ES2334840T3 - Procedure to check the functional fitness of armed flying arts not tripulated. - Google Patents

Procedure to check the functional fitness of armed flying arts not tripulated. Download PDF

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Publication number
ES2334840T3
ES2334840T3 ES07016887T ES07016887T ES2334840T3 ES 2334840 T3 ES2334840 T3 ES 2334840T3 ES 07016887 T ES07016887 T ES 07016887T ES 07016887 T ES07016887 T ES 07016887T ES 2334840 T3 ES2334840 T3 ES 2334840T3
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Spain
Prior art keywords
flying
check
test
defects
artifact
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Active
Application number
ES07016887T
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Spanish (es)
Inventor
Michael Grabmeier
Albert Schlegl
Werner Wohlgemuth
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
LFK-Lenkflugkorpersysteme GmbH
Original Assignee
LFK-Lenkflugkorpersysteme GmbH
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Priority to DE102006041140 priority Critical
Priority to DE102006041140A priority patent/DE102006041140B4/en
Application filed by LFK-Lenkflugkorpersysteme GmbH filed Critical LFK-Lenkflugkorpersysteme GmbH
Application granted granted Critical
Publication of ES2334840T3 publication Critical patent/ES2334840T3/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B35/00Testing or checking of ammunition

Abstract

Procedure for checking the functional aptitude of unmanned armed flying devices (1), - in which the flying device (1) comprises a large number of electronic components, - in which the flying device (1) has communication interfaces to communicate at least a part of the components with equipment provided outside the flying device (1), - in which at least some of the components have sensors and actuators, - in which the flying device (1) is supplied from the outside with energy, data and refrigerant during the check, - in which the check comprises at least - the functional aptitude of the sensors and actuators of the flying device (1) and - the communication of the flying device (1) through its communication interfaces, characterized in that - defects detected during checking are categorized into: - sporadically occurring defects, - non-fatal defects and - fatal defects, - when a defect appears Failure of a component causes an interruption of the check and a defect warning and a defect protocol that form an image of the defect of this component are emitted through a flying device interface, - sporadically appeared defects and defects are not stored fatal in a flying device memory device (1) and, once the check is completed, these defects are output through an interface of the flying device, even if the check is completed without the occurrence of a fatal defect and , therefore, has led to an approval of the flying device (1).

Description

Procedure to check fitness functional of unmanned armed flying artifacts.

Technical field

The present invention concerns a procedure to check the functional aptitude of artifacts unmanned armed flying according to the preamble of the claim 1.

State of the art

A procedure of this kind is known, by example, by document DE 10 2004 042 990 A1. The procedure revealed there provides that, in the event of a defect fatal, that is, a defect that leads to the inability to use of the flying device, a defect warning is issued that the constructive group in which the fatal defect. For a detailed analysis of the defect you have to then convert the flying device to the inert state (without the combat head or other pyrotechnic elements), modifying only by this reconversion the state in which the default. It can happen so the defect no longer appears after the reconversion of the flying device to the inert state or that Modify the default image.

Exhibition of the invention

Therefore, the problem of the present invention it consists of indicating a procedure of the commented gender for check the functional aptitude of armed flying artifacts not manned, that allows to carry out safely a check of the functional aptitude even in a flying device equipped with the combat head and pyrotechnic elements.

This problem is solved by procedure indicated in claim 1.

Advantages

By issuing according to the invention, when a fatal defect appears, of a defect protocol that forms an image of the defect of a defective component and comprising the identified defect and all the revealing information coming from the defective component and from the environment of the defective component, an improved and more expressive force procedure is provided compared to the procedure known by the state of the art, which is characterized by its detailed information on the defect in the defect protocol. In addition, through the registration and issuance - which is carried out after the development of the test - of the sporadic defects that appeared during the test, as well as of the non-fatal defects, information on the status of the flying device is provided.
from which the expert can deduce the initiation of defects or wear or aging phenomena.

The remaining claims indicate advantageous improvements of the procedure according to the invention.

It is advantageous to measure it during the check the respective time duration of technical processes within the flying device and this duration is stored on a computer memory of the flying device and deliver it through a interface of the flying artifact after the conclusion of the check, even if the check is completed without the occurrence of a fatal defect and, therefore, has led to a approval of the flying artifact. The check and the protocolization of the duration in time of technical processes within the flying device they also make a conscientious possible analysis of uncritical non-optimal functions and phenomena of wear that are starting.

Preferably, the check is performed to at least some of the following components of an artifact flying: inertial measurement unit, navigation unit by satellite, altimeter, combat head, white seeker head infrared, target distance meter, group motor, rudder machines, computer control flying artifact.

In a preferred execution of the procedure according to the invention is performed for each component during the checking the components of the flying device an essay of connection, a triggered self-test and a continuous test during A mission simulation.

An advantageous improvement of the procedure according to the invention it is characterized in that the unit of inertial measure during the checking of the flying device, to whose end the accelerations and speeds of rotation measured by the inertial unit of measure are compared to acceleration terrestrial and terrestrial rotation acting.

Preferably, during checking the flying artifact machines are tested helm machines, for which an operator conducts the essay through a dialogue and the operator must confirm each action preset by the test and then performed by him, presenting the essay the steps following:

- release of the rudders with respect to the bolts that hold them to the flying device,

- manual sequential unlocking of each rudder machine,

- individual activation of each rudder machine with a nominal value and automatic check of whether this value Nominal has been reached by the rudder machine,

- simultaneous movement of several machines rudder with corresponding check of the nominal value,

- return of helm machines to your Neutral position of 0º deflection of the rudder.

It is also preferred that the detector be tested. white search head during artifact check flying, to which end it is checked in a constant scenario if the measured pixel gray values increase so correspondingly linear with an integration time increased

Another preferred embodiment of the procedure is characterized because the function of target acquisition of the target search target by infrared during the checking of the flying device, executing the following steps:

- provision of a trademark mask ground with white contours recorded at a defined distance  in front of the infrared target search head,

- white head cooling by infrared,

- loading an essay mission plan - which presents a corresponding land mark- on the computer flying artifact control,

- proof of whether and how quickly the head infrared white finder detects a coincidence of the land mark preset in the mission plan with the outline of White engraved on the landmarks mask.

A preferred device for commissioning practice of the method according to the invention is characterized by a modular constitution and mobile usability resulting from it.

Preferred embodiments of the invention with additional configuration details and other advantages  they are described and explained in more detail below by doing Reference to the attached drawing.

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Brief description of the drawings

They show:

Figure 1, a schematic representation of the test constitution for the process according to the invention Y

Figure 2, a development flow chart of the method according to the invention.

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Statement of preferred embodiments

Figure 1 shows in representation schematic a flying artifact 1, an external simulation unit  2, an external test and test unit 3 and other components still to be explained.

The flying device 1 has a fuselage 10, lift plans 11, rudder gates 12, 13, at least one power unit, of which is shown in figure 1 only the right air inlet channel 14, and, at its front end, a head 15 infrared white finder. In the zone front 16 of the fuselage is provided inside the fuselage a test unit (TLP) that can be joined with components provided outside of the flying device 1 through a 16 'interface located behind a fuselage gate. The flying artifact it is provided, inside the fuselage, with one or several heads combat (for example, front or penetrating hollow load). At top side of the fuselage are mounted two devices of suspension 17, 17 'with which the device can be hooked flying 1 to a carrier plane, for example to the bomb pylon there existing. On the upper side of the flying device 1 is provided another interface 18 through which the flying device It is connected during use with the air carrier vehicle (umbilical interface) and which is used herein procedure for exchanging data with the unit of simulation 2.

The simulation unit 2, also called "umbilical box", contains a computer 20, for example a personal computer, and a signal distribution device 21 and signal gathering. The computer 20 joins the power grid usual through a power supply line 22 carried outward, but it can also be operated by accumulators regardless of the power grid. In addition, the computer 20 is connected to the device 21 for distributing signals and signal gathering through an internal line 23 of data exchange

The signal distribution device 21 and signal gathering is powered by an antenna line 24 from outside with the signal of a navigation antenna 25 by satellite, for example a GPS antenna. Finally, the device 21 signal distribution and signal gathering is attached, to via a power line link 26, with a power supply of current 27 of 3x115V 400Hz usual in the field of aeronautics.

The signal distribution device 21 and signal gathering of simulation unit 2 is linked to the umbilical interface 18 of the flying device 1 by means of a cable of union 28, the so-called "umbilical cable". With the computer 20 existing in simulation unit 2 can communicate and interact then with the flying artifact 1 of it way (for example, through a Mil bus or discrete lines depending on  the standard Mil 1760) than with a carrier plane.

The external test and test unit 3, which also called "TLP box", contains a computer 30 and a signal distribution device 31 and signal gathering.

The computer 30 is connected to an electrical network usual through a power supply line conventional 32, but can also be operated by accumulators regardless of the power grid. The computer 30 and the signal distribution and signal gathering device 31 are linked to each other inside the test and test unit 3 through an internal data exchange cable 33 and can Exchange data through this cable.

The signal distribution device 31 and signal gathering of test and test unit 3 is attached for data exchanges, through data cable 34, the called "TLP cable", with the 16 'interface provided in the area front 16 of the flying device 1 and, through it and a 16 '' communication element (TLP), with the on-board computer provided in fuselage 10 of the flying device 1. The data delivered by the 16 '' communication element (TLP) provided in the flying device 1 during and after the completion of a checking said flying device 1 are delivered to the unit of test and test 3 and especially to the computer 30 contained in it, for viewing and further evaluation, through the data line 34.

In addition to the external simulation unit 2 and the external test and test unit 3, a container of external cooling 4 that is connected, through a pipe refrigeration 40, with refrigeration equipment provided in the flying artifact for the head 15 white seeker by infrared so as to cool the latter during the realization of the check.

Also, as represented by the dashed data line 50, a data loading device 5 mission on an on-board computer of the flying device 1 can be linked with said on-board computer of the flying device 1 through the 16 'interface. With this device, which is called Also "ground loader unit" (GLU), can be loaded into the on-board computer of the flying device 1 a mission plan for a flight mission (here, in the embodiment example preferred represented, a special rehearsal mission plan). By mission data must be understood data that the device needs flying to reach its target, that is, data for the navigation, flight path, but also data on targets to undergo an approach flight, for example images or models of certain landmarks or images or a model of the target to undergo an approach flight.

In addition, certain figure is shown in Figure 1 distance in front of the nose of the flying device 1, that is, in front of the head 15 infrared white finder, a mask 19 of landmarks that is provided with contours of white engravings and serves to check the head 15 seeker of infrared white. The white contours engraved on the mask 19 of landmarks correspond to the image of the target or to the target model that has been fed by means of GLU 5 a the white memory of the computer on board the artifact flying 1.

Finally, the flying device 1 is attached, to through an antenna line 60, with an external antenna 6 of satellite navigation that provides navigation data by satellite to the on-board computer of the flying device.

A delay device 45 is also provided. for a radar altimeter arranged in the lower front zone of the fuselage of the flying device 1. Delay equipment 45 is it has in the area of the radar altimeter below the device flying 1. It consists of two antennas that are joined one with another through a delay line (RALT delay line) of defined length (for example, 31.6 m). The radar altimeter of the flying device 1 emits towards the first antenna, being conducted the electromagnetic impulses, through the delay line, towards the second antenna, which sends again after impulses to the radar altimeter antenna. When the team of 45 delay for the radar altimeter is positioned below this one as shown in figure 1, can be tested on the artifact flying 1 if the radar altimeter gets the default length of the delay line (in the example 31.6 m) as measured height. From this way, with the 45 delay equipment for the altimeter of the radar you can test the measurement function of said altimeter of the Radar.

The device for checking the flying device 1 is of modular construction and consists of several mobile equipment, substantially simulation unit 2 and the test and test unit 3, which can be housed each of they, for example, in a briefcase and, therefore, can be easily transported, so that the check can also be carried out on site, for example in a material warehouse or on an airfield, shortly before the use of the device flying. Another briefcase 7, which is also represented only schematic in figure 1, it serves to receive the cables of connection, the delay equipment 45 for the radar altimeter, the mask of landmarks and other individual parts, so that the complete team to check the flying device 1 can transported in a total of three briefcases.

The development of the checking using the flow chart represented in the figure 2.

The development of the procedure in the diagram The flow of Figure 2 begins after the start of the test with test pass 100 itself that presents a plurality of tests carried out successively or in parallel for different components of flying device 1 that must be checked A test is first carried out for a first component of connection 101 in which the component automatically tests its basic functions. Then follow in step 102 a self-test triggered 102 of the component that is commanded by the computer on board the flying device and in which the spectrum is activated of complete test of the isolated component. In the next step 103 a continuous test of the corresponding component is then carried out performed under a simulation of an existing carrier aircraft and a Mission software loaded on the flying artifact computer 1 especially testing the functional ability of sensors, detectors or actuators possibly existing in the component. In parallel with this, group tests are carried out in step 103a of components and function chains.

After the development of these three trials, make a decision about whether it has appeared in one of the essays a fatal defect, that is, a defect that causes the artifact Flying is not trained to be used. If this happens, it will then transmits a "NOPASA" ("NOGO") signal to the equipment test and external test 3 together with a complete picture of the defect of this newly tested component that has led to the "NOPASA" situation, and this signal is delivered from this equipment through a display device in step 106. This image complete defect includes substantially a complete protocol of the different tests carried out with their respective results, as well as the cause of the defect of the component notified as defective, including all relevant information from the defective component and the environment of said defective component.

The NOPASA check can also be performed continuously in the three steps 101, 102, 103.

They are also issued to the test team and external test 3 non-fatal sporadic defects that have arisen during the trials and that have been registered, so that a person evaluating the test result can be trained with help of this non-fatal sporadic defect data an image about the state of flying artifact 1, even when these defects have not contributed to the "NOPASA" decision. The person that evaluate the essay can draw from this conclusions about the state of the flying artifact, so that, based on this data, certain maintenance work may be performed or repair in the flying device so that it does not present any fatal defect in a possible subsequent trial.

During the test run they are also measured, protocolize and deliver to the external testing and testing team technical times of individual processes that take place in the Flying artifact 1 or on your control computer. From these technical times, a person who analyzes the result of the essays can draw conclusions about the state of the artifact flying and order maintenance work in due course weather.

If no fatal defect has appeared in the tests 101 to 103, it is then checked in an additional step 105 if the newly tested component has been the last component to test. If this does not happen, then the test of the next component and the trial 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 "yes" decision, after which the cycle of 100 full essay with a positive "PASS" ("GO") warning which is relayed to the external testing and testing team 3. At the same time, they are also issued by the test and test team 3 in the step 107 non-fatal sporadic defects and technical times,  so that, even in the case of a positive test result passed with approved, are available to the person who analyze the test data with whose help you can set repairs or maintenance that will eventually have to be undertaken soon.

Therefore, thanks to this procedure according to the invention not only created a mobile trial to check the aptitude functional of unmanned armed flying artifacts, which You can also use outside production equipment or stationary maintenance for flying device 1, but it they also indicate an essay and a test procedure with the which can also be obtained in the parking area, for flying artifacts that have passed the test properly said, indications concerning the state of the flying device that possibly they may lead to operation in the future defective or at a power reduction or that may give a indication about upcoming maintenance work.

The reference symbols included in the claims, description and drawings serve only to improve the compression of the invention and are not intended to restrict The scope of your protection.

List of reference symbols

Designate:

one
Flying artifact

2
Simulation unit

3
Test and test unit

4
Cooling vessel

5
Mission data loading device

6
Satellite navigation antenna

7
Briefcase

10
Fuselage

eleven
Lift plans

12
Rudder gates

13
Rudder gates

14
Drive Groups

fifteen
White Seeker Head by infrared

16
Front area of the fuselage

16 '
Interface

16 ''
Internal test unit (TLP)

17
Suspension device

17 '
Suspension device

18
Additional interface

19
Landmark Mask

twenty
Computer

twenty-one
Signal distribution device and meeting signals

22
Power supply line

2. 3
Data exchange line

24
Antenna line

25
Satellite navigation antenna

26
Power line link

27
Power supply

28
Junction cable

30
Computer

31
Signal distribution device and meeting signals

33
Data exchange cable

3. 4
Data cable

40
Cooling pipe

fifty
Data line

60
Antenna line

100
Test pass

101
Self test

102
Connection test

103
Continuous testing

104
First decision step

105
Second decision step

106
NOPASA defect and data output

107
PASS data output

Claims (9)

1. Procedure to check fitness functional of unmanned armed flying artifacts (1),
- in which the flying device (1) comprises a large number of electronic components,
- in which the flying device (1) presents communication interfaces to communicate at least part of the components with equipment provided outside the flying device (one),
- in which at least some of the components present sensors and actuators,
- in which the flying device (1) is supplied from outside with energy, data and refrigerant during the verification,
- in which the check includes the less
?
the functional aptitude of flying artifact sensors and actuators (1) and
?
artifact communication flying (1) through its communication interfaces,
characterized because
- defects detected during the check in:
?
defects that appear sporadically,
?
nonfatal defects and
?
fatal defects,
- when a fatal defect of a component appears there is an interruption of the check and they are issued through of a flying device interface a defect warning and a default protocol that forms a defect image of this component,
- defects are stored sporadically appeared and non-fatal defects in a memory device flying device (1) and, once the check is completed, it is given output to these defects through an artifact interface flying, even if the check is completed without the occurrence of a fatal defect and, therefore, has led to a approval of the flying device (1).
2. Method according to claim 1, characterized in that
- during the check the respective one is measured duration in time of technical processes within the artifact flying (1) and this duration is stored in a memory device of the flying device (1) and, once the check is completed, it is given output to that duration through an artifact interface flying, even if the check is completed without the occurrence of a fatal defect and, therefore, has led to a approval of the flying device (1).
3. Method according to claim 1 or 2, characterized in that the check is carried out for at least some of the following components of a flying device (1):
- inertial unit of measure,
- satellite navigation unit,
- altimeter,
- combat head,
- white search head (15) by infrared,
- target distance meter,
- power unit,
- rudder machines,
- flying artifact control computer (one).
4. Method according to claim 1, 2 or 3, characterized in that during the checking of the components of the flying device (1) it is performed for each component,
- a connection test (102),
- a triggered self-test (101),
- a continuous test (103) during a mission simulation and
- component group tests and, therefore, of function chains.
5. Method according to any of the preceding claims, characterized in that the inertial measurement unit and the navigation computer are tested during the checking of the flying device (1), for which purpose the accelerations and rotational speeds measured by the inertial measurement unit they are compared with the terrestrial acceleration and the terrestrial rotation acting.
Method according to any of the preceding claims, characterized in that the rudder machines, a local control computer and the on-board computer are tested during the checking of the flying device (1), for which an operator conducts the test by means of of a dialogue and the operator has to confirm each action preset by the test and then performed by it, presenting the test the following steps:
- release of the rudders with respect to the bolts that hold them to the flying device (1),
- manual sequential unlocking of each rudder machine,
- individual activation of each rudder machine with a nominal value and automatic verification of whether reached this nominal value by the rudder machine,
- simultaneous movement of several machines helm with corresponding nominal value check,
- return of helm machines to your Neutral position of 0º deflection of the rudder.
Method according to any one of the preceding claims, characterized in that the infrared target search sensor (15) is tested, especially its camera, the image processing computer and the on-board computer during the checking of the flying device (1), for which purpose it is tested in a constant scenario if the measured pixel gray values increase correspondingly linearly with an increased integration time.
Method according to any one of the preceding claims, characterized in that the target acquisition function of the target finder (15) is tested during the checking of the flying device (1), performing the following steps:
- arrangement of a mask (19) of marks ground with white contours recorded at a defined distance  ahead of the head (15) white seeker by infrared,
- head cooling (15) search engine infrared white,
- loading an essay mission plan - which presents a corresponding land mark - on the computer flying artifact control (1),
- proof of whether and how quickly the head (15) infrared white finder detects a coincidence of the land mark preset in the mission plan with the outline of white engraved on the mask (19) of landmarks.
9. Device to implement a method according to any of the preceding claims, that understands
- a simulation unit (2) that can be joined with a first interface (18) of the flying device (1), and
- a test and test unit (3) that can join with a second interface (16 ') of the flying artifact (one),
the simulation unit being configured (2) and the test and test unit (3) as respective equipment mobile, preferably portable.
ES07016887T 2006-09-01 2007-08-29 Procedure to check the functional fitness of armed flying arts not tripulated. Active ES2334840T3 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
DE102006041140 2006-09-01
DE102006041140A DE102006041140B4 (en) 2006-09-01 2006-09-01 Procedure for checking the functioning of unmanned armed missiles

Publications (1)

Publication Number Publication Date
ES2334840T3 true ES2334840T3 (en) 2010-03-16

Family

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Country Status (5)

Country Link
EP (1) EP1895265B1 (en)
AT (1) AT445139T (en)
DE (2) DE102006041140B4 (en)
ES (1) ES2334840T3 (en)
NO (1) NO339520B1 (en)

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DE102006054340A1 (en) 2006-11-17 2008-05-21 Lfk-Lenkflugkörpersysteme Gmbh A method for verifying the ability to interact between an aircraft and an armed unmanned missile coupled thereto
DE102008017975A1 (en) * 2008-04-10 2009-10-15 Lfk-Lenkflugkörpersysteme Gmbh Unmanned missile and method of flight guidance
DE102008054264B4 (en) * 2008-10-31 2012-09-13 Lfk-Lenkflugkörpersysteme Gmbh Multifunctional service and test facility for unmanned aerial vehicles
DE102009040304B4 (en) 2009-09-05 2012-10-04 Lfk-Lenkflugkörpersysteme Gmbh Device for controlling functional tests and / or service procedures for aircraft-unmanned aerial vehicles
DE102010017974A1 (en) * 2010-04-23 2011-10-27 Lfk-Lenkflugkörpersysteme Gmbh A method of simulating an unmanned armed missile mission
DE102010018186B4 (en) * 2010-04-26 2013-11-14 Mbda Deutschland Gmbh Method for error detection of an unmanned missile coupled to a carrier aircraft in a wing flight and unmanned missile
DE102010024541B4 (en) 2010-05-27 2013-11-07 Mbda Deutschland Gmbh Method for interrogating measurement and / or state data from a data memory of a sharp unmanned missile and device for carrying out the method
DE102012015363B4 (en) * 2012-08-06 2014-10-23 Mbda Deutschland Gmbh Device for detecting errors of an unmanned missile designed to fly on a carrier aircraft and method therefor
CN103309244B (en) * 2013-05-29 2016-05-04 哈尔滨工程大学 One owes to drive unmanned boat semi-physical system and dedicated emulated method thereof
CN104122885B (en) * 2014-07-15 2017-02-01 北京航空航天大学 422 bus solid-liquid power aircraft flying control testing system
CN105791056B (en) * 2016-04-26 2020-01-10 太原罗克佳华工业有限公司 Virtual-real testing system of mechanical device
RU2691783C1 (en) * 2018-07-11 2019-06-18 Федеральное государственное казенное военное образовательное учреждение высшего образования "Военная академия материально-технического обеспечения имени генерала армии А.В. Хрулёва" Ammunition supply device to rapid heating stand
RU2691782C1 (en) * 2018-07-11 2019-06-18 Федеральное государственное казенное военное образовательное учреждение высшего образования "Военная академия материально-технического обеспечения имени генерала армии А.В. Хрулёва" Installation of slow ammunition heating
CN110160415A (en) * 2019-05-09 2019-08-23 北京理工大学 A kind of remote test system and its test method applied to Missile Ground joint debugging

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US5721680A (en) * 1995-06-07 1998-02-24 Hughes Missile Systems Company Missile test method for testing the operability of a missile from a launch site
US5971275A (en) * 1996-12-30 1999-10-26 The United States Of America As Represented By The Secretary Of The Navy System for verifying nuclear warhead prearm/safing signals
DE102004042990B4 (en) * 2004-09-06 2008-11-20 Michael Grabmeier Method and device for testing an operational cruise missile in various test scenarios by means of maintenance mode

Also Published As

Publication number Publication date
EP1895265B1 (en) 2009-10-07
AT445139T (en) 2009-10-15
DE102006041140B4 (en) 2009-11-26
DE502007001667D1 (en) 2009-11-19
DE102006041140A1 (en) 2008-03-20
EP1895265A1 (en) 2008-03-05
NO339520B1 (en) 2016-12-27
NO20074450L (en) 2008-03-03

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