DE1556433A1 - Integrated arrangement for displaying aircraft data - Google Patents

Description

DR.-ING. DIPL-INQ. Q. RIEBLINQ 1 5 5 6 A 3 PATENT ADVOCATE My sign

N 147 Fr / Schu,

Please repeat in the answer

L- Your message from J 899 Lindau (Lake Constance) Rennerle 10 Poet Subject 365 Your sign My message from February 26, 1968

Reference:

Northrop Corporation, 9744 Uiilshire Blvd., Beverly Hills, California / USA

Integrated arrangement for displaying aircraft data.

This invention relates to an arrangement for machining of information about aircraft operating conditions and the simultaneous provision of audio warning signals corresponding to such View conditions and certain of the measured information for later use on sound recorders record.

When flying high-speed aircraft, especially

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for military purposes, very many parameters must be constant These parameters are and are used outside of the box If predetermined limits fall, appropriate measures must be taken be seized. Also, when servicing such aircraft, it is useful to miss, if during one If such parameters have deviated from the normal operating range · Furthermore, it is special in the investigation the causes of a plane crash extremely useful, complete information on the operational— to have parameters of the aircraft during the time immediately before such a crash.

This invention relates to an arrangement for providing all three functions enumerated above in a coordinated manner and integrated way.

It is therefore before the object of this invention to provide an integrated To create an arrangement for displaying and recording performance and operating data of an aircraft

It is another object of this invention to provide an integrated data display arrangement in which the Operational data are recorded during the last phase of a flight.

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It is another object of this invention to be detailed To provide aircraft operational data for use in maintenance and assessment.

It is a further object of this invention to provide an integrated arrangement for providing audible warning signals that are out of tolerance the operating parameters while these operating data are being recorded at all times.

Other objects of this invention will appear from the following Description will become apparent in conjunction with the accompanying drawings.

FIG. 1 is a block diagram of the basic arrangement of FIG Invention;

Figure 2 is a block diagram of a preferred embodiment the arrangement of the invention;

Figure 3 is a block diagram of the (multiplex component, which is used in the preferred embodiment of the arrangement of the invention;

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Figure 4 is a circuit diagram of a typical SignalpEuf ~ and from "erttmgsscfraltung," oak in the ftnoird— the invention is used.

In short, the arrangement of the invention employs one Signal checker and evaluator, which has a number of hairdryers processes and evaluates outputs, each of which represents a different parameter of the aircraft of these parameters is not within predetermined limits, the evaluator generates a control signal, which a certain corresponding transmitter component in a flleßwerttransfer pressed for sound messages. The outputs of the IfleßwBrttransfers for sound messages, which both in simple language as well as in encrypted form are recorded at the same time for later comparison and reproduced as a warning signal to the flight crew * information from the signal checker and evaluators, which provide certain aircraft data, are sent in the form of a sound signal or encrypted at the same time and recorded on a rotary recorder so that such information is for the very last Phase of the flight are always accessible. Also be Statements of the aircraft crew at this time also recorded · The arrangement of the invention thus monitors

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with constantly the operating parameters of the aircraft and at the same time provides immediate warning signals and a recording of both the fault indication for use as a maintenance aid and as information from Performance parameters of the aircraft during the all- last phase of a flight for use in the

maintenance, such as in the event of a crash · This information, which is detailed data of a large Number of separate aircraft parameters, is thus made available for an immediate warning of the Aircraft crew must be provided prior to a hazardous condition, which is recorded simultaneously to provide an accurate basis for detailed post-flight review and / or to create an accident investigation.

In Fig. 1 the basic arrangement of the invention is illustrated. Function sensors 11 create information, im generally in the form of an electrical voltage, over a number of aircraft functions · The outputs of the Function sensors 11 are fed to a signal tester and evaluator 12, which each of these sensor outputs evaluates against predetermined voltage ranges that correspond to normal operation and generates an output control signal to a tone signal transmitter 14, whenever

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the exits are not in these predetermined areas fall. The audio signal transmitter 14 includes a component such as that described in U.S. Patent No. 3,015,702, which issued on Jan. 1962 Northrop Corporation assigned the assignee of the present application has been granted.

The signal outputs of the audio signal transmitter 14 are fed to a tone converter 15, which audio warning signals for the operating personnel of the aircraft. Such notifications are also kept for later use in the (Hardening and the like recorded by a recording device 16. The signal tester and evaluator 12 has also has a special output, which provides for the continuous display of the absolute amounts of certain performance parameters of the aircraft, regardless of whether these parameters lie within the predetermined "normal" ranges or not. These outputs which of value in creating detailed data on aircraft performance during the monitored period are, are fed to a multiplex component 20, where they suitably processed to produce a fflehrfsch — sound signal to generate, which contains the added data

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The output of the multiplex component 20 is fed to a rotary recording device 22, if it is recorded appropriately. h # erases the recorded data and at the same time records the data obtained during the next time interval. In this way, the data is always forward for only the last part of the flight ^; act.

In Fig. 2 there is shown a preferred embodiment of the device of the invention. The various outputs of the function sensor 11 are used in the signal tester and evaluator 12 fed on them, as already admonished, each can be appropriately evaluated to determine whether or not they fall within the predetermined ranges. How a typical function sensor works and a signal checker and evaluator will be described later in the description in connection with FIG. 4. Outputs of the signal tester and evaluator for each of the signals received by the function sensor 11, which are outside the prescribed tolerances dBr, are one Sound warning signal transmitter 3CT supplied, wherein each of the Outputs of the signal tester that are outside the tolerance

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and evaluator a separate, appropriately recorded Tonu / arnsignal triggers in simple language. the Outputs of the signal tester and evaluator are also supplied to the transmitter of encrypted messages 31, wherein previously recorded audio signals in encrypted Form can be reproduced in response to suitable outputs of the signal evaluator and tester. Of the Audio alert transmitter 30 and encrypted message transmitter 31 is of the kind in the aforementioned U.S. Patent No. 3,015,702.

The speech signal outputs of the transmitter 30 are simultaneously to the sound converter 15 of the headphones of the pilot its immediate use and given to the recording device 16, where they are recorded, so that a Sound recording of such disturbances is performed. The recording device 16 operates in conjunction with a Timer component 34 to provide a time record, if the various recorded faults occurred during the flight. The recording device 16 is with provide and record at least four recording channels also the encrypted signal output of the transmitter 31 as well as the voice transmissions of the pilot

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his on-board intercom 40.

Certain signals received by the signal checker and -ausumrter 12, Predetermined outputs of the function sensor 11 u / earth processed by the signal checker and evaluator, as will be described in detail in connection with FIG. 4, to continuously provide DC outputs in accordance with these measured functions. This permanent Outputs of the signal tester and -ausuierters 13, which display selected flight and flilotor parameters of the aircraft, are given by the signal tester and evaluator to the multiplex component 20. It should be noted that the certain parameters fed to the multiplex component 20 are continuously received by the multiplex component, independently on whether or not their amounts are within or outside prescribed tolerances.

As can be explained in detail in connection with Fig. 3, becomes each of the received by the multiplexer 20 Signals used to set the frequency of a separate tone oscillator to modulate, which represents the respective parameter in question and the outputs of these oscillators are multiplied in frequency and fed to the rotary recorder 22, where they are used for later use

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recorded uierden. The rotary recorder 22 is a multi-channel sound recording device, which also encrypts the output of the on-board communication device 40 and the transmitter Messages 31 records, and which works for a limited period of time, for example 30 minutes and then erases the recorded information while at the same time erasing the information subsequently received records. Thus, the recording device 22 compiles a record of information that have arisen during the last phase of the flight, which could be, for example, those immediately before a crash. The recorders 16 and 22 and the timer component 34 are shown in FIG of the type set forth in U.S. Patent No. 5,490, issued on May 24, 1965 by Northrop Corporation, the assignee of the present application filed, pending U.S. patent application Serial No. 4,553. An override control 33 is used by the flight crew to control the Override the activity of the transformers 30 and 31 manually.

In Fig. 3 is a block diagram of an iflultiplex component Figure 3 illustrates which is used in the arrangement of the invention. A number of sensors 11a to 11n, where only a few of the components for the purpose of demonstration

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measurement are shown, each measure a predetermined parameter, uiie, for example, the engine oil pressure, the pilot speed etc. The outputs of the sensors 11a to 11n are passed to the signal checker and evaluator 12 where they are appropriately processed, as in connection to be described with FIG. 4. The signal tester and evaluator 12 has an output for each of the sensor outputs which are in the form of a DC voltage in accordance with each sensor signal. Each of these DC outputs are each fed to one of the voltage-controlled oscillators 42a to 42n. Everyone who voltage-controlled oscillators 42a to 42n, which contain self-excited fflultivibratoren, has a separate self-excited frequency in the audio frequency range, these frequencies by a suitable frequency frequency distributors are separated. Each of the voltage controlled oscillators 42a to 42n is activated by the signal input frequency modulated, d. i.e., the working frequency each such oscillator is varied as a function of the size of the DC input. Such Frequency change is well known in the art Techniques achieved, for example by sending the DC input signals to the self-excited Rlultivibrators as Preload signals can be entered for this

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The outputs of the voltage controlled oscillators 42a to 42n are fed to a Hilischerbauteil 45 to they are mixed together to form an integrated signal containing all of the oscillator output frequencies, which are modulated in accordance with the sensor outputs. The IKlischerbaueil 45 includes a conventional one Transistor amplifier, class "A". The output of the table component 45 is fed into the rotary recording device entered to it is recorded, uiie in connection with Fig. 2 described.

In Fig. 4 is a circuit diagram of a signal tester and evaluator used in the arrangement of the invention. The particular depicted Circuit is just one of many that can be used. The sensor 11, which has a float mechanism for what a fluid level could contain, such as for a fluid or oil level or an electrical meter that measures an electrical signal controls the arm of the potentiometer 50. The potentiometer 50 is connected to a DC voltage source 52 so that when the arm of the potentiometer 50 is controlled by the sensor 11, a direct current potential is applied to the line 53,

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which corresponds to the output of the sensor 11. The signal on line 53 is used to provide constant dynamic information in accordance with the output of the sensor 11, which, as described in connection with FIG. 3, for recording is multiplied. The signal on line 53 is also used as an input to transistors 55 and 55 56 given. The transistor 55 operates in conjunction with the transistor 57 as a differential voltage comparator, which produces an output signal when the input to transistor 55 is above a predetermined voltage level increases. Transistor 56 operates in conjunction with transistor 58 to produce an output signal when the input to transistor 56 drops below a predetermined voltage level.

Such a mode of operation is achieved as follows: The transistor 55 is biased so that it is blocked, when the voltage level on line 53 is below the predetermined one The reference level is the upper limit of the "normal" operational readiness to be measured Represents parameter. When transistor 55 is off, so is transistor 60 in terms of the fact that its base is connected to the collector of the transistor 55. When transistor 60 is blocked, there is no flow

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Current from this transistor to output line 70. The Transistor 55 receives its bias voltage via resistor 62. Resistor 62 with the conduction path is that Transistor 57 connected «The conduction state of transistor 57 and thus the bias on the Uliderstand 62 is made by adjusting the arm of the reference potentiometer 65 determined. The transistor 57 is biased so that it is in all settings of the potentiometer 65 heads. The voltage level, at u / elchem the transistor 55 becomes conductive, is thus determined by the setting of the reference potentiometer 65 and in this way becomes the upper limit of the "normal" operating range for the particular parameter in question calibrated »UJ en η thus the signal on the line 53 over a predetermined voltage level rises, as indicates that the parameter to be measured has risen above the normal operating limits, the transistor 55 is in the and makes transistor 60 conductive to provide an output signal on line 70.

Transistors 56 and 58 operate in the same manner in FIG Connection to transistor 74 to provide a signal on line 70 when the voltage level is at the

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Line 53 falls below the predetermined lower limits for the "normal ^II operating range. In this case, however, transistor 58 is normally off and transistor 56 is normally conductive, with transistor 74 being controlled by transistor 58. Transistor 58 is switched on by means of... of reference potentiometer 77 to apply a predetermined bias voltage to resistor 75 so that, if the voltage on line 53 falls below a predetermined level, transistor 56 is turned off, causing transistor 58 to conduct Transistor 58 becomes conductive, it brings transistor 74 into the conductive state, whereby a signal on line 70 is established.

The arrangement of this invention thus provides an apparatus for the simultaneous provision of a sound warning message to the operating personnel of an aircraft while this message is recorded for later use in maintenance and evaluation.

Although the arrangement of this invention has been described in detail and has been illustrated, it is to be understood that this is by way of illustration and example only

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serves and is not intended to serve as a limitation, the The spirit and scope of this invention is to be limited only by the language of the following claims.

Claims

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Claims (10)

Claims 1. Integrated arrangement for displaying aircraft data, characterized by a number of function sensors (11) for the selected aircraft characteristics, a device (12) for processing the outputs of the function sensor (11) to separate electrical To generate signals in accordance with each of the outputs, a device for separate ius— inerting the electrical signals and generating a corresponding control signal when one of the outputs does not lie within a predetermined range, a sound signal transmitter (14) which responds to the control signals responds to transmit sound messages for each of the probe outputs that are not within the predetermined area and a rotary recorder (22) for the continuous recording of selected electrical signal outputs of the processing device, which arose during a predetermined previous operating period. 2. Arrangement according to claim 1, characterized - 18 - 10 9 ii 1 h I η 1 3 9 by a multiplex component (20) between the Recording device (22) and the evaluation device (12) is arranged to measure the frequency of the electrical signals for recording on a single audio channel of the recording device. 3. Arrangement according to claim 1, characterized in that the electrical signals Are DC voltages, the size of which corresponds to the sensor outputs. 4. Arrangement according to claim 1, characterized in that the audio signal transmitter (14) contains a speech signal transmitter (30) in order to to transmit the signals in simple language and a transmitter (31) for transmitting the signals in encrypted form. 5. Arrangement according to claim 4, characterized by an IKIehrkanal recording device (16) for Maintenance information for simultaneous recording of the Outputs of the speech signal transmitter (30) and the Transmitter for encrypted signals (31), - 19 - 10981fi / 0139 6. Arrangement according to claim 2, characterized in that the Hflultiplex component (20) a voltage controlled tone oscillator (42a to 42n) for receiving the signals, each of the oscillators having a separate operating frequency and through the signal delivered to it is frequency modulated and a mixer component (45) for mixing the outputs of the voltage controlled oscillators, 7. Arrangement according to claim 5, characterized by an on-board communication device (40) for transmission of spoken messages, with the output of the On-board communication device (40) recorded on a separate channel of the recording device (16) for Uiartungsinformationen will. 8. Integrated arrangement for displaying data of a aircraft in flight by a number of function sensors (11) for measuring selected aircraft parameters, a device for processing the outputs of the function sensors (11.) »to separate electrical signals in accordance to generate with each of the outputs, a device for the separate evaluation of the electrical signals - 20 - 1 0 9 η ι κ / η ι 3 9 and for generating a corresponding control signal if one of the outputs is not within a predetermined one Area lies, a tone signal transmitter (14), which responds to the control signals, for transmitting of sound signals for each of the sensor outputs, the is not within the predetermined range, a tone converter (15), which is based on selected outputs of the Sound signal transmitter (14) is responsive to provide speech signals in accordance therewith, a recording device (16) for recording selected audio signal outputs of the transmitter (14) and a rotary recording device (22) for continuously recording selected electrical signals corresponding to aircraft parameters, during an immediately preceding period of operation. 9. Arrangement according to claim 8, characterized in that that the audio signal transmitter (14) contains a first transmitter (30) for transmitting of messages in plain language and a second transmitter (31) for transmitting messages in encrypted Form, the outputs of the first transmitter in the sound converter (15) and the recording device (16) and the outputs of the second transmitter in the recording device (16). Blank page