WO2010048919A1

WO2010048919A1 - Multi-functional servicing and test unit for unmanned flying objects

Info

Publication number: WO2010048919A1
Application number: PCT/DE2009/001424
Authority: WO
Inventors: Michael Grabmeier
Original assignee: Lfk-Lenkflugkörpersysteme Gmbh
Priority date: 2008-10-31
Filing date: 2009-10-13
Publication date: 2010-05-06
Also published as: DE102008054264A1; DE102008054264B4

Abstract

The invention relates to a multi-functional servicing and test unit for unmanned flying objects, comprising a servicing device (2) that can be connected to the flying object (1) and an external computer (4) that can be connected to the servicing device (2), said servicing device (2) containing test and servicing hardware and test and servicing software being stored in a memory of the external computer (2) and being run on the external computer (2). The servicing device (2) has at least the following hardware components: at least one flow rate measuring unit (28A) for at least one test/servicing fluid that can be fed to the flying object (1); at least one switchable valve (28B) for the test/servicing fluid; switching and control devices (29) for electric energy that can be supplied to the flying object (1); at least one isolation transformer (29A; 29B) for decoupling externally supplied electric energy from the mains supply of the service device (2); and the service device (2) has a communication and control computer (27) for communicating with the flying object (1) and with the external computer (4) and for controlling the hardware components.

Description

Multifunctional service and test facility for unmanned

missile

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 can be performed only 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 one may be detected when an error is detected Error analysis is not possible. 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.

PRESENTATION OF THE INVENTION

The object of the present invention is therefore to specify a multifunctional service and test device for unmanned missiles which, with a reduced number of device components and a substantially more compact design, enables a greater test depth in the case of missile tests outside the manufacturer's plant than in the prior art.

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

ADVANTAGES

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 is provided with test and service hardware. Corresponding test and service software is stored in a memory of the external computer and runs on the computer. The service device has at least the following hardware components: at least one flow-measuring device for at least one of

Missile to be supplied test / service fluid; at least one switchable 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 service device has a communication and control computer, which is used for communication with the missile and with the external computer and for controlling the hardware components of the service device.

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 device makes it possible to perform the tests on the missile with a conventional, external computer under a standard operating system, whereby the costs for the service and testing device over the previously used for the FET 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 furthermore advantageous if at least one mission planning software, e.g. for time-critical goals (see unpublished DE 10 2008 017 975) is stored and 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 a training missile connected to the service device, which enables error stimulation, search and module replacement, is stored and runs on the external computer 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 shows a schematic test setup for testing a missile by means of the service and test device according to the invention;

2 shows a schematic structure for importing or downloading

Data in or out of the missile. PRESENTATION OF PREFERRED EMBODIMENTS

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

The missile 1 comprises a payload-receiving hull 10, attached to the fuselage 10 wings 12, at least one drive device, of which only the right side of the fuselage 10 provided air inlet 14 of the drive device is shown, and control surfaces 16, by means not shown control surface drives in known Movably mounted on the hull 10 are attached.

The missile 1 is further provided with an avionics 3, which is also shown only schematically and which is located inside the hull 10. The avionics 3 contains an on-board computer 30 which, in addition to effective connections to navigation devices, also has a mission data memory 32 and a control computer 34. The control computer 34 is supplied after the landing of the missile 1 from a carrier aircraft from the mission data memory 32 with data of a predetermined flight path and a target and continues to receive navigation data from conventionally provided navigation devices, such as a satellite navigation system 36 and / or an inertial navigation system. Based on these data, the control computer 34 generates control signals which are sent to the control surface drives, whereupon they adjust the control surfaces 16 to control the missile 1.

The missile is provided at its front end with an image recognition device 16 serving the target recognition. In the front fuselage of the missile 1, an interface device (TLP) is provided in the interior of the fuselage 10, which can be connected to the service device 2 via a TLP interface 18 located behind a trunk flap.

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

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

In the test setup shown schematically in FIG. 1, a delay device 15 for signals emitted by the missile 1 of a radar altimeter is provided below the front fuselage area of the missile 1. 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 emits into 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 radar altimeter delay device 15 is positioned below it, as shown in FIG. 1, it can be checked in the missile 1 whether the radar altimeter determines the predetermined delay line (in the example 31, 6 m) as the measured altitude. In this way, the measuring function of the radar altimeter can be tested with the radar altimeter delay device 15. The service device 2 is provided with a first power supply terminal 2OA and a second power supply terminal 2OB. The first power supply terminal 20A is designed to be connected to a conventional 220V AC power supply 21A to provide electrical power to the consumers of the service equipment. The second power supply terminal 2OB is designed to be connected to an aircraft power supply 21B of 3 × 115 V 400 Hz, which is common for aircraft.

Furthermore, the service device 2 has a first data connection 22A, which is electrically connected to the umbilical interface 19 of the missile 1 via a umbilical cable 23A. A second data connection 22B provided on the service device 2 is electrically connected to the telemetry interface 17 of the missile 1 via a so-called TMP cable 23B. Via 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 data interface 22C provided on the service device 2 is electrically and mechanically connected to the TLP interface 18 of the missile 1 via a so-called TLP cable. In this case, both the interface 22C, as well as the interface 18, as well as the TLP cable 23C includes not only electrical connections, but also a hose connection as cooling fluid line for supplying a cooling fluid from the service device 2 to the missile 1, as will be described below , Via the electrical connections of the TLP cable, a connection between the on-board computer 30 of the missile 1 and the service device 2 is established, via which data is exchanged between the on-board computer 30 and the service device. The cooling fluid conduit in the TLP cable transports cooling fluid carried from the cooling fluid reservoir 25B to the service apparatus for infrared targeting head cooling means of the imaging device 16 provided in the missile 1 to cool it during performance of 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 entered 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 stored there in the mission data memory 32. 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 connected to a searcher mask 40 via a power supply cable 23D connected to a power supply terminal 22D to the service equipment 2. The searcher mask 40 is disposed in front of the optics of the image capture device 16 in the test setup shown in FIG. 1 and provides the image capture device 16 with a corresponding image of a target.

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

At a GPS port 24 of the service device 2, a GPS antenna 24B is connected via a first GPS cable 24A. Further connected to the GPS port 24 is another GPS cable 24C which is operatively connected to a GPS coverage 24D emitting a satellite navigation signal (GPS signal) placed over the satellite navigation system 36 of the missile. The GPS raw signal obtained via the external GPS antenna 24B is also fed to the umbilical cable 23A (for simulation of the GPS signal from the carrier aircraft). A cooling fluid port 25 of the service device is connected to a cooling fluid reservoir 25B via a cooling fluid line 25A so that cooling fluid from the cooling fluid reservoir 25B can flow through the cooling fluid line 25A and the cooling fluid port 25 into a corresponding cooling fluid conduit system 28C provided in the service device 2. The service device 2 includes a flow measuring device 28A for the cooling fluid introduced from the cooling fluid reservoir 25B through the cooling fluid line 25A and the cooling fluid port 25 into the service device 2, which forms a TesWService fluid. Furthermore, within the service device 2, a switchable valve 28B for the cooling fluid is provided in the cooling fluid line 28C provided inside the service apparatus 2. By means of the switchable valve, controlled by the external computer 4, the cooling fluid flow from the reservoir 25 B to the missile 1 can be opened or closed or dosed accordingly.

Finally, the service device 2 is still provided with at least one USB port 26 and it may optionally be provided with at least one Milbus port 26B, which can be connected to an external computer 4 for data exchange via corresponding connection cables 26A and 26C. The external computer 4 is associated with at least one USB memory stick 42 which is connectable to the computer 4 and which is provided for data transport into or out of the computer 4.

The service device 2 further comprises electrical switching and control devices 29, in the external electrical energy, which is supplied through the terminals 2OA and / or 2OB, is initiated and depending on the running on the computer 4 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 comprise at least one isolating transformer 29A, 29B for decoupling the externally supplied electrical energy from the power network of the service device. Finally, the service device 2 is still provided with a corresponding communication and control computer 27, which allows controlled by the external computer 4 select certain operating conditions in the on-board computer 30 of the missile 1. For this purpose, the communication and control computer 27, for example, corresponding control lines (so-called modelines) and configure RTU addresses that are read by the on-board computer 30 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 connected to an interface converter 27 A, which adapts the control computer to the standardized interfaces of the missile 1 and its on-board computer 30.

While the schematic illustration in FIG. 1 shows the complete test setup and the complete connection of the service device 2 to the missile 1 and to the external computer 4, which is required for carrying out comprehensive checks of the missile 1, FIG schematically the connection of the service device 2 according to the invention to the missile 1 and the external computer 4, as he for the upload of data, such as a stored on the USB memory stick 42 mission plan in the mission data memory 32 of the missile 1 or to read of data stored, for example, in a fault memory of the avionics 3 of the missile 1, in the external computer 4 for the local evaluation is required.

For this simplified data exchange, the service device 2 is merely connected to the power supply 21A for the service device 2 and to the external computer 4 via the USB cable 26A or alternatively via the Milbus cable 26C (not shown) as an external device , With the missile 1, the service device 2 is connected via the umbilical cable 23A and via the TLP cable 23C, these connections being made in the manner described in connection with FIG. 1 and 2, it is clear that a fast connection, adapted to the specific task requirement, between an external computer 4 and the missile 1 can be produced by means of the service device 2 according to the invention. Furthermore, it becomes clear from the illustration of FIG. 1 that, when the service device according to the invention is used, the outlay for connecting the external computer 4 to the missile 1 is markedly reduced compared to the prior art, since the number of persons to be carried to the test location and there aufzubauenden 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

describe:

missile

Service and testing facility

Avionics external computer

hull

wings

air intake

delay means

Image capture device

Telemetry interface

TLP interface

Umbilical Interface

A ₁ B Power supply connection

power supply

A ₁ B data connection

A umbilical cable

B TMP cable

C TLP cable

D power supply cable

GPS connection

A GPS cable

B GPS antenna

C GPS cable

D GPS coverage

Cooling fluid port

A cooling fluid line

B Cooling fluid reservoir USB port Communication and control computer A Interface converter A Flow measuring device B Switchable valve C Cooling fluid line Control device A ₁ B Isolation transformer Trip computer Mission data memory Control computer Satellite navigation system Searcher mask USB memory stick

Claims

claims

1. An unmanned aerial vehicle multifunctional service and testing facility, comprising a service device (2) connectable to the missile (1) and an external computer connectable to the service device (2)

(4) wherein the service device (2) includes test and service hardware; wherein test and service software is stored in a memory of the external computer (4) and runs on the external computer (4), the service device (2) comprising at least the following hardware components: at least one flow measuring device ( 28A) for at least one test object to be supplied to the missile (1).

/ Service fluid; at least one switchable valve (28B) for the TesWService

fluid;

Switching and regulating devices (29) for the missile

(1) electrical energy to be supplied; at least one isolating transformer (29A, 29B) for

Decoupling externally supplied electrical energy from

Power network of the service device (2); and wherein the service device (2) has a communication and control computer (27) for communication with the missile (1) and with the external computer (4) and for controlling the hardware components.

2. Multifunctional service and test device according to claim 1, characterized in that at least one electrical voltage converter is provided in the service device (2) as a further hardware component.

3. Multifunctional service and test device according to claim 1 or 2, characterized in that in the service device (2) as a further hardware component, at least one interface converter (27A) for converting between the external computer (4) and the missile (1) data to be exchanged is provided.

4. 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.

5. 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.

6. 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 a with the service device (2) connected training missile is stored and running on it.

7. 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 is stored and on it running.

8. 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 memory of the missile (1) stored video data is stored and runs on it.