Classifications

• • 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 with a base plate which has a first scaling for the airspeed, with a second plate which can be rotated relative to the base plate and which can be positioned relative to a second scaling of the base plate which denotes the flight altitude, and has a third scaling which measures the instrumentally measured Designates speed, wherein this third scaling of the second plate also forms a reading index for the first scaling of the base plate, so that a first corrected speed can be read there, and with a third plate that can be rotated relative to the base plate with a reading index.
• Flight computers that are formed from one or more mutually movable, in particular rotatable plates with scaling are known, they serve, similar to the function of a slide rule, for calculating a large number 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 ways. With flight speeds of more than 200 knots and an altitude above about 10,000 feet, such a correction is of great importance. Not only the flight speed and altitude are important, but also the temperature of the outside air.
• a flight computer of the type specified above is known under the trade name "ARC-2" from the company AFE.
• the second plate is positioned opposite the base plate, specifically in relation to the second scaling in accordance with the flight altitude of the aircraft determined by instruments and in accordance with the measured outside temperature.
• a first corrected speed is then read on the first scaling of the base plate, in that the user can use the value of the third scaling (as
• Reading index on the first scaling of the base plate reads the first corrected speed value.
• An arithmetic operation must then be carried out in the head, namely sensible, where x represents the first corrected speed.
• the second plate In accordance with the resulting value, the second plate must then be rotated again in a predetermined direction in accordance with a further scaling, and a second corrected speed value can then be read from the first scaling of the base plate based on the third scaling of the second plate (as reading index) become.
• the third plate which is rotatable relative to the base plate, is merely a tongue-shaped segment with a straight line running in the radial direction as a reading index, which can be used for a number of reading processes.
• the object of the present invention is to create 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 the extent of the considerations to be made by the user is reduced.
• the flight computer should therefore be easier to use overall.
• 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 also forms a reading index for the first scaling, so that a second corrected speed can be read there.
• a further, third plate with a fourth scaling is provided, with the aim that the second plate only needs to be positioned once with respect to the base plate.
• a correction factor that is dependent on the flight altitude and the first corrected speed can be found on the fourth scale.
• the correction factor dependent on it in itself any
• the correction factor dependent on it can directly determine the second corrected speed at the corresponding point on the fourth scaling of the third plate (as reading index for the first scaling) from the first scaling be read. It is therefore not necessary to carry out the difficult calculation as in the known flight computer and then to turn the first plate again relative to the base plate.
• the third plate has a scaling, namely the fourth scaling as claimed, which also functions as a reading index for the first scaling.
• the correction factor mentioned can be determined in any way, in particular can be read from a table that is carried along.
• This area of the second plate which is designed as an information carrier, can advantageously be formed or arranged concentrically to the pivot point of the second plate.
• the area of the second plate designed as an information carrier can also be arranged so that it can be covered by the third plate, in which case the third plate is designed to be transparent in the area of the overlap or has a recess which permits an inspection of the area designed as an information carrier.
• the region of the second plate designed as an information carrier is arranged radially within all scales.
• Has circular segment sectors which are assigned to areas on the third scale of the second plate by extending radially outward.
• specific information for example correction values, which correspond to an area on the third scaling, that is to say, for example, a speed range of 325 to 375 knots, can be provided in the relevant circle segment sector.
• the user then only needs to go radially inward from the region of interest on the third scaling and to read off corresponding information in the radially inward circular segment sector of the information carrier. All plates advantageously 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 scaling of the base plate. In this way, the penetration of dirt can be better prevented and the first scaling and the third scaling can be arranged such that they directly adjoin one another in the plan view.
• the third plate extends radially outward beyond the first scale of the base plate.
• the fourth scaling can then be arranged in a corresponding manner, at least up to and directly up to the first scaling, in order to enable the reading, i. H. to increase the reading comfort and the reading accuracy.
• a peripheral edge of the third plate terminates radially on the outside with a peripheral edge of the second plate.
• the base plate has a slot-shaped recess in which a slide tongue can be pushed back and forth.
• a slide tongue By means of this slide tongue, coordinates can be determined in a manner known per se from the determined and corrected flight speeds over the distance traveled.
• the spring element can be formed by a spring tongue which is formed in one piece with the base plate from the material of the base plate or an intermediate layer.
• the spring tongue can be shaped out of the material by milling.
• the spring tongue can be spaced apart from the remaining material of the intermediate layer or the base plate by a relatively narrow slot which extends in the direction of displacement, but can be flexibly connected to the intermediate layer or the base plate with a root section.
• Figure 1 is a plan view of the flight computer according to the invention.
• Figure 2 is a plan view of the flight computer according to the invention (omitting the second plate and partially omitting the base plate);
• FIG. 1 shows a plan view of a flight computer designated overall by reference number 2, only the components of the flight computer associated with the present invention being 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 plate-shaped second plate 8 which is arranged at its center 10 so as to be pivotable to the first plate 4, and a third plate 22 described below.
• the first plate 4 has a first scale 12 in the circumferential direction, which denotes the airspeed. Furthermore, the first plate 4 bears a second scale 14 in the area of overlap with the second plate 8, that is to say in the area below this second plate 8, which second scale 14 denotes the flight height.
• the second plate 8 is rotated or positioned in relation to the first plate 4 in such a way that a correspondence to the flight altitude determined in the instruments and displayed in the aircraft is achieved, possibly and preferably at the same time taking into account the instrumentally determined outside temperature.
• the second plate 8 also has, and preferably in the radially outer region, a third scale 16, which at the same time forms a reading index 18 for the first scale 12 of the base plate 4, so that a first corrected speed can be read there.
• the reading is carried out when the flight computer is used in such a way that the speed measured and displayed on the instrument on the third scale 16 is used as reading index 18 for the first corrected speed on the first scale 12 of the base plate 4.
• a third plate 22 which can 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, that is to say with the same pivot point 10 as the second plate 8, can be arranged rotatably relative to the base plate 4 and the second plate 8.
• This third plate 22 has a fourth scaling 24, this fourth scaling 24 also forming a reading index 26 for the first scaling 12.
• the third plate 22 also has a further reading index 28 which extends in the radial direction, but which is not absolutely necessary. By means of this further reading indexing 28, the third plate can be positioned with respect to the third scaling 16 of the second plate 8 in such a way that the instrumentally determined speed value corresponds to the position of the further reading device 28 on the third scaling 16.
• the final speed value can now be read as the second corrected speed from the first scaling 12 of the base plate 4 via the fourth scaling 24 and its reading index 26 for the first scaling 12.
• the fourth scaling 24 corresponds to the correction factors that could be found in a separate table for this flight computer.
• an area 30 of the second plate 8 is designed as an information carrier 32, the information stored there being straight include the correction factor that corresponds to the fourth scaling 24.
• a correction value can be read from the information carrier 32.
• the final second corrected speed value can then be read from the first scaling 12 at a corresponding point on the fourth scaling 24 as reading indexing 26.
• the second plate 8 in order to determine the twice corrected speed, starting from a speed determined by an instrument, in particular by dynamic pressure measurements, the second plate 8 only has to be positioned once with respect to the first plate 4, and in contrast to known ones No additional computing tasks need to be carried out for flight computers, which then lead to a new positioning or adjustment of the second plate 8 relative to the first plate 4. Rather, it is sufficient to read a corresponding correction value (which can also be determined in some other way) from the information carrier 32 and to read the second corrected speed value from the fourth scaling 24 on the first scaling 12. Before this, only the third plate 22 needs to be positioned, preferably on the basis of the further reading index 28, at the speed value of the third scale 18 that was originally determined and displayed experimentally.
• the flight computer according to the invention becomes Determination of a true airspeed against air ("True Air Speed") used as follows.
• the second plate 8 is rotated relative to the base plate 4 such that the second scale 14 and the temperature scale 19 are positioned in the window 20 in the second plate 8 in such a way that the value of
• the third plate 22 can now be positioned opposite the two plates 4, 8 in such a way that its further reading index 28 is set precisely on the third scale 16 of the second plate 8 at 30 (ie 300 nodes).
• a first corrected speed is not determined, which is then subjected to an arithmetic operation and again requires further adjustment of the plates to one another in order to further determine the true speed, but a correction value is read out on the information carrier 32 .
• the information carrier 32 is subdivided into sectors 40 in the form of segments of a circle, which are arranged in such a way that a respective sector comprises the flight height-dependent correction values which are assigned to the flight speeds indicated further radially on the third scale 16.
• the base plate 4 comprises a slot-shaped recess 42 in which the slide tongue 6 can be pushed back and forth.
• the slot-shaped recess 42 is formed between a front plate 44, a back plate 46 and two sections of an intermediate plate 48.
• the two sections of the intermediate plate 48 are formed with longitudinal guide walls 50 and 52 running in the direction of displacement, the parallel of which extending sections are slightly further apart than the slide tongue 6 is wide.
• two spring elements 54 are provided in the slot-shaped recess 42, which resiliently 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 integrally therewith. For this purpose, a piece of the intermediate layer 48 originally formed from a bow and a string has been milled until it has the shape shown in FIG.

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• Engineering & Computer Science (AREA)
• Theoretical Computer Science (AREA)
• Physics & Mathematics (AREA)
• Computer Hardware Design (AREA)
• General Physics & Mathematics (AREA)
• Remote Sensing (AREA)
• Radar, Positioning & Navigation (AREA)
• Ocean & Marine Engineering (AREA)
• Mathematical Physics (AREA)
• Navigation (AREA)
• Fluid-Pressure Circuits (AREA)
• Diaphragms For Electromechanical Transducers (AREA)
• Instructional Devices (AREA)

Applications Claiming Priority (3)

Publications (2)

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ID=34961802

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• 2004
  • 2004-03-19 DE DE102004013571A patent/DE102004013571A1/de not_active Withdrawn
• 2005
  • 2005-03-14 DE DE502005002537T patent/DE502005002537D1/de active Active
  • 2005-03-14 AT AT05716035T patent/ATE384303T1/de not_active IP Right Cessation
  • 2005-03-14 EP EP05716035A patent/EP1604324B1/fr not_active Not-in-force
  • 2005-03-14 WO PCT/EP2005/002691 patent/WO2005091208A1/fr active IP Right Grant

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