EP0257163B1 - Methode und Vorrichtung zum Abschuss einer Luft-Lenkwaffe von einem U-Boot aus - Google Patents

Methode und Vorrichtung zum Abschuss einer Luft-Lenkwaffe von einem U-Boot aus Download PDF

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Publication number
EP0257163B1
EP0257163B1 EP86401832A EP86401832A EP0257163B1 EP 0257163 B1 EP0257163 B1 EP 0257163B1 EP 86401832 A EP86401832 A EP 86401832A EP 86401832 A EP86401832 A EP 86401832A EP 0257163 B1 EP0257163 B1 EP 0257163B1
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EP
European Patent Office
Prior art keywords
missile
envelope
vehicle according
vehicle
underwater
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 - Lifetime
Application number
EP86401832A
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English (en)
French (fr)
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EP0257163A1 (de
Inventor
Emile Stauff
Jean Guillot
André Pinel
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.)
Airbus Group SAS
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Airbus Group SAS
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Publication date
Application filed by Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0257163A1 publication Critical patent/EP0257163A1/de
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Publication of EP0257163B1 publication Critical patent/EP0257163B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B17/00—Rocket torpedoes, i.e. missiles provided with separate propulsion means for movement through air and through water

Definitions

  • the present invention relates to a method and a vehicle for launching a missile from a submarine while diving against a surface ship, the control of the trajectory of the missile being ensured both in the underwater course and in the air course.
  • the projectiles launched by a submarine are essentially conventional missiles which force the submersible to run the risk of surfacing to launch.
  • the invention relates to an improved version of this weapon allowing an increase in the distances accessible to submarines attacking a surface ship while retaining the benefit of the discretion of the submarine while diving.
  • a vehicle for launching a missile comprising an airtight envelope containing the missile and provided with an engine compartment, characterized in that the engine compartment comprises an underwater propellant with a nozzle and rudders and that the envelope also comprises an electronic control unit, a thermal battery and a piston by means of which the ejection of the missile is obtained at a chosen moment by a thrust applied to said piston from the engine compartment so that it presses towards the forward on the missile and let it pass through the front of the envelope.
  • the aerial vehicle of such a vehicle with its range of the order of, for example, 38 km, gives submarines an efficiency in range which allows them to clearly outclass all types of existing torpedoes, whose range n '' does not exceed 10 km, as soon as the sonar information is sufficiently precise to allow at least partial localization of the objective.
  • current sonars have relatively large ranges which are often accompanied by suitable precision in bearing but poor precision in distance. The machine can then be satisfied with the precision in field and its self-directing organ or search head, be adapted to a search without precise knowledge of the distance from the designated objective on the surface.
  • a missile with trajectory mainly aerial can be easily animated with a considerable speed, for example 300 m / s instead of 25 m / s for a torpedo, which allows it to reach its goal in a time very short and reduces in considerable proportions the possibilities of evolution or countermeasures of the target.
  • the invention differs from the teaching of documents such as document US-A 3 853 081 which is concerned with the dropping of the propellant of a military charge, without disturbing the kinetics of this charge.
  • FIG. 1 shows a submarine submerged at a depth "p", for example 50 m, launching horizontally by a conventional tube a combined vehicle according to the invention, generally designated by the reference 2.
  • This combined vehicle 2 first follows the underwater trajectory 3 which cuts the surface of the sea 4 at 5 at a nose-up angle "a” of 30 ° for example and releases at an altitude "h” an air vehicle 6 which continues its course in a classic way.
  • a launch envelope 10 to the dimensions of the torpedo tubes, for example the usual diameter of the torpedoes, or 533 mm (21 inches), which requires the folding of the wings 32 and the control surfaces 33 of the missile 6 to l 'inside its launch envelope 10 ( Figure 1).
  • a simplified inertial unit 14 known per se is used according to the invention, either integral with the missile 6 itself or with the launch envelope 10.
  • the vehicle submarine is provided with a propellant 7, for example with powder, the thrust of which is directed by jet control surfaces 8 ensuring the vehicle an underwater trajectory stabilized in pitch and yaw.
  • Roll stabilization was not provided because the missile 6 is itself roll stabilized after it leaves the launch vehicle in position 20 and it then automatically returns to its correct flight position in roll, whatever his cottage at the exit of the vehicle.
  • the underwater vehicle 10 comprises in its rear engine compartment 9 amplifiers intended to control the jet control surfaces 8 and a computer intended to give orders to these amplifiers, organs contained in an electronic unit 11, and a source of electrical energy , for example a thermal battery 12.
  • the computer in the housing 11 uses the information from the launching submarine 1 stored in memory before launching into the missile calculator 13 6.
  • the control surfaces of the jet are controlled by this computer 13 secured to the missile.
  • the characteristic according to the invention according to which the vehicle 10 is self-propelled, after its exit from the submarine 1, instead of gaining the surface under the sole action of Archimedes' thrust, is advantageous not so much for the gain of speed given by the underwater propellant only to prevent the underwater vehicle 10 from appearing at the surface at 5 in any configuration, probably very close to vertical, which would then cause problems for the missile 6 to choose the correct vertical shot plan.
  • the preferred conditions for leaving the water are of the order of: nose-up of 30 ° and longitudinal speed: 25 m / s.
  • the acceleration thruster 21 of the missile 6 is ignited by a controlled delay timer (not shown) after the rear section 22 of the missile has passed through the front section 23 of the vehicle 10, and the missile continues its trajectory by its own means like a conventional missile launched at a site of 30 °.
  • the entire launch vehicle is shown in Figure 2.
  • the launch vehicle has a cylindrical shape of diameter "D" paxemple of 533 mm (21 inches), terminated at the front by a warhead 26 of elliptical section. It carries a certain number of empennages 40 which deploy after the exit from the torpedo tube.
  • the missile 6 is inscribed in a circumference of diameter "d" thus leaving the possibility of giving the wall of the launch vehicle a thickness compatible with hydrostatic pressure.
  • the total length "L" of the launch vehicle can be less than 7 m, its elongation (or fineness) is therefore close to 13.
  • FIG. 4 shows the arrangement of the jet control surfaces 8 in the rear zone of the compartment 9 of the vehicle 10.
  • the pallet 29 at the interior end of each of the four control surfaces 8 is moved from the interior to the exterior of the nozzle 25 or vice versa according to the orders of the computer housed in the electronic unit 11, to stabilize the vehicle 10 in the desired direction during its underwater trajectory 3.
  • FIG. 3 shows the cruise nozzle 30 and the acceleration nozzles 31 of the missile 6.
  • the wings 32 are folded back to fit inside the envelope 10; we see their position deployed in dotted lines 32 'as well as that of the rudders 33 which open at 33' when the machine reaches position 20.
  • Submarine 1 while diving is in principle capable of supplying the missile with the same information as that usually provided by a surface vessel, and this with satisfactory precision.
  • This information is the direction and if possible the distance that of the target, the reference of the vertical of the launching submarine and its speed.
  • the submersion of the submarine must be between the periscopic immersion of about 15 m and a maximum of 80 m.
  • the speed of the submarine at the time of launch is for example less than 5 m / s and the launch takes place by a torpedo tube approximately parallel to the longitudinal axis of the submarine, and practically always close to the horizontal .

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Claims (9)

1. Verfahren zum Abschuß einer taktischen Luft-Lenkwaffe großer Reichweite von einem getauchten U-Boot aus mit folgenden Verfahrensschritten: hermetischer Einschluß der Lenkwaffe (6) in einem Behälter (10) - mit eingezogenen Flügeln (32) und Steuerrudern (33), Ausstoßen des Behälters vom U-Boot (1) nach außen, Vortrieb des Behälters unter Wasser, laufende Kontrolle der Unterwasserbahn (3) sowie des Beginns der Flugbahn, Sicherstellung des Austritts aus dem Wasser mit einer bestimmten Fluggeschwindigkeit unter einem bestimmten Anstellwinkel (a) zum Horizont, Auslösen der Freigabe der Lenkwaffe (6) aus ihrem Behälter in einer bestimmten Höhe über dem Meeresspiegel, Ausfahren der Flügel (32) und der Steuerruder (33) der Lenkwaffe und Steuerung derselben auf das Ziel, dadurch gekennzeichnet, daß man die Bahn des Behälters unter Zuhilfenahme von Strahlrudern (8) mittels eines Trägheitsnavigationsleitwerks (14) kontrolliert und die Freigabe der Lenkwaffe durch Herausstoßen aus ihrem Behälter durch Ausüben eines Schubs nach vorwärts (f1) auf sie derart erfolgt, daß sie durch ihre Geschoßspitze (18) eine Öffnung der Vorderklappe des Behälters erzwingt, und daß danach das Beschleunigungstriebwerk (21) der Lenkwaffe gezündet wird, sobald der hintere Abschnitt (22) der Lenkwaffe den Vorderabschnitt (23) des Behälters durchfahren hat.
2. Wagen für den Abschuß einer Lenkwaffe zur Ausführung des Verfahrens nach Anspruch 1, mit einem hermetisch verschlossenen Behälter (10), der die Lenkwaffe (6) enthält und mit einem Motorabteil (9) versehen ist, dadurch gekennzeichnet, daß das Motorabteil mit einem Unterwasserantrieb (7) und mit einer Düse sowie mit Strahlrudern (8) versehen ist und der Behälter gleichermaßen ein Gehäuse (11) mit einer elektronischen Lagenregelung, eine thermische Batterie (12) sowie einen Kolben (17) aufweist, mit dem das Herausstoßen der Lenkwaffe zu einem gegebenen Zeitpunkt bewirkt wird, indem auf den Kolben vom Motorabteil aus ein Schub ausgeübt wird, damit er nach vorne (f1) auf die Lenkwaffe gedrückt wird und sich diese durch den vorderen Abschuß (19) des Behälters hindurch ihre Bahn bricht.
3. Wagen nach Anspruch 2, dadurch gekennzeichnet, daß der gewählte Zeitpunkt durch Öffnung einer Klappe (16) vorgegeben wird, die in der Vorderwand des Unterwasserantriebs (7) vorgesehen ist.
4. Wagen nach einem der Ansprüche 2 und 3, dadurch gekennzeichnet, daß der Unterwasserantrieb (7) ein Festtreibstoffantrieb ist.
5. Wagen nach einem der Ansprüche 2 bis 4, dadurch gekennzeichnet, daß der Außendurchmesser des Wagens der eines klassischen Unterwassertorpedos ist.
6. Wagen nach Anspruch 2, dadurch gekennzeichnet, daß die Strahlruder (8) von einem Rechner gesteuert werden, der im Gehäuse (11) aufgenommen und mit dem Behälter fest verbunden ist.
7. Wagen nach Anspruch 2, dadurch gekennzeichnet, daß die Strahlruder (8) von einem Rechner (13) gesteuert werden, der mit der Lenkwaffe fest verbunden ist.
8. Wagen nach Anspruch 2, dadurch gekennzeichnet, daß das Trägheitsnavigationsleitwert (14) das der Lenkwaffe selbst ist.
9. Wagen nach Anspruch 2, dadurch gekennzeichnet, daß das Trägheitsnavigationsleitwerk (14) fest mit dem Behälter verbunden ist.
EP86401832A 1969-11-13 1986-08-19 Methode und Vorrichtung zum Abschuss einer Luft-Lenkwaffe von einem U-Boot aus Expired - Lifetime EP0257163B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR6938131A FR2588241B1 (fr) 1969-11-13 1969-11-13 Engin amphibie.

Publications (2)

Publication Number Publication Date
EP0257163A1 EP0257163A1 (de) 1988-03-02
EP0257163B1 true EP0257163B1 (de) 1990-08-08

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP86401832A Expired - Lifetime EP0257163B1 (de) 1969-11-13 1986-08-19 Methode und Vorrichtung zum Abschuss einer Luft-Lenkwaffe von einem U-Boot aus

Country Status (4)

Country Link
EP (1) EP0257163B1 (de)
DE (1) DE2055707C1 (de)
FR (1) FR2588241B1 (de)
GB (1) GB1605263A (de)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2649194B1 (fr) * 1989-06-30 1994-05-13 Aerospatiale Ste Nationale Indle Dispositif d'ejection pour munition amphibie et propulseur independant en faisant partie
CN1061103C (zh) * 1993-04-15 2001-01-24 艾尔坎国际有限公司 中空壳体制造法
FR2766268B1 (fr) * 1997-07-21 1999-10-08 Aerospatiale Detecteur d'eau et munition sous-marine equipee d'un tel detecteur
RU2571664C1 (ru) * 2014-09-09 2015-12-20 Николай Борисович Болотин Торпеда

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2910953A (en) * 1950-07-20 1959-11-03 Horace E Karig Jet driven torpedoes
US2992794A (en) * 1950-12-13 1961-07-18 William H A Boyd Guided missile
US2655105A (en) * 1952-08-01 1953-10-13 George E Hansche Motor dropper
US2937824A (en) * 1955-07-11 1960-05-24 Aerojet General Co Bi-medium rocket-torpedo missile
US3853081A (en) * 1958-10-28 1974-12-10 Us Navy Method and apparatus for destroying submarines
US3216357A (en) * 1960-04-01 1965-11-09 John P Mertens Thrust reversal system
US3141409A (en) * 1961-03-02 1964-07-21 Elmer W Travis Aero fin removal system
US3137203A (en) * 1962-01-31 1964-06-16 Brown Joseph Underwater missile launching system
US3295411A (en) * 1965-01-25 1967-01-03 Guenther W Lehmann Deep submergence missile launching vehicle with hovering and missile ejecting systems
US3301132A (en) * 1965-07-29 1967-01-31 Guenther W Lehmann Submersible missile launching vehicle
US3457861A (en) * 1968-01-25 1969-07-29 Us Navy Missile booster pressure control mechanism

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
"Les Missiles antinavires Exocet", Revue Internationale de Défense, numéro spécial "Bâtiments de guerre et matériels navals", Interavia, Genève 1976 *

Also Published As

Publication number Publication date
EP0257163A1 (de) 1988-03-02
DE2055707C1 (de) 1987-10-22
GB1605263A (en) 1987-01-28
FR2588241B1 (fr) 1989-03-10
FR2588241A1 (fr) 1987-04-10

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