EP0257163A1 - 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
EP0257163A1
EP0257163A1 EP86401832A EP86401832A EP0257163A1 EP 0257163 A1 EP0257163 A1 EP 0257163A1 EP 86401832 A EP86401832 A EP 86401832A EP 86401832 A EP86401832 A EP 86401832A EP 0257163 A1 EP0257163 A1 EP 0257163A1
Authority
EP
European Patent Office
Prior art keywords
missile
envelope
underwater
vehicle according
vehicle
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.)
Granted
Application number
EP86401832A
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English (en)
French (fr)
Other versions
EP0257163B1 (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
Original Assignee
Airbus Group SAS
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Filing date
Publication date
Application filed by Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0257163A1 publication Critical patent/EP0257163A1/de
Application granted granted Critical
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 an amphibious vehicle and more particularly a missile which can be launched from a submarine while diving against a surface ship, the trajectory control of the missile being ensured both in the underwater course and in the aerial course.
  • the projectiles launched by a submarine are essentially conventional missiles which force the submersible to run the risk of surfacing to launch.
  • the present invention therefore provides a new weapon of great range against surface ships in the form of an amphibious tactical missile following a first submarine trajectory and a second aerial trajectory, the aerial missile proper being initially enclosed in a motor envelope underwater, whose trim is controlled at any time to cross, at an angle of about 30 ° to the horizon for example, the critical intermediate zone of the rough surface of the sea, which envelope opens at the appropriate time to let the airborne escape.
  • a missile with a 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 distances accessible to submarines attacking a surface ship are thus considerably greater while retaining the benefit of the discretion of the submarine when diving.
  • FIG. 1 shows a submarine 1 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 " ⁇ " 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 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 box 11 uses the information from the launching submarine 1 stored in memory before launching in the computer 13 of the missile 6.
  • 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 propeller 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 line 32 ⁇ as well as that of the tail control surfaces 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 from 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 .
  • the invention makes it possible to control at any time the attitude of the missile 6 from the moment of launching by the torpedo tube until the final impact.
  • This control is carried out by means of the inertial unit 14 of the missile 6 which works for the entire duration of the trajectory and which makes it possible to develop the orders to be given: - first to the launch vehicle 10, by the jet control surfaces 8 partially intercepting the gases of the underwater propellant 7 throughout its underwater trajectory 3 and the first part of its aerial trajectory 15, thus ensuring a good exit of water in the chosen direction, that is to say, in principle, a nose-up at 30 ° and making it possible to correct any disturbances due to the state of the sea at the time of leaving the water. - then to missile 6, itself stabilized in roll, by means of its four aerodynamic control surfaces 33.

Landscapes

  • 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)
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 true EP0257163A1 (de) 1988-03-02
EP0257163B1 EP0257163B1 (de) 1990-08-08

Family

ID=9042678

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)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU695653B2 (en) * 1993-04-15 1998-08-20 Luxfer Group Limited Method of making hollow bodies
RU2571664C1 (ru) * 2014-09-09 2015-12-20 Николай Борисович Болотин Торпеда

Families Citing this family (2)

* 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
FR2766268B1 (fr) * 1997-07-21 1999-10-08 Aerospatiale Detecteur d'eau et munition sous-marine equipee d'un tel detecteur

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2655105A (en) * 1952-08-01 1953-10-13 George E Hansche Motor dropper
US2910953A (en) * 1950-07-20 1959-11-03 Horace E Karig Jet driven torpedoes
US3216357A (en) * 1960-04-01 1965-11-09 John P Mertens Thrust reversal system
US3457861A (en) * 1968-01-25 1969-07-29 Us Navy Missile booster pressure control mechanism
US3853081A (en) * 1958-10-28 1974-12-10 Us Navy Method and apparatus for destroying submarines

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2992794A (en) * 1950-12-13 1961-07-18 William H A Boyd Guided missile
US2937824A (en) * 1955-07-11 1960-05-24 Aerojet General Co Bi-medium rocket-torpedo missile
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

Patent Citations (5)

* 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
US2655105A (en) * 1952-08-01 1953-10-13 George E Hansche Motor dropper
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
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
MACHINE DESIGN, vol. 35, no. 30, 19 décembre 1963, page 8, Cleveland, US; "Submarine-launched antisub missile passes battle tests" *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU695653B2 (en) * 1993-04-15 1998-08-20 Luxfer Group Limited Method of making hollow bodies
RU2571664C1 (ru) * 2014-09-09 2015-12-20 Николай Борисович Болотин Торпеда

Also Published As

Publication number Publication date
DE2055707C1 (de) 1987-10-22
EP0257163B1 (de) 1990-08-08
FR2588241B1 (fr) 1989-03-10
FR2588241A1 (fr) 1987-04-10
GB1605263A (en) 1987-01-28

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