WO2019033182A1 - Módulo de lançamento de foguetes e veiculo de lançamento de foguetes - Google Patents
Módulo de lançamento de foguetes e veiculo de lançamento de foguetes Download PDFInfo
- Publication number
- WO2019033182A1 WO2019033182A1 PCT/BR2017/050235 BR2017050235W WO2019033182A1 WO 2019033182 A1 WO2019033182 A1 WO 2019033182A1 BR 2017050235 W BR2017050235 W BR 2017050235W WO 2019033182 A1 WO2019033182 A1 WO 2019033182A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- module according
- rocket
- sliding table
- frame
- release module
- Prior art date
Links
Classifications
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- 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
- F41A23/20—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles for disappearing guns
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- 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
-
- 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
- F41A27/00—Gun mountings permitting traversing or elevating movement, e.g. gun carriages
- F41A27/06—Mechanical systems
- F41A27/22—Traversing gear
-
- 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
- F41A27/00—Gun mountings permitting traversing or elevating movement, e.g. gun carriages
- F41A27/06—Mechanical systems
- F41A27/24—Elevating gear
-
- 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
- F41A27/00—Gun mountings permitting traversing or elevating movement, e.g. gun carriages
- F41A27/28—Electrically-operated systems
-
- 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
Definitions
- the present invention relates to a rocket launcher module that can be operated independently or can be installed in the body of a vehicle.
- a typical type of rocket launch vehicle comprises a vehicle whose body has a flat support surface which receives launching equipment.
- the apparatus comprises a box type structure with rocket receiving cylinders.
- the carton is pivotable between a position where the rollers have their longitudinal axis parallel to the plane of the support surface and a position wherein the bottom surface of the carton frame makes an acute or straight angle with the support surface,
- the pivotal hinge axis is generally disposed near the rear end of the vehicle.
- the carton-like structure and the articulating device must be sized to support the weight of the pivoting structure and the rockets to be launched.
- the larger the weight of the rockets the smaller the amount able to be packed at a time in the box type structure.
- the box-like structure For heavy armaments, such as missiles, the box-like structure generally has a smaller capacity, housing two to four missiles at a time.
- the weight of the armament influences both the capacity of the box-like structure and the construction of the pivotable hinged system. Since the handling of the armament needs to be done with a large margin of safety, it is necessary that the pivoting joint system is robust and safe.
- known launching equipments also have a limitation related to the aim of the weapon, since the box structure has a limited movement to the pivoting hinge.
- EP 1739382 shows a projectile launcher comprising a vehicle with a pivoting launching platform with a plurality of launch structures arranged side by side.
- EP 2 754 989 shows a rocket launcher container which is received by a device having a lateral steering part and a vertical steering part.
- JP 2003/056997 discloses a missile launching apparatus which allows the setting of the launching angle with greater freedom.
- the adjustment system comprises a pneumatic system with articulation arms.
- US 2010/0282150 discloses a folding ramp especially adapted for use on ships.
- the ramp has a folding structure where the missile supports are installed.
- the collapsible structure comprises articulated arms.
- US 3316809 shows a retractable missile launcher for an armored vehicle.
- a housing containing the missiles is mounted in a shielded ring with a runway displacement system and a rack and gear system is used for retraction of the housing.
- US 7,013,790 discloses an armament drive system comprising a support cage, a movable platform carrying an armament and a retractable roof covering the armament.
- EP 0 612 969 discloses an all-terrain vehicle with a pivoting structure with an armature platform, wherein the structure is pivotable between a transport position and an operating position.
- a rocket launcher module comprising a base frame comprising at least one rail; a sliding table configured to slide substantially vertically on said rail when driven by at least one linear electric actuator; and a directing device comprising a rotatable base on which is mounted a pivotable body which supports a rocket support portion.
- the sliding table comprises a platform configured to receive the rotating base of the steering device.
- the base frame comprises a rectangular frame with four columns, each of the four columns defined a rail;
- the sliding table comprises a support structure that supports the substantially flat platform;
- the sliding table support structure comprises a plurality of shoulders configured to engage sliding on the rails of the frame;
- the substantially flat platform of the sliding table comprises an aperture which receives the rotatable base of the steering device.
- the module further comprises two linear actuators disposed at opposite ends of the frame, the actuators being powered by an electric motor and connected to the sliding table by a transition piece.
- the pivotable body of the targeting device is designed so that the position of its pivot axis coincides with the center of mass of the support portion receiving a set of rockets.
- the rotary movement of the rotary base and the pivotal movement of the pivotable body are preferably driven by an electric actuator.
- the module may comprise an outer cage that may be used for transportation or, when provided with feet, enable operation of the module independently.
- the present invention further contemplates a rocket launch vehicle comprising a body having an upper aperture which may be selectively opened or closed and the launching module of the present invention so that when the upper body opening is closed , the sliding table is in a retracted position relative to the frame; and, when the upper body opening is open; the sliding table is slid vertically in the rails of the frame to an extended position in which the steering device is exposed out of the vehicle body.
- Figure 1 is a front perspective view of a launching module according to one embodiment of the present invention, the module being shown in a retracted configuration;
- Figure 2 is a rear perspective view of a launching module according to one embodiment of the present invention, the module being shown in a retracted configuration;
- Figure 3 is a perspective view of a modular magazine module housing according to one embodiment of the present invention;
- Figure 4 is a perspective view of the inner part of a modular module housing of the launch module according to one embodiment of the present invention.
- FIG. 5 Top and bottom perspective views of a positioner of a modular module of the launch module according to one embodiment of the present invention
- FIG. 6 is a front perspective view of a launch module according to one embodiment of the present invention, the module being shown in a retracted configuration and with the modular rocket receiving compartments;
- FIG. 7 is a rear perspective view of a launching module according to one embodiment of the present invention, the module being shown in a retracted configuration and with the modular rocket receiving chambers;
- Figure 8 is a perspective view of a launching module according to one embodiment of the present invention, the module being shown in an expanded configuration and with the modular rocket receiving compartments;
- FIG. 9 is a second perspective view of a launch module according to one embodiment of the present invention, the module being shown in an expanded configuration and with the modular rocket receiving compartments;
- Figure 10 is a schematic view showing the main components of the linear actuator of the launching module according to one embodiment of the present invention.
- Figure 11 is a perspective view of a launching module according to a second embodiment of the present invention, the module being shown in expanded configuration;
- Figure 12 is a side view of the launching module according to the second embodiment of the present invention, the module being shown in expanded configuration with the hinged launch portion;
- Figure 13 is a perspective view of a launching module according to a second embodiment of the present invention, the module being shown in a retracted configuration;
- Figure 14 is a perspective view of the launcher base frame according to a second embodiment of the present invention.
- Figure 15 is a perspective view of the sliding table of the launching module according to a second embodiment of the present invention.
- Figure 16 is a perspective view of the slide module of the launch module according to a second embodiment of the present invention.
- Figure 17 is a perspective view of the launcher directing device according to a second embodiment of the present invention.
- Figure 18 is a perspective view of the external cage of the launching module according to one embodiment of the present invention.
- Figure 19 is a perspective view of the outer cage of the launching module according to one embodiment of the present invention, the cage receiving bearing feet.
- Figures 1 and 2 show a front perspective view and a rear perspective view of the launching module according to the preferred embodiment of the present invention.
- the release module comprises a base frame 1 and a table 3 configured to slide substantially vertically in rails of the base frame 1.
- the base frame 1 preferably comprises a rectangular frame with four columns 2 arranged in the corners of the rectangle shape. Part of the inner surface of each column - that is, part of the surface of each column facing the inside of the frame - forms a rail 2a.
- the sliding table 3 is configured to receive a steering device 4.
- the sliding table 3 comprises an opening for receiving the rotating base of the steering device 4.
- the sliding table 3 comprises a substantially flat platform 8 (with the aperture) and a support structure 9.
- the support structure 9 comprises rebates configured to engage the rails 2a of the base frame.
- the base structure comprises eight shoulders, two spaced aligned shoulders being arranged to engage each of the rails 2a
- the flat platform supporting the steering device 4 can be moved vertically in a secure and stable manner, as the platform is slidably supported on the four columns 2a of the base frame 1.
- the substantially vertical displacement of the sliding table 3 is preferably achieved by a linear actuator 11 supplied by an electric motor 12.
- a linear actuator 11 supplied by an electric motor 12.
- two linear actuators 11 supplied by a single actuator electric motor 12.
- the linear actuators are disposed at opposite ends of the frame 1, so that the vertical movement of the sliding table 3 is made in a stable manner.
- the connection between each actuator 11 and the slide table is performed by a respective transition piece 13 connected to the table.
- each actuator 11 is secured to the frame 1 through an attachment piece 14 connected to an upper transverse bar 15 of the frame 1.
- the lower part of each actuator 11 is secured to the frame in a lower attachment fitting 16.
- the directing device 4 preferably comprises a rotatable base 5 on which is mounted a pivotable body 6 which supports a rocket support portion 7.
- the pivotal body 6 is preferably designed so that the position of the pivot axis coincides with the center of mass / gravity of the support portion 7 receiving the modular rocket compartment.
- the rotary movement of the rotary base 5 and the pivotal movement of the pivotable body 6 are driven by an electric actuator which may, for example, be connected to the lower part of the flat platform 8 of the sliding table 3.
- the support portion 7 preferably comprises a substantially flat top portion where the modular rocket housing is supported and secured.
- Figures 3 to 5 illustrate the modular rocket housing M which is attached to the support portion 7 of the rotary device 4.
- modular housing M comprises an outer wrap 20 where positioners 21 are disposed.
- Figure 5 shows top perspective views (a) and lower perspective view (b) of the positioner.
- the outer wrap may include fairings 22 in the form of longitudinal shoulders.
- the outer wrap receives eight positioners, four in the top wall and four in the bottom wall.
- the inner part, shown in Figure 4 where the housing is shown without the wrapper 20, is formed by a plurality of tubes 23 with frames 24 which act as bearers and spacers.
- the tubes act as rocket receivers.
- each modular compartment M has sixteen rocket receiving tubes.
- the modular housings can be easily transported and stored.
- fastening and replacement of the M compartments in the launching module is done easily, quickly and safely.
- the support portion 7 of the launch module directing device 4 may receive more than one modular rocket housing (in the figure, the module receives three modular compartments).
- Figures 8 and 9 show the launch module in an extended configuration, i.e., after the sliding table 3 slides up onto the rails 2a in the columns of the frame 2.
- the modular compartments M can be directed by the rotation of the base 5 and by the pivoting of the pivoting body 6.
- the electric actuation of the directing device 4 is possible, which reduces the weight of the assembly and does not require the use of hydraulic or pneumatic actuation systems.
- Figure 9 shows a preferred embodiment of the linear actuator 11 according to the present invention.
- the linear actuator comprises the following elements: (a) body; (b) coverage; (c) male connector; (d) flange; (e) spacers; (f) flange-body gasket; (g) connector rod-cylinder rod; (h) body-cover gasket; (i) bush; (j) cylinder rod; (k) fixed tube and (I) planetary roller bolt, with sight of the AA cut shown in (m).
- Figures 11 through 17 show a second embodiment of the launching module of the present invention.
- the launch module receives a set of receiving tubes of rockets or F. missiles.
- Figures 118 and 12 show a perspective and side view of the launching module according to the second embodiment of the present invention, the module being shown in an extended configuration.
- Figure 13 shows a perspective view of the module according to the second embodiment of the present invention in retracted configuration.
- the release module comprises a base frame 1 and a table 3 configured to slide substantially vertically in rails of the base frame 1.
- the base frame 1 preferably comprises a rectangular frame with four columns 2 arranged in the corners of the rectangle shape. Part of the inner surface of each column - or either part of the surface of each column facing into the frame - forms a rail 2a.
- the sliding table 3 is configured to receive a steering device 4.
- the sliding table 3 comprises an aperture 3a for receiving the rotational base of the directing device 4.
- the sliding table 3 comprises a substantially flat platform 8 which comprises the aperture 3a and a support structure 9.
- the support structure 9 comprises shoulders 10 configured to engage the rails 2a of the base frame.
- the base structure comprises eight shoulders 10, two spaced aligned shoulders being arranged to engage each of the rails 2a
- the flat platform supporting the steering device 4 can be moved vertically in a secure and stable manner, as the platform is slidably supported on the four columns 2a of the base frame 1.
- the substantially vertical displacement of the sliding table 3 is accomplished by a linear actuator 110 fed by electric motor 120 (electric piston schematically illustrated in the figures).
- the launching module preferably comprises two linear actuators 110 driven by two electric motors 120.
- the linear actuators are disposed at opposite ends of the frame 1, so that the vertical movement of the sliding table 3 is made in a stable manner.
- the connection between each actuator 110 and the slide table is performed by a respective transition piece 13 connected to the table.
- each actuator 110 is secured to the frame 1 through an attachment piece 14 connected to an upper transverse bar 15 of the frame 1.
- the lower part of each actuator 110 is secured to the frame in a lower attachment fitting 16.
- the directing device 4 preferably comprises a rotatable base 5 on which is mounted a pivotable body 6 which supports a rocket carrier portion 7.
- the pivotable body 6 is preferably designed so that the position of the pivot axis 17 coincides with the center of mass / gravity of the support portion 7 receiving the receiving rocket assembly F.
- the rotary movement of the rotary base 5 and the pivotal movement of the pivotal body 6 are driven by an electric actuator which may, for example, be connected to the lower part of the flat platform 8 of the sliding table 3.
- the support portion 7 preferably comprises a substantially flat top portion where the receiving rocket assembly F is supported and secured.
- the launching module may further comprise an outer cage 18, within which can be arranged the frame / sliding assembly / steering device and drive means for transport.
- the upper portion of the outer cage 18 is preferably opened to allow passage of the assembly.
- support feet 19 may be connected to the cage 18.
- the cage 18 may be used as a support chassis for the module.
- the launching module of the present invention can function completely independently of any vehicle.
- the cage 18 may serve as a chassis in the case of independent operation.
- the launching module of the present invention can be installed in a vehicle, whereby the frame 1 is connected to the internal structure of the vehicle.
- the launching module of the present invention provides a compact, safe and stable solution for launching rockets (preferably 70mm diameter rockets).
- the device 4 when the sliding table 3 is in an extended configuration with respect to the frame 1, the device 4 can be rotated and the support surface 7 can be pivoted so as to adjust the throwing direction and angle.
- the module when the sliding table 3 is in a retracted configuration, the assembly becomes extremely compact.
- the module can be installed in an adapted 4x4 vehicle, so that the module is completely enclosed in the vehicle when retracted and can be expanded through an aperture provided in the roof of the vehicle (when expanded, the steering device 4 is external to the vehicle. body of the vehicle).
- the flat platform 8 with the steering device 4 can be vertically moved safely and steadily by the actuation of the linear actuator, without risk of tipping and without the need for hydraulic or pneumatic actuation systems, which reduces the risk of failures, especially considering sand or gravel operating environments.
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Transmission Devices (AREA)
- Toys (AREA)
- Motorcycle And Bicycle Frame (AREA)
- Body Structure For Vehicles (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Fittings On The Vehicle Exterior For Carrying Loads, And Devices For Holding Or Mounting Articles (AREA)
- Vehicle Cleaning, Maintenance, Repair, Refitting, And Outriggers (AREA)
- Accommodation For Nursing Or Treatment Tables (AREA)
Abstract
Description
Claims
Priority Applications (21)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
MA48321A MA48321B1 (fr) | 2017-08-17 | 2017-08-17 | Module de lancement de fusées et véhicule de lancement de fusées |
RU2020103308A RU2736531C1 (ru) | 2017-08-17 | 2017-08-17 | Модуль и носитель для ракетного запуска |
CA3071196A CA3071196C (en) | 2017-08-17 | 2017-08-17 | Rocket launch model and rocket launch vehicle |
US16/638,689 US11131521B2 (en) | 2017-08-17 | 2017-08-17 | Rocket launch module and rocket launch vehicle |
TNP/2020/000029A TN2020000029A1 (en) | 2017-08-17 | 2017-08-17 | Rocket launch modele and rocket launch vehicle |
BR112019027723-4A BR112019027723A2 (pt) | 2017-08-17 | 2017-08-17 | módulo de lançamento de foguetes e veiculo de lançamento de foguetes |
CN201780093945.4A CN110998219A (zh) | 2017-08-17 | 2017-08-17 | 火箭弹发射模块和火箭弹发射运载工具 |
EP17921678.3A EP3671100A4 (en) | 2017-08-17 | 2017-08-17 | MISSILE LAUNCH MODULE AND MISSILE LAUNCH VEHICLE |
JOP/2020/0036A JOP20200036A1 (ar) | 2017-08-17 | 2017-08-17 | نموذج إطلاق صاروخ ومركبة إطلاق صاروخ |
SG11202000836PA SG11202000836PA (en) | 2017-08-17 | 2017-08-17 | Rocket launch module and rocket launch vehicle |
MX2020001188A MX2020001188A (es) | 2017-08-17 | 2017-08-17 | Modulo de lanzamiento de cohete y vehiculo de lanzamiento de cohete. |
KR1020207003846A KR102384486B1 (ko) | 2017-08-17 | 2017-08-17 | 로켓 발사 모듈 및 로켓 발사 차량 |
AU2017427814A AU2017427814A1 (en) | 2017-08-17 | 2017-08-17 | Rocket launch module and rocket launch vehicle |
PCT/BR2017/050235 WO2019033182A1 (pt) | 2017-08-17 | 2017-08-17 | Módulo de lançamento de foguetes e veiculo de lançamento de foguetes |
PE2020000160A PE20200519A1 (es) | 2017-08-17 | 2017-08-17 | Modulo de lanzamiento de cohete y vehiculo de lanzamiento de cohete |
JP2020507036A JP7130031B2 (ja) | 2017-08-17 | 2017-08-17 | ロケット弾発射機モジュール及びロケット発射機用車両 |
IL272079A IL272079A (en) | 2017-08-17 | 2020-01-16 | Missile launch module and missile launch vehicles |
CONC2020/0001158A CO2020001158A2 (es) | 2017-08-17 | 2020-01-31 | Módulo de lanzamiento de cohete y vehículo de lanzamiento de cohete |
ZA2020/00694A ZA202000694B (en) | 2017-08-17 | 2020-02-03 | Rocket launch module and rocket launch vehicle |
PH12020500287A PH12020500287A1 (en) | 2017-08-17 | 2020-02-07 | Rocket launch module and rocket launch vehicle |
AU2023216798A AU2023216798A1 (en) | 2017-08-17 | 2023-08-16 | Rocket Launch Model and Rocket Launch Vehicle |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/BR2017/050235 WO2019033182A1 (pt) | 2017-08-17 | 2017-08-17 | Módulo de lançamento de foguetes e veiculo de lançamento de foguetes |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2019033182A1 true WO2019033182A1 (pt) | 2019-02-21 |
Family
ID=65362100
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/BR2017/050235 WO2019033182A1 (pt) | 2017-08-17 | 2017-08-17 | Módulo de lançamento de foguetes e veiculo de lançamento de foguetes |
Country Status (20)
Country | Link |
---|---|
US (1) | US11131521B2 (pt) |
EP (1) | EP3671100A4 (pt) |
JP (1) | JP7130031B2 (pt) |
KR (1) | KR102384486B1 (pt) |
CN (1) | CN110998219A (pt) |
AU (2) | AU2017427814A1 (pt) |
BR (1) | BR112019027723A2 (pt) |
CA (1) | CA3071196C (pt) |
CO (1) | CO2020001158A2 (pt) |
IL (1) | IL272079A (pt) |
JO (1) | JOP20200036A1 (pt) |
MA (1) | MA48321B1 (pt) |
MX (1) | MX2020001188A (pt) |
PE (1) | PE20200519A1 (pt) |
PH (1) | PH12020500287A1 (pt) |
RU (1) | RU2736531C1 (pt) |
SG (1) | SG11202000836PA (pt) |
TN (1) | TN2020000029A1 (pt) |
WO (1) | WO2019033182A1 (pt) |
ZA (1) | ZA202000694B (pt) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN113624070A (zh) * | 2021-07-08 | 2021-11-09 | 陕西中天火箭技术股份有限公司 | 一种发射角可调的便携式地面制导火箭发射架 |
CN114034212A (zh) * | 2021-11-05 | 2022-02-11 | 湖北三江航天万峰科技发展有限公司 | 一种发射箱垂直装填机构和装填方法 |
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IL268727A (en) * | 2019-08-15 | 2021-03-01 | Slinger Bag Ltd | A rotating device that oscillates horizontally to a tennis ball launcher |
CN111811321B (zh) * | 2020-07-10 | 2023-01-10 | 北京星途探索科技有限公司 | 一种新型简易导弹发射架 |
RU206042U1 (ru) * | 2021-03-16 | 2021-08-17 | Хаджи-Мурат Хасанович Байсиев | Противоградовая ракетная пусковая установка |
CN113945121A (zh) * | 2021-10-28 | 2022-01-18 | 贵州航天特种车有限责任公司 | 一种具有双发射装置的自行式火箭炮 |
FR3139193A1 (fr) * | 2022-08-30 | 2024-03-01 | Naval Group | Système modulaire et polyvalent de lancement de munitions et plateforme navale comportant au moins un tel système |
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EP0612969A1 (de) | 1993-02-24 | 1994-08-31 | STN ATLAS Elektronik GmbH | Kippbarer Aufbau für ein Militärfahrzeug |
JP2003056997A (ja) | 2001-08-09 | 2003-02-26 | Komatsu Ltd | 弾発射機 |
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EP1739382A1 (en) | 2005-06-30 | 2007-01-03 | Rafael-Armament Development Authority Ltd. | Mobile carrier for a projectile launcher |
KR20100056819A (ko) * | 2008-11-20 | 2010-05-28 | 삼성테크윈 주식회사 | 차량용 하역 장치 및 이를 구비한 다연장 로켓 시스템 |
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US20100282150A1 (en) | 2007-10-23 | 2010-11-11 | Onuk Ekber I N | Foldable ramp for missile launchers |
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CN113624070A (zh) * | 2021-07-08 | 2021-11-09 | 陕西中天火箭技术股份有限公司 | 一种发射角可调的便携式地面制导火箭发射架 |
CN114034212A (zh) * | 2021-11-05 | 2022-02-11 | 湖北三江航天万峰科技发展有限公司 | 一种发射箱垂直装填机构和装填方法 |
CN114034212B (zh) * | 2021-11-05 | 2023-02-28 | 湖北三江航天万峰科技发展有限公司 | 一种发射箱垂直装填机构和装填方法 |
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IL272079A (en) | 2020-03-31 |
JOP20200036A1 (ar) | 2022-10-30 |
AU2017427814A1 (en) | 2020-02-13 |
US20210190452A1 (en) | 2021-06-24 |
KR20200037257A (ko) | 2020-04-08 |
CA3071196A1 (en) | 2019-02-21 |
MX2020001188A (es) | 2020-08-20 |
PE20200519A1 (es) | 2020-03-06 |
ZA202000694B (en) | 2021-08-25 |
CA3071196C (en) | 2023-10-17 |
CO2020001158A2 (es) | 2020-04-13 |
MA48321A1 (fr) | 2020-12-31 |
JP7130031B2 (ja) | 2022-09-02 |
JP2020537102A (ja) | 2020-12-17 |
US11131521B2 (en) | 2021-09-28 |
CN110998219A (zh) | 2020-04-10 |
KR102384486B1 (ko) | 2022-04-08 |
TN2020000029A1 (en) | 2021-10-04 |
EP3671100A1 (en) | 2020-06-24 |
PH12020500287A1 (en) | 2021-01-11 |
EP3671100A4 (en) | 2021-03-10 |
SG11202000836PA (en) | 2020-03-30 |
MA48321B1 (fr) | 2021-03-31 |
BR112019027723A2 (pt) | 2020-09-15 |
RU2736531C1 (ru) | 2020-11-17 |
AU2023216798A1 (en) | 2023-09-07 |
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