DE19501862B3 - Starting device for guided weapons - Google Patents
Starting device for guided weapons Download PDFInfo
- Publication number
- DE19501862B3 DE19501862B3 DE19501862A DE19501862A DE19501862B3 DE 19501862 B3 DE19501862 B3 DE 19501862B3 DE 19501862 A DE19501862 A DE 19501862A DE 19501862 A DE19501862 A DE 19501862A DE 19501862 B3 DE19501862 B3 DE 19501862B3
- Authority
- DE
- Germany
- Prior art keywords
- missile
- control line
- shielding
- launch tube
- shielding body
- 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.)
- Expired - Fee Related
Links
- 230000035939 shock Effects 0.000 claims 1
- 239000000835 fiber Substances 0.000 description 3
- 238000004873 anchoring Methods 0.000 description 2
- 239000013307 optical fiber Substances 0.000 description 2
- 239000004925 Acrylic resin Substances 0.000 description 1
- 229920000178 Acrylic resin Polymers 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- KAATUXNTWXVJKI-UHFFFAOYSA-N cypermethrin Chemical compound CC1(C)C(C=C(Cl)Cl)C1C(=O)OC(C#N)C1=CC=CC(OC=2C=CC=CC=2)=C1 KAATUXNTWXVJKI-UHFFFAOYSA-N 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 210000003746 feather Anatomy 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
- F41G7/30—Command link guidance systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
- F41G7/30—Command link guidance systems
- F41G7/301—Details
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
- F41G7/30—Command link guidance systems
- F41G7/32—Command link guidance systems for wire-guided missiles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
- F42B15/04—Arrangements thereon for guidance or control using wire, e.g. for guiding ground-to-ground rockets
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
Startvorrichtung
für eine
Lenkwaffe mit den folgenden Merkmalen:
– ein Startrohr (16);
– eine Lenkwaffe
(10) innerhalb des Startrohres (16);
– eine Steuerleitung (14),
die von der Lenkwaffe verläuft;
– Mittel
(42) zur Abschirmung eines Abschnitts der Steuerleitung (14), benachbart
zur Lenkwaffe (10) während
des Starts,
dadurch gekennzeichnet, daß die Abschirmmittel (42) aus einem
verstaubaren, langgestreckten, rohrförmigen Abschirmkörper (42)
bestehen, der im hinteren Teil des Startrohres (16) angeordnet ist,
durch das der Abschnitt der Steuerleitung verläuft.Launching device for a missile with the following features:
A start pipe (16);
- A missile (10) within the launch tube (16);
A control line (14) extending from the guided missile;
- means (42) for shielding a portion of the control line (14), adjacent to the missile (10) during takeoff,
characterized in that the shielding means (42) consist of a stowable, elongated, tubular shielding body (42) disposed in the rear part of the launch tube (16) through which the portion of the control line passes.
Description
Die Erfindung bezieht sich auf eine Startvorrichtung für Lenkwaffen mit einer Steuerleitung, die zwischen der Lenkwaffe und der Startstation verläuft, und über die Daten übertragen und/oder empfangen werden können.The The invention relates to a launching device for guided weapons with a control line between the guided missile and the launch station runs, and over the Transfer data and / or can be received.
Die Steuerleitung kann ein faseroptisches Kabel oder ein elektrisch leitfähiges Kabel sein. Die Steuerleitung wird im typischen Fall auf einer Ablauftrommel am Hinterende der Lenkwaffe angeordnet, und während des Starts und während des Fluges der Lenkwaffe erfolgt eine Abwicklung der Steuerleitung. Dabei muß große Sorgfalt aufgewendet werden, um eine Beschädigung des Kabels während des Starts zu verhindern, beispielsweise unter der Wirkung des Startmotors, wodurch übermäßige Spannungsbelastungen eingeführt werden können, und es muß ein Knicken oder Biegen verhindert werden, und es muß verhindert werden, daß das Kabel zwischen der Lenkwaffe und dem Startrohr eingeklemmt wird. Ein faseroptisches Kabel neigt mehr zu einem Bruch als ein elektrisch leitfähiges Kabel. Der Ausdruck 'Startrohr' wird benutzt, um irgendeinen Behälter oder anderen Träger zu beschreiben, in dem der Flugkörper vor dem Start angeordnet ist.The Control cable can be a fiber optic cable or an electrical conductive Be cable. The control line is typically on a drain drum arranged at the rear end of the missile, and during takeoff and during the Flight of the missile is a settlement of the control line. there must take great care be used to damage the cable during the Prevent starts, for example under the action of the starter motor, causing excessive stress introduced can be and it must be a kink or bending to be prevented, and it must be prevented that the cable is trapped between the missile and the launch tube. A fiber optic Cable is more prone to breakage than an electrically conductive cable. The term 'launch tube' is used to indicate some container or other carrier to describe in which the missile is in front is arranged at the start.
Die US-PS 4 573 647 beschreibt eine spezielle Bauart einer Startvorrichtung, bei der eine optische Faser unter einer Abdeckung (die längs des Lenkwaffenkörpers verläuft) hindurchtritt, wobei die Abdeckung einen Reißfaden aufweist, der an einem festen Verankerungspunkt festgelegt ist. Beim Start reißt der Reißfaden einen Mittelteil der Abdeckung ab, wodurch die optische Faser freigelegt wird, ohne daß eine beträchtliche Belastung hierauf ausgeübt wird.The US Pat. No. 4,573,647 describes a special type of starting device, wherein an optical fiber passes under a cover (which extends along the missile body), the cover being a tear thread which is fixed to a fixed anchoring point. When starting rips the ripcord a middle part of the cover, whereby the optical fiber exposed will, without one considerable Exercise is exercised.
Die Erfindung bezieht sich auf eine Startvorrichtung für Lenkwaffen mit den folgenden Merkmalen:
- – ein Startrohr;
- – eine Lenkwaffe innerhalb des Startrohres;
- – eine sich von der Lenkwaffe weg erstreckende Steuerleitung;
- – Mittel zur Abschirmung eines Abschnitts der Steuerleitung, benachbart zur Lenkwaffe während des Starts, wobei die Abschirmmittel aus einem verstaubaren, langgestreckten, rohrförmigen Abschirmungskörper bestehen, der hinten im Startrohr angeordnet ist und durch den jener Abschnitt der Steuerleitung verläuft.
- - a starting pipe;
- A missile within the launch tube;
- A control line extending away from the missile;
- - Means for shielding a portion of the control line, adjacent to the missile during take-off, wherein the shielding means consist of a stowable, elongated, tubular shielding body, which is arranged in the rear of the starting tube and through which that portion of the control line.
Die Steuerleitung ist an einer Stelle verankert, die von der Lenkwaffe entfernt ist.The Control line is anchored at a point by the guided missile is removed.
Der Verankerungspunkt kann eine Startplattform, ein Bodenfahrzeug oder ein Hubschrauber sein, wobei der Verankerungspunkt dem Startrohr zugeordnet sein kann oder am Startrohr selbst angeordnet ist.Of the Anchoring point can be a launch platform, a ground vehicle or be a helicopter, with the anchor point associated with the launch tube may be or is arranged on the starting pipe itself.
Nachstehend wird ein Ausführungsbeispiel der Erfindung anhand der Zeichnung beschrieben. Die einzige Figur der Zeichnung zeigt eine schematische Seitenansicht einer Startvorrichtung für eine Lenkwaffe.below is an embodiment of Invention described with reference to the drawing. The only figure of the Drawing shows a schematic side view of a starting device for a missile.
Gemäß der Zeichnung
ist eine Lenkwaffe
Dieses Ausführungsbeispiel weist Abschirmmittel auf, die die Steuerleitung während des Start schützen, ohne eine übermäßige Belastung auf die Steuerleitung auszuüben.This embodiment has shielding means which connect the control line during the Protect start, without an excessive load exercise on the control line.
Die
Steuerleitung
Claims (3)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GBGB9401221.8A GB9401221D0 (en) | 1994-01-22 | 1994-01-22 | Missile launch apparatus |
GB9401221 | 1994-01-22 |
Publications (1)
Publication Number | Publication Date |
---|---|
DE19501862B3 true DE19501862B3 (en) | 2007-10-04 |
Family
ID=37671900
Family Applications (4)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE19501865A Expired - Lifetime DE19501865B3 (en) | 1994-01-22 | 1995-01-23 | Starting device for guided weapons |
DE19501864A Expired - Lifetime DE19501864B3 (en) | 1994-01-22 | 1995-01-23 | Starting device for guided weapons |
DE19501861A Expired - Lifetime DE19501861B3 (en) | 1994-01-22 | 1995-01-23 | Starting device for guided weapons |
DE19501862A Expired - Fee Related DE19501862B3 (en) | 1994-01-22 | 1995-01-23 | Starting device for guided weapons |
Family Applications Before (3)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE19501865A Expired - Lifetime DE19501865B3 (en) | 1994-01-22 | 1995-01-23 | Starting device for guided weapons |
DE19501864A Expired - Lifetime DE19501864B3 (en) | 1994-01-22 | 1995-01-23 | Starting device for guided weapons |
DE19501861A Expired - Lifetime DE19501861B3 (en) | 1994-01-22 | 1995-01-23 | Starting device for guided weapons |
Country Status (2)
Country | Link |
---|---|
DE (4) | DE19501865B3 (en) |
GB (5) | GB9401221D0 (en) |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4573647A (en) * | 1984-05-30 | 1986-03-04 | The United States Of America As Represented By The Secretary Of The Army | Fiber deployment mechanism |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2027118C3 (en) * | 1970-06-03 | 1973-09-27 | Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen | Recoil-propelled missile |
US4770370A (en) * | 1987-03-31 | 1988-09-13 | The Boeing Company | Optical fiber guided tube-launched projectile system |
FR2630202B1 (en) * | 1988-04-14 | 1990-08-17 | Aerospatiale | PACKAGING AND LAUNCHING INSTALLATION OF A FILOGUIDE MISSILE |
US4903607A (en) * | 1988-08-02 | 1990-02-27 | Optelecom, Inc. | Communication link winding and dispensing projectile |
US5022607A (en) * | 1988-11-18 | 1991-06-11 | Hughes Aircraft Company | Bend limiting stiff leader and retainer system |
US5014930A (en) * | 1989-06-23 | 1991-05-14 | Hughes Aircraft Company | Missile filament dispensing arrangement |
US5056406A (en) * | 1990-03-15 | 1991-10-15 | The Boeing Company | Fiber optic mortar projectile |
US5031997A (en) * | 1990-03-28 | 1991-07-16 | Hughes Aircraft Company | Open breech hot launched fiber optic payout system |
US5031982A (en) * | 1990-05-23 | 1991-07-16 | Hughes Aircraft Company | Flexible payout duct |
US5189253A (en) * | 1990-07-20 | 1993-02-23 | Hughes Aircraft Company | Filament dispenser |
-
1994
- 1994-01-22 GB GBGB9401221.8A patent/GB9401221D0/en not_active Ceased
-
1995
- 1995-01-16 GB GB9500770A patent/GB2434191B/en not_active Expired - Fee Related
- 1995-01-16 GB GB9500769A patent/GB2434190B/en not_active Expired - Fee Related
- 1995-01-16 GB GB9500772A patent/GB2434193B/en not_active Expired - Fee Related
- 1995-01-16 GB GB9500771A patent/GB2434192B/en not_active Expired - Fee Related
- 1995-01-23 DE DE19501865A patent/DE19501865B3/en not_active Expired - Lifetime
- 1995-01-23 DE DE19501864A patent/DE19501864B3/en not_active Expired - Lifetime
- 1995-01-23 DE DE19501861A patent/DE19501861B3/en not_active Expired - Lifetime
- 1995-01-23 DE DE19501862A patent/DE19501862B3/en not_active Expired - Fee Related
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4573647A (en) * | 1984-05-30 | 1986-03-04 | The United States Of America As Represented By The Secretary Of The Army | Fiber deployment mechanism |
Also Published As
Publication number | Publication date |
---|---|
GB2434193B (en) | 2007-12-05 |
GB2434190A (en) | 2007-07-18 |
GB2434191B (en) | 2007-12-05 |
DE19501865B3 (en) | 2007-08-30 |
GB9500769D0 (en) | 2007-01-10 |
DE19501861B3 (en) | 2007-08-30 |
GB9500771D0 (en) | 2007-01-10 |
GB2434191A (en) | 2007-07-18 |
DE19501864B3 (en) | 2007-08-30 |
GB2434192B (en) | 2007-12-05 |
GB2434192A (en) | 2007-07-18 |
GB9500772D0 (en) | 2007-01-10 |
GB2434190B (en) | 2007-12-05 |
GB9401221D0 (en) | 2007-01-10 |
GB9500770D0 (en) | 2007-01-10 |
GB2434193A (en) | 2007-07-18 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
8339 | Ceased/non-payment of the annual fee | ||
8364 | No opposition during term of opposition |