DE202004007747U1 - Aircraft monitoring system e.g. for air traffic control of aircraft, has on board computer for data storage and or data processing with measuring module - Google Patents

Abstract

The system comprises an on board computer (1) for data storage and/or data processing and a measuring module (2). Sensors (2a, 2b... 2n) detect the technical operational data of the aircraft and are interconnected. The measuring module is interconnected to the sensors and a GPS module to collect flight data and position data and in turn is connected to the communication module. The flight data is fed into the communication module (4) for long-distance data transmission with GPS information (3). An independent claim is included for a computer program and a computer-readable storage medium, on which a program is stored.

Description

The The invention relates to a device and a computer program for air traffic control of aircraft by means of data acquisition and remote data transmission and is applicable especially for small and medium-sized motor, sports and glider aircraft.

The Flight surveillance system according to the invention is preferred everywhere can be used where control and monitoring tasks in the to solve private aviation are.

Out It is well known in the prior art for operating data of vehicles in a suitable form and by radio Control stations transferred to. A well-known example of this is radio transmission for example engine speed, speed, temperature values etc. at car racing events.

Farther it is known to equip aircraft with a black box, which stores relevant operational and flight data so that this data can be targeted later, for example to determine the cause of the crash.

With the DE 196 08 516 A1 describes a documentation system for recording flight object data, in which the location and recovery of flight recorders is no longer necessary to clarify the causes of the crash. For this purpose, a data recording for recording the data relevant for clarifying the causes of the crash and a transmitter continuously emitting the data are associated with the flying object. The data are transmitted via satellite and collected by a receiver stationed on the ground, which is equipped with a recording device for the continuous storage of the received data.

adversely with this solution is that two flight recorders are needed and the data are transmitted via satellite.

From the DE 39 29 581 A1 a device for registering flight paths and flight maneuvers of aircraft is known, in which a data-collecting device is attached to the aircraft for this registration. This device is used to record flight paths and flight conditions. The purpose of the registration is the subsequent simulation during pilot training.

With this solution only flight data are recorded and there is no remote data transmission. The data is only evaluated after the flight.

The DE 100 46 007 C1 describes a flight control system, which is installed in the cockpit and automatically detects flight conditions that are critical to safety and provides the pilot with advice on how to correct these flight conditions in good time.

Under Use of a computer running parallel to the flight control and Fuzzi Logic carry out a risk assessment regarding the current flight status.

This solution is based on an error summation display and does not include any Remote data transmission.

The The invention has for its object a device and a Computer program for flight surveillance to create aircraft that are effective, safe and inexpensive data acquisition, data storage, data processing and data transfer enable.

This The object is achieved by the features in the characterizing part of claims 1, 11 and 18 in cooperation with the features in the respective generic term. Appropriate configurations the invention are contained in the subclaims.

On particular advantage of the invention is that a timely and comprehensive collection, processing and transmission of data via the technical condition and the flight condition of aircraft is made possible, by providing the following procedural steps:

• - registration technical operating data of the aircraft,
• - registration flight data and position data of the aircraft as well as general data,
• - storage and processing of the recorded operating data, flight data, position data and general data in the aircraft,
• - Transmission the recorded and / or stored and / or processed operating data, Flight data, position data and general data via radio to a receiving station.

On Another advantage of the invention is the recognition of the achievement or exceeding limit values and load limits using a device, which an on-board computer for data storage and / or data processing with a measuring module, which with sensors / data transmitters for recording technical operating data of the aircraft is connected, one GPS module for recording flight data and position data as well as a Communication module for remote data transmission is connected.

The Detect Exceeding of limit values and load limits of an aircraft is in particular important if the cause of damage to the engine and others damage must be determined and made liable. It also offers the opportunity the timely tracking of certain technical data and flight data (for example engine speed, pressure, temperature, altitude, speed, Acceleration, position and course) starting points to avoid Border crossings, to Compliance with flight areas, to increase flight safety, for example also the subjectively perceived safety of flight students and for counter-terrorism, for optimal flight evaluation and evaluation and for leading electronic flight books.

On additional Advantage of the invention is that a computer program for air traffic control of aircraft by means of data acquisition and data transmission it allows a computer after it has been loaded into the computer's memory, a flight surveillance process perform, in which

• - technical Operating data of the aircraft are recorded,
• - flight data and position data of the aircraft as well as general data become,
• - recorded Operating data, flight data, position data and general data in the aircraft stored and processed,
• - recorded and / or stored and / or processed operating data, flight data, Position data and general data are transmitted by radio to a receiving station become.

For example can these computer programs (for a fee or free of charge, free accessible or password protected) made available for download in a data or communication network become. The computer programs provided in this way can then be made usable by a method in which a computer program according to claim 18 from an electronic data network such as from the Internet to a data processing device connected to the data network is downloaded.

Around a procedure for flight surveillance of aircraft by means of data acquisition and data transmission perform, a computer-readable storage medium is advantageously used, on which a program is stored that enables a computer to after it has been loaded into the computer's memory to carry out such a procedure, in which

• - technical Operating data of the aircraft are recorded,
• - flight data and position data of the aircraft as well as general data become,
• - recorded Operating data, flight data, position data and general data in the aircraft stored and processed,
• - recorded and / or stored and / or processed operating data, flight data, Position data and general data are transmitted by radio to a receiving station become.

In a preferred embodiment of the computer program according to the invention it is provided that recorded data is compressed and / or in a nonvolatile Memory such as an EEProm can be saved. In order to is achieved that registered data is resistant to network, Battery failure and against destruction other components.

In another preferred embodiment of the computer program according to the invention, it is provided that the computer program carries out a storage space management, in particular a reduction in the storage space used for data to be read in and / or read out, in order to reduce access times to the data. In particular, this measure can prevent incoming commands, which may be contained in SMS, for example, from being lost. Long access times through the Modemhard ware (reading individual SMS) z. B. avoided by filling up and / or locking part of the storage space. The modem in particular then reports "memory full" to the provider center. The memory location is thereby shifted to the short message center.

A further preferred embodiment of the computer program according to the invention provides that to control the process of flight surveillance Protocols used by aircraft for used and / or device-specific Commands are expandable.

In addition is it possible that the computer program is a review of for the Remote data transmission necessary criteria, such as credit for communication fees. With a query of data that is not directly technical operating data or flight data, it is prevented that e.g. B. by a used up Communication credit the transmission is affected by critical technical operating data or flight data. It proves to be particularly advantageous that the computer program Data collected cyclically.

Of It is also an advantage that the computer program includes modules which, controlled by protocol commands, can be (de) activated. A particular advantage is that these protocol commands if necessary externally via Keyboard, cell phone or internet PC can be entered. Another Embodiment sees that modules are activated / deactivated depending on the password.

• – eine parallele oder sequentielle Abarbeitung von Protokollbefehlen,
• – eine Kennzeichnung von kritischen Betriebsdaten, Flugdaten, Positionsdaten und/oder Allgemeindaten und/oder
• – eine bevorzugte Abarbeitung und/oder eine zwangsweise Übermittlung von gekennzeichneten Daten

erfolgt.In a further special embodiment of the computer program according to the invention it is provided that

• - parallel or sequential processing of protocol commands,
• - Identification of critical operating data, flight data, position data and / or general data and / or
• - a preferred processing and / or a compulsory transmission of marked data

he follows.

The The present invention realizes a system solution with flight and technical data acquisition, data transfer and data evaluation and long-term storage, especially for small aircraft.

The system

• - increases the general and special flight safety (especially protection against sabotage and allows additional Protection against terrorism) or security against abuse or theft, including an optional intervention in the management of the aircraft such as switching off the engine over safe terrain and Prevention of unauthorized use of the aircraft (by means of Wegflugsperre)
• - can when triggered send the last position data of the rescue system to the fastest possible rescue and to provide first aid
• - supports the proper and careful Handling the aircraft,
• - avoids or reduces excessive wear on the airframe,
• - helps To receive warranty claims or enables assured liability of negligent or intentional Wrongdoers,
• - can basis for air sports events, competitions and championships and work tools of an optimal evaluation,
• - enables one electronic flight log,
• - can student pilot monitor better if exceeded of limit values and optimal flight evaluation and advice.

All Data registered in the aircraft or only limit violations can recorded, saved and sent. Before the aircraft lands, the most important flight and engine data have been received. As receiver is used, for example, a radio telephone (or the classic one Radio act as an intermediary to the GSM network). The data can too be sent to a central recording on a server (PC).

The Position and course data recorded can be informative or cartographic be determined.

The system works as an interaction of sensors / data transmitters, computing / data processing processing units as well as display and transmission components. The following actions take place in the system in an orderly and timely manner:

• - To capture
• - To calculate
• - Link
• - evaluate
• - Show in real time, acoustically and optically on site (in the aircraft or in the mobile system)
• - Send (timely) of data during of the flight or during landing via SMS and / or. DFÜ (remote data transmission) (u./o. using classic radio as an intermediary to the GSM network), i.e. via GMS modem, or during real-time viewing on other mobile systems and timely sending 1. as a limit or setpoint violation with "That" and "What" as an alarm message and   2. When requested as sending the complete data record the entire flight section or driving section for other mobile systems
• - Display is designed as a KAPI code as follows (based on existing Codings developed from avionics): - Date day, month / UTC / position / altitude feet / ground speed km / h / - Speed TAS km / h / course degree / temp. CHT (cylinder head) C ° / - Temp. Oil C ° / Temp. Water/ - Drez. RPM / acceleration g x = q, y = h, z = l

Example (SMS)

• 1803/1401 / N524343-E0133800 / ft: 04000 / GS 230 /
• TC: 050 / TAS: 210 / CHT: 170 /
• OT: 100 / WT: 85 /
• RPM: 3200 / g: 2q-3h

The selected System for small and medium-sized motor, sports and glider works with the following sensors / data transmitters:

Recording technical conditions:

• A speed (motor)
• B temperature cylinder head (engine)
• C engine oil temperature
• D Water temperature (with water-cooled engine), oil pressure

Acquisition of flight status data

• E speed over ground
• F speed versus the flowing one Air, true air speed
• G acceleration of all three spatial axes (x-, y- and z-axis)
• H height above MSN

Capture more / others Data

• I rain sensor
• J GPS position
• K GPS course
• L date, time

In The following table shows examples to be identified and avoided and technical or flight conditions to be checked listed with the respective "responsibilities" of the sensors / data transmitters:

The The invention is intended to be based on at least partially in the Illustrated embodiments are explained in more detail.

It demonstrate:

1 2 shows a block diagram of the device according to the invention,

2 an example of a flight diagram.

How out 1 can be seen includes the device for flight monitoring of aircraft next to the on-board computer 1 the GPS module 3 , the measuring module 2 and the communication module 4 ,

The The "flight data recorder" program consists of the following Main modules:

• - that GPS module
• - that Measuring, evaluation and processing module
• - that communication module

All modules 2 . 3 . 4 are linked via defined interfaces and with the on-board computer 1 connected. The modules run depending on the application 2 . 3 . 4 sequentially or in multitasking mode.

Besides, was implemented an open system during programming. perspective Extensions are therefore easily possible.

Within the modules 2 . 3 . 4 Individual program parts can be switched on externally using a keyboard, cell phone or Internet PC.

Below are the individual modules 2 . 3 . 9 described in detail.

The GPS module 3

The System has several serial interfaces. One of them is direct connected to a standard GPS device.

requirement for one Smooth reception is the standardized NMEA format.

The following functions are performed by the GPS module 3 realized:

• - multiple Reading the GPS data in the defined time cycle,
• - multiple exam for validity the data record in the defined time cycle,
• - selection the date, time, speed and position data record (RMC) and the height (GGA) data set,
• - Refurbishment of the RMC record for Date, world time (UTC), exact position, speed (above ground / GS in km / h or knots) and course (TC)
• - Refurbishment of the GGA record for the height (ft or m),
• - either the speed as well as the height are in depending on the option different measurands within converted the program,
• - visual Formatting for further processing in other modules,
• - mathematical Formatting for Comparison operations (e.g. maximum value determination),
• - assignment and linking the data with aviation technical vocabulary,
• - Construction switchable program parts for various output and visualization options (laptop, TV, LCD, 7-segment display, graphics terminal ...),
• - Structure of the I code (GPS part 1 and 2 ) for sending SMS and e-mail,
• - Administration the permanent memory bank for GPS raw data,
• - Layout the temporal reception and storage cycles (5 sec to 10 h).

The GPS data is read into a central memory buffer. Opposite the direct reading method has the advantage that a direct temporal Connection of the RMC and of the GGA data set guaranteed becomes. This means the speed (RMC record) is in the same time window like the height (GGA record) registered.

Out the memory buffer, the above Data records selected and separated stored. these can then over the communication module by SMS, mail or by fast GPRS data transmission be used.

conventional Card systems need the direct storage of a GPS device for cartographic output. In contrast, possible the system according to the invention savings by means of a microcontroller-controlled GPS simulation elaborate card programming or use existing map software.

The is called, the stored RMC and GGA data records from the transmitter modem (for example from a UL aircraft) into a stationary modem storage system. Thus the modem storage system can emulate a GPS device and thus directly in a PC or notebook transfer the data cyclically. A route tracking let yourself thus easy to implement.

After the RMC and GGA data sets have been selected, the core data such as date, UTC, position, speed over ground, course and altitude are processed. The core data are in character form (ASCII format). In order to be able to carry out fast logical operations, routines and further mathematical links, reformatting must be carried out, for example determining the maximum value of the speed and the altitude, as well as comparing "ground speed" (from GPS) and "true air speed" ( see description of measuring module 2 ) for the calculation of wind influence.

The core data is converted into strings for the construction of the code. This creates a clear form of relevant GPS and operating data (see description of measuring module 2 ). The code is implemented by multiple linking of GPS and operational data strings (see description of the measuring module 2 ). This is in turn suitable for sending SMS (cell phone, pocket PC).

A for this embodiment characterized SMS has the following content:

• - date Day, month / UTC / position / altitude Foot / Ground Speed km / h /
• - Course Degrees / Speed. TAS km / h / temp. CHT (cylinder head) C ° /
• - Temp. Oil C ° / Temp. Water/
• - Speed RPM / acceleration g x = q, y = h
• - Example (SMS) 1803/1401 / N524343-E0133800 / ft: 04000 / GS 230 / TC: 050 / TAS: 210 / CHT: 170 / OT: 100 / WT: 85 / RPM: 3200 / g: 2q-3h

Above The core data formats mentioned can also be viewed in different ways Use output media. The code has an optional variant the connectivity of LCD, LED and graphic display displays. Even the direct connection on notebook and TV is possible.

The GPS module 3 in the present exemplary embodiment also contains a time control for setting the reception cycle and a storage cycle chosen by the user. These settings include the compression or extension of the overall time documentation. Reception cycles can be set from permanent monitoring (real time) up to 1 minute, and accordingly the storage cycles.

All GPS raw data as well as the formatted core data are in one internal circular storage. Obtained at the largest storage capacity you have a total documentation of max. 50 hours. Nichtabgerufene Data is overwritten after a preset SMS warning.

The measuring module

The measuring module 2 includes the acquisition, formatting and preparation of the operating data. The measuring module exists on the hardware side 2 from measuring board 6 , Multiplexer 7 and measuring adapter 8th ,

The following Operating data can are recorded and processed:

• - the CHT
• - the oil temperature
• - the water temperature
• - the "true True air speed "
• - the barometric pressure
• - the direct speed (voltage follower) from the measuring instrument
• - the optically recorded speed
• - the magnetically detected speed
• - the humidity Index
• - the acceleration ( 3 Axes)
• - the angular acceleration

The Cylinder head temperature measurement is carried out with various sensors. Both analog resistance sensors and digital I2C bus sensors are used.

The The advantage is reliability and linearity of several components as well as in direct comparison (error minimization).

So can different measuring points (e.g. cylinder II) can be evaluated.

A multi-level averaging is implemented in the program. Up to 200 measurement accesses are linked to the following approximation methods. The accuracy is in the decimal range guaranteed.

Parallel runs in Background a calculation according to the following formula:

temperature = (0.390802 / (2 * 0.00005802)) - math.sqrt (((0.390802 * 0.390802) / (4 * 0.0000582 * 0.0005802) - ((Resistor-100) / (0.00005802))))) + 273.15

The Machining of oil and water temperature is carried out analogously to the procedure mentioned above.

The Capture the "true Speed " fed by a pressure difference sensor module. The pressure difference is output by a voltage. Via optocouplers and analog-digital converters a mathematical grid is created (0-1023 measured values). The other Access via an assignment table enables the Read out exact speed values. A careful calibration and testing is the prerequisite for the measurement method mentioned above.

Analogous the moisture is processed for the latter methods.

The direct measurement of the speed (tap from the measuring instrument) is in present embodiment the most technically and mathematically complex solution. Analog to the engine speed an alternating voltage of 0 to 11 volts follows. The fluctuation range per time unit is seriously large. Elaborate wiring, an average and correlation method determine the output of the Rotational speed. The cause of these peaks is the tap on the engine management of the plane.

The internal measuring instrument is very sluggish and thus enables in contrast to the digital evaluation an acceptable display.

programmatically is the smoothed and shared tension across an optocoupler and measuring board are fed to the AD converter. The Divisor factor must in turn be assigned to an empirically determined table become. Then there is a grid-oriented speed output.

in the Contrary to the direct speed output is the measurement via optical Sensors easier.

Only the restriction on night flights is taken into account.

Based An internal division factor is determined for the number of rotors. The physical signals are fed to a frequency port. There the frequency is determined. The subsequent multiplication is guaranteed the specification in rpm.

alternative a magnetic method can be used for direct measurement become. The installation is rotating in the internal engine management Parts attached. This process has proven itself in industry. Based Hall sensors are used for reading and further processing via the above called analog-to-digital conversion.

The Acquisition of acceleration / angular acceleration is subject to one time-critical routine.

On capacitive process guaranteed the acceleration measurement up to 10 g. To capture an impulse is a thread routine (parallel processing at the atomic level according to microcontroller manual) required. Enable extensive "on-site tests" but an empirical comparison.

Of The position of the circuit must also be calibrated (3-axis).

All processed data is a subroutine for maximum value determination fed. This Subroutine calculates the currently recorded maximum value and stands after appropriate formatting ready for SMS / mail request.

ever the subroutine can be switched on and off according to customer requirements.

In the running measuring module 2 the real-time values (operating data) are pre-tapped. These are minimized in a compression subroutine (masking out more significant bits).

advantage the action is the much larger storage volume (100: 1) opposite a string storage.

The The compressed values are stored in an EEProm. Enrolled Data are therefore resistant to mains, battery failure and destruction of the other components. In emergency situations, this can be done using a second unit read back and be evaluated.

After SMS / Mail request, the process runs in reverse order. The EEProm data is sent to the transmitter via a formatting program and code structure (see description of communication module 4 ).

The The structure of the software module "Measure" was designed that all additional innovative sensor technology as quickly as possible and can be easily integrated. Time-critical routines are running as described above in parallel.

To but note that the size and performance the software remains limited by the microcontroller.

The communication module GSM / GPRS

Hardware basis for the communication module 4 is an industrial modem in the present exemplary embodiment. The area of application mainly concerns the SMS / E-Mail / FAX and data transmission. Voice output can be activated optionally. All initializations, test sequences, send and receive routines must be emulated in the so-called modem language (AT programming) using the C language specified by the microcontroller. Each AT command is declared by a program function.

Example: "Delete SMS on modem storage space 1 "function cmgd1 () {// output interface A, at + cmgd = 1, ...}

The communication module 4 is extensively documented. All Hayes commands used (inventors of the modem language) are contained in the source (program code).

Additionally programmed Enable functions a visual (via Notebook) and acoustic (anthem, sound sequences) identification via the current status of the program.

The Modem has 40 SMS memory locations on the hardware side. To long access times through the modem hardware (reading individual SMS) following measure applied: Of the 40 memory locations, the code requires a maximum of 2 to be evaluated SMS. The rest is filled up and locked. The program thereby avoids having multiple incoming SMS can be lost. The modem reports after 2 received SMS messages, "memory full" to the provider center thereby moved to the short message center.

To Processing the SMS requests, the modem releases the memory spaces. The head office then delivers the accumulated SMS, which without losses can be edited.

to user-friendly use or from safety-related aspects the so-called KAPI protocol was created. The structure outgoing and incoming SMS is structured as follows:

weitere Anwendungen:Example 1:

other applications:

* pwdair # - shortcut
this means: incoming SMS request -> sending the general KAPI code to the cell phone and / or the Internet.

* pwdlcd # & call me back * - detailed command
This means: SMS appears on the on-board LCD with the text "Please call back".

*pwdeon#&andreaspilawski@web.de*
this means: parallel connection d. given email address,
the data / KAPI code are sent both to the cell phone / MDA and to the Internet.

* Pwdgua #
This means: Information request for credit from GSM card / prepaid card via SMS.

* Pwdflb #
This means: SMS request to send flight book entry (with mail connection to the Internet).

All in all Around 50 commands are currently available to the user. additional Let customer requests expand without complications.

Around a safe and trouble-free Procedure for GSM modem communication to ensure everyone log-on procedures interpreted and regulated individually.

The following Initialization steps are activated and evaluated in the online login.

• - Attitude the text mode,
• - Instruction on change the network status,
• - Automatic Dial-Up Network,
• - Attitude the syntax GSM 07.05 PH + (standardized outputs and messages )
• - Attitude the transfer rate (Baud rate),
• - activation the phone number the message center,
• - deactivation the modem echo,
• - parameter setting to register incoming SMS,
• - Settlement the temporal polling cycle.

The next Step includes the query "Modem online?". The subroutine the modem answers with the Hayes command "at". After a positive message, Flag (status cell) set.

Further Queries are:

• - query the required signal strength,
• - Read in the card balance,
• - control of the shortfall credit.

Sinks the credit limit (prepaid card) of the KAPI to less than 5.00 euros, the information is immediately sent to the user via SMS / mail. This is repeated cyclically for each start started.

The Flags of the individual procedures influence the further program flow essential.

The following Status messages are examined cyclically.

• - Password Flag
• - Tel. No flag
• - alarm Telephone number. Flag
• - text Flag
• - modem online flag
• - modem booked flag
• - Signal strength OK_Flag
• - Credit_Flag (not for contract cards)

The Initialization of the RS 232 interfaces ends the "check in "the KAPI.

To The main cycle begins when the modem is successfully initialized. As in the initial init, the functionality is checked cyclically.

Parallel the receive buffers and all Status cells reset.

The microcontroller begins to access the SMS memory locations 1 and 2 , For security reasons, access is carried out twice. A filter hides all invisible characters.

in the In text mode, the structure of the sent cell phone number is checked and separated stored. In connection with the SMS command "air", the calling GSM number (cell phone) be immediately registered as a destination.

The second step involves the grid-oriented selection of Password, command including additional information. Just like the above Tel storage is the separate storage of password / command and additional information.

To successful filtering of the SMS request begins in functions branched command processing. This is modular and can expanded by the command structure of 3 letters and / or numbers "air / lcd / 123 / xyz" be (see above).

To note that the surrender the "alarm flag" (for example speed> 2800 rpm) has top priority and is processed before all functional branches.

Accordingly also the hardware-based emergency situation report triggered automatically or by the pilot.

The Invention is not limited to the embodiments shown here. Rather, it is possible by combining and modifying the means and features mentioned further versions to realize without leaving the scope of the invention.

1

Bordcomupter

2

measurement module

3

GPS module

4

communication module

5

Cock-pit module

6

measurement board

7

multiplexer

8th

measuring adapter

Claims (17)

Device for flight monitoring of aircraft using sensors / data transmitters, on-board computers and GPS receivers, characterized in that an on-board computer ( 1 ) for data storage and / or data processing with a measuring module ( 2 ), which with sensors / data transmitters ( 2a . 2 B , ... 2n ) is connected to the acquisition of technical operating data of the aircraft, a GPS module ( 3 ) for recording flight data and position data as well as a communication module ( 4 ) is connected for remote data transmission. Device according to claim 1, characterized in that the on-board computer ( 1 ) has at least one microprocessor and at least one erasable and programmable read-only memory (EPROM). Device according to claim 1, characterized in that the on-board computer ( 1 ) with a cockpit display module ( 5 ) connected is. Device according to claim 1, characterized in that the sensors / data transmitters ( 2a . 2 B , ... 2n ) are separate sensors / data generators, which are arranged parallel to the conventional sensors / data generators arranged for cockpit instrumentation. Device according to claim 1, characterized in that the technical operating data, the engine speed and / or the Cylinder head temperature and / or the engine oil temperature and / or the cooling water temperature and / or the oil pressure are. Device according to claim 1, characterized in that the flight data the ground speed, the speed across from the flowing one Air, the acceleration of all three spatial axes and the height above sea level are. Device according to claim 1, characterized in that the position data is the GPS position and the GPS course and the General data is the date and time. Computer program that enables a computer after it has been loaded into the computer's memory Flight surveillance procedures of aircraft by means of data acquisition and data transmission perform, in which - technical Operating data of the aircraft are recorded, - flight data and position data of the aircraft as well as general data become,  - recorded Operating data, flight data, position data and general data in the aircraft saved, processed and evaluated, - recorded and / or stored and / or processed operating data, flight data, Position data and general data are transmitted by radio to a receiving station become. Computer program according to claim 8, characterized in that captured data is compressed and / or in a non-volatile Memory such as an EEProm can be saved. Computer program according to claim 8 or 9, characterized characterized that the computer program is a space management, in particular a reduction in the number to be read in and / or out Data used storage space, implemented to reduce access times on the data. Computer program according to claim 8 to 10, characterized characterized in that the computer program is implemented in such a way that to control the process of flight monitoring of aircraft Used protocols can be expanded with user- and / or device-specific commands are. Computer program according to claim 8 to 11, characterized characterized that the computer program is a review of for radio data transmission necessary criteria, such as credit for communication fees. Computer program according to claim 8 to 12, characterized characterized in that the computer program records data cyclically. Computer program according to claim 8 to 13, characterized in that the computer program Includes modules which, controlled by protocol commands, can be (de) activated. Computer program according to claim 14, characterized in that the activation / deactivation of modules is password-dependent. Computer program according to claim 8 to 15, characterized characterized that - one parallel or sequential processing of protocol commands, - a label of critical operating data, flight data, position data and / or General data and / or - one preferential processing and / or a forced transmission of marked data. Computer-readable storage medium on which a program is saved, which allows a computer after it is in memory the computer has been loaded, a method for flight monitoring of aircraft by means of data acquisition and data transmission perform, in which - technical Operating data of the aircraft are recorded, - flight data and position data of the aircraft as well as general data become, - recorded Operating data, flight data, position data and general data in the aircraft saved, processed and evaluated, - recorded and / or stored and / or processed and / or evaluated operating data, Flight data, position data and general data are transmitted by radio to a receiving station become.