DE1506630A1 - Flight instrumentation with electronic display - Google Patents

Description

Flight instrumentation old electronic display German present invention relates to flight instrumentation with an electronic display, with several pieces of information grouped together to form information groups uad on a screen of a @ raun'schen To be staled there.

The known conventional flight instrumentation always exists according to aircraft size and type from a large number of individual instruments, of which each one takes up a relatively large space. that forces that the entire only area was in front of the pilot and offered larger aircraft also of the copilot and the flight engineer completely for di. Accommodation of the individual instruments are required.

The pilot and the copilot are in control of each The aircraft's instruments overlook a considerable area. Wenm also the individual Instruments according to the membership of the group information to be displayed are summarized, @o results from the multitude of @izzelimstrumente and their Rum need and also by the often lonely uhmiche way of displaying the information, that the pilot's instruc- tion is confusing. The on @@ chem one Certain instrument requires hereditary time usa - can also have albic defects not always be excluded.

Further developments of the flow instrumentation lead to simplification the Aufhaues of the instruments and to heighten their reliability, however, could with this must copy the existing difficulties, in particular Disq Clarity and clear unambiguous presentation of information, not eliminated will To eliminate the existing powers, tet eq became known, the conventional flight instrumentation you electronic display of the information quantities - The worst. Cathode ray tubes are used for this purpose, their screen the information is recorded.

It is from such recording methods that the present invention proceeds off, and it @@@ whose task with the electronic recording as possible large information density taking into account an easy-to-understand presentation to achieve, so that the information from the aircraft guide staff as possible at a glance and every note can be clearly recognized. Furthermore, it was that The object of the invention is to record the system groups of the aircraft, like engine d old monitoring of temperature, oil level and thrust etc., as well as Eufstoffvorrst @@@ age and Rollmonnetenazaeige etc., according to the To brim open the picture chirp.

According to the invention, the task set is essentially thereby solved that all information quantities assigned to a plant group do Time multiples tested and with regard to their position to a Beferems in the aircraft and their shape, direction and size are clearly shown.

Furthermore, there is a small merit of the de @ discovery that the display sizes on the screen vectorial, e.g. for thrust and speed, and akalar i @ form of variable lengths, e.g. for @@@@ peraturm, Bruck and Exehzhbl the drive notes, are represented.

By means of such an amm-guided Fugimstrumatierung @@ is made possible, Send the information to the smallest possible @@@@ @@@ and only a few to achieve greater information density. This gives the pilot the opportunity Given @ easier and faster the instrumentation @@ general @@, @@ ate shorter ones Response pages for executing a Kor @@ kturmaneuvers or the like. and an essential one Kntlstung the pilot @@ - is enough will. The pilot can get his attention in have measure of his actual task, namely the fulfillment] of a certain one Fly to the beach. As a result of the clearly different recorded Information symbols on a screen for a. Anagen group of the flight zegue becomes once achieved the placement of several pieces of information on a maximally small space and further errors in diverting hew. Avoid recognizing the values shown.

The flight instrumentation according to the invention also offers the advantage that the information is meaningful in Besug on the location of the individual systems of a System group in the aircraft can be recorded on the screen so that the pilot, Oboe made special considerations about the location of the individual systems in aircraft only Position of the information on the screen. is informed and if necessary without delay. Influencing the corresponding systems in the form of control commands or the like. in front of chew. In addition, an early morning meal is worth it the information capacity, i.e. the information for the flight management and operational control both for the pilot and for the Copilots can be shown on separate screens $ without loss of clarity to question the instrumentation. It is also achieved that the pilots Evaluation of information and the resulting messages from witgeband removed and the pilot is recorded as a command signal on the screen.

This applies in particular to information on the flight.

In the drawing is an embodiment according to the present Founding for an instrumentation made.

Fig. 1 inclines the structure of the flight instrumentation in a circuit diagram.

Fig. 2 inclines a screen in plan view old the order Reference symbols and the related information symbols for the system group "Mutbjettriebwerke of a flight @@@@ ".

Fig. 3 shows a screen in plan view itt the plotted @@ ferezsynbolen and the associated information symbols for the A system group "marching engines".

Fig. 4 shows a screen in plan view with the plotted Reference symbols and the associated information symbols for the plant group "Amount of fuel in each fuel tank".

Fig. 5 shows a screen in plan view with the plotted reference symbols and the associated information symbols for the system group "chassis and landing gear" Fig. 6 shows a screen in plan view with the applied reference symbols and the associated information symbols for flight guidance.

7 shows the arrangement of the individual screens with the information groups on the instrument panel of an airplane.

Fig. 8 shows the implementation of a circuit of the individual screens for the exchange of information groups with each other The one shown in the drawing groove electronically operating flight instructions are in the exemplary embodiment shown intended for an aircraft, which has several thrusters on each side and Se has a cruise engine, wherein the earsch thrusters deflecting means for contain the propellant gas jets of the marching harnesses.

In Fig. 1, nit 1 denotes the signal processing that leads to% erection of distraction signlane is used. Connected to the signal processing is the time shift working cyclical scanning 2 of the deflection signals to the serving as a display device cathode ray tube 3 with its screen 4 is guided The structure of a symbol generator and the circuit of the cathode ray tube serving as a display device is known and therefore described below no insofar as it is necessary for an understanding of the present invention seems necessary.

D.r electronic switch 2, which uses time division multiplexing Provides deflection signals for the display device is here for example jait operated with a 10 kHz cycle. All channels are divided into groups. By a variable feedback in the control (after each group @@) can thus determine the number of channels be changed. One group @@ at a time in a group amplifier, where the actual deflection signal has a fixed zero point coordinate in each channel and a programmable lost coordinate can be added up. The last zero point coordinate is set in the X and Y directions in the potentiometer field. As a variable coordinate Any time functions can be used depending on the symbols. Under signal conditioning the conversion of the input signals (direct or a combination of several) can be understood in deflection signals that are suitable for vision devices in animal desired way to steer. For the signal processing are for the conversion from polar to cartesian coordinates sine and cosine function generator provided. The functional volume i is approximated by straight lines and with a 1% deviation balanced. Hall multipliers are provided for multiplications. To the generation Chopper amplifiers are used by dashed symbols to represent digital W @@ ten is provided with a @@@ digit generator to hide unused @@@ ile a programmable D @@@@ key is built in. For special information theory for @corzuchungen there is the possibility to land any Syuboie for a short time.

As shown in FIG. 2, there is a cathode ray tube 3 in plan view shown on their screen 4. The individual reference symbols are on the screen 4 @@ r the system group "lift jet engines" applied. There are some in the middle of the screen 4 to a reference symbol representing the flight 8 concentric circles 9 equidistant from one another for electronic recording of the thrust vector z over an angular range that gives the thrust directional change # applied. In the upper right and left halves of the screen are the Reference symbols 12 and 12 'in percent for the Speeds of each Husbjet engines according to the position of the husbjet engines on the aircraft and Liesen assigned In the left and right lower half of the screen the Reference symbols 14 or @@@ in percent for the temperature of the hot gas jet broken the screen. There are also jewels below the reference symbols 14 or 14 'Reference unfortunately or scales 15 or 15' for the level of 1 air inlet temperatures recorded in the Hubstrahlte @ ebwerke de @ corresponding aircraft side on the screen. .½u @erdem is below the reference symbols 8 baw. # a talked about Retention field 18 @ extending over the screen for the thrust comparison of the lift jet engines both sides of the aircraft in an area of @ 10% from its envelope line on the Screen raised.

As already described, the specified reference symbols are the electronically generated r. @formation symbols recorded on the screen, and was the information symbols for the speeds of one of the thrusters, the hot beam temperature and the utltint @@@ t temperature The information symbols are zon of a zero line by vertical line symbols that can be changed in length 20 or 20 '; 21 or 21 '; 22 or 22 'shown. u the display of the thrust vectors the lift jet engine on one or the other side of the aircraft becomes the corresponding one Retirement symbols 8, 9, t: L around a zero point 0 on the plane @ symbol in their angular position Information symbols that are variable and variable in length starting from the zero point in the form of lines 26 and 26 'for one or the other side of the aircraft on the Screen d electronically uigeze @ chnet, with the information symbol 26 for differentiation the engines of one and the other side of the vehicle through a loop (26) is pictured. I am another information symbol 27 for the thrust comparison by a length that varies from zero to plus or minus uit Line icon for the reference folder 18 recorded on the screen. Like Fig. 2 reveals. shows the thrust comparison display 18, 27 a thrust difference between the lift engines the one and the other plane @ the second. In the present The case is one of the Sehubüb @ chu @ of the @@@ trahl engines of the local aircraft side @ of ca minure 2%.

All information for the n @@ gen group "Hubsterahltriebwerke" of the aircraft is @@@ according to the illustration according to Fig. 2 for the Piltoen on @@@ er @ l @@ nst possible @ smoothness, with each piece of information on the screen clear is shown recognizable and due to the pilot.

In Fig. 3 is for the system group "cruise engines with thrust deflection possible to support the lifting engines during the vertical stat or landing "another Information group consisting of more mature nz and information symbols on the screen 4 recorded in a separate cathode ray tube 3a.

Corresponding to the two May real works on both sides of the aircraft is au @@ aut the screen 4 the cathode ray re 3a approximately in the middle of it Plane representing Sym 91 8 and concentric to it in the zero point aw plane symbol Circles 9 of equal distances to each other over an angular range # on the screen dissolved @ agen. On both sides of this reference symbol are corresponding @ @ the left one or right marching engine Reicrenzysmbole for the temperature of the hot gas jet THS or THS ', the temperature of the oil TOL or

TOI ', the speed nN or nN' of the low-pressure compressor, the speed nH baw. nH 'for the high-pressure compressor and pN or pN' for the pressure in the combustion chamber in percent. Furthermore, St below the reference sy @ole 8, 9 and Kein sich Reference field extending horizontally across the screen for the slider match applied with percentages on the screen. Become the reference symbols also here the electronically generated information symbols are recorded on the screen. For the drawing of the thrusters of the cruise engines of one or the other Aircraft side become the corresponding reference symbols 8, 9 and # around the zero point 0 at the aircraft arm t3 variable un <l starting from the zero point 0 variable in length Information symbols in the form of lines 26 or loops 26 'for the right or left engine recorded on the screen. To the reference symbols Tiis, T115 'TÖL, TÖL'. nN, nN ', nH, nH', pN, PNI are in the form of variable length vertical lines mark the information symbols 20 and 20 'from a zero line recorded. The information symbol 27 is also used for the thrust comparison corresponding to the reference field 18 from the zero point 0 by a length reduction Line drawn after plus or minus horizontally.

In FIG. 4 there is information for the plant group "fuel quantity" provided for the screen 4 of a further cathode ray tube 3b.

On the screen 4, this information is in the form of a vertical running scale graduation with horizontal lines for the in the individual fuel tanks existing fuel quantities reference symbols 31 applied. To one the plane Symbol 30 representing the position of the fuel tanks in the aircraft Obvious information symbols 32 relating to the location of the fuel tanks Longitudinal aircraft axis in the form of variable length from a common zero line outgoing strokes recorded on the screen 4.

There is a dependency on the filling level of the individual fuel tanks to the roll position of the aircraft, there is a reference symbol horizontally above the screen 33 applied to the screen and eo is electronically one of a Zero line 0, O, i.e. from the aircraft longitudinal axis in the direction of the aircraft transverse axis to the left or right, outgoing length-variable information symbol 34 recorded on the screen and compared with the reference tool 33 on the screen.

This gives the pilot both the amount of fuel in each of the fuel tanks and at the same time the size of the roll moment is shown.

In Fig. 5 is for the information of the Polots for the: system group "undercarriage and Landklppen "another cathode ray tube 3c with the associated screen 4 forward. There are in addition, reference symbols in the form next to each other the vertical scale divisions are 35 in percent for the battery truck of the chassis hydraulics of the main haulage and booing works, based on their location on the aircraft, There is also one on the longitudinal axis below the specified reference symbol of the aircraft related vertical scale division 38 as Referen @@ mbol for the brake pressure of the left and right Fahrwerkstel les plotted in percent on the screen 4 In addition, there is a reference symbol 39 in the form of a; Aircraft in one exchange upright from behind on the screen, evident on its longitudinal axis or zero line also the shale release for the battery pressure and the brake pressure according to the position of the chassis can be obtained. In addition, there are reference symbols 40, 41 and 42 for the position of the landing gear on the aircraft is shown on the screen. To the reference symbols For the battery pressure, the information symbols 46, 47 and 48 in the form of vertical lines varying in length corresponding to the existing one Battery pressure recorded on the screen. Furthermore, for the brake through to the corresponding reference symbol 38 for the main landing gear part of the left or right side of the aircraft information symbols 49 and 50 in the form of vertically adjustable horizontal bar recorded on the screen 4. To reference symbol 39 and the reference symbols 40, 41 and 42 are also shown in the form of vertical lines 52, 53 and 54 recorded information symbols for the display of the extension process of the landing gear and the completed extension process through information symbols in the form of each the circle symbols 57 assigned to the vertical line drawings 52, 53 or 54, 58 and 59 shown. On the indicated wings of the aircraft reference symbol 39 the landing flap position is also shown on the screen by straight lines, which rotate around the zero point O at the wing ends.

In the case of the instruments according to FIGS. 4 and 5, the different Representation of the individual information on a screen achieves that the pilot the instrument people can easily overlook. The whole System group "landing gear and flaps" can therefore be monitored quickly, wogel through tlie obvious arrangement of the reference and associated information symbols The pilot has special considerations about the location of the individual systems in the aircraft influencing the flight guidance instru- ments to be taken sid.

In Fig. 6 is a representation for the flight guidance required Information shown for hover and aerodynamically borne flight. at this instrumentation is assumed that the pilot is optimal in a VFR flight Receives flight information. The flight control instrument described below gives it the pilot information about roll, pitch and yaw angles, as well as height and sink angle and translation movements.

It is assumed that there is an earth-fixed coordinate system, where the point of the earth-fixed coordinate system X, Y, Z in the starting point of the machine lies. The origin of the aircraft-fixed coordinate system #, #, # is instantaneous Location S of the aircraft, where g is the roll axis, # the pitch axis and # the vertical axis of the aircraft. The compass heading, i.e. the machine's yaw angle, is related on manet. North, is intended to be written on the horizontal as a numerical value, so that the pilot can read the compass heading in any position on the horizon. So lie the label information clearly fixed.

Only the movement information can be added. For the pilot are mainly three siblings from maresse, namely the airplane festivals in the coordinate system (variometer display), the ground speed by amount and direction and the incident flow velocity. On the screen 4 of the cathode ray tube 3d reference synbols are drawn for flight guidance, in different ways Colors can appear to better match the various reference symbols among themselves to be able to distinguish and to make changes in scale clear. the zero point of the aircraft-fixed coordinate system (#, # -plane) is represented by an aircraft symbol 70 shown.

Arrow marks are used for pure rolling movements and for the variometer zero point 71, 71 'for reference. In the # # level there is a Radialfied 74 of 0 ° to 360 ° specified with an angular distance v <'n 100. The radii of -40 ° @@ 0 ° are drawn up over the horizon marks 72, 72 'and with the corresponding Abtriftwinkel # labeled and zaar except for ob - (i, which is the compass course mark 73 represents. The velocity vectors in the plane is a collentric field Circles 75 indicated. In order to be large enough for hovering and aerodynamic flight To obtain readable reference symbols, at least two speed standards are required available. This change in scale can be clearly seen by varying the circle colors do.

The references for the Flung necessary related information symbols on the screen recorded, the symbols by the endpoint coordinates with the corresponding Control voltages are given. The individual information symbols are in a Symbol generator of known type generated. The artificial horizon is. here with 77 indicated, which is in the form of a long-variable striclies in the upper part of the Picture tube is recorded and the angular position information with regard to roll and pitch axes reproduces. The variometer display 71, 71 'is by means of a horizontal line symbol 76 constant length moving across the scale. The target point 78 is indicated by an information symbol in the form of a cross, to which constant distance circles 79 are recorded. The distance circles show The given representation does not offer a defined scale only displays the distance information, it also conveys it to the pilot at the same time the impression of speed, as it is familiar from the practice of VTR flights. In order to better estimate the course abs, a north mark can be inserted, in the #, # -plane the current position of magnet. North indicates: She is represented by a straight line of constant length, which is at an angle # around the Origin rotates. The course indicated on the horizon line 77 appears on the screen also above the horizon above the mark of # -also in direction the longitudinal axis of the aircraft as a three-digit decimal number (73). By this digital indication allows a better differentiation of the individual information symbols reach. The speed display is a vector representation in the #, # coordinate system. The inflow velocity vector in aerodynamic flight is called a vertical bar 81 shown in the 5 »0 direction. It comes in the hover flight, i.e. in the jet-borne Flight, a further speed component added, whereby the ground speed as a vector addition of the inflow speed and wind speed, the is given by amount and angle, results. The ground velocity vector is represented here by the recording of a bar 82.

Another information symbol appears for the map course display recorded the screen that coincides in the direction with 129, of which Tip, however, falls on the course scale 77. Thus the drift angle and the map course read.

If the course is on the right course, the course line must pass through the target cross 78.

This gives the pilot control over the approach to the target at the same time. Is the above ground speed prescribed by amount and direction over the flight time and if the wind vector 84 varies over the flight path, the pilot can control can be made much easier if it receives a command signal that provides information about the indicating the required oll approach speed according to the amount and course is recorded. A circular information symbol 85 is provided for this recording, its Midpoint indicates the setpoint end point of the speed vector in the #, # -plane.

In Fig. 7, a complete instrument panel 9 is schematically with the corresponding screens 4 of the cathode ray tubes 3 to 3d shown, being the size of the instrument panel and the screens of the cathode ray tubes are shown approximately in an actual size ratio to one another. It is it can be seen from the illustration that the type of instrumentation shown is extremely clear, with the display of the flight guidance data for both the pilot as well as for the copilot: s by means of a cathode ray tube will can without affecting the overview of the display or representation.

In Fig. 8 a circuit is indicated schematically, with the help of which it is possible to use the individual systems 1, 2; 3 to 3d ft for recording the flight control or to exchange operational monitoring data with one another. Between the individuals Systems that Qe through a signal preparation 1 and an ini time division multiplex ark end s; cyclic scanning 2 are formed, a switching device 90 is used, with the help of which it is possible to control the level signals for the Xahtode ray tubes 3 to 3d optionally to be separated from each other at will. For example the deflection signals for the display of the information symbols on the screen 4 of the cathode ray tube 3s also in exchange on the screen of the cathode ray tube 3c can be recorded. There is thus the possibility of failure of one the cathode ray tubes which explored in a certain section of the flight information data on an incidental screen of one of the remaining cathode ray tubes eigh.,

Claims (19)

Claims: 1. Flight instrumentation with electronic display, whereby flohrore zeinzelininformation to information groups combined and on displayed on a screen of a Braun tube, characterized in that that all of the information quantities assigned to an announcement group are multiplexed in time scanned and, with regard to their location, suggestive of a reference in the aircraft corresponding point of the screen for representation and there related their shape, direction and size are shown. 2. Flight instrumentation according to claim 1, characterized in that the information sizes. on the picture link (s) (4) vectorially, e.g. for Thrust and speed, and / or scalar in the form of variable-length lines, z II for temperature, pressure and speed of the engine. 3. Flight instrumentation according to claim 1 and / or 2, characterized in that datL the vectorially represented information quantities (26, 26 ') for the engine thrust and pushing direction (pushing tube) and the information quantities displayed in akalar (20, 20 '; 21, 21'; 22, 22 ') for temperature, pressure and speed on a common Screen (4). 4. Flight instrumentation for aircraft with several engine systems on both sides of the aircraft longitudinal center plane according to claims 1 to 3, characterized thereby, that the information variables for the thrust vector of the individual propulsion systems through angles and variable lengths related to common reference symbols (8, 9, #) Lines (26, 26 ') are recorded on a screen (4). 5. Flight instruction for airplanes with several engine systems according to claim 1 to 4, characterized in that the information symbols (26, 26 ') for the thrust vector of the engines on one or the other side of the aircraft different symbols in the form of an aircraft reference symbol (8) as the origin rotating and variable-length lines (26 ') or loops (26) on a screen (4) can be recorded. 6. Flight instrumentation according to claim 1 to S, characterized in that that on the 13 screen (4) for the vector display for the thrust the speeds and the hot jet temperature of each of the engines represented by scalar form variable-length vertical lines (20, 20 '; 21, 21'; 22, 22 '), which by a go out to the corresponding reference symbols (12, 12 '; 14, 14 '; 15, 15 ') can be recorded on the screen (4). 7 flight instrumentation according to claim 1 to 6, characterized in that then the air inlet temperature on the same screen (4) of the cathode ray tube (3) into the drive system through scalar representation in the form of a horizontal extension variable-length information symbols (22, 22 ') are drawn out. 8. flight instrumentation according to claim 1 to 7, characterized gekenazea hnet, because 3 of the thrust electrical recording a thrust comparison between the Trieberken one and the other side indicating horizontally. Cathode ray tube screen (3) running information symbol (27) in the form of a coincident from a zero point with the origin of the vector representation (26, 26 ') in the Flugzesymbol (as) -after the one or the other side variable-length line symbol (27) is recorded. 9. Flight instrumentation according to Anspurch 1 to 8, marked thereby, that the reference and information symbols (L ', 9, @ or 26, 2G ') for specifying the thrust vector in the middle field of the screen (4) of the cathode ray tube (3) and the reference and information symbols (12, 12 '; 14, 14', 15, 15 '; or 20, 20 '; 21.21 '; 22, 22 ') for the speeds and hot-jet temperature accordingly the position of the engines on the aircraft on both sides of the reference or Information display of the thrust vector applied or recorded on the screen will. 10. Flight instrumentation according to claim t to 9, characterized in that that on the screen (4) a separate cathode @ beam tube (3b) for the system group "Fuel tanks" to an aircraft reference symbol (30), the location of the tanks in the aircraft after, meaningfully on the screen (4) reference symbols (31) applied, soie information symbols (32) associated therewith are recorded. 11. Flight instrumentation according to claim 1 to 10, characterized thereby, that the information symbols (32) in the form of 1 starting from a common zero line, The filling of the individual tanks indicating vertical line symbols variable in length on the screen (4) of the cathode ray tube (3D signed the. 12. Flight instrumentation according to claim 1 to ii, characterized in that that the aircraft symbol (30) or the reference and information symbols (31 or 32) for refueling a sicti perpendicular to the longitudinal axis of the aircraft symbol (30) and from this as a zero line to one side or the other, variable in length Information symbol (34) for the size of the roll moment on the aircraft on the screen is recorded to a reference symbol (33). 13. Flight instrumentation according to claim 1 to 12, characterized in that that on the screen (4) of a further cathode ray tube (3c) through vertical Variable information symbols (4E, 47, 48) the storage pressure of the chassis hydraulics and The brake pressure is indicated by horizontal, vertically changeable information symbols (49, 50) as well as through a flying eye symbol (39) angle changing area Bal @ en opposite (60, 610 the landing pitch of @andeklppen is recorded on the Bildssch @@ m. 14. Flight instrumentation according to claims 1 to 13, characterized in that that the reference symbols (36; 38; 40, 41, 42) and the associated information symbols (16, @@ 18, 19, 50; 52, 53, 51) for the accumulator pressure and the braking pressure of the position of the Landing gear parts (main and base landing gear) on the aircraft make sense accordingly to that rlas Fluzung representing reference symbol (39) on the screen (1) of the cathode ray tube (30) recorded or displayed in F flight instrumentation according to ANspr @ ch 1 to 14, characterized in that from the Fluzeugreferenaxymbol (39), antsprel @ der Position of the landing gear on the aircraft Information symbols (52, 53, 54; 57, 58, 59) in Form of vertical lines for the display of the training or Running-in process of the Undercarriage and the completion of the extension process by circle symbols at the end of the Lines are recorded on the screen. 16. Flight instrumentation according to claim 1 to 15, characterized in that that on the screen (4) another Sathode tranlrohre (3 d) for recording the flight guidance data reference symbols are plotted and that these reference symbols electronically generated information symbols overlay @ t t and recorded on the screen will. 17. Fluginstrunantierung close to claim 1 to 16, characterized in that that the reference symbols divided by an aircraft symbol (70) with a radially Field (74), marks (72, 72 ') representing the artificial horizon, a line marking for the., variable indicator (71, 71 '), arranged concentrically to the aircraft symbol (70) Geschqwindkgieitskrise (75) applied to the screen, and being in a certain area the radial lines emanating from the aircraft symbol (7 ') are extended and include the drift angle information (@) are labeled. 18. Flight instrumentation according to claim 1 to 17, characterized in that that the information sound symbols superimposed on the reference symbols by one of the artificial Hortont line (77), a vertically movable line marking (76) for the variometer, a point (78} with concentric circles of distance (79), aine @@ rdmarke for specifying the course as a straight line of constant length, which drifts around its origin, a digigale @@ gasbe of the compass course (73), a the flight speed vector as well as one of the Übergundgeschwingkeite i t vek t only In the vicinity of the F aircraft symbol (70), mutable long stroke symbols (81 or 82) and a variable length associated with di @ sen, the free ends the dashes for the vector r Übergundgeschwindkgiekit and the vector of the airspeed connecting line symbol (84) for the wind vector, as well as by one with the above ground speed vector (82) coincide in position and direction, but extended beyond this Line for the indication of the card shape (#) and through in the form of a nominal circle mark (85) for the necessary Solanstrpmeschwinkkgiet according to amount and rurs on the screen are recorded. 19. to F Fluginstrumentieurng according to claim 1 to 18, characterized in that that a Umsteuerainrcihung (90) between the signal conditioners (1) and associated @ Time-division multiplexed cyclic scanners (2) and associated cathode tubes (3 to 3d) is switched on, 80 that each of the signal preparations (1) and cyclic Samples (2) can be assigned to any one of the cathode ray tubes (3 to 3d) can.