EP1604324B1 - Flight computer - Google Patents

Flight computer Download PDF

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Publication number
EP1604324B1
EP1604324B1 EP05716035A EP05716035A EP1604324B1 EP 1604324 B1 EP1604324 B1 EP 1604324B1 EP 05716035 A EP05716035 A EP 05716035A EP 05716035 A EP05716035 A EP 05716035A EP 1604324 B1 EP1604324 B1 EP 1604324B1
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EP
European Patent Office
Prior art keywords
plate
scaling
base plate
flight computer
computer according
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EP05716035A
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German (de)
French (fr)
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EP1604324A1 (en
Inventor
Harald Riehle
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Iwa-F Riehle & Co KG GmbH
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Iwa-F Riehle & Co KG GmbH
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Publication of EP1604324A1 publication Critical patent/EP1604324A1/en
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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06G—ANALOGUE COMPUTERS
    • G06G1/00—Hand manipulated computing devices
    • G06G1/0005—Hand manipulated computing devices characterised by a specific application
    • G06G1/0052—Hand manipulated computing devices characterised by a specific application for air navigation or sea navigation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06G—ANALOGUE COMPUTERS
    • G06G1/00—Hand manipulated computing devices
    • G06G1/02—Devices in which computing is effected by adding, subtracting, or comparing lengths of parallel or concentric graduated scales
    • G06G1/04—Devices in which computing is effected by adding, subtracting, or comparing lengths of parallel or concentric graduated scales characterised by construction
    • G06G1/08—Devices in which computing is effected by adding, subtracting, or comparing lengths of parallel or concentric graduated scales characterised by construction with circular or helical scales

Definitions

  • the invention relates to a flight computer comprising a base plate having a first airspeed scaling with a second plate rotatable relative to the base plate and positionable with respect to a second altitude scale indicative of the base plate and having a third scale representing the instrumentally measured one Speed, said third scale of the second plate at the same time forms a Ableseindizierung for the first scaling of the base plate, so that there is a first corrected speed readable, and with a third relative to the base plate rotatable plate with a Ableseindiz réelle.
  • Flight computers which are formed from one or more mutually movable, in particular rotatable plates with scales, are known, they serve, similar to the function of a slide rule, for calculating a variety of sizes and parameter values required for navigation purposes. For example, it is necessary to correct the airspeed determined by pitot tube measurements in various respects. At airspeeds greater than 200 knots and altitude above about 10,000 feet, such a correction is of great importance. It is not only the speed and altitude, but also the temperature of the outside air is important.
  • a flight computer of the type indicated above is known under the trade name "ARC-2" AFE.
  • the document US-A-2,585,618 discloses such a flight computer.
  • the second plate is positioned relative to the base plate, relative to the second scale according to the determined by instruments altitude of the aircraft and according to the measured outside temperature.
  • the third scale of the second plate is then used to read a first corrected velocity on the first scale of the base plate by correcting the first according to instrument velocity at the respective third scale value (as read indication) on the first scale of the base plate Read speed value. Then an arithmetic operation has to be performed in the head, namely extended, where x represents the first corrected velocity.
  • the second plate must then be rotated again in a predetermined direction according to a further scaling, and it can in turn be read on the basis of the third scale of the second plate (as Ableseindiztechnik) at the first scale of the base plate, a second corrected speed value become.
  • the third plate rotatable relative to the base plate is merely a tongue-shaped segment having a straight radial line as a reading indication which can be used for a number of readings.
  • the present invention has the object to provide a flight computer, in which the number of adjustment steps between the base plate and the first plate is reduced and in which the number or scope of the user to be initiated considerations is reduced.
  • the flight computer should therefore be easier to use overall.
  • a further, third plate with a fourth scale is provided, with the aim that the second plate needs to be positioned only once against the base plate.
  • a correction factor which depends on the altitude and the first corrected speed can be found on the fourth scale.
  • the second corrected velocity at the corresponding location of the fourth scale of the third plate (as Ableseindiztechnik for the first scaling) of the first scaling be read. So it does not have to be carried out the difficult calculation as in the known flight computer and then again the first plate against the base plate to be twisted.
  • the third plate has a scaling, namely the claimed fourth scaling, which at the same time functions as read-out indexing for the first scaling.
  • said correction factor can be determined in any desired manner, in particular can be read from a table of contents.
  • This formed as an information carrier area of the second plate may advantageously be formed or arranged concentrically to the pivot point of the second plate.
  • the trained as an information carrier area of the second plate can also be arranged überdeckbar from the third plate, in which case the third plate is transparent in the region of the overlap or has a recess which allows inspection of the trained as an information carrier area.
  • the region of the second plate designed as an information carrier is arranged radially within all scales.
  • the region of the second plate designed as an information carrier has a plurality of visually recognizable circular segment sectors, which are assigned by extension to radially outward regions on the third scale of the second plate.
  • certain information for example correction values corresponding to an area on the third scale, that is to say, for example, a speed range of 325 to 375 nodes, can be provided in the relevant pie-segment sector.
  • the user then only needs to go radially inward from the region of interest on the third scale and to read off corresponding information in the circular segment sector of the information carrier provided radially inwardly.
  • all plates have a common pivot point.
  • the first scale of the base plate is advantageously arranged radially outside the third scale of the second plate, which makes the reading of a final value appear pleasant.
  • the second plate extends radially outward beyond the first scale of the base plate. It is transparent in the overlap area with the first scale of the base plate. In this way, the ingress of dirt can be better prevented and the first scaling and the third scaling can be arranged so that they directly adjoin one another in the plan view.
  • the third plate extends radially outward beyond the first scale of the base plate. Its fourth scaling can then be arranged in a corresponding manner, at least as far as directly to the first scaling, in order to achieve the reading, that is to say the second scaling. H. to increase the reading comfort and the reading accuracy.
  • a peripheral edge of the third plate terminates radially outwardly with a peripheral edge of the second plate.
  • the base plate has a slot-shaped recess in which a slide tongue can be moved back and forth.
  • this slide tongue coordinates can be determined over the distance traveled in a conventional manner from the determined and corrected airspeeds.
  • the spring element may be formed by a spring tongue, which is integrally formed from the material of the base plate or an intermediate layer of the base plate with this.
  • the spring tongue can be formed out of the material by milling.
  • the spring tongue can be spaced from the rest of the material of the intermediate layer or the base plate by a relatively narrow slot extending in the displacement direction, but be flexibly connected to the intermediate layer or the base plate with a root section.
  • FIG. 1 shows a plan view of a generally designated by the reference numeral 2 flight computer, wherein only the components of the flight computer in connection with the present invention will be described below.
  • the flight computer 2 comprises a base plate 4 in the form of a laminate with a slot-shaped recess in which a rectangular slide tongue 6 can be moved back and forth.
  • a circular disk-shaped second plate 8 is provided, which is pivotally arranged at its center 10 to the first plate 4, and a third plate 22 described below.
  • the first plate 4 carries in the circumferential direction a first scale 12, which denotes the airspeed. Furthermore, the first plate 4 carries a second scale 14 in the overlap region with the second plate 8, ie in the region below this second plate 8, which second scale 14 denotes the flying height.
  • the second plate 8 is rotated or positioned relative to the first plate 4 so that a correspondence to the instrumentally determined and displayed in the aircraft altitude, optionally and preferably at the same time taking into account the instrumentally determined outside temperature is reached.
  • the second plate 8 also has, preferably in the radially outer region, a third scaling 16, which at the same time forms a read-off index 18 to the first scaling 12 of the base plate 4, so that a first corrected velocity can be read there.
  • the reading is done using the flight computer such that the instrumentally measured and displayed speed on the third scale 16 is used as Ableseindiztechnik 18 for the first corrected speed on the first scale 12 of the base plate 4.
  • the second plate 8 in the above-mentioned positioning of the second plate 8 relative to the base plate 4 not only the instrumentally determined altitude, for example according to the barometric altitude formula, is taken into account when positioning relative to the second scale 14, but also the outside temperature, preferably is arranged on a temperature scale 19 at the edge of a window 20 in the second plate 8.
  • a third plate 22 is provided, which may be a transparent circular disk or, as in the case shown, a segment which is preferably opposite the center 10 of the second plate 8, ie with the same pivot 10 as the second plate 8, relative to the base plate 4 and the second plate 8 can be rotatably arranged.
  • This third plate 22 has a fourth scaling 24, this fourth scaling 24 at the same time forming a read-out index 26 to the first scaling 12.
  • the third plate 22 also has a further readout index 28 extending in the radial direction, which, however, is not absolutely necessary. By means of this further read-off indexing 28, the third plate can be positioned with respect to the third scale 16 of the second plate 8 such that the instrumentally determined speed value corresponds to the position of the further read-out device 28 at the third scale 16.
  • the final speed value can now be read as the second corrected velocity from the first scaling 12 of the base plate 4.
  • the fourth scale 24 corresponds to the correction factors that could be taken from a separate table to this flight computer.
  • an area 30 of the second plate 8 is designed as an information carrier 32, with the information stored there being straight the correction factor corresponding to the fourth scale 24 include.
  • a correction value can be read from the information carrier 32, a correction value.
  • the final second corrected velocity value at the first scaling 12 can then be read as a read-out index 26 at the corresponding position of the fourth scaling 24.
  • the second plate 8 needs to be positioned only once against the first plate 4 and that in contrast to known Flight computers no additional arithmetic tasks must be performed, which then lead to a repositioning or adjustment of the second plate 8 relative to the first plate 4. Rather, it is sufficient to read out from the information carrier 32 a corresponding correction value (which, however, can also be determined in another way) and to read the second corrected speed value in accordance with this value by the fourth scaling 24 at the first scaling 12.
  • the flight computer according to the invention is Determine true airspeed against air ("True Air Speed") as follows.
  • the second plate 8 is rotated relative to the base plate 4, that in the window 20 in the second plate 8, the second scale 14 and the temperature scale 19 are positioned to each other such that the value of - 40 ° C exactly at the instrumental altitude of 30,000 Foot is adjusted.
  • the third plate 22 can now be positioned opposite the two plates 4, 8 such that its further read indicia 28 is set exactly on the third scale 16 of the second plate 8 at 30 (ie 300 knots).
  • a first corrected speed determined which is then subjected to an arithmetic operation and again for further determination of the true speed requires further adjustment of the plates to each other, but it is read on the information carrier 32, a correction value .
  • the information carrier 32 is subdivided into circular segment-shaped sectors 40, which are arranged such that a respective sector comprises the flying height-dependent correction values which are assigned to the airspeeds further specified radially on the outside of the third scaling 16.
  • the user can then at the corresponding altitude of 30,000 feet read a correction value of 0.95
  • the correction values thus determined are arranged on the fourth scale 24 of the third plate 22 and can be used as read-out index 26 for the first scaling 12.
  • the user is given a correction value of 0, 95 on the fourth scale 24 as Ableseindizierung 26 then read on the first scale 12 is a true speed value of 470 nodes ("True Air Speed").
  • the base plate 4 comprises a slot-shaped recess 42 in which the slide tongue 6 can be moved back and forth.
  • the slot-shaped recess 42 is formed between a front plate 44, a back plate 46 and two portions of an intermediate plate 48.
  • the two sections of the intermediate plate 48 are, as is apparent from Figures 2 and 3, with extending in the direction of longitudinal guide walls 50 and 52, the parallel extending portions are slightly further apart than the slide tongue 6 is wide.
  • two spring elements 54 are provided in the slot-shaped recess 42, which preload the slide tongue 6 against the opposite longitudinal guide wall 50.
  • the spring elements 54 are formed by spring tongues 56 which are formed from the material of the intermediate layer 48 and integral therewith.
  • spring tongues 56 which are formed from the material of the intermediate layer 48 and integral therewith.
  • a piece of the intermediate layer 48 originally formed from bow and tendon has been milled until it has the apparent form of Figure 2, wherein between the spring tongues 56 and the remaining material of the intermediate layer 48 a relatively thin slot 58 extended in the displacement direction has been introduced and the respective spring tongue 56 protrudes with its contact region 59 to the slide tongue 6 via the recessed longitudinal guide wall 52 formed.

Abstract

The invention relates to a flight computer comprising a base plate (2) provided with a first flying speed scaling (12), a second plate (8) which is rotatable with respect to the base plate (2) and can be positioned against the second scaling (14) of the base plate displaying a flight altitude and provided with a third scaling (16) displaying the speed measured by instruments, wherein said third scaling (16) of the second plate (8) forms at the same time a readout indexing (18) for the first scaling (12) of the base plate (2) in such a way that it is possible to read a first corrected speed and the third plate (22) which is rotatable with respect to the base plate (2) and provided with a readout indexing. The aim of said invention is to facilitate the operation of the flight computer. For this purpose, the inventive computer is characterised in that a third plate (22) is provided with a fourth scaling (24) which forms at the same time a readout indexing (26) for the first scaling (12) in such a way that it is possible to read a second corrected speed.

Description

Die Erfindung betrifft einen Flugrechner, mit einer Basisplatte, die eine erste Skalierung für die Fluggeschwindigkeit aufweist, mit einer gegenüber der Basisplatte verdrehbaren zweiten Platte, die gegenüber einer zweiten die Flughöhe bezeichnenden Skalierung der Basisplatte positionierbar ist und eine dritte Skalierung aufweist, die die instrumentell gemessene Geschwindigkeit bezeichnet, wobei diese dritte Skalierung der zweiten Platte zugleich eine Ableseindizierung zur ersten Skalierung der Basisplatte bildet, so dass dort eine erste korrigierte Geschwindigkeit ablesbar ist, und mit einer dritten gegenüber der Basisplatte verdrehbaren Platte mit einer Ableseindizierung.The invention relates to a flight computer comprising a base plate having a first airspeed scaling with a second plate rotatable relative to the base plate and positionable with respect to a second altitude scale indicative of the base plate and having a third scale representing the instrumentally measured one Speed, said third scale of the second plate at the same time forms a Ableseindizierung for the first scaling of the base plate, so that there is a first corrected speed readable, and with a third relative to the base plate rotatable plate with a Ableseindizierung.

Flugrechner, die aus einer oder mehreren gegeneinander bewegbaren, insbesondere verdrehbaren Platten mit Skalierungen gebildet sind, sind bekannt, sie dienen, ähnlich der Funktion eines Rechenschiebers, zur Errechnung einer Vielzahl von zu Navigationszwecken erforderlichen Größen und Parameterwerten. Beispielsweise ist es erforderlich, die durch Staurohrmessungen ermittelte Fluggeschwindigkeit in verschiedener Hinsicht zu korrigieren. Bei Fluggeschwindigkeiten von mehr als 200 Knoten und einer Flughöhe von oberhalb etwa 10 000 Fuß ist eine solche Korrektur von großer Bedeutung. Dabei ist nicht nur die Fluggeschwindigkeit und Flughöhe, sondern auch die Temperatur der Außenluft von Bedeutung.Flight computers, which are formed from one or more mutually movable, in particular rotatable plates with scales, are known, they serve, similar to the function of a slide rule, for calculating a variety of sizes and parameter values required for navigation purposes. For example, it is necessary to correct the airspeed determined by pitot tube measurements in various respects. At airspeeds greater than 200 knots and altitude above about 10,000 feet, such a correction is of great importance. It is not only the speed and altitude, but also the temperature of the outside air is important.

Ein Flugrechner der vorausgehend angegebenen Art ist unter dem Handelsnamen "ARC-2" der Firma AFE bekannt. Das dokument US-A-2 585 618 offenbart einen solchen flugrechner. Bei diesem Flugrechner wird die zweite Platte gegenüber der Basisplatte positioniert, und zwar gegenüber der zweiten Skalierung entsprechend der durch Instrumente bestimmten Flughöhe des Flugzeugs und entsprechend der gemessenen Außentemperatur. Über die dritte Skalierung der zweiten Platte wird dann eine erste korrigierte Geschwindigkeit auf der ersten Skalierung der Basisplatte abgelesen, indem der Benutzer entsprechend der durch Instrumente bestimmten Fluggeschwindigkeit an dem betreffenden Wert der dritten Skalierung (als Ableseindizierung) auf der ersten Skalierung der Basisplatte den ersten korrigierten Geschwindigkeitswert abliest. Es muss dann eine Rechenoperation im Kopf durchgeführt werden, nämlich (...), wobei x die erste korrigierte Geschwindigkeit darstellt. Entsprechend dem sich hieraus ergebenden Wert muss die zweite Platte dann erneut in eine vorgegebene Richtung entsprechend einer weiteren Skalierung verdreht werden, und es kann dann wiederum anhand der dritten Skalierung der zweiten Platte (als Ableseindizierung) an der ersten Skalierung der Basisplatte ein zweiter korrigierter Geschwindigkeitswert abgelesen werden.A flight computer of the type indicated above is known under the trade name "ARC-2" AFE. The document US-A-2,585,618 discloses such a flight computer. In this Flight computer, the second plate is positioned relative to the base plate, relative to the second scale according to the determined by instruments altitude of the aircraft and according to the measured outside temperature. The third scale of the second plate is then used to read a first corrected velocity on the first scale of the base plate by correcting the first according to instrument velocity at the respective third scale value (as read indication) on the first scale of the base plate Read speed value. Then an arithmetic operation has to be performed in the head, namely (...), where x represents the first corrected velocity. Corresponding to the resulting value, the second plate must then be rotated again in a predetermined direction according to a further scaling, and it can in turn be read on the basis of the third scale of the second plate (as Ableseindizierung) at the first scale of the base plate, a second corrected speed value become.

Es sind also mehrere Einstellungsschritte bzw. Einstellungsmaßnahmen zwischen der Basisplatte und der ersten Platte erforderlich. Die dritte gegenüber der Basisplatte verdrehbare Platte ist lediglich ein zungenförmiges Segment mit einer geraden in radialer Richtung verlaufenden Linie als Ableseindizierung, die für eine Anzahl von Ablesevorgängen verwendet werden kann.So there are several adjustment steps or adjustment measures between the base plate and the first plate required. The third plate rotatable relative to the base plate is merely a tongue-shaped segment having a straight radial line as a reading indication which can be used for a number of readings.

Hiervon ausgehend liegt der vorliegenden Erfindung die Aufgabe zugrunde, einen Flugrechner zu schaffen, bei dem die Zahl der Einstellungsschritte zwischen der Basisplatte und der ersten Platte reduziert ist und bei dem die Anzahl bzw. der Umfang der vom Benutzer anzustellenden Überlegungen reduziert ist. Der Flugrechner soll also insgesamt leichter bedienbar sein.On this basis, the present invention has the object to provide a flight computer, in which the number of adjustment steps between the base plate and the first plate is reduced and in which the number or scope of the user to be initiated considerations is reduced. The flight computer should therefore be easier to use overall.

Diese Aufgabe wird bei einem Flugrechner der genannten Art erfindungsgemäß dadurch gelöst, dass die dritte Platte eine vierte Skalierung aufweist und diese vierte Skalierung zugleich eine Ableseindizierung zur ersten Skalierung bildet, so dass dort eine zweite korrigierte Geschwindigkeit ablesbar ist.This object is achieved according to the invention in a flight computer of the type mentioned in that the third plate has a fourth scaling and this fourth scaling at the same time forms a Ableseindizierung the first scaling, so that there is a second corrected speed can be read.

Es wird also erfindungsgemäß vorgeschlagen, dass zusätzlich zu der zweiten Platte eine weitere, dritte Platte mit einer vierten Skalierung vorgesehen wird, mit dem Ziel, dass die zweite Platte nur ein einziges Mal gegenüber der Basisplatte positioniert zu werden braucht. Ein von der Flughöhe und der ersten korrigierten Geschwindigkeit abhängiger Korrekturfaktor findet sich nämlich auf der vierten Skalierung wieder. Nach Ermittlung der ersten korrigierten Geschwindigkeit kann nach (an sich beliebiger) Ermittlung eines hiervon abhängigen Korrekturfaktors, insbesondere von einer separaten Tabelle, direkt die zweite korrigierte Geschwindigkeit an entsprechender Stelle der vierten Skalierung der dritten Platte (als Ableseindizierung zur ersten Skalierung) von der ersten Skalierung abgelesen werden. Es muss also nicht die schwierige Berechnung wie bei dem bekannten Flugrechner durchgeführt werden und anschließend noch einmal die erste Platte gegenüber der Basisplatte verdreht werden. Dies wird erfindungsgemäß dadurch umgangen, dass die dritte Platte eine Skalierung, nämlich die anspruchsgemäße vierte Skalierung aufweist, die zugleich als Ableseindizierung zur ersten Skalierung fungiert.It is therefore proposed according to the invention that, in addition to the second plate, a further, third plate with a fourth scale is provided, with the aim that the second plate needs to be positioned only once against the base plate. Namely, a correction factor which depends on the altitude and the first corrected speed can be found on the fourth scale. After determination of the first corrected velocity, after (any) determination of a correction factor dependent thereon, in particular from a separate table, directly the second corrected velocity at the corresponding location of the fourth scale of the third plate (as Ableseindizierung for the first scaling) of the first scaling be read. So it does not have to be carried out the difficult calculation as in the known flight computer and then again the first plate against the base plate to be twisted. This is avoided according to the invention in that the third plate has a scaling, namely the claimed fourth scaling, which at the same time functions as read-out indexing for the first scaling.

Es wurde bereits darauf hingewiesen, dass der genannte Korrekturfaktor in beliebiger Weise ermittelt werden kann, insbesondere aus einem mitgeführten Tabellenwerk abgelesen werden kann. In Weiterbildung der Erfindung erweist es sich aber als vorteilhaft, wenn ein Bereich der zweiten Platte als Informationsträger ausgebildet ist und die dort hinterlegten Informationen mit der vierten Skalierung der dritten Platte korrespondieren.It has already been pointed out that said correction factor can be determined in any desired manner, in particular can be read from a table of contents. In a further development of the invention, it proves to be advantageous if an area of the second plate as Information carrier is formed and the information stored there correspond with the fourth scale of the third plate.

Dieser als Informationsträger ausgebildete Bereich der zweiten Platte kann vorteilhafterweise konzentrisch zum Drehpunkt der zweiten Platte ausgebildet oder angeordnet sein.This formed as an information carrier area of the second plate may advantageously be formed or arranged concentrically to the pivot point of the second plate.

Der als Informationsträger ausgebildete Bereich der zweiten Platte kann auch von der dritten Platte überdeckbar angeordnet sein, wobei solchenfalls die dritte Platte im Bereich der Überdeckung durchsichtig ausgebildet ist oder eine Ausnehmung besitzt, die eine Einsichtnahme auf den als Informationsträger ausgebildeten Bereich gestattet.The trained as an information carrier area of the second plate can also be arranged überdeckbar from the third plate, in which case the third plate is transparent in the region of the overlap or has a recess which allows inspection of the trained as an information carrier area.

Des Weiteren erweist es sich als vorteilhaft, wenn der als Informationsträger ausgebildete Bereich der zweiten Platte radial innerhalb aller Skalierungen angeordnet ist.Furthermore, it proves to be advantageous if the region of the second plate designed as an information carrier is arranged radially within all scales.

Es erweist sich des Weiteren als ganz besonders vorteilhaft, wenn der als Informationsträger ausgebildete Bereich der zweiten Platte mehrere visuell erkennbare Kreissegmentsektoren aufweist, die durch Verlängerung nach radial außen Bereichen auf der dritten Skalierung der zweiten Platte zugeordnet sind. Solchenfalls können nämlich bestimmte Informationen, beispielsweise Korrekturwerte, die einem Bereich auf der dritten Skalierung entsprechen, also beispielsweise einem Geschwindigkeitsbereich von 325 bis 375 Knoten in dem betreffenden Kreissegmentsektor vorgesehen werden. Der Benutzer braucht dann von dem gerade interessierenden Bereich auf der dritten Skalierung lediglich nach radial innen zu gehen und in dem radial innen vorgesehenen Kreissegmentsektor des Informationsträgers eine entsprechende Information abzulesen.Furthermore, it proves to be particularly advantageous if the region of the second plate designed as an information carrier has a plurality of visually recognizable circular segment sectors, which are assigned by extension to radially outward regions on the third scale of the second plate. In that case, certain information, for example correction values corresponding to an area on the third scale, that is to say, for example, a speed range of 325 to 375 nodes, can be provided in the relevant pie-segment sector. The user then only needs to go radially inward from the region of interest on the third scale and to read off corresponding information in the circular segment sector of the information carrier provided radially inwardly.

Vorteilhafterweise weisen alle Platten einen gemeinsamen Drehpunkt auf.Advantageously, all plates have a common pivot point.

Die erste Skalierung der Basisplatte ist vorteilhafterweise radial außerhalb der dritten Skalierung der zweiten Platte angeordnet, was die Ablesung eines schlussendlichen Werts als angenehm erscheinen lässt.The first scale of the base plate is advantageously arranged radially outside the third scale of the second plate, which makes the reading of a final value appear pleasant.

Des Weiteren erweist es sich als besonders vorteilhaft, wenn die zweite Platte sich nach radial außen bis über die erste Skalierung der Basisplatte erstreckt. Sie ist im Überlappungsbereich mit der ersten Skalierung der Basisplatte durchsichtig ausgebildet. Auf diese Weise kann das Eindringen von Schmutz besser verhindert werden und die erste Skalierung und die dritte Skalierung können so angeordnet werden, dass sie in der Draufsicht unmittelbar aneinander angrenzen.Furthermore, it proves to be particularly advantageous if the second plate extends radially outward beyond the first scale of the base plate. It is transparent in the overlap area with the first scale of the base plate. In this way, the ingress of dirt can be better prevented and the first scaling and the third scaling can be arranged so that they directly adjoin one another in the plan view.

Es erweist sich auch als vorteilhaft, wenn sich die dritte Platte nach radial außen bis über die erste Skalierung der Basisplatte erstreckt. Deren vierte Skalierung kann dann in entsprechender Weise wenigstens bis unmittelbar an die erste Skalierung heranreichend angeordnet werden, um die Ablesung, d. h. den Ablesekomfort und die Ablesegenauigkeit zu erhöhen.It also proves to be advantageous if the third plate extends radially outward beyond the first scale of the base plate. Its fourth scaling can then be arranged in a corresponding manner, at least as far as directly to the first scaling, in order to achieve the reading, that is to say the second scaling. H. to increase the reading comfort and the reading accuracy.

Auch erweist es sich als vorteilhaft, wenn ein Umfangsrand der dritten Platte radial außen mit einem Umfangsrand der zweiten Platte abschließt.It also proves to be advantageous if a peripheral edge of the third plate terminates radially outwardly with a peripheral edge of the second plate.

In besonders vorteilhafter Weiterbildung des erfindungsgemäßen Flugrechners weist die Basisplatte eine schlitzförmige Ausnehmung auf, in der eine Schieberzunge hin-und herverschiebbar ist. Mittels dieser Schieberzunge können in an sich bekannter Weise aus den ermittelten und korrigierten Fluggeschwindigkeiten Koordinaten über die zurückgelegte Flugstrecke ermittelt werden. Es wird nun vorgeschlagen, dass in der schlitzförmigen Ausnehmung wenigstens ein Federelement vorgesehen ist, welches die Schieberzunge spielfrei und dennoch leichtgängig in der schlitzförmigen Ausnehmung verschiebbar führt. In Weiterbildung dieses Erfindungsgedankens kann das Federelement von einer Federzunge gebildet sein, die aus dem Material der Basisplatte oder einer Zwischenlage der Basisplatte einstückig mit dieser geformt ist. Beispielsweise kann die Federzunge aus dem Material durch Fräsen herausgeformt werden. Hierdurch kann die Federzunge durch einen in Verschieberichtung erstreckten verhältnismäßig schmalen Schlitz vom übrigen Material der Zwischenlage oder der Basisplatte beabstandet sein, jedoch mit einem Wurzelabschnitt biegsam an die Zwischenlage oder die Basisplatte angebunden sein. Mit der vorstehend beschriebenen erfindungsgemäßen Weiterbildung des Flugrechners kann ein hoher Bedienkomfort erreicht werden, weil die Basisplatte einerseits leicht in der schlitzförmigen Ausnehmung verschiebbar ist; sie ist aber dennoch so spielfrei und widerstandsbehaftet geführt, dass ein unbeabsichtigtes Verstellen weitgehend verhindert werden kann.In a particularly advantageous development of the flight computer according to the invention, the base plate has a slot-shaped recess in which a slide tongue can be moved back and forth. By means of this slide tongue coordinates can be determined over the distance traveled in a conventional manner from the determined and corrected airspeeds. It is now proposed that in the slot-shaped recess at least one spring element is provided, which guides the slide tongue without play and yet smoothly displaceable in the slot-shaped recess. In development of this invention, the spring element may be formed by a spring tongue, which is integrally formed from the material of the base plate or an intermediate layer of the base plate with this. For example, the spring tongue can be formed out of the material by milling. In this way, the spring tongue can be spaced from the rest of the material of the intermediate layer or the base plate by a relatively narrow slot extending in the displacement direction, but be flexibly connected to the intermediate layer or the base plate with a root section. With the development of the flight computer according to the invention described above, a high level of operating comfort can be achieved, because the base plate on the one hand easily slidable in the slot-shaped recess; but it is still so backlash-free and resistive led that accidental adjustment can be largely prevented.

Weitere Merkmale, Einzelheiten und Vorteile der Erfindung ergeben sich aus der zeichnerischen Darstellung und nachfolgenden Beschreibung einer bevorzugten Ausführungsform der Erfindung. In der Zeichnung zeigt:

Figur 1
eine Draufsicht auf den erfindungsgemäßen Flugrechner;
Figur 2
eine Draufsicht auf den erfindungsgemäßen Flugrechner (unter Weglassung der zweiten Platte und teilweiser Weglassung der Basisplatte) ; und
Figur 3
eine Schnittansicht nur durch die Basisplatte.
Further features, details and advantages of the invention will become apparent from the drawings and the following description of a preferred embodiment of the invention. In the drawing shows:
FIG. 1
a plan view of the flight computer according to the invention;
FIG. 2
a plan view of the flight computer according to the invention (omitting the second plate and partial omission of the base plate); and
FIG. 3
a sectional view only through the base plate.

Figur 1 zeigt eine Draufsicht auf einen insgesamt mit dem Bezugszeichen 2 bezeichneten Flugrechner, wobei nachfolgend nur die im Zusammenhang mit der vorliegenden Erfindung stehenden Komponenten des Flugrechners beschrieben werden. Der Flugrechner 2 umfasst eine Basisplatte 4 in Form eines Laminats mit einer schlitzförmigen Ausnehmung, in welcher eine rechteckförmige Schieberzunge 6 hin- und herbewegbar ist. Oberhalb der Basisplatte 4 ist eine kreisscheibenförmige zweite Platte 8 vorgesehen, die in ihrem Mittelpunkt 10 drehgelenkig zur ersten Platte 4 angeordnet ist, und eine weiter unten beschriebene dritte Platte 22.Figure 1 shows a plan view of a generally designated by the reference numeral 2 flight computer, wherein only the components of the flight computer in connection with the present invention will be described below. The flight computer 2 comprises a base plate 4 in the form of a laminate with a slot-shaped recess in which a rectangular slide tongue 6 can be moved back and forth. Above the base plate 4, a circular disk-shaped second plate 8 is provided, which is pivotally arranged at its center 10 to the first plate 4, and a third plate 22 described below.

Die erste Platte 4 trägt in Umfangsrichtung eine erste Skalierung 12, welche die Fluggeschwindigkeit bezeichnet. Ferner trägt die erste Platte 4 eine zweite Skalierung 14 im Überdeckungsbereich mit der zweiten Platte 8, also im Bereich unterhalb dieser zweiten Platte 8, welche zweite Skalierung 14 die Flughöhe bezeichnet. Bei Benutzung des Flugrechners wird die zweite Platte 8 so gegenüber der ersten Platte 4 verdreht bzw. positioniert, dass eine Entsprechung zur instrumentell bestimmten und im Flugzeug angezeigten Flughöhe, gegebenenfalls und vorzugsweise zugleich unter Berücksichtigung der instrumentell ermittelten Außentemperatur erreicht wird.The first plate 4 carries in the circumferential direction a first scale 12, which denotes the airspeed. Furthermore, the first plate 4 carries a second scale 14 in the overlap region with the second plate 8, ie in the region below this second plate 8, which second scale 14 denotes the flying height. When using the flight computer, the second plate 8 is rotated or positioned relative to the first plate 4 so that a correspondence to the instrumentally determined and displayed in the aircraft altitude, optionally and preferably at the same time taking into account the instrumentally determined outside temperature is reached.

Die zweite Platte 8 weist ferner und vorzugsweise im radial äußeren Bereich eine dritte Skalierung 16 auf, die zugleich eine Ableseindizierung 18 zur ersten Skalierung 12 der Basisplatte 4 bildet, so dass dort eine erste korrigierte Geschwindigkeit ablesbar ist. Die Ablesung erfolgt dabei bei Benutzung des Flugrechners derart, dass die instrumentell gemessene und angezeigte Geschwindigkeit auf der dritten Skalierung 16 als Ableseindizierung 18 für die erste korrigierte Geschwindigkeit auf der ersten Skalierung 12 der Basisplatte 4 verwendet wird.The second plate 8 also has, preferably in the radially outer region, a third scaling 16, which at the same time forms a read-off index 18 to the first scaling 12 of the base plate 4, so that a first corrected velocity can be read there. The reading is done using the flight computer such that the instrumentally measured and displayed speed on the third scale 16 is used as Ableseindizierung 18 for the first corrected speed on the first scale 12 of the base plate 4.

Es wird noch darauf hingewiesen, dass bei der vorstehend erwähnten Positionierung der zweiten Platte 8 gegenüber der Basisplatte 4 nicht nur die instrumentell ermittelte Flughöhe, beispielsweise nach der barometrischen Höhenformel, bei Positionierung gegenüber der zweiten Skalierung 14 berücksichtigt wird, sondern auch die Außentemperatur, die vorzugsweise auf einer Temperaturskalierung 19 am Rand eines Fensters 20 in der zweiten Platte 8 angeordnet ist.It should be noted that in the above-mentioned positioning of the second plate 8 relative to the base plate 4 not only the instrumentally determined altitude, for example according to the barometric altitude formula, is taken into account when positioning relative to the second scale 14, but also the outside temperature, preferably is arranged on a temperature scale 19 at the edge of a window 20 in the second plate 8.

Schließlich ist eine dritte Platte 22 vorgesehen, bei der es sich um eine transparente Kreisscheibe handeln kann oder aber, wie im dargestellten Fall, um ein Segment, welches vorzugsweise gegenüber dem Mittelpunkt 10 der zweiten Platte 8, also mit demselben Drehpunkt 10 wie die zweite Platte 8, gegenüber der Basisplatte 4 und der zweiten Platte 8 drehbar angeordnet sein kann. Diese dritte Platte 22 weist eine vierte Skalierung 24 auf, wobei diese vierte Skalierung 24 zugleich eine Ableseindizierung 26 zur ersten Skalierung 12 bildet. Die dritte Platte 22 weist ferner eine in radialer Richtung erstreckte weitere Ableseindizierung 28 auf, die jedoch nicht zwingend erforderlich ist. Vermittels dieser weiteren Ableseindizierung 28 kann die dritte Platte so bezüglich der dritten Skalierung 16 der zweiten Platte 8 positioniert werden, dass der instrumentell ermittelte Geschwindigkeitswert der Position der weiteren Ableseeinrichtung 28 an der dritten Skalierung 16 entspricht.Finally, a third plate 22 is provided, which may be a transparent circular disk or, as in the case shown, a segment which is preferably opposite the center 10 of the second plate 8, ie with the same pivot 10 as the second plate 8, relative to the base plate 4 and the second plate 8 can be rotatably arranged. This third plate 22 has a fourth scaling 24, this fourth scaling 24 at the same time forming a read-out index 26 to the first scaling 12. The third plate 22 also has a further readout index 28 extending in the radial direction, which, however, is not absolutely necessary. By means of this further read-off indexing 28, the third plate can be positioned with respect to the third scale 16 of the second plate 8 such that the instrumentally determined speed value corresponds to the position of the further read-out device 28 at the third scale 16.

Über die vierte Skalierung 24 uhd deren Ableseindizierung 26 zur ersten Skalierung 12 kann nun der schlussendliche Geschwindigkeitswert als zweite korrigierte Geschwindigkeit von der ersten Skalierung 12 der Basisplatte 4 abgelesen werden. Die vierte Skalierung 24 entspricht den Korrekturfaktoren, die einem separaten Tabellenwerk zu diesem Flugrechner entnommen werden könnten. Vorliegend ist jedoch ein Bereich 30 der zweiten Platte 8 als Informationsträger 32 ausgebildet, wobei die dort hinterlegten Informationen gerade den Korrekturfaktor, der mit der vierten Skalierung 24 korrespondiert, beinhalten. Je nach dem abgelesenen ersten korrigierten Geschwindigkeitswert und je nach Flughöhe kann aus dem Informationsträger 32 ein Korrekturwert abgelesen werden. Entsprechend diesem Korrekturwert kann dann an entsprechender Stelle der vierten Skalierung 24 als Ableseindizierung 26 der schlussendliche zweite korrigierte Geschwindigkeitswert an der ersten Skalierung 12 abgelesen werden.Via the fourth scaling 24 and its read-off indexing 26 to the first scaling 12, the final speed value can now be read as the second corrected velocity from the first scaling 12 of the base plate 4. The fourth scale 24 corresponds to the correction factors that could be taken from a separate table to this flight computer. In the present case, however, an area 30 of the second plate 8 is designed as an information carrier 32, with the information stored there being straight the correction factor corresponding to the fourth scale 24 include. Depending on the read first corrected speed value and depending on the altitude can be read from the information carrier 32, a correction value. Corresponding to this correction value, the final second corrected velocity value at the first scaling 12 can then be read as a read-out index 26 at the corresponding position of the fourth scaling 24.

Es erweist sich als besonders vorteilhaft, dass zur Ermittlung der zweifach korrigierten Geschwindigkeit, ausgehend von einer instrumentell, insbesondere durch Staudruckmessungen, ermittelten Geschwindigkeit, die zweite Platte 8 nur ein einziges Mal gegenüber der ersten Platte 4 positioniert zu werden braucht und dass im Unterschied zu bekannten Flugrechnern keine zusätzlichen Rechenaufgaben durchgeführt werden müssen, die dann zu einer erneuten Positionierung oder Verstellung der zweiten Platte 8 gegenüber der ersten Platte 4 führen. Es genügt vielmehr, aus dem Informationsträger 32 einen entsprechenden Korrekturwert auszulesen (der aber auch in sonstiger Weise ermittelt werden kann) und entsprechend diesem Wert durch die vierte Skalierung 24 an der ersten Skalierung 12 den zweiten korrigierten Geschwindigkeitswert abzulesen. Zuvor braucht nur die dritte Platte 22, vorzugsweise anhand der weiteren Ableseindizierung 28 an demjenigen Geschwindigkeitswert der dritten Skalierung 18 positioniert zu werden, der ursprünglich experimentell ermittelt und angezeigt wurde.It proves to be particularly advantageous that for determining the twice-corrected speed, starting from an instrumentally, in particular by dynamic pressure measurements, determined speed, the second plate 8 needs to be positioned only once against the first plate 4 and that in contrast to known Flight computers no additional arithmetic tasks must be performed, which then lead to a repositioning or adjustment of the second plate 8 relative to the first plate 4. Rather, it is sufficient to read out from the information carrier 32 a corresponding correction value (which, however, can also be determined in another way) and to read the second corrected speed value in accordance with this value by the fourth scaling 24 at the first scaling 12. Previously, only the third plate 22, preferably on the basis of the further read-off indexing 28, needs to be positioned at the speed value of the third scale 18 which was originally determined experimentally and displayed.

Nachfolgend sei ein Beispiel für die Bedienung des erfindungsgemäßen Flugrechners gegeben. Wenn eine Flughöhe von 30 000 Fuß und eine Außentemperatur von -40° C instrumentell im Flugzeug ermittelt wird und der Geschwindigkeitsmesser vermittels einer Staudruckmessung 300 Knoten anzeigt, so wird der erfindungsgemäße Flugrechner zur Ermittlung einer wahren Fluggeschwindigkeit gegenüber Luft ("True Air Speed") folgendermaßen benutzt. Die zweite Platte 8 wird so gegenüber der Basisplatte 4 verdreht, dass im Fenster 20 in der zweiten Platte 8 die zweite Skalierung 14 und die Temperaturskalierung 19 derart zueinander positioniert werden, dass der Wert von - 40° C genau bei der instrumentellen Flughöhe von 30 000 Fuß eingestellt wird. Es kann nun die dritte Platte 22 so gegenüber den beiden Platten 4, 8 positioniert werden, dass ihre weitere Ableseindizierung 28 genau auf der dritten Skalierung 16 der zweiten Platte 8 bei 30 (d. h. 300 Knoten) eingestellt wird. Es wird nun aber nicht, wie beim Stand der Technik, eine erste korrigierte Geschwindigkeit ermittelt, die dann einer Rechenoperation unterzogen wird und erneut zur weiteren Ermittlung der wahren Geschwindigkeit ein weiteres Verstellen der Platten zueinander erfordert, sondern es wird auf dem Informationsträger 32 ein Korrekturwert ausgelesen. Der Informationsträger 32 ist in kreissegmentförmige Sektoren 40 unterteilt, die so angeordnet sind, dass ein jeweiliger Sektor die flughöhenabhängigen Korrekturwerte umfasst, die den weiter radial außen auf der dritten Skalierung 16 angegebenen Fluggeschwindigkeiten zugeordnet sind. Ein Benutzer kann also in angenehmer Weise die weitere Ableseindizierung 28 nach radial innen in dem betreffenden Sektor verfolgen (hier im dargestellten Fall der Sektor 40 bei 300 Knoten Fluggeschwindigkeit (CAS = "Calibrated Air Speed"). Der Benutzer kann dann bei der entsprechenden Flughöhe von 30 000 Fuß einen Korrekturwert von 0,95 ablesen. Die so ermittelten Korrekturwerte sind auf der vierten Skalierung 24 der dritten Platte 22 angeordnet und können als Ableseindizierung 26 zur ersten Skalierung 12 verwendet werden. Im vorliegenden Fall wird der Benutzer bei einem Korrekturwert von 0,95 auf der vierten Skalierung 24 als Ableseindizierung 26 dann auf der ersten Skalierung 12 einen wahren Geschwindigkeitswert von 470 Knoten ("True Air Speed") ablesen.Below is an example of the operation of the flight computer according to the invention. If an altitude of 30,000 feet and an outside temperature of -40 ° C instrumentally determined in the aircraft and the speedometer indicates by means of a dynamic pressure measurement 300 nodes, so the flight computer according to the invention is Determine true airspeed against air ("True Air Speed") as follows. The second plate 8 is rotated relative to the base plate 4, that in the window 20 in the second plate 8, the second scale 14 and the temperature scale 19 are positioned to each other such that the value of - 40 ° C exactly at the instrumental altitude of 30,000 Foot is adjusted. The third plate 22 can now be positioned opposite the two plates 4, 8 such that its further read indicia 28 is set exactly on the third scale 16 of the second plate 8 at 30 (ie 300 knots). However, it is now not, as in the prior art, a first corrected speed determined, which is then subjected to an arithmetic operation and again for further determination of the true speed requires further adjustment of the plates to each other, but it is read on the information carrier 32, a correction value , The information carrier 32 is subdivided into circular segment-shaped sectors 40, which are arranged such that a respective sector comprises the flying height-dependent correction values which are assigned to the airspeeds further specified radially on the outside of the third scaling 16. A user can thus conveniently follow the further reading indication 28 radially inward in the relevant sector (in this case the sector 40 at 300 knots airspeed (CAS = "Calibrated Air Speed").) The user can then at the corresponding altitude of 30,000 feet read a correction value of 0.95 The correction values thus determined are arranged on the fourth scale 24 of the third plate 22 and can be used as read-out index 26 for the first scaling 12. In the present case, the user is given a correction value of 0, 95 on the fourth scale 24 as Ableseindizierung 26 then read on the first scale 12 is a true speed value of 470 nodes ("True Air Speed").

Wie eingangs bereits erwähnt, umfasst die Basisplatte 4 eine schlitzförmige Ausnehmung 42, in der die Schieberzunge 6 hin-und herverschiebbar ist. Die schlitzförmige Ausnehmung 42 ist gebildet zwischen einer Vorderplatte 44, einer Rückenplatte 46 und zwei Abschnitten einer Zwischenplatte 48. Die beiden Abschnitte der Zwischenplatte 48 sind, wie aus Figuren 2 und 3 ersichtlich ist, mit in Verschieberichtung verlaufenden Längsführungswänden 50 und 52 ausgebildet, deren parallel verlaufende Abschnitte geringfügig weiter voneinander entfernt sind als die Schieberzunge 6 breit ist. Um dennoch eine spielfreie, jedoch leichtgängige Verschiebbarkeit der Schieberzunge 6 in der schlitzförmigen Ausnehmung 42 sicherzustellen, sind in der schlitzförmigen Ausnehmung 42 zwei Federelemente 54 vorgesehen, welche die Schieberzunge 6 gegen die gegenüberliegende Längsführungswand 50 federnd vorbelasten. Die Federelemente 54 sind von Federzungen 56 gebildet, die aus dem Material der Zwischenlage 48 und einstückig mit dieser geformt sind. Hierfür ist ein ursprünglich aus Bogen und Sehne gebildetes Stück der Zwischenschicht 48 fräsend bearbeitet worden, bis es die aus der Figur 2 ersichtliche Gestalt aufweist, wobei zwischen den Federzungen 56 und dem übrigen Material der Zwischenlage 48 ein in Verschieberichtung erstreckter verhältnismäßig dünner Schlitz 58 eingebracht wurde und die jeweilige Federzunge 56 mit ihrem Kontaktbereich 59 zur Schieberzunge 6 über die zurückgesetzt ausgebildete Längsführungswand 52 vorsteht. Wenn die jeweilige Federzunge 56 beim Einschieben der Schieberzunge 6 in die schlitzförmige Ausnehmung 42 geringfügig in Richtung des Pfeils 60 ausgelenkt wird, so wird hierdurch eine leichte Vorspannung auf die Schieberzunge 6 ausgeübt, welche die Schieberzunge 6 spielfrei, aber dennoch leicht verschieblich in der schlitzförmigen Ausnehmung 42 der Basisplatte 4 führt.As already mentioned, the base plate 4 comprises a slot-shaped recess 42 in which the slide tongue 6 can be moved back and forth. The slot-shaped recess 42 is formed between a front plate 44, a back plate 46 and two portions of an intermediate plate 48. The two sections of the intermediate plate 48 are, as is apparent from Figures 2 and 3, with extending in the direction of longitudinal guide walls 50 and 52, the parallel extending portions are slightly further apart than the slide tongue 6 is wide. In order nevertheless to ensure a backlash-free but smooth displaceability of the slide tongue 6 in the slot-shaped recess 42, two spring elements 54 are provided in the slot-shaped recess 42, which preload the slide tongue 6 against the opposite longitudinal guide wall 50. The spring elements 54 are formed by spring tongues 56 which are formed from the material of the intermediate layer 48 and integral therewith. For this purpose, a piece of the intermediate layer 48 originally formed from bow and tendon has been milled until it has the apparent form of Figure 2, wherein between the spring tongues 56 and the remaining material of the intermediate layer 48 a relatively thin slot 58 extended in the displacement direction has been introduced and the respective spring tongue 56 protrudes with its contact region 59 to the slide tongue 6 via the recessed longitudinal guide wall 52 formed. If the respective spring tongue 56 is slightly deflected during insertion of the slide tongue 6 into the slot-shaped recess 42 in the direction of the arrow 60, then a slight bias is exerted on the slide tongue 6, which the slide tongue 6 play, but still easily displaceable in the slot-shaped recess 42 of the base plate 4 leads.

Claims (15)

  1. Flight computer, comprising a base plate (2) having a first scaling (12) for the flying speed, comprising a second plate (8) which is rotatable with respect to the base plate (2) and may be positioned with respect to a second scaling (14), indicating the flying altitude, of the base plate and a third scaling (16) indicating the speed measured by instruments, this third scaling (16) of the second plate (8) simultaneously forming a readout indexing (18) for the first scaling (12) of the base plate (2), such that it is possible to read out a first corrected speed on said first scaling (12), and comprising a third plate (22) which may be rotated with respect to the base plate (2), having a readout indexing, characterised in that the third plate (22) has a fourth scaling (24) and this fourth scaling (24) simultaneously forms a readout indexing (26) for the first scaling (12), such that it is possible to read out a second corrected speed on said first scaling (12).
  2. Flight computer according to claim 1, characterised in that a region (30) of the second plate (8) is configured as an information carrier (32) and the items of information stored in said carrier (32) correspond with the fourth scaling (24) of the third plate (22).
  3. Flight computer according to claim 2, characterised in that the region (30), configured as an information carrier (32), of the second plate (8) is configured to be concentric to the pivotal point (10) of the second plate (8).
  4. Flight computer according to either claim 1 or claim 2, characterised in that the region (30) configured as an information carrier (32), of the second plate (8) may be overlapped by the third plate (22) and the third plate (22) is transparent in the overlap region or has a recess.
  5. Flight computer according to one or more of the preceding claims, characterised in that the region (30) configured as an information carrier (32), of the second plate (8) is positioned radially inside all the scalings (12, 14, 16, 24).
  6. Flight computer according to one or more of the preceding claims, characterised in that the region (30) configured as an information carrier (32), of the second plate (8) has a plurality of visible circular segment sectors (40) which are associated, by extension, with radially outer regions on the third scaling (16) of the second plate (8).
  7. Flight computer according to one or more of the preceding claims, characterised in that all the plates (2, 8, 22) have a common pivotal point (10).
  8. Flight computer according to one or more of the preceding claims, characterised in that the first scaling (12) of the base plate (2) is positioned radially outside the third scaling (16) of the second plate (8).
  9. Flight computer according to one or more of the preceding claims, characterised in that the second plate (8) extends radially outwards over the first scaling (12) of the base plate (2).
  10. Flight computer according to one or more of the preceding claims, characterised in that the third plate (22) extends radially outwards over the first scaling (12) of the base plate (2).
  11. Flight computer according to one or more of the preceding claims, characterised in that a peripheral edge of the third plate (22) terminates radially outwards with a peripheral edge of the second plate (8).
  12. Flight computer according to one or more of the preceding claims, characterised in that the base plate (4) has a slot-shaped recess (42) in which a sliding tongue (6) may be moved to and fro.
  13. Flight computer according to claim 12, characterised in that provided in the slot-shaped recess (42) is at least one spring element (54) which guides the sliding tongue (6) so that it may move without clearance in the slot-shaped recess (42).
  14. Flight computer according to claim 13, characterised in that the spring element (54) is formed by a flexible tongue (56) formed from the material of the base plate (4) or formed from an intermediate layer (48) of the base plate integrally with said base plate (4).
  15. Flight computer according to claim 13, characterised in that the flexible tongue (56) is at a distance from the rest of the material of the base plate (4) or from an intermediate layer (48) of the base plate by a slot (58) extending in the displacement direction, but is flexibly joined to the intermediate layer by a root portion.
EP05716035A 2004-03-19 2005-03-14 Flight computer Not-in-force EP1604324B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102004013571A DE102004013571A1 (en) 2004-03-19 2004-03-19 flight computer
DE102004013571 2004-03-19
PCT/EP2005/002691 WO2005091208A1 (en) 2004-03-19 2005-03-14 Flight computer

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EP1604324A1 EP1604324A1 (en) 2005-12-14
EP1604324B1 true EP1604324B1 (en) 2008-01-16

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EP (1) EP1604324B1 (en)
AT (1) ATE384303T1 (en)
DE (2) DE102004013571A1 (en)
WO (1) WO2005091208A1 (en)

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Publication number Priority date Publication date Assignee Title
DE102014200866A1 (en) * 2014-01-17 2015-07-23 Iwa - F. Riehle Gmbh & Co Kg Device for determining an amount of insulin to be injected in diabetic patients
CN209372087U (en) * 2019-03-07 2019-09-10 上海崇越航空科技有限公司 A kind of rotating disc type aviation slide ruler

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US2585618A (en) * 1950-10-30 1952-02-12 Oscar E Batori Navigational computer of the slide rule type
DE8228400U1 (en) * 1982-10-09 1983-03-24 Schiffmann, Friedrich, 5064 Rösrath NAVIGATION TOOLS FOR AVIATION

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WO2005091208A1 (en) 2005-09-29
DE102004013571A1 (en) 2005-10-13
ATE384303T1 (en) 2008-02-15
EP1604324A1 (en) 2005-12-14
DE502005002537D1 (en) 2008-03-06

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