WO2020093115A1 - Système de ravitaillement pour véhicule de lancement de fusées - Google Patents

Système de ravitaillement pour véhicule de lancement de fusées Download PDF

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Publication number
WO2020093115A1
WO2020093115A1 PCT/BR2018/050408 BR2018050408W WO2020093115A1 WO 2020093115 A1 WO2020093115 A1 WO 2020093115A1 BR 2018050408 W BR2018050408 W BR 2018050408W WO 2020093115 A1 WO2020093115 A1 WO 2020093115A1
Authority
WO
WIPO (PCT)
Prior art keywords
compartment
refueling
rocket
launch
vehicle
Prior art date
Application number
PCT/BR2018/050408
Other languages
English (en)
Portuguese (pt)
Inventor
Simon PIERRE JEANNOT
Original Assignee
Mac Jee Indústria De Defesa Ltda.
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 Mac Jee Indústria De Defesa Ltda. filed Critical Mac Jee Indústria De Defesa Ltda.
Priority to PCT/BR2018/050408 priority Critical patent/WO2020093115A1/fr
Publication of WO2020093115A1 publication Critical patent/WO2020093115A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A23/00—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A23/00—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles
    • F41A23/34—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles on wheeled or endless-track vehicles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A23/00—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles
    • F41A23/34—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles on wheeled or endless-track vehicles
    • F41A23/40—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles on wheeled or endless-track vehicles on rail vehicles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A23/00—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles
    • F41A23/34—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles on wheeled or endless-track vehicles
    • F41A23/42—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles on wheeled or endless-track vehicles for rocket throwers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A9/00—Feeding or loading of ammunition; Magazines; Guiding means for the extracting of cartridges
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A9/00—Feeding or loading of ammunition; Magazines; Guiding means for the extracting of cartridges
    • F41A9/82—Reloading or unloading of magazines
    • 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
    • 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
    • F41F3/042—Rocket or torpedo launchers for rockets the launching apparatus being used also as a transport container for the rocket
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B39/00—Packaging or storage of ammunition or explosive charges; Safety features thereof; Cartridge belts or bags
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B39/00—Packaging or storage of ammunition or explosive charges; Safety features thereof; Cartridge belts or bags
    • F42B39/22—Locking of ammunition in transport containers

Definitions

  • the present invention relates to a refueling system for a rocket launch vehicle, and, more specifically, a system comprising a launch vehicle and a refueling vehicle.
  • a common type of rocket launch vehicle comprises a vehicle with launch equipment.
  • the equipment generally comprises a rotatable and pivotable structure between a resting position and a launch position.
  • the launching structure must be dimensioned to support the weight of the pivoting structure and the rockets to be launched.
  • Document FR2519422 describes a refueling vehicle that has a crane that assists in the transfer of missiles to the launch vehicle.
  • the missiles are placed in baskets or containers and such baskets or containers are moved by the crane.
  • DE 3240846 describes a refueling system for rocket launchers that comprises a cargo unit. At the time of reloading, the missiles are pushed, using cylindrical guides, out of the unit and into the launch system. The unit is moved by a suspension mechanism and a plate and rod configuration is used to push the missiles.
  • EP 0 549 178 describes a logistical support equipment for armament vehicles that comprises a coupling structure between the armament vehicle and a refueling vehicle.
  • the present invention achieves the above objectives by means of a refueling system for a rocket launch vehicle, which comprises a rocket module, a launch vehicle, a refueling vehicle and a transfer medium.
  • the rocket module comprises a housing and an internal rocket receiving structure.
  • the launch vehicle comprises a body where a rocket launch compartment is installed, having at least a rocket receiving part; the rocket receiving part being configured to receive, in a linearly sliding way, the rocket module.
  • the refueling vehicle comprises at least one refueling compartment with a plurality of refueling cells; each of the refueling cells being configured to receive, in a linearly sliding way, the rocket module.
  • the transfer medium transfers the full rocket module from the refueling compartment of the refueling vehicle to the rocket launch compartment of the launch vehicle, and also transfers the empty rocket module from the rocket launch compartment of the launch to the refueling compartment of the refueling vehicle.
  • the rocket module may further comprise at least one anchoring device; and the rocket launch compartment of the launch vehicle may comprise an engagement arm with at least one pin for engaging the anchoring device.
  • the anchoring device can comprise a first track defining a flat friction surface, and a second track defining a path with at least two different depths; where the first track has a stop portion, and the second track has an uneven surface that forms a ramp portion and at least a stop portion, and the hitch arm has at least one pin being configured to rest against the stop portion.
  • first track stop when the module is transferred from the launch compartment to the refueling compartment; and to lean against the stop portion of the second lane when the module is transferred from the refueling compartment to the launch compartment.
  • the body of the launch vehicle may comprise U-tracks; and the launch compartment may comprise rolling devices that interact with the U-rail to allow the compartment to slide linearly back and forth in relation to the vehicle body.
  • Each bearing device may comprise two rollers that fit into a U-rail slot and an oscillating plate arranged on a turning axis.
  • the launch vehicle can also comprise four stabilizing feet configured to move from a retracted position close to the body to an extended position where they are supported on the ground, and a pantographic movement structure with jack used to lift and tilt the cargo compartment. launch.
  • Figure 1 - is a rear perspective view of a rocket launch vehicle according to an embodiment of the present invention.
  • Figure 2 - is a side view of a rocket launch vehicle according to an embodiment of the present invention.
  • Figure 3 - is a detailed view of an internal portion of the rocket launch vehicle according to an embodiment of the present invention, where a means of moving the launch compartment is illustrated;
  • Figure 4 - is an enlarged view of one of the components of the launch compartment r medium
  • Figure 5 - is an enlarged view of another of the components of the means of movement of the launch compartment;
  • Figure 6 - is an enlarged view of the articulation means of the rocket launch compartment of the rocket launch vehicle according to an embodiment of the present invention;
  • Figure 7 - is a rear perspective view of a refueling vehicle according to an embodiment of the present invention.
  • Figure 8 - is a perspective view of a rocket module of the refueling system according to an embodiment of the present invention.
  • Figure 9 - is a bottom view of a rocket module of the refueling system according to an embodiment of the present invention.
  • Figure 10 - is an enlarged top view of a refueling system anchoring device according to an embodiment of the present invention.
  • Figure 11 - is an enlarged view of the cross section of an anchoring device of the refueling system according to an embodiment of the present invention.
  • Figure 12 - is a schematic illustration of the refueling system according to an embodiment of the present invention.
  • Figures 1 and 2 show a rear perspective view and a side view of the rocket launch vehicle 1 according to the present invention.
  • vehicle 1 is shown in transport configuration and in figure 2 vehicle 1 is shown in launch configuration.
  • rockets as used herein, must be interpreted as any high caliber projectile, with or without a guidance system.
  • Vehicle 1 comprises a body where a launching compartment 2 is installed.
  • Launching compartment 2 is preferably an articulated structure, so that the compartment can be articulated between at least one transport position and at least one transport position. launch.
  • Launching compartment 2 preferably comprises at least one receiving portion 2a for rockets.
  • the launching compartment 2 comprises receiving parts parallel in the same plane. In the embodiment shown in the figures, compartment 2 comprises three receiving parts 2a.
  • the launching compartment 2 can be formed as a compartment with a housing where the receiving parts 2a are arranged as a compartment directly formed by the parallel receiving parts 2a.
  • the body of the launch vehicle 1 can comprise U-track 3, in order to allow the launch compartment to slide linearly.
  • compartment 2 can be moved back and forth in relation to the vehicle body by rolling bearings on the tracks.
  • the linear displacement system is powered by a ball screw.
  • other types of drives could be envisioned by a technician on the subject.
  • Figure 4 shows an enlarged view of one of the rolling devices 4 that interact with the rail 3.
  • the rolling device 4 comprises two rollers 4a and 4b that fit in the rail gap 3 and an oscillating plate 4c arranged on a turning axis.
  • the oscillating plate 4c allows any variation or curvature in the longitudinal direction to be compensated, without disturbing the sliding or rolling of rollers 4a and 4b.
  • Figure 5 shows schematically the oscillation of the plate, where the dashed lines of reference 4c show the oscillated position of the placam
  • stabilizing feet 5 connected to the body of the vehicle 2 move from a stowed position next to the body to an extended position in which they are resting on the ground.
  • the launch vehicle 2 has four stabilizing feet 5.
  • length 2 slides linearly backwards (the term “backwards” should be understood as towards the rear of the vehicle).
  • a pantographic movement structure with jack 6 is used to lift, tilt and rotate, as necessary for the desired positioning for the launch compartment.
  • Moving compartment 2 will also help the refueling process, as will be described later.
  • Figure 7 shows a rear perspective view of a refueling vehicle 10 according to the refueling system of the present invention.
  • the refueling vehicle 10 comprises a refueling compartment 12.
  • the refueling compartment 12 preferably comprises a plurality of refueling cells 12a, each configured to receive, in a linearly sliding manner, a rocket module 11.
  • FIG. 8 to 10 better illustrate the rocket module 1 1.
  • the rocket module 1 1 preferably comprises a frame 13 and an internal structure with rocket receiving tubes 14.
  • frame 13 has a prismatic rectangular shape with open ends, with walls 13a formed by metal plates (for example, aluminum). At the junction edges of the plates, aluminum reinforcements 13b can be provided.
  • the internal structure can be formed by tubes 14 and metallic material (for example, aluminum), and the structure can also include spacers for support and stability of the tubes.
  • metallic material for example, aluminum
  • each of the rocket modules 11 has, on one of its walls, at least one anchoring device 15, through which the module can be engaged for translation (transfer).
  • anchoring devices 15 are arranged on the lower wall, close to one of the open ends of the module (see figure 9, showing the lower wall of the module).
  • Figure 10 shows a schematic top view and Figure 11 shows a cross-sectional view of one of the anchoring devices 15, with Figure 11 also showing the anchoring pin of the translation module of the launch module. (not shown), in positions ⁇ ”and“ 2 ”corresponding to positions“ 1 ”and“ 2 ”in figure 10.
  • Each anchoring device comprises two tracks 16 and 17, where a first track 16 defines a flat friction surface, and a second track 17 defines a trajectory with at least two different depths.
  • the first lane 16 has, in its portion most distally opposite the end 15a, a stop portion 16a.
  • the second track 17 has an irregular surface, forming a ramp portion 17a two stop portions 17b and 17c.
  • the rocket launch compartment 2 has, for each receiving portion of module 2a, at least one coupling arm (not shown), at the end of which at least one pin 18 is mounted.
  • each coupling arm has two pins 18, being that each pin is inserted into one of the anchoring devices 15.
  • pins 18 and 19 are metallic pins.
  • the arm After the projectiles are fired, the arm starts to push to lay the module down. Thus, the pin runs along track 16 until stop 16a. The arm force is transmitted to the module by the stop 16a, so that the module is pushed into the refueling vehicle.
  • the launch vehicle's coupling arm could have any suitable construction, for example, a rack-driven arm whose end has two articulated projections and connected by a spring, each of the articulated projections having a pin 18.
  • the arms could be built in different ways.
  • the arms can be actuated by a remote actuation system, for example, by means of an electric actuator.
  • Figure 12 shows schematically the launch vehicles 1 and refueling 2.
  • the vehicles are arranged so that it is possible to position the launch compartment 2 with the module receiving portion 2a in a position corresponding to one of the cells 12a of the refill compartment 12.
  • the vehicles are arranged perpendicularly, and the launch compartment 2 of the launch vehicle is rotated by 90 Q , so that it faces the cells 12a of the refueling compartment 12.
  • the moving structure 6 of the launching compartment 2 allows the compartment to be moved up and down, so that the module receiving portion can be positioned in height correct to transfer the empty module to an empty cell in the refill compartment.
  • the supply vehicle 10 can have one of the cells 12a empty (in the figure, one of the lower cells of compartment 12) so that the used rocket module can be transferred from the launch compartment 2 of the launch vehicle 1 to the empty cell of the refueling compartment 12. Then, a respective of the rocket modules from one of the filled cells 12a can be transferred to the launch compartment.
  • the modules can be transferred in a completely automated way, with a motorized transfer (translation) system, so that the refueling operation is done in a faster, safer and more efficient way.
  • the refueling system of the present invention also has an empty module emptying function, which allows empty modules to be quickly removed from the module receiving portion of the launch compartment, so that the compartment can quickly receive new ones. full modules.
  • the movement structure 5 of the launch compartment 2 tilts the compartment enough to allow the empty module to be ejected from the open rear end of the module receiving portion (similar to the position shown in figure 2).
  • This feature of the system of the present invention is particularly useful during a battle situation, as it allows refueling to be carried out even more quickly.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Motorcycle And Bicycle Frame (AREA)

Abstract

La présente invention concerne un système de ravitaillement pour un véhicule de lancement de fusées, comprenant un module de fusées (11), un véhicule de lancement (1), un véhicule de ravitaillement (10), et un moyen de transfert pour transférer le module de fusées (11) plein du compartiment de ravitaillement (12) du véhicule de ravitaillement (10) au compartiment de lancement de fusées (2) du véhicule de lancement (1), et pour transférer le module de fusées (11) vide du compartiment de lancement de fusées (2) du véhicule de lancement (1) au compartiment de ravitaillement (12) du véhicule de ravitaillement (10).
PCT/BR2018/050408 2018-11-09 2018-11-09 Système de ravitaillement pour véhicule de lancement de fusées WO2020093115A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/BR2018/050408 WO2020093115A1 (fr) 2018-11-09 2018-11-09 Système de ravitaillement pour véhicule de lancement de fusées

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/BR2018/050408 WO2020093115A1 (fr) 2018-11-09 2018-11-09 Système de ravitaillement pour véhicule de lancement de fusées

Publications (1)

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WO2020093115A1 true WO2020093115A1 (fr) 2020-05-14

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PCT/BR2018/050408 WO2020093115A1 (fr) 2018-11-09 2018-11-09 Système de ravitaillement pour véhicule de lancement de fusées

Country Status (1)

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Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5461961A (en) * 1994-01-20 1995-10-31 Firma Wegmann & Co. Gmbh Combat vehicle and system for transporting it for loading onto aircraft
DE10045051A1 (de) * 2000-09-12 2002-03-21 Krauss Maffei Wegmann Gmbh & C Kampffahrzeug mit Abschußvorrichtung für Artillerieraketen
EP1400773B1 (fr) * 2002-09-23 2005-01-05 Krauss-Maffei Wegmann GmbH & Co. KG Dispositif pour adapter un conteneur pour plusieurs roquettes à un lanceur pour roquettes d'artillerie
KR20100056819A (ko) * 2008-11-20 2010-05-28 삼성테크윈 주식회사 차량용 하역 장치 및 이를 구비한 다연장 로켓 시스템
DE102009050006A1 (de) * 2009-10-21 2011-04-28 Diehl Bgt Defence Gmbh & Co. Kg Raketenstartbehälter und Verfahren zum Verbinden eines Raketenstartbehälters mit einem Raketenwerfer
DE102010016542A1 (de) * 2010-04-20 2011-10-20 Krauss-Maffei Wegmann Gmbh & Co. Kg Vorrichtung und Verfahren zum Richten eines Abschussbehälters
KR101138154B1 (ko) * 2008-12-18 2012-04-23 두산디에스티주식회사 로켓 포드 탑재 시스템
DE102011054963B3 (de) * 2011-10-31 2013-01-03 Krauss-Maffei Wegmann Gmbh & Co. Kg Militärisches Fahrzeug, Transportbehälter und Verfahren zum Verstauen von Ausrüstungsgegenständen
RU2568820C2 (ru) * 2014-04-03 2015-11-20 Публичное акционерное общество "Научно-производственное объединение "Алмаз" имени академика А.А. Расплетина" (ПАО "НПО "Алмаз") Мобильная пусковая система для транспортировки и пуска ракет из транспортно-пусковых контейнеров при помощи пороховых аккумуляторов давления или парогазогенераторв
RU2578917C1 (ru) * 2014-09-30 2016-03-27 Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" Автоматическая система загрузки ракет в самоходную пусковую установку

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5461961A (en) * 1994-01-20 1995-10-31 Firma Wegmann & Co. Gmbh Combat vehicle and system for transporting it for loading onto aircraft
DE10045051A1 (de) * 2000-09-12 2002-03-21 Krauss Maffei Wegmann Gmbh & C Kampffahrzeug mit Abschußvorrichtung für Artillerieraketen
EP1400773B1 (fr) * 2002-09-23 2005-01-05 Krauss-Maffei Wegmann GmbH & Co. KG Dispositif pour adapter un conteneur pour plusieurs roquettes à un lanceur pour roquettes d'artillerie
KR20100056819A (ko) * 2008-11-20 2010-05-28 삼성테크윈 주식회사 차량용 하역 장치 및 이를 구비한 다연장 로켓 시스템
KR101138154B1 (ko) * 2008-12-18 2012-04-23 두산디에스티주식회사 로켓 포드 탑재 시스템
DE102009050006A1 (de) * 2009-10-21 2011-04-28 Diehl Bgt Defence Gmbh & Co. Kg Raketenstartbehälter und Verfahren zum Verbinden eines Raketenstartbehälters mit einem Raketenwerfer
DE102010016542A1 (de) * 2010-04-20 2011-10-20 Krauss-Maffei Wegmann Gmbh & Co. Kg Vorrichtung und Verfahren zum Richten eines Abschussbehälters
DE102011054963B3 (de) * 2011-10-31 2013-01-03 Krauss-Maffei Wegmann Gmbh & Co. Kg Militärisches Fahrzeug, Transportbehälter und Verfahren zum Verstauen von Ausrüstungsgegenständen
RU2568820C2 (ru) * 2014-04-03 2015-11-20 Публичное акционерное общество "Научно-производственное объединение "Алмаз" имени академика А.А. Расплетина" (ПАО "НПО "Алмаз") Мобильная пусковая система для транспортировки и пуска ракет из транспортно-пусковых контейнеров при помощи пороховых аккумуляторов давления или парогазогенераторв
RU2578917C1 (ru) * 2014-09-30 2016-03-27 Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" Автоматическая система загрузки ракет в самоходную пусковую установку

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