DE102010024541B4 - Method for interrogating measurement and / or state data from a data memory of a sharp unmanned missile and device for carrying out the method - Google Patents

Abstract

Method for interrogating measurement and / or state data from a telemetry data memory (20) of a sharp unmanned missile (1 '); the missile (1 ') having an umbilical connection (12) at which the missile (1') can be connected to a carrier aircraft for exchanging mission data and / or status data via a umbilical cable (50); wherein the umbilical cable (50) comprises an external bus line forming part of an external data bus (4) through which a missile central computer (2) and a carrier aircraft computer can communicate with each other; wherein the missile in the non-sharp state with a test module (76) is connectable, which is connectable to an internal data bus (3) of the missile and which can monitor the data traffic of the internal data bus (3) and thus the measurement and / or state data of the missile,   wherein the test module (76) in the sharp state of the missile (1 ') is not connected to the missile and -. wherein the central computer (2) is provided with a software object which always collects all the relevant internal data of the missile (1 ') in real time and caches it in the volatile telemetry data memory (20), characterized in that; in the sharp state of the missile (1 ') from an operating device (56) which is connected via an adapter box (5') to the external data bus (4), an instruction for a in the central computer (2) of the missile (1 ') executable software for activating data access is sent; Figs; that interrogation commands are sent via the external data bus (4) to the central computer (2) of the missile (1 '); in that the central computer (2) of the missile (1 ') sends measurement and / or status data from the telemetry data memory (20) via the external data bus (4) and the adapter box (5') to the operator device (56) in response to the query data , - the operational embassy and transfer design remains unchanged.

Description

TECHNICAL AREA

The present invention relates to a method for interrogating measurement and / or state data from a data memory, in particular from a telemetry data memory, a sharp unmanned missile according to the preamble of claim 1. It further relates to an apparatus for performing this method.

In the case of unmanned operational missiles, it has hitherto not been possible for safety reasons to carry out a detailed measurement data collection for troubleshooting or for a status investigation on a sharp, ie equipped with a weapon, missile. So far, the missile had to be made inert first. This means that the armament and pyrotechnic actuators were first to be removed from the missile. Only then could a data monitoring device for the internal data bus of the missile be installed, for which purpose an external computer with suitable software was connected to the internal data bus of the missile. By means of this recording module, relevant data could then be recorded and made available by monitoring the internal data traffic of the missile during corresponding tests.

However, this known approach is disadvantageous for two reasons. On the one hand, the time required to retrofit a sharp missile into an inert missile and the required after the test retrofitting the inert missile in a sharp missile several hours and it is for the expansion of the armament special tool required that not at every storage place of armed missiles is available, so that in addition a transport of the sharp missile may be necessary in a corresponding workshop. On the other hand, when refitting the missile from the sharp to the inert state, changes are made to the configuration of the missile, which may make it possible that certain errors that occurred in the armed state of the missile after the conversion no longer occur and therefore not can be determined.

The DE 10 2006 041 140 B4 discloses a method for checking the operability of unmanned, armed and sharp missiles. This test procedure serves to test the missile connected to a test setup and not attached to a carrier aircraft by means of a defined test procedure. The missile is not in operational mode, but in a defined test mode. When performing these tests, categorized error messages and error images are detected, and non-fatal errors are stored in a special memory device that can be queried upon completion of the test.

The DE 10 2004 042 990 B4 relates to a test method and apparatus for sharp missiles. This is a test procedure and not an operational operation of the missile. From this citation no transmission of measurement and / or condition data of the missile to the outside is already known.

PRESENTATION OF THE INVENTION

It is therefore an object of the present invention to provide a generic method, with which it is possible without reading a sharp unmanned missile and without interference with the sharp unmanned missile read measurement and / or state data of the sharp unmanned missile from the telemetry data store in the test mode to be able to.

This object is achieved by the method specified in claim 1.

This inventive method relates to the retrieval of measurement and / or state data from a telemetry data memory of a sharp unmanned missile, wherein the missile has a Umbilical connection, at which the missile via a Umbilical cable with a carrier aircraft for the exchange of operational mission data and / or Condition data connectable, wherein the Umbilical cable has an external bus, which is part of an external data bus through which a central computer of the missile and a computer of the carrier aircraft can communicate with each other for operational data exchange, wherein the missile in the non-sharp state with a test module connectable, which is connectable to an internal data bus of the missile and can monitor the traffic of the internal data bus and thus can access measurement and / or condition data of the missile, wherein the test module in the sharp state of the missile not with the Flu Body is connected and wherein the central computer is provided with a software object, which always collects all relevant internal data of the missile in real time and caches in the volatile telemetry data memory.

The achievement of the object is that in the sharp state of the missile from an operating unit, which is connected via an adapter box to the external data bus, a command for a in the central computer of the Missile executable software is sent to enable data access, polling commands are sent via the external data bus to the missile central computer, and the missile central computer sends measurement and / or status data from the telemetry data store over the external data bus and adapter box in response to the polling data sends to the HMI device, leaving the operational message and transfer design unchanged.

ADVANTAGES

The invention thus consists in using the external data bus, which is actually provided only for the operational communication of the missile with the carrier aircraft, via which a mission data exchange between the carrier aircraft and the missile takes place in the armed state of the missile for test purposes, by the test device interrogation commands to send to the central computer, which cause the central computer to send back measurement and / or status data from the present in the operational state telemetry data memory to the tester. In this case, the fact is used that the central computer of the missile is already provided with a software object, which always collects all relevant internal data of the missile in real time and caches in a volatile telemetry data memory for the telemetry radio transmission. Instead of carrying out a bus monitoring with a test device connected to the internal data bus of the initially inertized missile, according to the invention a test device is connected to the external data bus not provided and the interrogation commands for outputting the measurement and / or status data are sent by the test device via this external data bus sent the missile's central computer, which converts it into data streams into the telemetry data store and then sends the read data back to the tester via this external data bus. Since the operational embassy and transfer design remains unchanged, unwanted and disruptive side effects in operational operations can be avoided.

The operator can configure which data is accessed (freely selected, module-related or function-related data) and with which update cycle the data is read out and transmitted (once, cyclically and rate).

For this purpose, the write and read access to the telemetry data store is preferably first enabled via a activation command sent to the central computer of the missile via the external data bus before the commands for data query of the telemetry data store are sent.

An advantage of this solution according to the invention that no additional hardware for the missile such. B. Equipment for radio telemetry or data bus monitoring or for the external test equipment is required. It can thus be carried out in a simple cost-effective manner, a detailed data acquisition for debugging or for a state examination on the sharp missile, so that it is no longer necessary to spend the missile from its current storage in a workshop and initially put in the inert state , The check by the method according to the invention can thus also be carried out, for example, on a missile immediately before attaching the missile to a carrier aircraft before a mission or immediately after the missile has been suspended from the carrier aircraft after a mission abort. Thus, not only the time and costs are saved by the inventive method, but also the reliability and operational readiness of unmanned missiles is significantly improved.

Further advantageous embodiments of the method according to the invention are specified in the subclaims.

Finally, the invention also relates to a device for carrying out the method according to the invention, which in particular has an adapter box connectable to the Umbilical connection of the missile, which is wired or wirelessly connectable to an operating device, which in this way can be connected to the central computer of the missile for data communication ,

Preferred embodiments of the invention with additional design details and other advantages are described and explained in more detail below with reference to the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

It shows:

1 the previous test setup for measuring and / or condition data query on an inert missile and

2 the test structure according to the invention for measuring and / or condition data query on a sharp missile.

PRESENTATION OF PREFERRED EMBODIMENTS

In 1 is a test setup with an inert missile 1 as previously used in the prior art to detect measurement and / or condition data of the missile by means of data bus monitoring.

The missile 1 has a central computer 2 on that with a volatile telemetry data store 20 is provided. The central computer 2 is to an internal data bus 3 connected in the 1 is shown only schematically and is also referred to as "IMBUS". To this internal data bus 3 are other facilities of the missile 1 connected to the central computer 2 communicate for data exchange, such as one in the nose of the missile 1 provided search head 10 ,

The missile 1 is at its top with an umbilical connection 12 provided via an external data bus 4 in the case of use with a carrier aircraft, in the test case shown, however, with a carrier aircraft simulating control unit 5 is connected as a simulation device. The control unit 5 is via a power supply line 52 with a source 54 connected for electrical energy. The umbilical connection 12 The missile is inside the missile via a data bus line 14 with the central computer 2 connected. The data bus line 14 and corresponding data bus lines of the umbilical cable 50 together form an external data bus 4 which conforms to the MILBUS standard (see Mil standard 1553, Mil standard 1763) and is also referred to as "MILBUS".

In 1 you can still see that in the front of the missile 1 a housing cover 16 open, so that the inside of the nose of the missile 1 is accessible. There is an IMBUS cable 70 via a branch on the data bus connection of the seeker 10 to the internal data bus 3 connected. The IMBUS cable 70 is with a level converter 72 connected and runs from there via a digital input / output 74 to an external test computer provided with a monitoring software, which is a test module 76 forms for the missile.

The test computer is thus able to monitor the internal data traffic of the missile between the central computer and the missile subsystems (navigation system, steering system, steering gear, sensors, safety system, engine, warhead, etc.) and thus to measurement and / or condition data of the Missile if the missile 1 through the control unit 5 is activated. However, to enable this it is necessary to have a data transmission connection with the inside of the missile 1 running internal data bus 3 to manufacture, including the flap 16 must be opened. Such opening a housing flap or body flap of the missile 1 However, it is not allowed if the missile is in its sharp state, so it is equipped with an armament. The in 1 shown test setup is therefore possible only with an inert missile without arming.

2 now shows the test structure according to the invention on a sharp missile 1' , The construction of the missile 1 corresponds to - except for in 2 dashed armament 18 - largely the structure of in 1 shown missile 1 ,

At the in 2 The test setup shown is merely the umbilical cable 50 to the umbilical connection 12 of the missile 1' connected. The umbilical cable 50 connects over the data bus 14 the central computer 2 with an external adapter box 5 ' as they are in the DE 10 2008 054 264 A1 is disclosed and next to the power supply 52 . 54 also an operator panel 56 (portable maintenance aid, for example a Toughbook) via an Ethernet cable 58 is connected so that the HMI device 56 via the ethernet cable 58 on the external data bus 4 can access.

• – die Daten werden vom Bediener am Bediengerät 56 entsprechend seiner Untersuchungsabsicht frei selektiert oder
• – der Bediener selektiert am Bediengerät 56 die Daten nach einem bestimmten Kritierum: zum Beispiel baugruppenbezogen oder funktionsbezogen.

It is possible in this way that of the HMI device 56 a command for one in the central computer 2 of the missile 1' executable software for activating the data access is sent while the missile is operated in a test sequence, as described for example in the DE 10 2006 041 140 B4 or in the DE 10 2004 042 990 B4 is described. Furthermore, during this test sequence from the HMI device 56 over the external data bus 4 Query commands to the central computer 2 be sent in the telemetry data store 20 currently stored measurement and / or status data via the external data bus 4 and over the adapter box 5 ' to the HMI device 56 to send. In this way it is possible without interference with the sharp missile 1' on the telemetry data store 20 of the missile 1 to access during test operation and to read out relevant data. The query of the measurement and / or state data can be different:

• - The data is provided by the operator on the HMI device 56 freely selected according to his intention to examine or
• - The operator selects on the HMI device 56 the data according to a certain criterion: for example, module-related or function-related.

The reading of the contents of the selected data from the telemetry data store 20 and the transmission via the external data bus 4 This can be done once (asynchronously) or cyclically (synchronously). In the case of cyclic readout and transmission, it is advantageous if the reading out and the transmission take place with the same or similar frequency as the data in the telemetry data memory 20 be registered.

It is also advantageous if for the request and the transfer of measurement and / or status data via the external data bus 4 Not unused words are used by operational messages, but when new data sets are defined and used for these data collection purposes so that the operational embassy and transfer design remains unchanged. As a result, unwanted and disruptive side effects in operational operation can be avoided.

It is also advantageous if the adapter box 5 ' a web server functionality (for example, a web server software with the network protocol TCP / IP) includes and over the Ethernet cable 58 (instead of the HMI device 56 ) or via a radio link 59 is connected to the Internet, whereby the determined measurement and / or condition data of the missile for remote maintenance purposes are accessible and the remote control of the missile (remote control) for troubleshooting and state detection is enabled.

Of particular advantage is the fact that no additional hardware is needed to carry out the method according to the invention, since the already approved for sharp missiles hardware equipment, namely the adapter box 5 ' and the HMI device 56 with the software running on it and already approved for operation on the sharp missile.

Reference signs in the claims, the description and the drawings are only for the better understanding of the invention and are not intended to limit the scope.

LIST OF REFERENCE NUMBERS

1

missile

1'

missile

2

central computer

3

internal data bus

4

external data bus

5

control unit

5 '

Adapterbox

10

seeker

12

Umbilical port

14

Data bus line

16

housing cover

18

arming

20

Telemetry data storage

50

Umbilical cable

52

power supply

54

power supply

56

external operating device

58

Ethernet cable

59

radio link

70

IMBUS cable

72

level converter

74

digital input / output

76

test module

Claims (10)

Method for requesting measurement and / or status data from a telemetry data memory ( 20 ) of a sharp unmanned missile ( 1' ), The missile ( 1' ) an umbilical connection ( 12 ), on which the missile ( 1' ) via an umbilical cable ( 50 ) is connectable to a carrier aircraft for the exchange of mission data and / or condition data, - the umbilical cable ( 50 ) has an external bus that is part of an external data bus ( 4 ), via which a central computer ( 2 ) of the missile ( 1' ) and a computer of the carrier aircraft can communicate with each other for data exchange, - wherein the missile in the non-sharp state with a test module ( 76 ) which can be connected to an internal data bus ( 3 ) of the missile is connectable and that the data traffic of the internal data bus ( 3 ) and can thus derive measurement and / or condition data of the missile, - the test module ( 76 ) in the sharp state of the missile ( 1' ) is not connected to the missile and - wherein the central computer ( 2 ) is provided with a software object which always contains all relevant internal data of the missile ( 1' ) in real time and in the volatile telemetry data memory ( 20 ), characterized in that - in the sharp state of the missile ( 1' ) from an operator panel ( 56 ) via an adapter box ( 5 ' ) to the external data bus ( 4 ), a command for one in the central computer ( 2 ) of the missile ( 1' ) executable software for activating the data access is sent; - that query commands via the external data bus ( 4 ) to the central computer ( 2 ) of the missile ( 1' ) and - that the central computer ( 2 ) of the missile ( 1' ) in response to the query data measurement and / or status data from the telemetry data store ( 20 ) via the external data bus ( 4 ) and the adapter box ( 5 ' ) to the HMI device ( 56 ), whereby the operational message and transfer design remains unchanged. Method according to claim 1, characterized in that from the adapter box ( 5 ' ) first an activation command for the writing and reading access to the telemetry data memory ( 20 ) via the external data bus ( 4 ) to the central computer ( 2 ) is sent before the query commands are sent and the data contents are transmitted. A method according to claim 1 or 2, characterized in that the measurement and / or status data from the operator at the with the adapter box ( 5 ' ) communicating operating device ( 56 ) are selected freely or according to a predetermined criterion, preferably module-related or function-related. Method according to one of the preceding claims, characterized in that the reading of the contents of the selected data from the telemetry data memory ( 20 ) and the transmission via the external data bus ( 4 ) take place once asynchronously or cyclically synchronously. A method according to claim 4, characterized in that the cyclic reading and transmission of the selected data with the same or similar large frequency as the entry of the data in the telemetry data memory ( 20 ). Method according to one of the preceding claims, characterized in that for the request and the transfer of the measurement and / or state data via the external data bus ( 4 ) not unused words are used by operational messages, but new messages are defined and transmitted, leaving the operational embassy and transfer design unchanged. Method according to one of the preceding claims, characterized in that the adapter box ( 5 ' ) has a web server functionality and is connected to the Internet and that the determined measurement and / or status data of the flying body are transmitted via the Internet and are thus accessible for remote maintenance purposes. Method according to one of the preceding claims, characterized in that the adapter box ( 5 ' ) has a web server functionality and is connected to the Internet and that the missile ( 1 ) is remotely controlled via the Internet for troubleshooting and / or status determination purposes. Apparatus for carrying out a method according to one of the preceding claims. Apparatus according to claim 9, characterized in that a to a Umbilical connection of the missile ( 1' ) connectable adapter box ( 5 ' ) provided with an operating device ( 56 ) is wired or wirelessly connectable, so via the adapter box ( 5 ' ) with the central computer ( 2 ) of the missile ( 1 ) is connectable to the data communication.

Images