DE2353255A1 - SYSTEM FOR EVALUATING THE FOREIGN PILING INFORMATION OF A FLIGHT NAVIGATION ROTARY RECEIVER - Google Patents

Description

G.Fiedler - page jf

Addition to patent application P 23 51 9G1.1

Systam for evaluating the Frenulpeilinformat .- 'on of a flight navigation - "! Rahf unkf euers.

The patent application P 23 51 961.1 relates to a system for evaluating the external direction finding information under the name "UOR" known Flugnavigatiqns rotary radio beacon in which the obtained by demodulating the bearing-dependent broadcast of such a rotary radio in a UKU air navigation receiver, are composed of a direct "variable" 30Hz vibration and a frequency modulated with 30Hz 9960Hz subcarrier vibration UQR external DF information is evaluated by the direct 30Hz oscillation and the sub-carrier oscillation of each other be separated - and by demodulating the subcarrier oscillation a second 30 Hz oscillation to be used as a reference oscillation is formed, and the VOR bearing angle is derived from the low-frequency one SOHz phase shift is detected. To create an evaluation system: create, which with comparatively simple means automatically provide a clear display of the VOR external bearing angle or the by given VOR approach course, without going to other systems to be bound is mentioned in the patent application P 23 51 961.1 proposed from the phase difference between the two 30Hz oscillations to derive several vector components, which in a 'vector indicator automatically produce a clear display of the V / OR approach course.

For a quick overview of the flight situation, it is now desirable to have a VOR course display, which shows both the direction to the VOR ground station on one and the same display instrument tion as well as the compass course of the aircraft and thus also the at the same time indicates the relative self-bearing angle that can be calculated from this. Such a display system is called "RFlI" (RfII = radio magnetic indicator) known per se. The technical However, there is a lot of effort with the common RMI systems (see Fig. 1) relatively large. The usual RMI converters (11) have servomechanics required to use a differential resolver mechanically to adjust the VOR approach course and thus to change the course information of a compass system (17) so that the vehicle relative self-bearing angle arises. This calculated

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G. Fiedler, addendum to patent application P 23 5'ι "3u1.1 page

relative UOR self-bearing angle is then like the real self-bearing a radio direction finder on an Rf'II combination indicator (15).

The object of the invention is an equivalent to the known RMI systems UOR display system, which is based on the use of the in the above-mentioned patent application P 23 51 961.1 proposed principle provides the desired combination advertisement in an economical manner.

The object is achieved according to the invention in that the vehicle course by mechanical or electronic angle subtraction in the display is included and the calculated relative UOR internal bearing together with the vehicle course and the UOR external bearing given UOR approach course is displayed.

In a first embodiment of the UOR evaluation system according to the invention becomes the Uektorindikator (5), similar to patent application P 23 51 961.1 claim 5, including its angle scale (51), automatically with the aid of heading information from a compass system (17) adjusted so that between the angle scale (51) and the display element (53) of the UektorIndikator (5) the UOR-Anflygkurs, between a fixed marking (52) and the angle scale (51) of the Compass heading of the aircraft and between the fixed mark (52) and the display element (53) of the Uektorindikators (5) the calculated relative UOR self-bearing next to each other, read off can be.

In. a second embodiment of the UOR evaluation system according to the invention becomes the SOHz reference vibration via a per se ·. known variable phase shifter (7) which is controlled by the compass system (17) and which corresponds to the vehicle heading Phase shift causes in the phase decaders (4a, 4b, 4c) initiated, and the Uektorindikator fixed in the normal direction (5c) shows the calculated relative UOR intrinsic allocation directly anj using a common standard RMI combination indicator (15) can also use the aircraft's compass heading at the same time and the UOR approach course can be read.

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G. Fiedler, addendum to patent application P 23 51 961.1 page

■ -J. ·

The invention will now be explained in more detail with reference to the drawings uerden.

For comparison purposes, the basic mode of operation of the known Rfil systems (see Fig. 1) should first be explained. The VOR external DF information demodulated by the flight navigation receiver (1) is broken down within the so-called RMI converter (11) by the filter arrangement (2) into the direct "variable" 30Hz oscillation ω and the 9960Hz subcarrier oscillation Q, which is frequency-modulated at 30Hz. The 30 Hz oscillation ω resulting from the demodulation of the subcarrier oscillation Q in the frequency demodulator (3) is transmitted to the phase demodulator (8) which is controlled simultaneously with the variable 30 Hz oscillation ω via a variable phase shifter (7), which effects a phase shift corresponding to its mechanical angular position. forwarded. As long as the phase difference between the two 30 Hz vibrations deviates from 90 °, the phase demodulator (8) emits a voltage which sets the servomotor (9) in rotation. The control circuit (7-8-9) is therefore always set in such a way that the angular position of the variable phase shifter (7) compared to the 90 ° position corresponds to the received VOR approach course. A differential resolver (10) set in parallel to the same angle φ changes the course information emanating from the resolver (16b) of the Kornpaßanlage (17) so that it is analogous to the calculated relative VOR self-bearing angle ß. This calculated relative VOR internal bearing ß, like the real internal bearing of a radio direction finder, is displayed in the standard RTII indicator (15) by the resolution receiver acting as a vector indicator (5c) »The angle scale (51) is indicated by a further control chain , ^ consisting of the rotary receiver (12), the servo amplifier (13) and the servo motor (14), set to the compass heading θ of the aircraft, which is reported electrically by the rotary encoder (16a) from the grain pass system (17). This creates the combination display of the RFII indicator (1.5), as shown in FIG. Between the fixed marking (52) (see Fig. 2), also called "lubber line" in English, and the. The angle scale (51) is the vehicle heading Θ, ie the angle scale (51) serves as a heading for the Kompaö display. Between the 0 ° direction of the angle scale (51) and the display element (53) of the vector indicator (5c) lies.

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G. Fiedler, addendum to patent application P 23 51 961.1 page ^

Approach course φ. Between the fixed mark (52) and the The display element (53) shows the calculated VOR self-bearing angle ß. Ois assemblies (5c, 51,52,53,12,14, partly also 13) are usually housed in the standard RT-II display device (15).

In the first. Training form of the VOR evaluation system according to the invention (see Fig. 3), similar to patent application P 23 51 961.1 claim 5, an adjustable vector indicator (5) is used. The connections of the vector indicator (5) are determined via a set (21) of Sliding contacts out. The VOR angle converter (19) is in accordance with Patent application P 23 51 961.1 constructed and provides the vector indicator (5) the vector components derived from the phase difference between the two 30 Hz vibrations and an identification signal (Ref.) O The resolver (16a) produces the analog information about the compass heading θ in the compass system (17) of the aircraft. The response receiver (12) forms together with the servo amplifier (13) and the servo motor (14) the known Compass course tracking circuit, which includes the vector indicator (5) the Uinkels / kala (51) tracks in parallel, so that between the fixed marking (52) and the angle scale (51) of the compass course of the aircraft. The display element (53) of the vector indicator (5) always points to the angle scale (51) VGR approach course φ. Overall, an angular combination is created which is the same as the display of the known RMI system. Of the Compass heading 8 of the aircraft is therefore simply mechanically won subtracted from the received VOR approach course φ; The result is the calculated relative VOR self-bearing angle ß.

In the second embodiment of the VOR evaluation system according to the invention (see Fig. 4) one of the two SOHz oscillations, e.g. the reference oscillation ω resulting from the demodulation of the subcarrier oscillation Ω, before the phase decoding via a per se known variable phase shifter (7) passed. This variable phase shifter (7) is controlled by the compass system (17) mechanically controlled with the compass course of the aircraft β and causes a phase shift corresponding to the current vehicle course θ and thus a shift of the display by • the amount of the vehicle course. When using certain adapting scarf

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G.F-iedler, addendum to patent application P 23 51 961.1 page S ^

The three-phase type of built-in resolver encoder can perform the tasks (16b) in the compass system (17) as a variable phase shifter (Replacement for 7) can be used «apart from the additionally introduced Phase shift θ, is the UOR-Uinkelkonuertpr der second form of training (20.) that of the first form of training (19) same. Since the angular subtraction takes place electronically, a fixed vector indicator (5c ") is used, which is e.g. part of the Standard RFII indicator can be.-The second form of training of the VOR evaluation system according to the invention can therefore be used with the known RPII systems are designed to be compatible.

The combined display of several angles, as in the known ones RMI systems always entail more effort than that connected to a pure -UOR display, but with This invention achieves advantages by comparing the Estimate block diagrams "(FIG. 1 versus FIG. 3 and FIG. 4).

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Claims (3)

Günter Fiedler 2818 Syke, October 22, 1973 • w · Fasanenweg 2 Addition to patent application P 23 51 96-1 * 1 ' "System for evaluating external DF information from a · Air navigation rotary radio beacon " Patent claims System for evaluating the external DF information of a flight navigation rotary radio beacon according to patent application P 23 5.1 -961.1, characterized in that that the vehicle course by mechanical or electrical angle subtraction is included in the display and the calculated relative self-bearing together with the vehicle course and the I / OR approach course given by the VGR external bearing is brought to the display. 2) System 'for evaluating the foreign bearing information of a flight navigation rotary radio euers according to claim 1, ■ characterized in that the vector indicator (5) including its Uinkelskale (51), with the help of the course information of a compass system (17), adjusted automatically is that between a fixed marker (52) and the angular scale (51) the compass course of the vehicle, between the angular scale (51) and the display element (53) of the vector indicator (5) the VOR approach course and between the fixed marker (52) and the display element (53) of the vector indicator the calculated internal bearing can be read off. 3) System for evaluating the Frempeilinformation of a flight navigation rotary radio euers according to claim 1, characterized in that the reference oscillation has a known variable phase shifter (7), which is controlled by a compass system (17) and a vehicle- course causes a corresponding phase shift, in the phases- decoder (4a, 4b etc -; *) is initiated and the normal direction device attached vector indicator (5c) shows the calculated relative self-bearing directly, and when using a known one Standard ^ MI) combination display device also the vehicle course and the VOR approach course can be read. 509819/04 1-0 Blank page