EP0652153B1 - Entlüftungsvorrichtung für das Abgas eines Flugkörpers auf einem Schiff - Google Patents

Entlüftungsvorrichtung für das Abgas eines Flugkörpers auf einem Schiff Download PDF

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Publication number
EP0652153B1
EP0652153B1 EP19940402355 EP94402355A EP0652153B1 EP 0652153 B1 EP0652153 B1 EP 0652153B1 EP 19940402355 EP19940402355 EP 19940402355 EP 94402355 A EP94402355 A EP 94402355A EP 0652153 B1 EP0652153 B1 EP 0652153B1
Authority
EP
European Patent Office
Prior art keywords
frame
missile
ship
group
protective cap
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
EP19940402355
Other languages
English (en)
French (fr)
Other versions
EP0652153A1 (de
Inventor
Christian Laine
Thierry Bigot
Georges Pensec
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.)
Direction General pour lArmement DGA
Etat Francais
Original Assignee
Direction General pour lArmement DGA
Etat Francais
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Direction General pour lArmement DGA, Etat Francais filed Critical Direction General pour lArmement DGA
Publication of EP0652153A1 publication Critical patent/EP0652153A1/de
Application granted granted Critical
Publication of EP0652153B1 publication Critical patent/EP0652153B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/0413—Means for exhaust gas disposal, e.g. exhaust deflectors, gas evacuation systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING 
    • B63B19/00—Arrangements or adaptations of ports, doors, windows, port-holes, or other openings or covers
    • B63B19/08—Ports or like openings in vessels' sides or at the vessels' bow or stern
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
    • B63G1/00—Arrangements of guns or missile launchers; Vessels characterised thereby

Definitions

  • the invention relates to a device for discharging combustion gases generated during the launching of a missile by a weapon system installed on a ship.
  • the subject of the invention is therefore a device for evacuating combustion gases from the missile (s) from a weapon system installed in particular on a ship, characterized in that it is constituted by a frame integrated into the hull of the ship. and conforming to its external shape, this frame delimiting at least one orifice obstructed by a cover, the cover being ejectable under the pressure of combustion gases when at least one missile of the weapons system is fired.
  • the device according to the invention is such that the covers are made of a composite material and such that the frame structure is made of metallic or composite material.
  • the device is such that around each cover or group of covers to be ejected during the firing of a missile the structure of the frame present on the internal face subjected to gas pressure, a shape converging towards the external face.
  • the device is such that the cover or the group of covers to be ejected during the firing of a missile are fixed to the frame which surrounds it by calibrated bolts, of which failure occurs as soon as the gas pressure exceeds a predetermined threshold.
  • the device is such that it comprises, for each cover or group of covers to be ejected, at least one coiled cable connecting this cover or this group of covers to the frame, the cable is then drop down at the time of ejection.
  • the device is such that the frame delimits a rectangular orifice, or else such that the frame delimits four rectangular orifices two by two superimposed.
  • the present invention provides a simple and effective solution to the problem; in principle, it consists in "weakening" the hull of the ship at predetermined locations, corresponding to the outlets of missile nozzles (generally at the level of the walls) and thus allowing the weakened zones to be ejected under the pressure of the gases of combustion which then escape through the hull of the ship.
  • the hull while retaining a smooth appearance for opposing radars, comprises near each missile battery a frame comprising at least one cover, the frame being fixed to the hull of the ship.
  • the gas pressure causes the ejection of at least one seal, while leaving intact the covers which may not be affected, the ejection of which will only occur during the following shots.
  • the frame may include only one cover, a configuration sufficient for firing a missile.
  • the framework will include several lids (at least as many as missiles to fire) and the arrangement of the lids will depend on the configuration of the missiles on the firing battery.
  • Figure 1 is a view of the frame in the plane of the shell.
  • Figure 2 is a view of the same frame in a plane perpendicular to the plane of the hull.
  • Figure 3 is a view of an operculum and its recovery system after a shot, in a plane perpendicular to the plane of the hull.
  • Figure 4 is a view of the device for ejecting a cover in a plane perpendicular to the plane of the shell.
  • the structure of the frame 1 defines four lids 2.
  • the frame 1 is inserted into the hull 3 of the ship by bolts 4 or rivets or any other means.
  • the frame 1 therefore remains fixed to the hull 3 of the ship when the lids 2 are ejected.
  • the lids 2 are fixed to the structure of the frame 1 by calibrated bolts 5 or other equivalent means, such as for example a click, (see FIG. 4), in order to maintain these lids 2 on the frame 1 as long as the pressure flue gas did not exceed a threshold related to the type of missile fired.
  • This threshold should not be too low, so as to keep the seal 2 in place until the missile is fired: in fact, when the weapon system is not activated, the closing presence of cover 2 is necessary, not only to promote radar stealth but also to resist the rise of "sea packets" on deck.
  • the threshold should also not be too high, this in order to cause the ejection of the cover 2 sufficiently early so that the high temperature of the combustion gases has not been able to damage the deck and the walls of the ship.
  • the value of the pressure generated by the gas jet of the missile being high, that of the threshold can be easily calculated.
  • the structure of the frame 1 present on its internal face, exposed to the jet of gases combustion, a shape converging towards the external face: this shape is due to deflectors 6, 7, 8, 9 which aim to channel the jet on the ejectable cover 2, as well as to avoid the ejection of the covers neighbors.
  • This gas pipeline does not require a significant straightening of the jet, the deflectors 6, 7, 8, 9 used (unlike those mentioned previously for the conventional gas evacuation devices) do not penalize the size, the weight and the cost.
  • the lids 2 can be provided with handles 10, so as to facilitate their handling and their positioning.
  • the frame structure can be made of resistant metallic or composite material.
  • the lids are preferably made of composite material, essentially for reasons of weight and thermal resistance: but it is possible to use other materials which are less technically suitable (metallic materials for example) or more expensive (special glasses, ceramics, etc.). .).
  • the device according to the invention has the particularity of being able to operate autonomously and passively with respect to the missile. Indeed, no signal or command to open the hatch is necessary; it is the firing of the missile and the gas jet that it causes which causes the ejection of the cover or group of covers.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Claims (7)

  1. Vorrichtung zum Ablassen von Verbrennungsgasen von mindestens einer Rakete eines insbesondere auf einem Schiff installierten Waffensystems, dadurch gekennzeichnet, daß sie aus einem im Schiffsrumpf (3) integrierten und sich an dessen äußere Form anpassenden Rahmen (1) besteht, wobei dieser Rahmen (1) mindestens eine von einer Verschlußplatte (2) abgedeckten Öffnung abgrenzt und die Verschlußplatte (2) unter dem Druck der Verbrennungsgase ausgestoßen wird, wenn mindestens eine Rakete eines Waffensystems gezündet wird.
  2. Vorrichtung gemäß Patentanspruch 1, dadurch gekennzeichnet, daß die Verschlußplatten (2) aus einem Komposit-Material und die Struktur des Rahmens (1) aus Metall oder Komposit-Material gefertigt sind.
  3. Vorrichtung gemäß Patentanspruch 2, dadurch gekennzeichnet, daß die Struktur des Rahmens (1), welche jede bei der Zündung einer Rakete auszustoßende Verschlußplatte (2) oder Gruppe von Verschlußplatten umgibt, auf der dem Abgasdruck ausgesetzten Innenseite eine nach der Außenseite hin konvergierende Form aufweist.
  4. Vorrichtung gemäß Patentanspruch 1, dadurch gekennzeichnet, daß die bei der Zündung einer Rakete auszustoßende Verschlußplatte (2) oder Gruppe von Verschlußplatten an dem diese umgebenden Rahmen (1) mit tarierten Bolzen (5) befestigt sind, deren Bruch erfolgt, sobald der Druck der Abgase einen zuvor bestimmten Grenzwert überschreitet.
  5. Vorrichtung gemäß irgendeinem der vorangehenden Patentansprüche, dadurch gekennzeichnet, daß sie für jede auszustoßende Verschlußplatte (2) oder Gruppe von Verschlußplatten mindestens ein aufgespultes Kabel (11) enthält, welches diese Verschlußplatte (2) oder Gruppe von Verschlußplatten mit dem Rahmen (1) verbindet, wobei sich das Kabel bei dem Ausstoß abwickelt.
  6. Vorrichtung gemäß irgendeinem der vorangehenden Patentansprüche, dadurch gekennzeichnet, daß der Rahmen (1) eine rechteckige Öffnung abgrenzt.
  7. Vorrichtung gemäß irgendeinem der Patentansprüche 1 bis 5, dadurch gekennzeichnet, daß der Rahmen (1) vier rechteckige, jeweils paarweise übereinanderliegend angeordnete Öffnungen abgrenzt.
EP19940402355 1993-11-04 1994-10-20 Entlüftungsvorrichtung für das Abgas eines Flugkörpers auf einem Schiff Expired - Lifetime EP0652153B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9313129 1993-11-04
FR9313129A FR2711966B1 (fr) 1993-11-04 1993-11-04 Dispositif d'évacuation des gaz de combustion de missiles sur un navire.

Publications (2)

Publication Number Publication Date
EP0652153A1 EP0652153A1 (de) 1995-05-10
EP0652153B1 true EP0652153B1 (de) 1996-04-10

Family

ID=9452505

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19940402355 Expired - Lifetime EP0652153B1 (de) 1993-11-04 1994-10-20 Entlüftungsvorrichtung für das Abgas eines Flugkörpers auf einem Schiff

Country Status (5)

Country Link
EP (1) EP0652153B1 (de)
DE (1) DE69400133T2 (de)
ES (1) ES2088313T3 (de)
FR (1) FR2711966B1 (de)
TW (1) TW367035U (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2933373B1 (fr) * 2008-07-03 2010-08-20 Dcns Principe d'integration, contre menaces asymetriques, de systemes d'armes missiles sur rampe fixe pour batiment de surface furtifs
CN114459286A (zh) * 2021-08-06 2022-05-10 北京天兵科技有限公司 一种火箭尾焰导出装置

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4186647A (en) * 1978-08-09 1980-02-05 General Dynamics Corporation, Pomona Division Multiple area rear launch tube cover
US4471684A (en) * 1981-09-14 1984-09-18 Fmc Corporation Transom missile launcher module
GB2121149B (en) * 1982-05-27 1985-07-24 British Aerospace Missile housing and launch arrangement
US5162605A (en) * 1992-01-16 1992-11-10 General Dynamics Corporation Self-activated rocket launcher cell closure

Also Published As

Publication number Publication date
DE69400133T2 (de) 1996-09-05
EP0652153A1 (de) 1995-05-10
TW367035U (en) 1999-08-11
FR2711966B1 (fr) 1995-12-22
DE69400133D1 (de) 1996-05-15
FR2711966A1 (fr) 1995-05-12
ES2088313T3 (es) 1996-08-01

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