JPS5934997A - Device for displaying flight data from flight data-recorder of aircraft - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to the field of aircraft flight data display devices. Especially aircraft flight data recorder (recording device #)
The present invention relates to a flight data display device that can visually display flight data directly from a computer.

BACKGROUND OF THE INVENTION Most commercial aircraft in service today include flight data recorders for recording various aircraft flight parameters such as altitude, airspeed, heading, and engine data. It is equipped. The primary purpose for recording aircraft flight data is to obtain flight data for accident analysis; however, the flight data recorded onboard the aircraft may also be used for aircraft maintenance, rough landings, go-arounds, etc. It has been found to be useful for route control for other purposes, including minor accident analysis such as landing approaches.

With the advent of modern digital flight data recorders that can store multiple flight parameters, the usefulness of the data to route operations management personnel has increased dramatically. The availability of a large number of flight parameters has enabled management to analyze actual flight data, resulting in extremely significant improvements in flight operational safety and economics. However, to be useful. This type of data must be available for management in a timely manner and in a useful format.

A review of conventional methods for generating aircraft flight data from flight data recorders for analysis by route management personnel has shown that these conventional methods have a number of significant deficiencies. A typical example is that data from a digital flight data recorder that is stored in bit-serial form must be converted to a format that can be used as input to a large scale computer system. After converting the format of the data from the digital flight data recorder, the main computer system converts the data into appropriate engineering units (engi).
The data is then printed out in a table or table for analysis or shown on a chart. This process has several drawbacks, one of which is that it can result in significant delays in making data available. For example, it typically takes several hours to format or transcribe data, and not only that, but the transcription equipment is massive! Delays often occur due to the distance from the in-machine installation location. Also.

When using a company's base IT computing machines, priority problems arise in that data conversion and tabulation very often compete with other business functions of the computing machine, resulting in slow delays. I knew I was being invited.

Besides the issue of delays in making data available,
Further disadvantages of the currently used procedures arise from the fact that the computer printout is very large and therefore requires a very large amount of engineering processing time for inspection and analysis. There are drawbacks. Therefore, the processes traditionally used in airway monitoring to obtain flight data are flexible in providing timely data in the form deemed most useful to operational and technical personnel. I can say that I am lacking.

It is an object of the present invention to provide a data storage unit, an input unit for receiving flight data from the data storage unit, and a unit for converting selected portions of the reformatted flight data into engineering units and transmitting the converted flight data to the storage unit. A processor for memory and one processor.

an aircraft digital flight data controller having a video display unit with a keyboard for selecting the portion of the formatted flight data to be converted to flight data engineering units and displaying the converted flight data; The object of the present invention is to provide a device for displaying flight data from a recorder.

An additional object of the present invention is to provide a data storage unit for storing flight data from the input unit and the flight data in the data storage unit.

a system having a processor for converting a selected portion of the flight data into engineering units in response to a synchronization word in the data; and a display unit for displaying the converted data in engineering units; - It aims to display selected digital flight data directly from the recorder.

Still other objects of the invention include: an interface circuit connected to a flight data recorder for converting serial flight data into flight data words; and a data storage unit for temporarily storing the data words. The interface circuit inputs serial flight data from a flight data recorder, converts the serial data to word format, and stores the flight data word in a first predetermined location of the data storage unit. , converting the flight data word into calibrated flight data;
and storing the calibrated flight data in a second predetermined location within the data storage unit of the selected aircraft from an aircraft digital flight data recorder with a display having a data access +j(!:). The display device is also intended for direct display of flight parameters.

It also has a display unit responsive to the processor for visually displaying the calibrated flight data stored in the data storage unit.

Other objects of the invention include a raw flight data source, an interface unit for format conversion of the raw flight data, a high speed random access memory, and a bulk memory.
memory and causing the interface unit to load the formatted raw flight data into a first location of random access memory.

a central processing unit for converting selected portions of the raw flight data into engineering units and storing the converted flight data in a second location in the random access memory; and a visual display unit for displaying converted flight data stored at a co-location.

Description of examples The present invention will be described in detail below with reference to the drawings.

FIG. 1 is an overall functional block diagram illustrating a preferred embodiment of a system for directly displaying selected aircraft performance data from a digital flight data recorder. Aircraft speed.

Aircraft performance data regarding factors or parameters such as altitude, vertical acceleration, engine pressure ratio, and pitch and roll attitude are accumulated and stored during flight in an aircraft flight data recorder designated by the reference numeral 10. be done. “5undstrand Data C
ontrol general purpose flight data recorder part number 9t
Some of the most recently developed flight data recorders, such as the θ-qlooJ, are capable of storing more than /θθ different flight parameters over a single flight time. Digital flight data as indicated by reference numeral 10.
In recorders, data is typically stored in a bit-serial format consisting of frames, which can be divided into q subframes, each consisting of 6 words of 2 bits each. has been done. Regarding the format of data stored in commercially available flight data recorders, please refer to the "ARINO Elspecificat" published by Aeronautical Radio Engineering Co., Ltd., located in Annapolis, Maryland, USA.
ions (specifications)! 73 and 7/7''. Each subframe represents seven seconds of aircraft performance data.

In many cases, each word of 7.2 bits represents an aircraft flight parameter such as altitude or airspeed, and such parameters such as vertical It appears more frequently than l words in 7 subframes. P1-like data such as engine speed is 7 for each 7 Raynaud.
7 times or every 7 seconds. The first word of each subframe is a synchronization word.

This word is used to mark the start of a subframe and to identify the subframe. Currently, several different subframe formats are known, depending on the manufacturer of the data accumulation equipment on board the aircraft. "ARINOS73" The hexadecimal value of the non-cross word is listed below.

//// θθθ /θθ /θ00θ/ Oθ/
0θθ ///, 2 000 /// 0/
/ θ10 010 /10 ///
θOO,? /// 000 100 1
0/ 10/ 00/ 000 ///
4' 000 /// 0// θ/
/ /10 /10 /l/ 000 When attempting to extract and analyze flight data stored in the flight data recorder 10.

The flight data recorder itself can be connected directly to the aircraft flight data display or playback device provided in conjunction with the display device shown in FIG. However, the flight data recorder 10 from the aircraft
Since it is often impractical to remove the
Flight data recorder 1 installed on the aircraft
A copy recorder is used as shown by the dashed line /lI to record data from 0, and the copy recorder /
It may be convenient to connect the cable to the playback device as shown by line /A. “5undetrand Data Cont.
rol copy recorder part number qgl-ao, 2y
Commercially available copy recorders such as -oot J can record hours of flight data in about 30 minutes, thereby making the flight data recorder 1
The need to physically remove the 0 from the aircraft is eliminated.

One function of the playback device // is flight data recorder IQ.
It is to control. For example, in a digital flight data recorder, a playback device
7 can now place marks or markers on the tape, direct the tape to run forward or backward, and sequence the tape number tracks.

Playback device t// is also available. By squaring the 24-bit signal and decoding it into a non-return-to-zero (NTZ) signal, it also functions as a data backup processor for the flight data recorder 10 or copy recorder/4'. Such a playback device may be 1, e.g.
d Data control playbank unit part number tr/-/s/g J.

An interface board /, 2 is connected to the playback unit or playback device // by a data line 1g, the latter being, for example, a 76-pit computer [Data General Nova MO
ael <ZS J is connected to the central processing unit 20 of a computer system. The central processing unit has an input/output (Ilo) board, 2/. Central processing unit, 20 also.

Via the I10 portco/, it is connected to a visual display device, 2.2, as indicated by line 2da.

Preferably said display device-1 is a color graphics terminal having a color display cathode ray tube and a keyboard sg. In a preferred embodiment of the invention said color graph ink visual display device 2+l is
c1vanced.

Electronic Design's "AED&7"
．． 2 type color graphic video terminal device. The terminal device is manufactured by Advanced Electron located in Sunipale, California, USA.
FAED&/ available from icsDθθign
, 2 'Users' Manual J. In the case of
It may be desirable to connect 0 to obtain tabulated data in printed or plotted black and white form.

Another integral part of an aircraft flight data display such as that shown in FIG. It has three high-speed random e-access memories. Note that the disk memory may be a floppy φ disk or a fixed disk. As shown in FIG. 1, the memory is connected to the central processing unit -0 as represented by the data line 3t, and the bulk memory J6 is connected to the central processing unit 8! by ayθ. Device B is connected to 2 or 7c. In the embodiment of the invention shown in FIG.
is part of the random access memory normally provided in 1qOva 461 computers. A buffer portion +, 2 is provided at the place or location.

Note that the random access memory, 74(), is organized into a seventh buffer <<+ and a third buffer QA. Each of the buffers <(4/ and q6 is divided into /B subframes). and each of the 7 sub-frames is A
It is divided into 1/6 bit words. Buffer memory plus high-speed random access memory3
Da is.

Flight Data Recorder/θ Temporarily stores some conversion tables yg for converting raw aircraft performance data into data used in engineering units and selected portions of raw aircraft performance data retrieved from Banfa II. Beat data buffer for storing data! ro, 51g exchange 1.
and a conversion data buffer 5.2 for temporarily storing aircraft performance data compatible with other engineering units. Also, as is customary, random access - memory, ? ll also has a predetermined location or memory location S for storing the part of the computer program that drives the central flosetusa, 2O, and the subtractor operating system. The bulk or disk Φ memory 3A has a portion 5g for storing a parameter data base, a portion 60 for storing a drawing data base, and a location S6 for storing a computer program. and parts 6 and 6q for storing the machine operating system.

FIG. 12 shows a detailed functional block diagram of an interface board/2 which is implemented on a circuit board within a computer in a preferred embodiment of the present invention. The bit-serial flight data from the flight data recorder or copy recorder/da is supplied to the serial-to-parallel converter 6A from the data line 7gk via the playback device //. This serial-to-parallel converter 66 has a λ g-bit shift register for converting the serial data received via the line /g into a /-bit parallel word, which word is then transferred to the data bus. 6g to the data bus transceiver 70. This serial-to-parallel converter is used for temporarily storing a 2-bit data word for a sufficiently long time so that it can be transmitted via the data bus 6g to the random access memory 3'l. It also has a data register.

A new /cobit data word is latched into the data register every l strobe cycles and transmitted from the player /co onto line 6q. The data bus 6g is compatible with the 16-bit data system of the central processing unit.

76-bit parallel data bus, therefore bus 6g
The high order bits of each data word added to will be zeroed out. As shown in FIG. 12, I10 data bus transceiver 70 transmits data to central processing unit 9.2.
It is connected to the data bus 7/ for transmission to the high speed random access memory 741 shown in FIG. 1 via the I10 board U/. A synchronization word detector 71I is connected to a parallel converter 66 by means of a bit data bus 7.2.

The sync word detector 7 includes two 7-bit data registers to hold the sync words being searched for and a pair of lines 76 to indicate which of the sync words has been detected. and 7g. Lines 76 and 7
A status word register gO is connected to g.

This status word register θ is connected to the interrupt control circuit 6 by a pair of control lines θ and gw.

Together with the status word register 10, a word/bit counting circuit it is connected to the interrupt control circuit or controller 6 via a pair of control lines 90 and 9.2 and a clock signal line 9da. Word/bit argument gt is connected to flight data recorder 1 via line q6.
A strobe signal is received on line 96 representing each bit received by serial-to-parallel converter 66 from recorder /lI on line /l. Thus, the word/bit counter g counts the number of data bits being received by the interface board shown in FIG. It serves to generate appropriate control signals to interrupt controller t6. Furthermore, g in the word/bit counter is the number of words/bits accumulated for each subframe.
It has a status register that stores bits.

The interface board in Figure 12 is also.

A data write channel controller 9g is operatively connected to the serial-to-parallel converter 66 via control lines 100 and to the central processing unit 20 via control lines 10 and 103.

In addition, the interface circuit shown in Figure 1.

A command word register IO'l is provided which is connected to either the copy recorder/41 or the flight data recorder IO by control line 10B. This command word register 10 constitutes means for controlling the playback device //. Information is transmitted from the central processing unit, 2O, via the data bus 7/, via the I10 data bus transceiver, by the data bus 101 to the sync word detector 71 and the command word register/04, where the 1 interrupt controller 6 Note that the state word register θ and the data channel controller data are connected to the input data bus A along with the parallel converter circuit 66. Word register go is connected to command word register 10f by control lines /10 and l/co.

Similarly, the word/bit counter gt is connected to the data channel controller ? by the clock signal #il//4t. 8, and the sync word detector 7da is connected to the interrupt controller g6 by a control line //ch. The interrupt signal is generated by the interrupt controller g6 and directly transmitted to the central processing unit-0 via the control line //6. Detailed design criteria for the interface board/2 and its interaction with a suitable central processing unit are as follows:
Data General Corporation cvrfM User Manual - InterfaceDesi
gner'e Reference, Nova and
It is described in Eclipse Line Computers, publication number θ/II-0004ko9-ooJ.

11/-1-' Visual display of flight data of Aircraft 9 from flight data recorder 10; 2. ! The process of generating the upper l and visible display is
The process begins with the initial setting of the interface circuit 7.2 by the central processing unit-0 shown in FIG. Program
Under the control of the central processing unit 20 based on the logic program stored in the memory S<t, the appropriate synchronization word is stored in the data motherboard #il? The output data is transmitted to the interface board of FIG. 2 via / and output data mother ? s/ Og f
The signal is then transmitted to a register provided in the synchronization word detector 7q. 72 bits by serial-parallel converter A
The hardware word address specified by the location or memory location of the seventh buffer 'j'412, which stores the aircraft flight data converted to a word, is also entered here by Iql. Data bus line 7/
transmitted via. This address is stored in a register within the r-channel controller 9g. To provide a data path to central processing unit 20 and memory 3g, a data channel request signal is transmitted from data channel controller 9g via line 102 to central processing unit -0 and is acknowledged by a signal on line 103. be done. After the synchronization word detector 7 has been initialized with the appropriate synchronization word, a start signal is transmitted via line 6 to the command word register IO'l and from there to the control line //6. Via 7, playback device //
Depending on which one is connected to the copy recorder/data recorder 10, it is transmitted either to the copy recorder/data recorder 10 or to the data recorder 10.

Upon receiving the start signal, the flight data recorder/θ or copy recorder/lI directly outputs the data via the playback device//.
The transmission of flight parameters to the parallel converter 66 is started. At the same time, as each lλ bit parallel word is generated on A4, line //'1 is driven to indicate that a /word is being formed. Line 102 is driven to request access to the data channel. Data channel receipt or confirmation signal 103 is sent to the CPU, 2
After returning from 0, the parallel word is on line 6g or 7
transferred to the buffer month via o. This flight parameter data converted into the format of nocopit words is transmitted via line 7.2 to the synchronization word detector 7da, and b deviations among the q synchronization words are detected by the synchronization word detector 7tI. Then, a synchronous interrupt signal is generated and transmitted to line //9 interrupt controller g6. At the same time, this particular synchronization word
and 7g by the status word register go. Note that these signals 76 and 7g serve to identify the specific synchronization word detected by the synchronization word detector.

From the information stored in the status word register θ,
The central processing unit -0 calculates the memory address at which the subframe of the specific data identified by the synchronization word is to be stored in the buffer 4t or A of the high-speed random access memory 3+', and this address is - Transmitted to the address register in the channel controller 9g. For example, if the first synchronization word detected represents the third subframe, the node\ware memory value calculated by the central processing unit
The address would be the starting address of subframe ", 2" as shown in buffer q.

Once the synchronization word consisting of is identified by the synchronization word detector 71I, the interface board of FIG.
Address in data channel controller 99g
Initiate the transfer of the synchronized raw flight parameter data directly to the location or memory location in the buffer ψ memory pointed to by the address stored in the register. Each time the word/bit counter detects 7 points, a clock signal is transmitted on line //'I, thereby causing the data channel controller 9
The word address in the word register of g will be loaded into the incremental memory 4 into the next word of -. Each time each subframe in the buffer memory is filled, the count of subframes is equal to the count in the random access memory ala.

A central processing unit, 20, is maintained within the computer. When the last subframe "/!; The controller is supplied with data to begin writing data to the first buffer tlp.In this way, only a limited amount of random access memory is required to process the flight data.

The flight parameter data is automatically transmitted directly to the buffer memory 1JtI2, so that the central processing unit 2
0 is free to initiate the conversion of raw flight parameter data stored in a buffer device or unit into engineering units such as feet, knots, or degrees for display on a visual display device.

Seven of the main functions of the word counter in the word/pit counter trg are that the last sync word is the sync word detector 71.
counting the number of data words received from those detected by. When the count reaches 63, the train tracks? The clock signal generated on '1 consists of 7
Indicates that the last data word of a subframe is ready to be taken. As a result, the interface board is switched to synchronous search mode. When the next sync word is detected by sync word detector 7da, both the bit and word counters in word/bit counter 1g are reset to zero.

One of the functions of word/bit counter gg is to count the number of data bits received by serial-to-parallel converter 6A. , and the synchronization word detector 741
If no synchronization word is detected by interrupt controller gB, 1711i! An overflow signal is generated on the path qλ which causes the central processing unit 20 to interrupt the conversion process and determine the nature of the received flight data and the memory location in the buffer memory where the flight data is to be stored. Based on this, the memory address (memory address) for the buffer memory is calculated. This memory address is then transmitted to an address register within data channel controller 9g. In addition, CPU (Central Processing Unit)-〇 is
An error fluff is set in the buffer memory indicating that this particular flight data being loaded into the buffer memory may be problematic or erroneous. In addition, the central processing unit-0 creates suitably formatted synchronization words, and these synchronization words are used in the buffer memory group for data received without the detection of synchronization words by the synchronization word detector 7. P6 is paid within. In this way, the flight performance data or flight performance data can be continuously loaded into the buffer memory λ and made available on the display device 2.2 even if no synchronization word is detected, thereby making it possible to include the data. Valuable flight performance data can be prevented from being lost due to possible synchronization errors.

Before the data conversion process takes place, the relevant parameters and flight data units must be selected, typically during system initialization. This is normally done by the operator using the keyboard 2g of the visual display device. Once the relevant flight data parameters and units have been selected,
This information is transmitted to the central processing unit by means of a visual display, 2-.
The central processing unit λ0 then causes the relevant parameters from the parameter data base jg to be transmitted from the bulk memory 3A to a translation table in the high speed random access memory 3. After initialization is complete, selected flight parameters, such as airspeed or altitude, are retrieved from the raw flight performance data stored in the buffer CO and placed in the extracted data buffer SO. This process is performed by the interrupt controller g such that seven complete subframes are identified and stored in the seventh associated memory location within the seventh buffer 179.
The data buffer starts only after an interrupt is generated on the line //A by 6 and thus extracts the relevant data node from this first subframe which is loaded into the buffer memory FF. 50 is certainly possible. 4. After all subframe data has been loaded, the information stored in the conversion table t1.g is used to create the raw data representing the selected flight parameter values. The location of the word within the subframe and the data hit within the word that is accessed to extract the portion of data can then be determined. This extracted raw data is then placed into the extracted data buffer SO. Conversion of raw data to data standardized in appropriate engineering units is performed by converting all selected parameters from Subframe to Buffer Memo I.
J 4t Performed after being transferred to 4t. Each flight parameter is associated with a parameter code stored in a conversion table pr that determines the specific process of converting the raw flight data to the associated engineering units for display on the visual display. There is.

The processing unit, 2O, converts the flight parameters of interest from the raw data values into engineering units using a conversion process coupled to a parameter type code.
unit). This conversion process is accomplished by the system sequentially comparing the table of desired parameter types with its own table of available parameter types. When a match is detected between the tables, the system branches to perform a special conversion process for each parameter type.0 Once the raw data has been converted to a value in final engineering units, this data is stored in the conversion data buffer j − is stored in
A maximum/minimum excursion checking process is then performed if necessary during initialization. In this procedure, if maximum or minimum values are given for predefined flight parameters such as altitude or airspeed, so that these values are not exceeded by the actual flight data, then the visual display , 22 (H(T2) can generate a blinking display.

defined in the parameter database 5g (
All parameters (with the exception of BCD and distance parameters), together with their special scale factors and offset amounts, can be combined with a lookup (index) consisting of pairs of data values and corresponding engineering $ positions. Chiful can be moved south. If the table exists, direct lv!! interpolation to the lookup table can be performed after adding the general(Cfd, off(ant) amount and scaling factor to the raw data values to obtain the intermediate engineering unit result. .

The general flow of the conversion process is as follows.

Raw data: final engineering unit of off-sesoto J and multiplication intermediate results niltukup (index) table.

We use abbreviations below in the detailed description of the conversion process.

EU - final calculated engineering unit XR - intermediate result after one or more calculation steps R/ - lowest word of raw data R2 - most significant word of raw data R3 - third word of raw data (Pneumatic altitude conversion algorithm index) SD Synchronization angle expressed once (Funko angle) FD Fine synchronization angle expressed once CD Coarse synchronization angle expressed once Parameter type: Al (Analog paddle from a single data word meter)
IR = (R/-offset) x magnification (scale factor) KU
=Engineer R: Table lookup (table lookup) Parameter type: A (analog parameter from one data word)
Work R = (R2 x 11091) 10R/ Work R =, (Work R - Offset) x Magnification FiU - Work R: Table lookup parameter type:
Dl ((signed) digital parameter from a single data word) (sign may be from the Uth data word) IR= (+/-)R/ IR= ( IR-offset) x magnification Eυ, = IR,: table lookup parameter type: Dco (signed) digital parameter from λ data words) (sign is the 2nd@th data word) (must be from Word) “EngR = (R u x μ094) + R no E R = (+/-) E R FiU = E R: Table lookup parameter type:
X/ (discrete parameters from a single data word) gU=
R/ Parameter type: X (discrete parameter from one data word) FJU
(L2XJ)+R/ Parameter type: 02 (GMT encoded as BOD value in one data word) 1!1U=HH: MM ('Hours and minutes converted from BOD to ASCII characters) Parameter type: H / (linear from a single data word () standard)
Synchronization) SD=R/: # type synchronous conversion R=(SD-offset) x magnification 1 [J=R: Table lookup parameter type: H, 2 (from 2 data words (altitude) Linear()\Milton standard) synchronous) CD==RConi linear synchronous transformation FD=R/: Linear synchronous transformation if CD is greater than or equal to yro degrees, so QD=C! D-J'AO EngR=((CDXJ7!r)-(FDX/J, zag 9
) Vsoo.

IR, = IR: Round to the nearest integer xR-(vDX
t3. ggq) + (xnxsooo) IR = (EngR - offset) x magnification EU = LR: Table lookup parameter type: T/ (Nonlinear from a single data word (Tθ1θayn
e) Synchronous) SD=R/: Nonlinear synchronous conversion IR=(8D-offset) x magnification EU-Engine R: Table lookup parameter type: T, 2 (Nonlinear (1 'e
:Ledyne) Synchronous) OD:R,2: Nonlinear synchronous conversion FD, -R/ : Nonlinear synchronous conversion when CD is greater than or equal to 3 SO degrees, therefore CD, ,=CD-,? 60 IR=((cDxa7s)−(rrDxiJ, ggy>
)/soo.

Engineering R = Engineering R: Round off to the nearest integer value IR = (FDX/, 7Jff?) + (IRXjOOO)
IR = (R - Offset) x Multiplier KU = R: Table Lookup Parameter Type: P/ (Air Pressure Parameters from a Single Data Word (Airspeed with UFDR Air Pressure)) R' =: R / : Table tool pull-up parameter type: PS (Pneumatic parameters from 3 data words (UFDR pneumatic altitude)) Selects the conversion algorithm based on the value of RJ (Conversion algorithm index).

Index 0-) Determine the calibration coefficient of the transducer from the table θ.

Determine the calibration factor of the index/-transducer from the table/.

Index K to 7 - Diffuse the transducer coefficients
Determine from.

Isn't the index O? Conversion algorithm for: TT, , =
R, 2/10. ．． 2: ) Transducer temperature OT,
,=: Calibration coefficient KT- interpolated from the table indexed by temperature TTi: Calibration coefficient IR interpolated from the table indexed by temperature TT=(17096-RJ)×0I)01! ; Engineering R = (
IR-o'r) / (O, G/eXKT) Engineering R = (Engineering R-
Offset: PS engineering A) engineering R = engineering RX /4t4t00
0,0: PSNA Ru. The information stored in the converted data buffer j- is then converted by the central processing unit into a format compatible with the particular visual display device 22 for direct display on the cathode ray tube, 26. Also, if desired, track J2
It should be noted that this data may be sent to printer/plotter 30 for use in tabulating or plotting aircraft flight parameter data.

In FIG. 3, the graphical (graph) output of the flight data display is shown. That is, a front view of the visual display device 22 is shown, and a typical example of a graphical display of flight data is projected onto the ORT λ6. In this example, the flight parameters of altitude, airspeed, heading, and vertical acceleration are plotted as a function of time (in seconds) on the lower orthogonal axis/here during takeoff of the aircraft. The dashed line 7.2 represents the aircraft altitude, the two-dot dashed line/coro represents the airspeed, the one-dot dashed line l-g represents the magnetic heading,
The solid line /, 30 represents the vertical acceleration. The values of these flight parameters' are displayed on grid segments represented by lines /3 and /3. Preferred visual display device, 2
Since this is a color graphics terminal, various parts of the display are generated in color, such as advanced songs HB/
2y is yellow, airspeed curve 7.26 is green, heading curve 1.2 is light, vertical acceleration curve /, 30 is red, and grid segment lines /32 and /39 are dark. colored in blue. In this particular case, C
The display on the RT2A is generated seven segments or pixels at a time and is expanded to the left. The central processing unit 20 generates seven seconds worth of data at a time from the conversion data buffer S2, so that the visual display device 2.2 can generate the entire display in pixels. Therefore, the operator can use the keyboard 2F to expand the display on the CRT 2A to the right or left to view desired data.

The visual display device -1 is used for initialization and control of the system via the keyboard 2g, so that signals are transmitted via line /36 to the central processing unit -0 so that the operator can define the desired flight parameters. Then, flight data can be entered into the system from the flight data recorder 10 or copy recorder/4I- using the keyboard 2g. In a preferred embodiment, g
Up to two different flight parameters can be displayed simultaneously with λ discrete values.

Furthermore, the operator can start, stop, select a particular trunk, hold or continuously operate the copy recorder/41 in operation via the keyboard λg using the control functions transmitted via the central processing unit 20 and the playback device ii2. It is possible to command. Additionally, the preferred visual display device has zoom capabilities so that operator
Any item of interest using control with Keyhotco S>
It is possible to magnify and intensively observe any flight parameters.

[Brief explanation of drawings]

1 is a functional block diagram of the aircraft flight data display system; FIG. 2 is a functional block diagram of an interface circuit used with the aircraft flight data display system of FIG. 1; and 3M is a functional block diagram of the aircraft flight data display system shown in FIG. FIG. 3 is a diagram illustrating an example of a graph display of flight data. go...Status digit register, gg...Word/bit counting circuit, 9θ, 92...Control line, 9q...Clock its number IHz g A-, controller, 1
0.1.Flight data recorder, /9..Copy recorder, 9g..Data channel controller, 6.
6...Car parallel converter, 70g...command word register, //...playback device 1.20...central processing unit [θ(c
pu), A'g, 7'/, /θg...Data bus line, //q...Clock signal line, 7q...Synchronization word detector, //Otsu, //q, //7... Control line, /co...
Interface board, 511...Program memory, 4tλ, +47. &A...Buffer 1341...
High-speed random access memory, 36...bulk memory, 4gg...conversion table, Sθ...extracted data...
Buffer, 7g...Data line 1.2/...Input/output board, Sg,! ;4. Sg, 40,62. All...Location (memory location), 10...10 data bus transceivers, 7 da...synchronization word detector, gno...interrupt controller, S2...conversion data buffer 1.2 co...visual display device , 3θ... printer/block, 2g
・・Keyboard, λ6・, CRT. 4025 Thirty-Third Street, Three Hundred, Federal Way Southwest, Washington, United States 0 Inventor Dipid Nyuusma 13331 One Hundred Ninety-First Brace Southeast, Washington, United States

Claims (1)

Claims: (1) a data storage device for displaying flight data from an aircraft flight data recorder; input means operatively connected to a source of flight data and said data storage device for formatting and storing flight data in said data storage device; and input means operatively connected to said input means and said data storage means for said formatting. processor means for converting selected portions of the converted flight data into engineering units and storing the converted flight data in the storage device; and a video display device for selecting said portions of said re-formatted flight data to be converted to engineering units, and having a keyboard for displaying said converted flight data. flight data display device u0 for displaying flight data from an aircraft flight data recorder (2) data storage means for storing data for direct display of flight data from an aircraft flight data recorder; input means operatively connected to said data storage means for storing flight data including synchronization words in said data storage means; processor means for converting selected portions into engineering units while data from said flight data source is stored in said data storage means; and display means for displaying said selected portion. A flight data display device for directly displaying flight data from an aircraft flight data recorder. Example: The flight data display device according to claim 2, wherein the processor uses the input means to cause the flight data to be stored in the data storage means. (i) The flight data display according to claim 3, wherein the input means comprises means for converting the format of the flight data from the aircraft flight data recorder into a format compatible with the data recording (fi) means. Apparatus. (&) A flight data display device according to claim 3, wherein the input means comprises detection means for detecting a synchronization word and generating a synchronization signal. (6) From an aircraft flight data recorder. a source of raw flight data and an interface circuit operatively connected to the source of raw flight data to enable formatting of the raw flight data for displaying the resulting flight data; and a high speed random access memory; a bulk memory, the interface circuit being operatively connected to the high speed random access memory and the bulk memory to cause the interface circuit to transfer the reformatted raw flight data to the high speed random access memory; converting selected portions of the re-formatted flight data into engineering units and loading the converted flight data into a first predetermined location within the fast random access memory; a central processing unit that stores data in one predetermined location;
a 5-view display unit operatively connected to the central processing unit for displaying the converted flight data stored at the first predetermined location.