected.

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An information display device according to the invention employs a cathode ray tube with helical or polar raster scanning, the image of the beam making a continuous helical path across the image surface of the tube. This can make getting a proper perspective too substantially simplify at any time and also make it possible to subdivide the representation of the information between the outwardly running and the backward running paths of the scan.

The invention is explained in more detail below with reference to the exemplary embodiment shown in the drawing. In the drawing show:

Fig. 1 is an illustration of a representation appearing on the screen of the cathode ray tube of the apparatus;

Flg. 2 shows a thematic block diagram of a polar raster generator;

FIG. 5 is a partially illustrated block diagram

Circuit diagram of a voltage controlled symmetrical limiter;

Fig. 4a is a detailed circuit diagram of the polar raster generator and 4b tors;

Fig. 5 is a block diagram of the horizontal and roll generator;

Figure 6 is a detailed circuit diagram of the horizon and bank generator j

Figure 7 is a graphical representation of the waveform relationships from Fig. 5;

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Flg. 8 is a block diagram showing the provided to the representation Roll and pitch information showed

Fig. 9 shows the appearance of a representation for any pitch and roll input signal;

10 shows the formation of the runway display;

11 shows a graphic representation of the symmetrical expansion of the pulse width T? via the ^ * «, corresponding time phase j

Flg. Figure 12 is a block diagram of a portion of the runway generator;

Fig. IJ is a graph showing the relationships of the wave fronts from Fig. 12;

14 is a display showing line diffraction, where r is variable and S is constant;

Fig. 15 is an illustration showing line generation where r is constant and f is variable;

16 is a graph and display showing the Show creation of a straight line on the polar raster;

Figure 17 is a block diagram of a portion of the runway generator;

18 is a representation of the runway image, the shows the blocked areas;

1 0 9 8 1 G / 1 6 1 G

Pig. 19 a detailed circuit diagram of the runway « Perspective generator ^ s;

Fig. 20 is a display showing the parallel ground planes » Grid line forming varsfcärlcten area

Pig. 21 is a block diagram AEAS Genarators for d: le pai * all € ile Orundebenon grid line;

Pig. 22 is a graph showing the relationship dor wave form of Fig. 21;

Pig. 23a a detailed circuit diagram of the Örundebenen-Personpalc- and 23b tivegeneratorsj

Fig. 24 is an illustration of the reinforced area having a converging oriindplane grid lines form j

Fig. 25 is a schematic Elockach map of the generator for the converging ground plane grid line i

Fig. 26a representations of the formation without and with transverse inclination and 26b input signals j

FIG. 27 shows an illustration which shows an additional, for the rotation of the grid center around the display center shows required distraction;

28 is a block diagram of the xy0 coordinator j 29 is a detailed circuit diagram of the xy0 ~ coordinator;

Fig. 30 is a circuit diagram partially shown in block form of the absolute value circle;

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31a include a representation of the flight heading bar and 31b and the center point "Bezufesskreüzes and the associated- · gene deflection voltages;

Fig. 32 is a block diagram of the flight control ^ course bar and Mid-point reference circuit i

5 "ig» 33a detailed circuit diagrams of the I? Lüg ~ control: r.'kursbalken- and 33b and mid-point Besugs-SchsUungi

34 is a composite block diagram of the attitude control and flight control course display system according to FIG Invention.

The present invention provides according to FIG. 1 a constant, analog flight attitude display 10 for an assumed flight situation, in which the following information is presented on the screen of a cathode ray tube (CRT) 11 v? lrds

1. Horizon 12

2. Aircraft roll or cross inclination angle 0

3. Longitudinal elongation θ

4.! Runway 13 in a one-point perspective suit changeable Position and size (a, b, / «, ^ χ)

5. Heading error χ (when the runway is not in use)

6. Orundebenen-Oltter 14 in perspective

7. Horizontal and vertical flight direction bars 15 and 16, the by e or g compared to the

8. Horizontal and vertical positions of the center reference mark 17 are displaceable.

The letters listed above represent the changeable ones Parameters of illustration 10.

The illustration 10 to be described uses a novel method for generating the position information on the cathode

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Beampipes (KSR) 11. The display inputs © are bi-polar Analog voltages that each of the parameters according to Pig. I ent « speak. The image change on the K3R 11 depending on an input is automatic without the use of electromechanical Parts, a digital computer or some kind of storage device in perspective. The image is refreshed about 60 times a second * without this an external synchronization is required ;, this simplification is possible by using a polar or spiral raster scan instead of the usual horizontal raster scan borrowed. With this simplification, an internal, itity-modulated Ray from the center and spirals outwards. After scanning the entire image area of the KSR the beam is returned to the center and the scan is repeated. The image is created by modulating the electron beam intensity obtained by polar scanning in a manner to be described. The advantage of this type of scanning for Generating a representation of a one-sided vanishing point perspective results from the following description of the generation of the information for display 10.

The first thing to be achieved is the creation of the polar grid. The distance R between the center of origin of the polar grid and the beam position and the angle 0 of the beam position are the polar coordinates of the beam. Then, assuming that the vertical distance (y) from the center t

ψ t siniJt (1)

where E is the peak baffle voltage y, T is the deflection period and K is the deflection sensitivity, and assuming that the horizontal distance (x) from the center »

t cosiJt (2)

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is, the polar coordinates of the ray as a function of time by inserting the equations (1) and (2) in the equations O) and (4) ι

+ y ² O)

0 - tan ' ¹ 2 (*)

found. The result is

(5) 0- Wt (6)

From equations (5) and (6) it can be seen that the ray begins at the center and spirals near the outside emotional. The number of spiral arcs of the scan is durohi

N- Tf (7)

where f is the frequency of the deflection voltages. The parameters are selected such that the increase in R for the period of γ seconds is on the order of one point diameter for non-interlaced scanning. Alternatively, for an interleaved scan, the first scan may move the beam in a spiral path one point apart between the adjacent lines near the outside. In the second scan, the spiral path covers the area not covered by the first deflection. This results in twice the resolution of the representation 10 for the same number of lines per line scan.

As shown above, there must be a sine and cosine voltage can be modulated in amplitude using a sawtooth voltage in order to generate a polar raster. A block diagram a polar raster generator 19, which does this, is in Flg.2

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shown. A square wave generator 20 outputs a square wave to one voltage controlled symmetrical limiter 2J. away. A sawtooth generator 22 is connected to a monostable feedback circuit 23, which in turn is connected to an input terminal of the sawtooth generator 22. The other output of the sawtooth generator 22 is connected to a different input connection of the limiter 21 connected to provide a sawtooth voltage. The outcome of the Limiter 21 is filtered in a Tlefpaßfller 24, whereby

t? 'O

a signal e "" "t sin <j t is generated, and via a 90 -phase

* E

Slider network: 25 a signal e is obtained that is mt cosw-t,

It will be appreciated that although only some oscillations within the sampling period T are shown for reasons of simplicity, in FIG Reality a large number exists to make a continuous one Get grid. It is further understood that in practice the jet is suppressed during the return travel and is amplified when the beam starts from the center point moved forward.

The voltage controlled symmetrical limiter 21 is shown schematically in Pig. 3 and comprises a low impedance amplifier 30 suitable for receiving a limiting voltage and having its output connected to the input of an inverting amplifier 31. Opposite polarity modes 32 and 33 are connected with a point with a relatively high impedance on the signal path to be limited, which is represented by the line 3 ^f *. The other terminal of the diode 32 is connected to the connection point of the amplifiers 30 and 31, while the other terminal of the diode 33 is connected to the output of the amplifier 31. If the positive section of E ^. E. exceeds, the diode 32 conducts and thus limits E _QU ^. on E _A> if. E _{Qut is} less than E, the diode 33 conducts and limits E _QUt to E ₀ .

A detailed circuit diagram of the polar raster generator 19 is shown in FIG Pig. 4 shown. Throughout the description, the same considerations are

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Marks for designating the same elements or components used. An entangled polar raster scan is used generated by a grid interlacing circuit 26. this will achieved in that the sawtooth generator 22 is synchronized with the square wave generator 20 in such a way that the sawtooth starting point is shifted by half an oscillation for each further deflection. The output of the monostable foot guide element causes a change in state of the flip-flop 27 of the grid interleaving circuit 26 in the end, every distraction. The state of the Plop-Plop 27 determines via the Dlodengatter 28, which Output of the square wave generator 20 terminates the deflection sawtooth. Because the flip-flop 27 changes its state after each deflection, the sawtooth becomes through alternating half-waves of the square wave generator 20 ended, whereby the raster interlace is achieved.

After the polar grid is generated, the next step is to provide a method for intensity modulation of the beam, zn generate the image NaOH Fig. I. This is explained in successive steps. The first step is to generate the horizon 12. It can be seen from equation (6) that the angle of the sampling point is the same as the angle of the deflection voltage. This means that the point moves for each oscillation of the deflection voltage by J60 ° on the image surface of the KSR 11 on a spiral path. If the beam is amplified over exactly 180 ° of each oscillation of the deflection voltage, only half of the grid is visible. Which half of the grid is visible depends on the phase of the boost pulse relative to the deflection voltage. When the phase changes, the reinforced half of the grid will rotate around the center. This effect is exactly what is required to display the aircraft bank information on the KSR U. In order to achieve the image of the horizon and the aircraft's bank angle, it is only necessary to amplify the beam for exactly 180 ° of each oscillation of the deflection voltage »u

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and to change the phase of this boosting pulse to the Obtaining Slope Information «Figure 5 is a block diagram of a horizon and transverse inclination.agenax'ator 35 · The The square wave signal of the square wave generator 20 (shown in FIG. 2) is fed to a low-pass filter 36 for generating a sine wave A fed to a zero crossing detector 37. The zero crossing -Detektor 37 is a Dlfferentialverscärker, one of which Input is related to ground or zero potential and generates two pulses B from each oscillation of the input, because one Sine wave passes through gauze twice per oscillation. Am Half-cycle sawtooth generator 38 is powered by these pulses synchronizes and thus generates two saw oscillations C for each oscillation applied to the zero crossing detector 37., i.e. one sawtooth wave for every half wave. Both the zero crossing detector 37 and the half-period sawtooth generator 38 are shown in detail in the circuit diagram of the horizon and bank angle generator according to 51g. 6 shown. Like in Pig. 6th As shown, the half-cycle sawtooth generator 38 consists of one a capacitor 40 and one through the input synchronizer pulses B actuated discharge circuit 41 feeding constant current source.

In Pig. 5 in turn speaks a voltage comparator 42 to the output sawtooth C of the half-period sawtooth generator 38 and the bipolar voltage D, which e.g. from a vertical gyro or a stabilized platform obtained bank angle 0 of the aircraft. The output pulses E of the voltage comparator 42 are connected to an input terminal of the bistable Plip-Plops 45 connected, the other input terminal to receive the synchronizing pulses B from the detector 37 iat · The output P of the Plip-Plop 45 is with a Buffer circuit 46 connected, in turn, to a video amplifier 50 after Pig. 8 is connected.

Pig. 7 shows the relationships of the various voltage waveforms after Pig. 5. Like Pig. 7 shows, two sawtooth waves are

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- Il -

for each oscillation of A that has the same frequency and phase as one of the deflection voltages. This sawtooth is symmetrized with respect to ground and is compared with the cross slope voltage (D). If the two voltages are the same, an output pulse (E) is generated, which flips a flip-flop and generates a voltage (P). It must be noted that (P) is exactly 180 ° from (A) and a phase shift proportional to the Qiiarnoigunga voltage (D) 0 ia * fw ©: Isfc. 0 is the actual angle by which the horizon is rotated around the center point and corresponds to the angle of inclination of the plug tool.

The addition of the long slope info window can be done by moving of the grid near the top or bottom by adding up the pitch stress and the vertical. Relaxation reached will. Pig. 8 shows the block diagram of a for generating a pitch and cross-slope position information suitable representation «The rectangle generator 20 is with the polar raster generator 19 and the horizon and slope generator 35 connected. The output of the folar raster generator 19 and a pitch angle Q of the aircraft and signals derived from a vertical gyro or stabilized platform (not shown) are fed into a Y summing amplifier summed, the output of which is connected to the Y-deflection amplifier 48 of the KSR 11. The output of the polar raster generator 19 is also directly connected to the X deflection amplifier 49 of KSR 11 connected. The output of the horizon and bank generator 35 1st with the video amplifier 50 of the KSR 11 connected.

Fig. 9 shows how the representation for any longitudinal inclination and bank input signal would look like. It is Please note that the grid area is larger than the actual field of view of the cathode ray tube. This is necessary because the grid for pitch ElPs is up or down

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is moved. The grid also becomes horizontal for others Entrances moved in a manner yet to be explained. If the grid is only used to cover the visible surface of the cathode ray tube would suffice, a part of the picture would be sufficient if the grid were shifted vertically or horizontally get lost. This technique greatly simplifies both Longitudinal inclination display as well as the runway arrangement and the course display, as explained in the following will.

The next step is the creation of oXne's method for generating the runway IJ. A single vanishing point always on the horizon 12 is required. Fig. 1 shows such a runway image IJ and defines the parameters a, b, / * t, T and χ of the runway IJ, which can be changed to control their position and size. In the illustrated embodiment according to the invention, the above variable parameters a, b, / 4 ₉ V and χ are all offset by easily obtainable measured values of the aircraft position and attitude in relation to the runway, as indicated by ILS rays and course directions be determined. Furthermore, it is understandable that the runway represents only one possible reference path and that other orbit representations can be used, for example a type of airway representation {"path in the sky"]. Because of the use of the polar grid, this can be achieved in a simple manner. Recall that the horizon 12 was created by amplifying the beam for one-half oscillation or 180 ° of the deflection voltage. This resulted in a visibility of the polar grid for 180 °. If the gain pulse had been less than 180 °, the visible part of the grid would have been smaller and sector-shaped (pie-shaped). In other words, if a gain pulse with a width that corresponds to 15 ° of the sinusoidal deflection voltage is applied to the video amplifier 50, the resulting image on the KSR 11 is a sector-

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shaped area with an angle of 15 °,

When the phase of the 15 ° wide pulse is changed relative to the deflection voltage, the sector-shaped area rotates an angle / j, around the center of the grid. This sector-shaped segment can be used to represent the basic image of the runway 13 according to Flg. 10 can be used. It should be noted that the runway 13 regardless of how f and μ. are changed, converged on the horizon 12. Therefore it is always in complete single point perspective. The point at which the runway converges on the horizon relative to the center of the display is set by shifting the grid horizontally by a value χ. To complete the St & ** t ~ and runway it is then only necessary that only a given section of the sector-shaped (pie-shapod) area can be shown Csh. Fig. 1). This will be explained later. It is then clear that the basic runway image of FIG. 10 is provided by a voltage-controlled phase shift circuit for setting / U. and a voltage-controlled pulse width circuit for setting t can be generated. Of course, this must be done phase-locked to the phase of the deflection voltage. One point that should be noted is that the pulse width f must be centered with respect to the phase corresponding to the center of the runway. If it were not centered, a change in T would also change JL

/and vice versa. '

result / The pulse width cannot simply be increased, but must be symmetrically expanded by the / i corresponding time phase, as shown in FIG. 11.

Flg. 12 is a block diagram of a circuit 61 for generating the runway image according to FIG. 10, which enables / i and f to be voltage-controlled and independent. As in Flg. 12, the output A ^! the horizon and bank generator buffer latch 46 to a half-period sawtooth bracket 55 (generally of the type shown at 38 in FIG. 5) and to an input terminal of a NAND

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Circuit 56 applied. The output B ^{8 of} the sawtooth hold 55 is connected to the respective input terminals of an inverting and summing circuit 57 and a summing circuit 58. A signal X / t is applied to the other input terminals of circuits 57 and 58. The output C ° of the inverting and summing circuit 57 is connected to a voltage comparator 59, the other input terminal of which is supplied with the K'f signal. The outputs E *, F 'of the voltage comparators 59 and 60 are connected to the respective input terminals of the NAND circuit 56 connected. The remaining input terminal of the NAND circuit 56 responds to a runway blocking pulse in a manner to be described below. The output of the NAND circuit 56 is fed to the video amplifier 50.

Understanding the generation of runway 1? can be achieved by looking at the block diagram of FIG. 12 and the waveforms of FIG. The waveforms correspond to assumed values of? * And / t. As K y "is decreased, the waveform (C ⁰ ) shifts up and (D ') down with respect to ground. Daduroh increases the bottom width of (E ⁸ ) and increases the top width of (F ⁸ ) This shifts the pulse (Q ⁸ ) to the right without changing the width T. When K · T is decreased, the lower width of (E ') is increased and the upper width of (F *) is decreased Width T reduced without changing the position of the center of the pulse, ie ^ remains the same

To complete the runway generator 6l 1st It is necessary to provide a means to represent only a part of the sector-shaped area as in FIG. These Setting the beginning a and end b of the runway IjJ enables the length and distance to be controlled from the horizon 12. This requires a method of generating a straight line on the polar grid, Be eel assumed that a

The output D ^{1 of the} output D 1 is connected to a voltage comparator 60, the other input terminal of which the "If" signal is fed.

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Voltage P can be obtained which is equal to the deflection voltage of the y-axis, but is shifted in phase by <f radians.

P « ψ sin ((J« t + f ) (8)

The extension of this results in:

sinW «t cosiT + ψ- cosfc / t sin / (9)

Substituting equations (1) and (2) into equation (9) gives t

P «y + X (10)

The resolution for y results in:

y «-tan ^ X + gJLp (U)

Equation (11) is a straight line equation, but with the separated y-expression a puncture of the tent, because B is a puncture of the tent. If the beam is amplified using suitable circuitry each time P passes a predetermined level, equation (11) indicates that a straight line is generated on the polar grid. The slope of this line is -tan cf and the y term or location can be placed anywhere on the plot by detecting and amplifying the ray at various constant values of r. This is in Pig. 14 shown for constant 0 . If cf is changed but the beam is amplified each time P passes a fixed value r, a different set of straight lines will be created. That group is in Pig. 15 shown.

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Flg. 15 shows that if f is changed and r is held constant, a group of straight lines, all touching a circle of radius Kr, is created. 1st be clear that a straight line _e with any gradient or layer on the Polarraeter by adjusting the phase of P (<T) and r can be generated as shown in Flg. 16, which shows the creation of a straight line on the polar grid. The line is created by amplifying the beam every time P goes through a fixed value r. If the beam were amplified for all values of P greater than r, the area enclosed by the maximum polar raster arc and the chord created by the straight line would become visible.

Once a method of creating a straight line or an area to the right or left of the straight line has been established, two things can be achieved. Firstly, the runway generator 61 can be completed and secondly the lines of the ground plane oitter 14 can be generated (see a and b of Flg. 1) required circuits completed ο This is achieved by blocking the output of the runway generator in the areas of the grid where it should not appear Runway 12 must remain in perspective when the aircraft is being banked so that the restricted areas must rotate and remain parallel to the horizon 12 during the bank. This can be done by deriving P from the output of the cross-linking generator j55. This forces J * to be in synchronicity to 0 and causes the leading and trailing edges of the runway to be parallel to the horizon 12 at all times.

Flg. 17 is a block diagram of the diagram used to complete the Runway generator 61 required circuit. Of the

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Output from the horizon and Quemelgungs generator 35 of FIG. 5 and the signal from the voltage controlled symmetrical limiter 21 of Fig. 2 is applied to the respective input terminals of the Schwellwertbegrenzer diodes 65 (clipper diodes) "via a low-pass filter 66 having first and second voltage comparators 6? or * 68 are connected. The output signal of the low-pass filter is P. The voltage comparator 67 also responds to a ^{signal proportional to "a n} , while the voltage comparator 68 continues to respond to a ^{signal proportional to w} b ^H. The outputs of the voltage comparators 67 and 68 are with a negative logical OR Circuit 69 which provides a runway blocking pulse The output of circuit 69 goes to zero when one of the inputs goes to zero.

The output of the first voltage comparator 67 is a negative pulse for the length of time that P is greater than a. The pulse occurs at the second voltage comparator 68 for a time in which F is greater than b. It follows that the runway opener output according to FIG. 13 is blocked in two areas of the polar grid, as is shown in FIG As shown in the circuit diagram of the runway generator 61 according to FIG. 19, the circuit configuration of the negative logical OR circuit 69 according to FIG. 17 and the NAND circuit 56 according to FIG. 12 combines both. The combined logic circuit is shown in Flg. 19 shown as runway generator output logic 70. If the connection points 71 and 72 are "high" (indicating the waveforms of FIG. 13 corresponds to), the collectors of the transistors 73 and 74 are "low" and thus produce a low output to the video amplifier 50. If the connection points 75 and 76 ^h low "are the collectors of the transistors 77 and" high "with the result that the output of the video amplifier 50" is held high, "regardless of the state of the connection points 71 or 72. the output is therefore by a signal

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locked at one of the connection points 75 or 76, which is the desired result.

Of course, the runway image of Figure 18 rotates around the center of the grid during cross slopes, maintaining the correct distance from horizon 12 and length. This is only possible because of the constant r and variable ei bendings according to FIG. 15.

The next thing that needs to be explained is the creation of the orund plane perspective lines which form part of the grid 14 and converge at the center of the horizon 12 as shown in FIG. It should be remembered that the runway 12 always converges at the center of the grid and not necessarily at the center of the representation or the viewing area (see Fig. 10). This requires that the orund plane lines do not necessarily converge at the center of the grid, but rather must move relative to the center of the grid in such a way that they always converge at the point on the horizon which corresponds to the center of the representation for a zero angle. In order to achieve this, the constant oT, variable r properties according to FIG. 14 are used. A closer inspection of Fig.l reveals that the orund plane oitter 14 consists of two lines 80 and 81 with constant width parallel to the horizon and six lines 82 to 87 converging at a point on the horizon 12. Any of the parallel? Constant width lines 80 and 81 are generated in the same general way as the runway start and end. The only sub-sole is that the two areas are overlapped and that the beam is strengthened in the area created by the overlap. This is shown in FIG.

Fig. 21 shows the blooksalt image for generating one of these lines. A signal from the output of the low pass filter 66 of the runway generator 6l is a buffer peeling

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device 90 supplied, which an output signal P to the first and second voltage comparators 91 and 9? - delivers. The comparator 91 also responds to a fixed voltage V, while the comparator 92 continues to respond to a fixed voltage V ₂ . The outputs of the comparators 91 and 92 are connected to a negative logic USD circuit 95, which in turn is connected to a negative logic OR circuit 9 ^ which supplies signals to the video amplifier 50 according to FIG. 8. The negative logical OR circuit 94 responds to the blocking signal from the negative logical OR circuit 69 of the runway generator 61.

Signals V ₁ and Vg are fixed voltages selected to align the amplified area and adjust its width. Flg. 22 shows the phase relationships of the voltages at points A, D and C of FIG. 21. Well, the signal P does not have a constant amplitude, the widths of the signals A and D start at zero and are enlarged as the amplitude of the signal P increases. However, the pulse width of waveform C remains constant. These line amplification pulses are blocked by the runway pulses in order to maintain a constant runway brightness. If this were not carried out, the runway 1.3 would appear brighter at the points where the lines cross them, because all these pulses are summed up at the video amplifier 50 of constant width are two circuits according to Flg. 21, except that both use the buffer circuit 90 and the negative logical OR circuit 94 as shown in the detailed circuit diagram of the ground plane spectrum generator IO8 of Fig. 25, which is also used for the basic converging grid line circuits 82 to 87 is used.

As in Fig. 2? is shown nega ive logical OR circuit is slightly different 94 _s by a low voltage

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at the cathode of one of the line circuits 80 to 87 correspondingly connected diodes 95 to 102 the transistor 104 brings into saturation, which in turn blocks the transistor, which acts so that the collector of transistor 105 assume a low value "I) Ieü is through the blocking circuit 106 prevented by turning on the transistor 107, the holds the collector of transistor 105 high regardless of the other inputs.

The negative logical AND circuit 93 has two with each other connected diodes 108 and 109. If both diode-anode voltages are low, the cathode voltage is likewise low.

The converging grid lines 82 through 87 are mapped to similar ones Way generated. Two areas are overlapped and the beam is amplified in the resulting area as shown in FIG.

As explained above, the grid for setting the runway 12 is shifted horizontally, but the converging lines 82 to 87 must always converge on a point on the horizon 12 which corresponds to the center of the representation for the pitch zero. This means in Pig. 24 that the reinforced area, while maintaining its angular position in relation to the horizon line 12, must be displaceable to the left or right, but must always converge on the horizon line. To achieve this, the variable r, constant & * properties of FIG. 14 are used. By changing r and keeping <f constant, the reinforced area according to FIG. 24 can be shifted to the left or right of the grid center point. A block diagram for a converging ground plane grid line such as 82 is shown in FIG. The waveforms at points A, B and C are shown with the waveforms denoted by the same letters in FIG. 22 same.

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Bel comparing the Pig. 21 and 25 it can be seen that the creation of a converging ground plane grid line differs from the creation of a parallel ground plane grid line in only two respects determine. _{The second are the reference voltages C 1} X and CpX applied to voltage comparators 112 and 113, respectively; these are not constant, but proportional to the hasty shift from the center point of the representation. It is these tensions that keep the converging lines at a proper point on the horizon. For six converging lines 82 up to Fig. * 1, six of the circuits of Fig. 25 used. As explained above, to perform pitch and runway positions, the grid center point is shifted relative to the display center point, as shown in FIGS. However, because of the manner in which the horizon 12 and bank generator 35 operate, the horizon 12 is rotated about the center of the grid. To keep the image in perspective, the image must be rotated around the center of the display and not the center of the grid because the center of the grid for longitudinal and runway entrances is not at the center of the display. To do this, it is necessary to rotate the grid center point around the display center point when receiving a bank input. 26b shows that a bank entry of 0 means that the grid center point must be rotated by 0 radians around the center of the display, whereby the image is held at the center. Generating this rotation requires additional inputs to the x and y deflection circuits 49 and 48, respectively. The required inputs can be derived with the aid of FIG.

From Fig. 27 it can be seen that X _{1 represents} the additional x deflection

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input and y ^ represents the additional y input that is required to rotate the grid center point around the display center point. The relationship of X ₁ or y · to the bank angle 0 results from PIg. 27:

X ₁ - -x (1 - cos 0) (12)

Y ₁ - x sin 0 (13)

With a longitudinal incline input Q (eh. Flg. 1) results for the additional inputs:

y ₂ - - 0 (1 - cos 0) (U)

-O sin 0 (15)

it will be understood that O is the vertical or y-displacement of the raster from center. For incline and cross-slope entrances, all of the above entrances are required. Two puncture generators, two two-quadrant and two four-quadrant multipliers will typically be required to perform the inputs expressed by equations 12-15. It has been found that the linear approximation of the functions 1-oo 0 and sin 0 gives an acceptable representation and at the same time simplifies the execution of the multiplication. Using a linear approximation, equations (12) become bla (15) *

K x _1/0 / (16)

K ₂ 0 (17)

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y ₂ - - OK _1/0 / ( ₁₈₎

X ₂ - OK ₂ 0 ₍₁₉₎

Pig. 28 is a block diagram of a coordination hold 115 which does these calculations and adds the result to the x and y deflection voltages. The outputs are given by:.

^e x * ^K 4 cos ψ- "J t + OK ₂ 0 + K ^ xf - K _1/0 / J (20) sin _{W 2} t + XK 0 + β [kj - K _1/0 /] {21)

If the constants are selected correctly, the picture for x, 0 and 0 - rotate inputs around the center of the display and not around the center of the grid

The generation of the equations (16) to (19) is now based on the circuit 115 according to Pig. 28 explained. The bl-polar cross-linking voltage 0 is passed through an absolute value circuit 116 and its output modulates a filter module 117. This results in a pulse duty factor proportional to the absolute value of the cross-linking voltage 0. The pulse-width-modulated signal actuates a switch 118 or 119. which enables the passage of the x or 0 voltage with the same duty cycle. The mean value is extracted by low-pass filters 120 bsw * 121. The mean value is proportional to the product of the absolute values of the bank voltage 0 and χ bsw. of pitch 0. This creates equations (16) and (18), but with imprecise constants at this point. The constants are obtained by the x and y Sunmier amplifiers 125 bsw. 47 corrected. Equations (17) and (19) are now developed by changing the sign of equations (16) and (18).

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when the polarity of the bank angle voltage changes. This causes the absolute tick marks from the equations

(16) and (18) can be removed, resulting in equations (17) and (19), but again with incorrect constants which are corrected in the summing amplifiers 47 and 125. This is done through polarity detector 126, switches 127 through 150 and amplifiers 131 and 132. The polarity detector 126 determines which of the inputs, either the inverting or the non-inverting input of the amplifier 131, 132 the signal is fed. Thus, if the crossover voltage changes polarity, polarity of the signal at the output of the amplifiers 131, 132 also changed. The circuit can be thought of as two the equations

Think of (17) and (19) generating four-quadrant multipliers in which equations (16) and (18) are in an intermediate step Finally, all voltages are added up in the appropriate x and y summing units 125 and 47, respectively. this gives the complete x and y deflection voltages, which were expressed above by equations (20 and (21)).

A detailed circuit diagram of the coordination circuit 115 is shown in FIG. The absolute value circuit 116 includes an inverting amplifier 135 as shown in FIG. 30 and two diodes 136 and 137. When E _{1n is} positive, the output of amplifier 135 is negative so that diode I37 is reverse biased and diode 136 is forward biased. The exit then follows the entrance. When E _{1n is} negative, the output of amplifier 135 is positive with diode 136 reverse biased and diode 137 forward biased. The output is then of the same size as the input, but positive. In other words, the greetings from the output are always of the same greetings as the input, but always with the same polarity, regardless of the polarity of the input.

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BATH

To complete the description of the illustration, the center point reference cross 17 and the flight direction bars 15 and 16 will now be explained. Until now, the entire image on the KSR 11 was generated by intensity modulation of a polar grid. The center reference cross 17 and the flight direction bars 15 and 16 are not generated in this way. When the polar grid reaches its maximum diameter, it must be retracted or returned to the center so that it can be repeated. The grid is not started again immediately, but rests for the length of a time _{4 to} allow the filters to recover from the return jump. The length of time for this delay corresponds to approximately 8 oscillations of the deflection voltage. This tent is controlled by the monostable feedback circuit 23 (see Fig. 2), which blocks the sawtooth generator 22. The time corresponds to about 5 % of the deflection tent. During this feedback period, the video amplifier 50 and the deflection circuits 48 and 49 are unused and can be used to generate additional information on the KSR 11 .

The center point reference cross 17 and the flight direction bars 15 and 16 are in Flg. 31a and are shown by analog switching and a logic that is synchronized by the raster return, generated. This process takes four steps. The generation of:

1. the horizontal line 140 of the center reference

2. the vertical line 141 of the center reference

3. the horizontal flight direction bar 15

4. of the vertical flight direction bar 16.

Figure 31b shows the deflection voltages for the four steps. Tue The sequence shown is repeated each time the return

10 9 816/1616 BAD ORIGINAL

run takes place. The raster deflection voltages are generated by the deflection amplifiers! 48 and 49 removed during the return time and the Voltages according to Fig. 31b are applied. The line 140 is generated in that two oscillations of a sinusoidal wave with small amplitude can deflect the beam in the x-direction. At this time the y deflection voltage is zero. The line l4l is then formed by the fact that two oscillations of the same sinusoidal oscillation can deflect the beam in the y-direction. Because the lines 140 and 14l are formed by sinusoidal voltages without a DC voltage being present on the opposite axis, their points of intersection lay the Display center for the images formed by the polar grid and for the plug direction bars. The bar 15 is formed by making two oscillations of a sine wave deflect the beam in the x-direction with a larger amplitude can · The bar 15 is displaced in the vertical direction from the center point by applying the horizontal flight direction bar signal to the x-axis. The beam 16 is thereby formed that two oscillations of the same sine wave can deflect the beam in the y-direction. The bar 16 will by applying the vertical flight direction bar signal the x-axis offset in the horizontal direction from the center. Two waves are selected for each of the lines because eight waves of the grid deflection voltage frequency are available during the retrace time period.

32 is a block diagram of the plug direction bars and center point reference circuit 145. The result is a pulse from the monostable flyback circuit 23 of the polar raster generator 19 according to Flg. 2 initiated. This pulse removes the raster _{deflection voltages β χ} and e from the deflection circuit via analog switches 146 and Ι4γ, respectively. At the same time it triggers the counter 148 consisting of three flip-flops 149, 151 and 152. The payer 148 becomes through the signal

10 9 816/1616

of the square wave generator 20 according to Flg. 2 controlled, which also the polar grid generator 19 and the horizon and bank generator 35 controls. The decoding for the four steps is done by analog circuits 153 through I56 achieved, which also serve as AND gates, i.e. the Switch enables the passage of the analog signal when all of its bi-polar digital signals are negative. The change in amplitude of the sine wave guided through the gate is given by the circuit 157 with a defined change in gain 'The two monostable circuits Call 158, 159, AND gate 3.60 and OR gate I6I a beam obscuration emerges when the?. · »beam is moved from one line or bar to the next. At the end of the pulse the monostable return circuit, the counter 148 is blocked and the signals e and e can through the analog

χ y

switches 146 or 1 * 7 run, while all other analog switches ter 155 to 156 are kept open until the next one Reverse occurs. A detailed circuit diagram of circuit 145 is shown in FIG.

Fig. 34 is a block diagram of the overall system using the circuits explained above. The polar raster generator is connected both to the horizon and bank angle generator 35 and to supply input signals to the x and y summing amplifiers 47 and 125 and to the runway perspective generator 61. The horizon and bank angle generator 35 is also connected to the runway perspective generator 61 and responds to the bank angle signals 0 . The output of the horizon and bank angle generator 35 is connected to the video summing amplifier 50. The runway perspective generator 61 is connected to the ground plane perspective generator 108 and responds to the signals / * -, f, a, b and to those of the polar grid generator 19. The exit of the runway

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20A9A82

Perspective generator 61 is; connected to an input terminal of the video summing amplifier 50. The basic area perspective generator 108 responds to the x signal and is connected to another input terminal of the video signal processor 50. The χ, θ and 0 coordinator 13S responds to the G, χ and 0 signals to deliver a / tiiseangssignals to the y and x Suramier amplifiers 4 7 and 4 respectively. '. ^ 3 nn, The y-Suramier amplifier 47 will continue to use the fc'-SJgi)?' directly suggests and it supplies a summing signal to the direction bar circuit 145 · The x summing amplifier 123 continues to be supplied with the x signal directly and it sends a summing signal to the direction bar circuit J45. The circuit 145 receives the vertical and horizontal bar signals directly to generate output signals. added to the x and y deflection amplifiers 49 and MB, respectively. The mode of operation of the KSR 11 as a function of the above-mentioned signals has been described above with reference to the individual circuits.

Claims t

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BATH ORIGINAL

Claims (1)

Claims Information display device for vehicles with a cathode ray tube and means for generating olnes Beam to create a natural representation of the position of the vehicle or other parameters as the sum of the übeam projected image on the CRT screen, thereby indicates that means for such Ablerlccung the beam are provided that the image continuously follows a beam path across the RHhran picture screen. 2, information presentation according to claim 1 with means for the generation of beam components, the display in the representation, a path reference, for example elntn flight path od se (ILü runway of a serviced airfield, characterized in that DAO dlaae advertisements Einzelpunktpörspektlvö are shown and that dlesar point dor center of the 3plraiweges 1st J. Infonmatlons display device naoh Anepruoh I with means to return the beam between Aufdinandsrfo lindan movements of the picture over the Dplralweg, daduiOh gakunnzeich, d * ß mlnd9 »tens elnlgo dor Para-In the representation wJUu-enrl him ftüokiaufs dos Btrahias : t be, rnformatlon3-DarstaLlur.gavorrlohfcung naoh Anjprufsh 1, gekennzdlohnöt that this «Kur 'jr Uihtunga lines and ο In Mitbelpiaikt dar β Intl, 10 9 8 16/1618 3 <r Empty barrels