DE102008054264B4 - Multifunctional service and test facility for unmanned aerial vehicles - Google Patents

Abstract

Multifunctional service and test device for unmanned missiles, with - a service device (2) which can be connected to the missile (1) and - an external computer (4) which can be connected to the service device (2) - the service device (2 ) Contains test and service hardware; - Test and service software is stored in a memory of the external computer (4) and runs on the external computer (4) under a commercially available operating system, - wherein the service device (2) is a communication and control computer (27) for communication with the missile (1) and with the external computer (4); - wherein the service device (2) further comprises at least the following hardware components: • at least one flow measurement device (28A) for at least one test / service fluid to be supplied to the missile (1); • at least one valve (28B) for the test / service fluid controlled by the external computer (4); • switching and control devices (29) for the missile (1) to be supplied with electrical energy; • at least one ...

Description

TECHNICAL AREA

The present invention relates to a multifunctional service and testing device for unmanned aerial vehicles.

STATE OF THE ART

Unmanned missiles, such as cruise missiles, are subjected to a variety of tests and inspections throughout their life to ensure their continued readiness. After manufacturing in the factory or after major overhauls at the factory, the missiles are tested there in a production final acceptance test (FET) with an extensive test program by means of a correspondingly complex test equipment arrangement. Simplified tests are carried out at predetermined intervals on the delivered and stored in the depot missiles. Likewise, corresponding simplified tests are carried out after a transport of the missile and before its use. These tests outside the factory can not be performed with the same intensity and depth of testing as in the final production test (FET), as the complex test equipment required for this purpose is not available outside the manufacturer and can not be used on a mobile basis. Furthermore, the final manufacturing test is only feasible by specially trained professionals who can handle the different test equipment.

A disadvantage of these simplified tests outside the manufacturer is the low test depth. As a result, errors may not be detected, or a deeper error analysis may not be possible when an error is detected. The missile must then be brought to the factory to be subjected to a more intensive test there. This is not only costly and expensive, but requires ammunition containing missiles either secure transport of a sharp missile or defusing the missile before transport to the factory and the subsequent sharpening of the missile after returning.

The DE 10 2004 042 990 B4 shows a final acceptance tester, which is exclusively connected via an umbilical cable to a missile. The tests carried out there are carried out by the on-board computer or by the on-board test facility of the missile, with a Milbus control unit contained in the final acceptance tester checking certain results of the tests controlled by the on-board computer of the missile. Actuation and control externally, ie outside the final acceptance tester, of hardware connected to the missile (eg GPS signal simulator, search head coolant, radar altimeter simulator) must be done manually, with each test cycle being interrupted, to issue a corresponding request for the operating personnel. The operator must then confirm the action taken, so that the test run can then be continued. As a result, not only is the test run delayed in time, but also the action and reaction times of checked missile components determined in the performed test can become inaccurate as a result of these test interruptions that are necessary due to the manual interventions.

The EP 0 286 988 B1 discloses a method and apparatus for testing missile systems wherein an external computer is connected to a rocket-provided Logical Interface Unit (LIU / XRAM). The external computer is used only for reading and retrieving certain control signals of the rocket. This interrogation of data stored in a data memory of the rocket by the external computer is not a control of a test procedure nor a control of an external hardware peripheral required for a test procedure.

The US 5,490,093 A discloses a method for improving computer-controlled rocket performance, with flight-model-specific parameters being determined in order to overcome manufacturing tolerances, and these parameters then being stored in the program memory of the missile. These missile-inherent parameters can be used to correct missile control, thereby improving missile flight accuracy. A multi-functional service and test facility for unmanned aerial vehicles, which has a service device, which is in particular provided with a control computer for communication with the missile and with the external computer, is not known from this.

The US Pat. No. 7,228,261 B2 discloses a method and apparatus for testing and diagnosing weapon control systems. Such a device comprises a computer and an interface unit, the computer being connected to the interface unit and being connectable to the weapon control system. The interface unit contains a DC-DC converter as well as two signal inputs and one signal output. Between these signal inputs and the signal output a plurality of indicator lights and sockets are provided in a front panel, which are interconnected by means of shorting plugs to direct a signal from a signal input to the signal output.

From the DE 10 2005 058 546 A1 a weapons station test unit is known, with the readiness of the weapon station of a carrier aircraft can be tested. This test unit is equipped with an integrated computer that simulates the behavior of a weapon connected to the weapon station. An external computer can be connected to the firearms testing unit and serves as a data entry and output terminal.

From the DE 10 2006 041 140 A1 For example, there is known a device for testing the operability of unmanned armed missiles comprising a simulation unit provided with a first computer for simulating the behavior of the weapon station of a carrier aircraft and an external testing and testing unit provided with a second computer. The second computer serves as a data input and output terminal.

PRESENTATION OF THE INVENTION

Object of the present invention is to provide a multi-functional service and testing device for unmanned missiles, which allows a reduced number of device components, cost and in a much more compact design compared to the prior art greater test depth in missile tests outside the manufacturer.

This object is achieved by the service and test device having the features of patent claim 1.

• – einen Kommunikations- und Steuerungsrechner zur Kommunikation mit dem Flugkörper und mit dem externen Computer;
• – zumindest eine Durchfluss-Messeinrichtung für zumindest ein zum Flugkörper zuzuführendes Test-/Service-Fluid;
• – zumindest ein vom externen Computer gesteuert schaltbares oder einstellbares Ventil für das Test-/Service-Fluid;
• – Schalt- und Regelungseinrichtungen für dem Flugkörper zuzuführende elektrische Energie;
• – zumindest einen Trenntransformator zur Entkopplung extern zugeführter elektrischer Energie vom Stromnetz des Service-Geräts.

The inventive multifunctional service and test device for unmanned missiles comprises a connectable to the missile service device and connectable to the service device external computer. The service device contains test and service hardware. Corresponding test and service software is stored in a memory of the external computer and runs on this external computer under a standard operating system. The service device has at least the following hardware components:

• A communication and control computer for communication with the missile and with the external computer;
• At least one flow-measuring device for at least one test / service fluid to be supplied to the missile;
• - At least one controlled by the external computer switchable or adjustable valve for the test / service fluid;
• - switching and control devices for the missile to be supplied electrical energy;
• - At least one isolation transformer for decoupling externally supplied electrical energy from the power network of the service device.

In addition, the communication and control computer for controlling the hardware device provided in the service device is connected to these.

ADVANTAGES

The service device of the service and test device according to the invention integrates a plurality of components that are provided as discrete hardware components in the conventional test arrangement for the FET. Furthermore, the service device includes a communication and control computer adapted to communicate with corresponding computers in the missile and configured to communicate with the external computer. The provision of such a communication and control computer in the service unit makes it possible to perform the tests on the missile with a conventional, external computer under a standard operating system, whereby the cost of the service and testing device compared to the previously for the FET used different, individually adapted to the technology of the missile special computers can be significantly reduced. Furthermore, the communication and control computer takes over the control of the provided in the service device or externally connectable to the service device hardware components for the tests.

Preferably, at least one electrical voltage converter is provided in the service device as a further hardware component.

Further preferably, at least one interface converter for converting data to be exchanged between the external computer and the missile is provided in the service device as a further hardware component.

It is also advantageous if on the external computer at least one mission planning software z. B. for time-critical goals (see the unpublished DE 10 2008 017 975 A1 ) and is running on it. As a result, the multifunctional service and test facility can also be used to create a mission plan and to upload a mission plan to an on-board computer of the missile.

Preferably, at least one test software for functional testing of the missile and / or its components is stored on the external computer and runs on the external computer.

Further preferably, at least one training software for simulating errors in one with the service device on the external computer connected training missile, which allows error stimulation, search and module replacement, stored and running on the external computer. As a result, the service and test device according to the invention can also be used for training purposes by the operating staff for training purposes.

If at least one updater software for updating computer programs stored in an on-board computer of the missile is stored on the external computer and runs on the external computer, the multifunctional service and test device according to the invention can also be used to include new or revised computer programs in or Board computer of the missile. This makes it possible to make updates or upgrades of the unmanned missile outside of the factory in a simple way without the missile must be spent in the factory.

Preferably, at least one downloader software for downloading video data stored in a video data memory of the missile is stored in the external computer and runs on the external computer. A equipped with this feature service and testing device can be used in a designed, for example, as a reconnaissance drone missile to read the reconnaissance captured video data from its video memory without the need for a further device.

Furthermore, a downloader software can be provided in the external computer, which makes it possible to read other data from the on-board computer or from associated memories in the missile, such as data from a fault memory.

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 a schematic test setup for testing a missile by means of the service and test device according to the invention;

2 a schematic structure for importing or downloading data in or out of the missile.

PRESENTATION OF PREFERRED EMBODIMENTS

In 1 is a schematic test setup for testing a missile 1 by means of a service and test device according to the invention 2 shown.

The missile 1 includes a payload receiving hull 10 , on the hull 10 attached wings 12 , At least one drive device, of which only the right side of the fuselage 10 provided air intake 14 the drive device is shown, as well as control surfaces 13 , which by means not shown control surface drives in a known manner movable on the fuselage 10 are attached.

The missile 1 is still with an avionics 3 provided, which is also shown only schematically and located in the interior of the fuselage 10 located. The avionics 3 contains an on-board computer 30 , which in addition to effective connections to navigation devices also a mission data storage 32 as well as a control computer 34 having. The control computer 34 will be after the missile has dropped off 1 from a carrier aircraft from the mission data store 32 is supplied with data of a predetermined flight path and a destination to be attached and further receives navigation data from conventionally provided navigation devices, such as a satellite navigation system 36 and / or an inertial navigation system. Based on this data, the control computer generates 34 Control signals that are routed to the cam drives, whereupon these control surfaces 13 for control of the missile 1 adjust.

The missile is at its front end with an image recognition device serving the target recognition 16 Mistake.

In the front fuselage of the missile 1 is inside the hull 10 an interface device (TLP) provided via a behind a hull flap located TLP interface 18 with the service device 2 is connectable.

At the top of the missile 1 is another interface 19 provided over which the missile 1 in use with the aircraft carrying it is connected (umbilical interface) and in the case of the invention for data exchange with the service device 2 is being used.

Finally, the missile 1 with a telemetry interface 17 a telemetry panel of the avionics of the missile 1 provided, which also with the service device 2 is connectable. This interface is used to load software in the image processing computer of the missile 1 ,

In the in 1 schematically shown test setup is below the front fuselage of the missile 1 a delay device 15 for the missile 1 emitted signals of a radar altimeter provided. The delay device 15 for the radar altimeter consists of two antennas, which are connected to each other via a delay line (RALT delay line) of defined length (for example, 31.6 m). The radar altimeter of the missile 1 emitted in the first antenna, wherein the electromagnetic pulses are conducted via the delay line to the second antenna, which then emits the pulses to the antenna of the Radarhöhenmessers again. If the delay device 15 for the radar altimeter, as in 1 shown, positioned under this, can be in the missile 1 be checked whether the radar altimeter determines the predetermined delay line (31.6 m in the example) as the measured height. In this way, with the delay device 15 For the radar altimeter, test the measuring function of the radar altimeter.

The service device 2 is with a first power supply connection 20A and a second power supply terminal 20B Mistake. The first power supply connection 20A is intended for use with a conventional AC mains 21A 220 V to provide the consumers of the service unit with electrical energy. The second power supply connection 20B is intended to be used on a standard for aircraft power supply 21B of 3 × 115 V 400 Hz.

Furthermore, the service device indicates 2 a first data port 22A on top of an umbilical cable 23A with the umbilical interface 19 of the missile 1 electrically connected. On the service device 2 Provided second data connection 22B is via a so-called TMP cable 23B with the telemetry interface 17 of the missile 1 electrically connected. About the TMP cable 23B In addition to the transmission of data, an electrical voltage of usually 28 V is provided for the missile.

A third on the service device 2 provided data interface 22C is via a so-called TIP cable with the TLP interface 18 of the missile 1 electrically and mechanically connected. It contains both the interface 22C , as well as the interface 18 , as well as the TLP cable 23C not only electrical connections, but also a hose connection as cooling fluid line for the supply of a cooling fluid from the service device 2 to the missile 1 , as will be described below. About the electrical connections of the TIP cable 23C will connect the on-board computer 30 of the missile 1 and the service device 2 via which a data exchange between the on-board computer 30 and the service device 2 he follows. The cooling fluid line in the TIP cable 23C transported from the cooling fluid tank 26B in the service unit led cooling fluid to one in the missile 1 provided cooling device for an infrared homing head of the image capture device 16 to cool it while performing the tests.

By means of the service and test software running on the external computer, a mission plan for a mission to be flown by the missile can be obtained via the service device 2 and the data lines in the TLP cable (as well as via the milbus of the umbilical cable) into the on-board computer 30 of the missile 1 loaded and there in the mission data store 32 get saved. Missions data are data that the missile requires to reach its target, ie data for navigation, trajectory, but also data about targets to be tracked, such as images or models of particular landmarks or images, or a model of the target to be approached.

The service device 2 is via a power supply cable 23D which is connected to a power supply connection 22D to the service device 2 is connected, with a viewfinder mask 40 connected. The searcher mask 40 is in the in 1 shown test setup in front of the optics of the image capture device 16 arranged and supplies the image capture device 16 a corresponding picture of a goal.

The searcher mask 40 is for example provided with engraved target contours that correspond to the target image or the target model, which in a target memory of the on-board computer 30 is stored. Alternatively or additionally, the searcher mask 40 also have landmarks images stored in the mission data store 32 saved landmark images correspond.

At a GPS port 24 of the service device 2 is via a first GPS cable 24A a GPS antenna 24B connected. Furthermore, the GPS connection 24 another GPS cable 24C connected with a GPS cover sending out a satellite navigation signal (GPS signal) 24D effectively connected to the satellite navigation system 36 of the missile is placed. The via the external GPS antenna 24B recovered GPS raw signal is also in the umbilical cable 23A fed (to simulate the GPS signal from the carrier aircraft).

A cooling fluid connection 25 of the service device 2 is via a cooling fluid line 25A with a cooling fluid reservoir 25B connected such that cooling fluid from the cooling fluid reservoir 25B through the cooling fluid line 25A and the cooling fluid port 25 in one corresponding in the service device 2 provided piping system 28C can flow for the cooling fluid. The service device 2 contains a flow measuring device 28A for that from the cooling fluid reservoir 25B through the cooling fluid line 25A and the cooling fluid port 25 in the service device 2 introduced cooling fluid, which forms a test / service fluid. Furthermore, within the service device 2 a switchable valve 28B for the cooling fluid in the inside of the service unit 2 provided cooling fluid line 28C intended. By means of the switchable valve can, controlled by the external computer 4 , the cooling fluid flow from the reservoir 25B to the missile 1 opened or closed or dosed accordingly.

Finally, the service device 2 still with at least a USB connection 26 provided and it can be optional with at least one Milbus connector 26B Be provided with the appropriate connection cable 26A respectively 26C with an external computer 4 can be connected to the data exchange. The external computer 4 is at least a USB memory stick 42 associated with the computer 4 is connectable and for data transport in or out of the computer 4 is provided.

The service device 2 further includes electrical switching and control devices 29 , into the external electrical energy passing through the connections 20A and or 20B is fed, initiated and depending on the on the computer 4 running test and service program with the required voltage and possibly current-limited to the missile 1 is forwarded. The switching and control devices 29 also include at least one isolation transformer 29A . 29B for decoupling the externally supplied electrical energy from the power network of the service device.

Finally, the service device 2 still with a corresponding communication and control computer 27 that makes it possible, controlled by the external computer 4 certain operating conditions in the on-board computer 30 of the missile 1 select. For this purpose, the communication and control computer 27 For example, configure appropriate control lines (so-called modelines) and RTU addresses that the on-board computer 30 can be read in, so that it can be switched, for example, between a test mode, a service mode, a programming mode or other modes. The control computer 27 is with an interface converter 27A connected to the control computer to the standardized interfaces of the missile 1 and from its on-board computer 30 adapted.

While the schematic representation in 1 the complete test setup and complete connection of the service device 2 to the missile 1 and to the external computer 4 shows that for carrying out extensive checks of the missile 1 is required, shows 2 in a schematic way the connection of the service device according to the invention 2 to the missile 1 and to the external computer 4 as for uploading data, for example from one to the USB memory stick 42 stored mission plan in the mission data store 32 of the missile 1 or for reading data, for example, in an error memory of avionics 3 of the missile 1 stored in the external computer 4 to the local evaluation is required.

This simplified data exchange becomes the service device 2 only with the power supply device 21A for the service device 2 and with the external computer 4 via the USB cable 26A or alternatively via the Milbus cable (not shown) 26B connected as an external device. With the missile 1 is the service device 2 via the umbilical cable 23A as well as the TLP cable 23C connected, these compounds being in connection with in the 1 be made described manner.

From the different connection structure representations of 1 and 2 it becomes clear that by means of the service device according to the invention 2 a fast, customized connection between an external computer 4 and the missile 1 can be produced. Furthermore, from the presentation of the 1 clear that when using the service device according to the invention, the effort to connect the external computer 4 with the missile 1 Compared with the prior art is significantly reduced, since the number of entrained to the test site and built there external hardware components compared to the prior art is significantly reduced.

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

2

Service and testing facility

3

Avionics

4

external computer

10

hull

12

wings

13

control surfaces

14

air intake

15

delay means

16

Image capture device

17

Telemetry interface

18

TLP interface

19

Umbilical Interface

20A, B

Power connector

21

power supply

22A, B, C

data port

22D

Power connector

23A

Umbilical cable

23B

TMP cable

23C

TLP cable

23D

Power cable

24

GPS connection

24A

GPS cable

246

GPS antenna

24C

GPS cable

24D

GPS coverage

25

Cooling fluid port

25A

Cooling fluid line

25B

Cooling fluid reservoir

26

ISB port

26A

connection cable

26B

Milbus port

26C

connection cable

27

Communication and control computer

27A

Interface Converter

28A

Flow measurement device

28B

switchable valve

28C

Cooling fluid line

29

control device

29A, B

Isolation transformer

30

board computer

32

Mission data storage

34

control computer

36

Satellite Navigation System

40

viewfinder mask

42

USB Memory Stick

Claims (8)

Multifunctional service and test facility for unmanned aerial vehicles, with - one with the missile ( 1 ) connectable service device ( 2 ) and - one with the service device ( 2 ) connectable external computer ( 4 ) - whereby the service device ( 2 ) Contains test and service hardware; - where test and service software in a memory of the external computer ( 4 ) and on the external computer ( 4 ) runs under a standard operating system, - wherein the service device ( 2 ) a communication and control computer ( 27 ) for communication with the missile ( 1 ) and with the external computer ( 4 ) having; - where the service device ( 2 ) further comprises at least the following hardware components: • at least one flow measuring device ( 28A ) for at least one of the missile ( 1 ) to be supplied test / service fluid; • at least one from the external computer ( 4 ) controlled switchable or adjustable valve ( 28B ) for the test / service fluid; • switching and control devices ( 29 ) for the missile ( 1 ) to be supplied electrical energy; At least one isolating transformer ( 29A . 29B ) for decoupling externally supplied electrical energy from the power network of the service device ( 2 ); and - wherein the communication and control computer ( 27 ) for controlling the in the service device ( 2 ) hardware components ( 28A . 29 . 29A . 29B ) is connected to these. Multifunctional service and test device according to claim 1, characterized in that in the service device ( 2 ) is provided as a further hardware component, at least one electrical voltage converter. Multifunctional service and test device according to claim 1 or 2, characterized in that in the service device ( 2 ) as an additional hardware component at least one interface converter ( 27A ) to convert between the external computer ( 4 ) and the missile ( 1 ) is provided. Multifunctional service and test device according to one of claims 1 to 3, characterized in that on the external computer ( 4 ) at least one mission planning software is stored and running on it. Multifunctional service and test device according to one of the preceding claims, characterized in that on the external computer ( 4 ) at least one test software for functional testing of the missile ( 1 ) and / or its components is stored and running on it. Multifunctional service and test device according to one of the preceding claims, characterized in that on the external computer ( 4 ) at least one training software for simulating errors in one with the service device ( 2 ) associated training missile is stored and running on it. Multifunctional service and test device according to one of the preceding claims, characterized in that on the external computer ( 4 ) at least one updater software for updating in an on-board computer ( 30 ) of the missile ( 1 stored) computer programs and is running on it. Multifunctional service and test device according to one of the preceding claims, characterized in that on the external computer ( 4 ) at least one downloader software for downloading in a video data storage of the missile ( 1 ) stored video data and is running on it.

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