EP1895265A1 - Method for checking the functionality of unmanned armed missiles - Google Patents

Abstract

The procedure for testing the operativeness of remote-piloted, armed missile (1) having electronic components, comprises testing the operativeness of sensor and actuators of the components and testing communication of the missile over its communication interfaces for the communication of a part of the component with arrangements arranged outside of the missile. During the testing, the respective time duration of technical process in the missile is measured and then stored in a storage arrangement of the missile. The missile is furnished during the testing without energy, data and coolant. The procedure for testing the operativeness of remote-piloted, armed missile (1) having electronic components, comprises testing the operativeness of sensor and actuators of the components and testing communication of the missile over its communication interfaces for the communication of a part of the component with arrangements arranged outside of the missile. During the testing, the respective time duration of technical process in the missile is measured and then stored in a storage arrangement of the missile. The missile is furnished during the testing without energy, data and coolant. During the testing, assessed errors are categorized in sporadic appearing errors, not embarrassing errors and embarrassing errors. A discontinuance of the testing is carried out in the appearance of an embarrassing error and an error message and/or an error protocol forming a defect image of the component is issued over a missile interface. The sporadic appearing errors and non-embarrassing errors are stored in the storage arrangement and are issued after termination of the test over the missile interface. The embarrassing error is terminated when testing without appearance. The testing is carried out for inertial measuring unit, satellite navigation unit, altimeter, battle head, control head, drive unit, target spacing analyzer, engine, rudder machine and control calculator of the missile. During testing, the component of the missile is implemented for actuation test, demand-pull self-test and continues test during a missionary simulation and/or test of component group and function chain, and the inertial measuring unit and the navigation computer are tested in which the acceleration measured through the inertial measuring unit and rolling rate is compared with the effective earth rotation and earth acceleration. During the test of the missile, the rudder machine, a local control computer and the board computer are tested, for which the test leads to a control person through a dialogue and the control person is given each of test and then to confirm its predetermined action. The test comprises detaching the rudder of the bolts holding at the missile, sequentially and manually unlocking of each rudder machine, individually actuating each rudder machine with a control input, automatically testing weather reaching the control input from the rudder machine, simultaneously moving several rudder machine with corresponding control input check, and back controlling the rudder machine on its neutral position of 0[deg] . During testing of the missile, detector of infrared-guidance head is tested its camera, image processing computer and on-board computer, in which the measured pixel grey tone with increased integration time of corresponding linear rise is tested in constant scenario. The target acquisition function of the target guidance head is tested during the test by arranging a land mark mask with an engraved target contour in a defined interval of the infrared target guidance head, cooling the infrared target guidance head, and controlling a test mission plan having a corresponding land mark in the control computer of the missile. An independent claim is included for a device for testing the operativeness of remote-piloted, armed missile.

Description

TECHNICAL AREA

The present invention relates to a method for checking the operability of unmanned, armed missiles according to the preamble of patent claim 1.

STATE OF THE ART

Such a method is for example from the DE 10 2004 042 990 A1 known. The method disclosed there provides that in the case of the occurrence of a fatal error, that is, an error that leads to the non-operational capability of the missile, an error message is issued, which shows in which assembly the fatal error has occurred. For a detailed fault analysis, the missile must then be converted to the inert state (without the warhead and other pyrotechnic elements), whereby only by this conversion, the state in which the error has occurred, is changed. As a result, it may happen that the error no longer occurs after the conversion of the missile to the inert state or the fault pattern changes.

PRESENTATION OF THE INVENTION

It is therefore an object of the present invention to provide a generic method for checking the operability of unmanned, armed missiles, which makes it possible to make a safe check on the functionality even on a equipped with the warhead and pyrotechnic elements missile.

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

ADVANTAGES

Due to the inventive output of an error image of a defective component forming error log on the occurrence of a fatal error that includes the identified error and all relevant information from the defective component and from the environment of the defective component, there is a comparison with the known from the prior art method improved, more meaningful method available, which is characterized in particular by its detailed error information of the error log. In addition, recording and post-test output of the sporadic errors and non-fatal errors that occurred during the test provide information about the condition of the missile from which the skilled artisan can derive anticipated errors or signs of wear or deterioration ,

Advantageous developments of the method according to the invention are specified in the remaining claims.

It is advantageous if, during the check, the respective duration of technical processes within the missile is measured and stored in a memory device of the missile and output after completion of the check via a missile interface, even if the check has been completed without the occurrence of a fatal error is and has thus led to a release of the missile. Reviewing and logging the duration of technical operations within the missile further allows for a basic analysis of non-critical, non-optimal functions and emerging signs of wear.

Preferably, the check is performed for at least some of the following components of a missile: inertial measuring unit, Satellite navigation unit, altimeter, warhead, infrared homing head, target range finder, engine, steering machines, missile control computer.

In a preferred implementation of the method according to the invention, a check-in test, a triggered self-test and a continuous test during a mission simulation are performed for each component during the inspection of the components of the missile.

An advantageous development of the method according to the invention is characterized in that the inertial measuring unit is tested during the examination of the missile by comparing the accelerations and rotation rates measured by the inertial measuring unit with the acting acceleration of gravity and earth rotation.

• Lösen der Ruder von den diese am Flugkörper haltenden Bolzen,
• sequenzielles, manuelles Entriegeln einer jeden Rudermaschine,
• einzelnes Ansteuern einer jeden Rudermaschine mit einem Sollwert und automatische Überprüfung, ob dieser Sollwert von der Rudermaschine erreicht worden ist,
• gleichzeitige Bewegung mehrerer Rudermaschinen mit entsprechender Sollwertüberprüfung,
• Zurücksteuern der Rudermaschinen auf ihre Neutralposition von 0° Ruderausschlag.

Preferably, during the missile inspection, the steering machines are tested, for which purpose the test guides an operator through a dialogue and the operator must confirm each action dictated by the test and then performed by it, the test comprising the following steps:

• Loosening the rudders from the bolts holding them to the missile,
• sequential, manual unlocking of each rowing machine,
• individually controlling each steering machine with a target value and automatically checking whether this command value has been reached by the steering machine,
• simultaneous movement of several steering machines with appropriate set point check,
• Returning the rudders to their neutral position of 0 ° rudder deflection.

It is also preferable if, during the examination of the missile, the detector of the homing head is tested by using a constant scenario It is checked whether the measured pixel gray values increase correspondingly linearly with increased integration time.

• Anordnen einer Landmarken-Maske mit eingravierten Zielkonturen in einem definierten Abstand vor dem Infrarot-Zielsuchkopf,
• Kühlung des Infrarot-Zielsuchkopfes,
• Laden eines Test-Missionsplans, der eine entsprechende Landmarke aufweist, in den Steuerrechner des Flugkörpers,
• Prüfen ob und wie schnell der Infrarot-Zielsuchkopf eine Übereinstimmung der im Missionsplan vorgegebenen Landmarke mit der in die Landmarken-Maske eingravierten Zielkontur feststellt.

A further preferred embodiment of the method is characterized in that, during the inspection of the missile, the target detection function of the infrared homing head is tested, wherein the following steps are carried out:

• Arranging a landmark mask with engraved target contours at a defined distance in front of the infrared homing head,
• Cooling of the infrared homing head,
• Loading a test mission plan, which has a corresponding landmark, in the control computer of the missile,
• Check whether and how quickly the infrared homing head detects a match of the landmark given in the mission plan with the target contour engraved in the landmark mask.

A preferred device for carrying out the method according to the invention is characterized by its modular structure and the resulting mobile applicability.

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

BRIEF DESCRIPTION OF THE DRAWINGS

Fig. 1

eine schematische Darstellung des Test-Aufbaus für das erfindungsgemäße Verfahren und

Fig. 2

ein Flussdiagramm des Verfahrensablaufs des erfindungsgemäßen Verfahrens.

It shows:

Fig. 1

a schematic representation of the test setup for the inventive method and

Fig. 2

a flowchart of the process flow of the method according to the invention.

PRESENTATION OF PREFERRED EMBODIMENTS

Fig. 1 shows a schematic representation of a missile 1, an external simulation unit 2, an external test and test unit 3 and further and still explained components.

The missile 1 has a fuselage 10, wings 11, rudder flaps 12, 13, at least one engine, of which only the right air inflow duct 14 is shown in FIG. 1, and an infrared homing head 15 at its front end. In the front fuselage area 16, a test unit (TLP) is provided in the interior of the fuselage, which can be connected via an interface 16 'located behind a fuselage flap with components provided outside of the missile 1. The missile is provided inside the fuselage with one or more warheads (for example Vorhohlladung or Penetrator). At the top of the hull two suspension devices 17, 17 'are attached with which the missile 1 can be attached to a carrier aircraft, for example, at the local bomb pylon. Another interface 18 is provided at the top of the missile 1, via which the missile is in use connected to the aircraft carrying it (umbilical interface) and which is used in the present method for data exchange with the simulation unit 2.

The simulation unit 2, also called "umbilical box", contains a computer 20, for example a laptop, and a device for signal distribution and signal combining 21. The computer 20 is connected via an outwardly guided power supply line 22 to the usual power grid, but it can be operated independently of the mains by means of accumulators. Furthermore, the computer 20 is connected via an internal data exchange line 23 to the device 21 for signal distribution and signal combining.

The device 21 for signal distribution and signal combination is the signal of a satellite navigation antenna via an antenna line 24 from the outside 25, for example, a GPS antenna supplied. Finally, the device 21 for signal distribution and signal combining via an electrical line connection 26 is connected to a power supply 27 of 3x115V 400 Hz which is common in aviation.

The signal distribution and signal combining device 21 of the simulation unit 2 is connected to the umbilical interface 18 of the missile 1 by means of a connection cable 28, the so-called "umbilical cable". The computer 20 present in the simulation unit 2 can then communicate and interact with the missile 1 in the same manner (for example, via Milbus or Mil-standard discrete lines 1760) as with a carrier aircraft.

The external test and test unit 3, also referred to as "TLP box", includes a computer 30 and a signal distribution and signal merging device 31.

The computer 30 is connected via a conventional power supply line 32 with a conventional power grid, but it can also be operated by means of accumulators independent of the mains. The computer 30 and the signal distribution and signal combining device 31 are connected within the test and test unit 3 via an internal data exchange cable 33 and can exchange data via this cable.

The device 31 for signal distribution and signal combination of the test and test unit 3 is connected via a data cable 34, the so-called "TLP cable", with the interface 16 'which is provided in the front fuselage area 16 of the missile 1, and above with the one in the fuselage 10 The on-board computer of the missile 1 is provided for data exchange via a communication element 16 "(TLP) .The data output by the communication element 16" (TLP) provided in the missile 1 during and after carrying out a check of the missile 1 are transmitted via the Data line 34 to the test and test unit 3 and in particular to the computer 30 contained therein for display and further evaluation.

In addition to the external simulation unit 2 and the external test and test unit 3, an external cooling vessel 4 is provided, which is connected via a cooling line 40 to a cooling device provided for the infrared homing head 15 in order to cool it during the execution of the test.

Furthermore, as represented by the dashed data line 50, a device 5 for loading mission data into an on-board computer of the missile 1 can be connected to the on-board computer of the missile 1 via the interface 16 '. With this device, which is also referred to as "Ground Loader Unit" (GLU), a mission plan for a mission to be flown (here in the illustrated preferred embodiment, a special test mission plan) can be loaded into the on-board computer of the missile 1. Missions data are data that the missile needs 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.

In Fig. 1 also at a distance in front of the nose of the missile 1, ie before the infrared homing head 15, a landmark mask 19 is shown, which is provided with engraved target contours and is used to check the infrared homing head 15. The target contours engraved in the landmark mask 19 correspond to the target image or the target model which has been recorded into the target memory of the on-board computer of the missile 1 by means of the GLU 5.

Finally, the missile 1 is connected via an antenna line 60 to an external satellite navigation antenna 6, which supplies the missile-own on-board computer with satellite navigation data.

Furthermore, a deceleration device 45 is provided for a radar altimeter arranged in the lower front fuselage area of the missile 1. The deceleration device 45 is arranged in the region of the radar altimeter below the missile 1. It 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 45 is positioned below it, as shown in FIG. 1, it can be checked in the missile 1 whether the radar altimeter determines the predetermined length of the delay line (31.6 m in the example) as the measured altitude. In this way, the measuring function of the radar altimeter can be tested with the radar altimeter delay device 45.

The device for carrying out the inspection of the missile 1 is modular and consists of several mobile devices, essentially from the simulation unit 2 and the test and test unit 3, which may be housed for example in a suitcase and thus are easily transportable, so that the Check also on site, for example, in a material depot or on an air base can be done shortly before using the missile. Another suitcase 7, which is likewise shown only schematically in FIG. 1, serves to receive the connecting cable, the delay device 45 for the radar altimeter, the landmark mask and further individual parts, so that the entire device for checking the missile 1 is transported in a total of three suitcases can.

The flow of the check will now be described with reference to the flowchart shown in FIG.

The process flow in the flowchart of Fig. 2 begins after the start of the test with the actual test run 100, a plurality of tests has, which are performed successively or in parallel for different components to be checked of the missile 1. First, a power-on test 101 is performed for a first component in which the component independently tests its basic functions. This is followed in step 102 by a triggered self-test 102 of the component, which is commanded by the on-board computer of the missile and in which the complete test spectrum of the isolated component is activated. In the following step 103, a continuous test of the corresponding component carried out under a simulation of an existing carrier aircraft and a mission software loaded into the computer of the missile 1 is then carried out, wherein in particular the functionality of any sensors, detectors or actuators present in the component is checked. In parallel, in step 103a, tests of component groups and functional chains are performed.

At the end of these three tests, a decision is made as to whether a fatal error has occurred in one of the tests, that is, an error that renders the missile unusable. If this is the case, then a "NOGO" signal is transmitted to the external test and test device 3 together with a complete error image of this component just tested, which has led to the "NOGO", and from this via a display device in step 106 output. This complete error image essentially contains a complete log of the individual tests carried out with their respective results and the error cause of the component reported as defective including all relevant information from the defective component as well as from the environment of the defective component.

The NOGO check can also be carried out continuously in all three steps 101, 102, 103.

Furthermore, sporadic, non-fatal errors that have been recorded during the tests are output to the external testing and testing device 3 during the tests, so that a person evaluating the test result can obtain an image of the state from this sporadic, non-fatal error data of the missile 1, even if these failures did not contribute to the "NOGO" decision. The person evaluating the test can thus draw conclusions about the condition of the missile, so that on the basis of this data, certain maintenance or repair work on the missile can be made so that it has no fatal error in a possible later test.

During the test run, technical times of individual processes taking place in the missile 1 or its control computer are also measured, logged and output to the external test and test device. Even from these technical times, a person analyzing the test result can draw conclusions about the condition of the missile and thus arrange maintenance work in good time.

If no fatal error has occurred in tests 101 to 103, then in a further step 105 it is verified whether the component just tested has been the last component to be tested. If this is not the case, the next component is tested and the test starts again for this next component with step 101.

If the component just tested has been the last component to be tested, then in step 105 the decision "yes" will be made, whereupon the entire test cycle 100 will be completed with a positive "GO" message sent to the external test and test device 3 is forwarded. At the same time, the sporadic, non-fatal errors and the technical times are also output by the testing and checking device 3 in step 107, so that, if the test result of the test person is positive, data are available on the basis of which data will possibly be available shortly Repairs or maintenance can be determined.

By this method according to the invention thus not only a mobile test for checking the operability of unmanned, armed missiles is created, which also outside of stationary manufacturing or Maintenance equipment for the missile 1 can be used, but there is also a test and a test method specified, with which even missiles who have passed the actual test, in advance, already indications of the condition of the missile can be obtained, which may in future may result in a malfunction or a reduction in performance, or that may give an indication of due maintenance work.

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

Flugkörper

2

Simulationseinheit

3

Test- und Prüfeinheit

4

Kühlgefäß

5

Vorrichtung zum Laden von Missionsdaten

6

Satellitennavigationsantenne

7

Koffer

10

Rumpf

11

Tragflächen

12

Ruderklappen

13

Ruderklappen

14

Triebwerke

15

Infrarot-Zielsuchkopf

16

vorderer Rumpfbereich

16'

Schnittstelle

16"

interne Testeinheit (TLP)

17

Aufhängevorrichtung

17'

Aufhängevorrichtung

18

weitere Schnittstelle

19

Landmarkenmaske

20

Computer

21

Vorrichtung zur Signalverteilung und Signalzusammenführung

22

Stromversorgungsleitung

23

Datenaustauschleitung

24

Antennenleitung

25

Satellitennavigationsantenne

26

elektrische Leitungsverbindung

27

Stromversorgung

28

Verbindungskabel

30

Computer

31

Vorrichtung zur Signalverteilung und Signalzusammenführung

33

Datenaustauschkabel

34

Datenkabel

40

Kühlleitung

50

Datenleitung

60

Antennenleitung

100

Prüfdurchlauf

101

Selbsttest

102

Einschalttest

103

kontinuierlicher Test

104

erster Entscheidungsschritt

105

zweiter Entscheidungsschritt

106

NOGO-Fehler- und Datenausgabe

107

GO-Datenausgabe

They denote:

1

missile

2

simulation unit

3

Test and test unit

4

cooling vessel

5

Device for loading mission data

6

Satellite navigation antenna

7

suitcase

10

hull

11

wings

12

rudders

13

rudders

14

engines

15

Infrared homing head

16

front hull area

16 '

interface

16 "

internal test unit (TLP)

17

suspension

17 '

suspension

18

further interface

19

Landmark mask

20

computer

21

Device for signal distribution and signal combining

22

Power line

23

Data exchange line

24

aerial cable

25

Satellite navigation antenna

26

electrical line connection

27

power supply

28

connection cable

30

computer

31

Device for signal distribution and signal combining

33

Communications Cables

34

data cable

40

cooling line

50

data line

60

aerial cable

100

test run

101

self-test

102

power-

103

continuous test

104

first decision step

105

second decision step

106

NOGO error and data output

107

GO-data output

Claims (9)

Method of checking the functioning of unmanned armed missiles, the missile has a plurality of electronic components, the missile has communication interfaces for communicating at least a part of the components with devices provided outside the missile, wherein at least some of the components comprise sensors and / or actuators, - the missile is supplied with energy, data and coolant during the external inspection, - the review at least , the functioning of the sensors and actuators of the missile and , includes communication of the missile via its communication interfaces, characterized, - that errors found during the verification are categorized in: , sporadic errors, , non-fatal flaws and , fatal mistakes, if a fatal error of a component occurs, the check is aborted and an error message as well as an error record forming an error pattern of this component is output via a missile interface, that sporadic errors and non-fatal errors are stored in a missile memory device and output via a missile interface after completion of the check, even if the check is performed without the Occurrence of a fatal error has been completed and thus has led to a release of the missile. Method according to claim 1,
characterized, - is that the respective time duration of technical processes measured during the verification in the missile and stored in a memory device of the missile and issued after the inspection via a missile interface, even if the check without the occurrence of a fatal error has been completed and thus led to a release of the missile. Method according to claim 1 or 2,
characterized,
that the check is performed on at least some of the following components of a missile: - inertial measuring unit, - satellite navigation unit, - altimeter, - warhead, - homing head, - target distance meter, - engine, - rowing machines, - control computer of the missile. Method according to claim 1, 2 or 3,
characterized,
that while checking the components of the missile for each component - a switch-on test, a triggered self-test, - a continuous test during a mission simulation as well - Tests of component groups and therefore of functional chains are performed. Method according to one of the preceding claims,
characterized,
in that during the inspection of the missile the inertial measuring unit and the navigation computer are tested by comparing the accelerations and rotation rates measured by the inertial measuring unit with the acting gravitational acceleration and earth rotation. Method according to one of the preceding claims,
characterized,
that during the inspection of the missile the rowing machines, a local control computer and the on-board computer are tested, for which the test guides an operator through a dialogue and the operator has to confirm each action dictated by the test and then performed by it, the test comprising the following steps having: Release the rudders from the bolts holding them to the missile, - sequential, manual unlocking of each rowing machine, individual control of each steering machine with a set point and automatic check whether this set point has been reached by the steering machine, simultaneous movement of several steering machines with appropriate setpoint checking, - Returning the oars to their neutral position of 0 ° rudder deflection. Method according to one of the preceding claims,
characterized,
that are tested during the check of the missile, the detector of the infrared target seeker head, in particular its camera, the image processing computer and the on-board computer by at A constant scenario is checked whether the measured pixel gray values with linear increase in integration time accordingly increase linearly. Method according to one of the preceding claims,
characterized,
that during the checking of the missile the target acquisition function of the target seeker head is tested, with the following steps are performed: Arranging a landmark mask with engraved target contours at a defined distance in front of the infrared homing head, Cooling the infrared homing head, Loading a test mission plan, which has a corresponding landmark, into the control computer of the missile, Check whether and how quickly the infrared homing head detects a match of the landmark prescribed in the mission plan with the target contour engraved in the landmark mask. Apparatus for carrying out a method according to one of the preceding claims with - A simulation unit (2) which is connectable to a first interface (18) of the missile (1), and a test and test unit (3) connectable to a second interface (16 ') of the missile (1), wherein the simulation unit (2) and the test and test unit (3) are each designed as a mobile, preferably portable, device.

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