DE502007001667D1 - Procedure for checking the functioning of unmanned armed missiles - Google Patents
Procedure for checking the functioning of unmanned armed missilesInfo
- Publication number
- DE502007001667D1 DE502007001667D1 DE502007001667T DE502007001667T DE502007001667D1 DE 502007001667 D1 DE502007001667 D1 DE 502007001667D1 DE 502007001667 T DE502007001667 T DE 502007001667T DE 502007001667 T DE502007001667 T DE 502007001667T DE 502007001667 D1 DE502007001667 D1 DE 502007001667D1
- Authority
- DE
- Germany
- Prior art keywords
- missile
- testing
- test
- during
- errors
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
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.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102006041140A DE102006041140B4 (en) | 2006-09-01 | 2006-09-01 | Procedure for checking the functioning of unmanned armed missiles |
Publications (1)
Publication Number | Publication Date |
---|---|
DE502007001667D1 true DE502007001667D1 (en) | 2009-11-19 |
Family
ID=38740168
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE102006041140A Expired - Fee Related DE102006041140B4 (en) | 2006-09-01 | 2006-09-01 | Procedure for checking the functioning of unmanned armed missiles |
DE502007001667T Active DE502007001667D1 (en) | 2006-09-01 | 2007-08-29 | Procedure for checking the functioning of unmanned armed missiles |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE102006041140A Expired - Fee Related DE102006041140B4 (en) | 2006-09-01 | 2006-09-01 | Procedure for checking the functioning of unmanned armed missiles |
Country Status (5)
Country | Link |
---|---|
EP (1) | EP1895265B1 (en) |
AT (1) | ATE445139T1 (en) |
DE (2) | DE102006041140B4 (en) |
ES (1) | ES2334840T3 (en) |
NO (1) | NO339520B1 (en) |
Families Citing this family (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
CN109883643A (en) * | 2018-12-21 | 2019-06-14 | 中国航天空气动力技术研究院 | A kind of rotary missile band rudder control force test in wind tunnel method and system |
CN109737837B (en) * | 2019-01-16 | 2021-03-23 | 中国人民解放军陆军工程大学 | Semi-physical simulation system for fixed rudder trajectory correction fuse |
CN109900157B (en) * | 2019-02-22 | 2021-04-02 | 中国人民解放军海军工程大学 | Semi-physical simulation platform and method for guidance ammunition terminal guidance law |
CN110160415B (en) * | 2019-05-09 | 2020-07-10 | 北京理工大学 | Remote test system and method applied to missile ground joint debugging |
CN112212735A (en) * | 2020-09-27 | 2021-01-12 | 中国电子信息产业集团有限公司第六研究所 | Interactive semi-physical simulation test system |
CN113188382B (en) * | 2021-05-12 | 2021-11-19 | 中国人民解放军海军航空大学航空作战勤务学院 | Missile technology preparation simulation system |
CN115218732A (en) * | 2022-07-08 | 2022-10-21 | 江西洪都航空工业集团有限责任公司 | Missile batch rapid diagnosis system and diagnosis method based on remote and remote communication integration |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE58906626D1 (en) * | 1988-08-27 | 1994-02-17 | Honeywell Ag | Method and device for checking the function of a weapon system. |
CA2100156C (en) * | 1992-07-13 | 1998-07-28 | Ronald W. Monk | Method and apparatus for missile interface testing |
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 |
-
2006
- 2006-09-01 DE DE102006041140A patent/DE102006041140B4/en not_active Expired - Fee Related
-
2007
- 2007-08-29 DE DE502007001667T patent/DE502007001667D1/en active Active
- 2007-08-29 EP EP07016887A patent/EP1895265B1/en active Active
- 2007-08-29 ES ES07016887T patent/ES2334840T3/en active Active
- 2007-08-29 AT AT07016887T patent/ATE445139T1/en active
- 2007-08-31 NO NO20074450A patent/NO339520B1/en not_active IP Right Cessation
Also Published As
Publication number | Publication date |
---|---|
EP1895265B1 (en) | 2009-10-07 |
NO339520B1 (en) | 2016-12-27 |
ATE445139T1 (en) | 2009-10-15 |
DE102006041140A1 (en) | 2008-03-20 |
DE102006041140B4 (en) | 2009-11-26 |
NO20074450L (en) | 2008-03-03 |
ES2334840T3 (en) | 2010-03-16 |
EP1895265A1 (en) | 2008-03-05 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
8364 | No opposition during term of opposition |