SA520411761B1 - Rocket launch model and rocket launch vehicle - Google Patents

Abstract

The present invention relates to a rocket launching module comprising a base frame (1) comprising at least one rail (2a); a sliding table (3) configured to slide substantially vertically on said rail (2a) when driven by at least one electric linear actuator (11), and a targeting device (4) comprising a turntable (5) on which a pivotable body (6) is mounted, supporting a rocket support portion (7). The sliding table (3) comprises a platform (8) configured to receive the turntable (5) of the targeting device (4). fig 8

Description

ROCKET LAUNCH MODEL AND ROCKET LAUNCH VEHICLE Full Description

Invention background

The present invention relates to a modular missile launch unit that can be operated separately or that can be installed on

vehicle body.

Cajal Various artillery equipment for transporting artillery in the field. For land use; includes

5 Most Popular Solution on Jie Vehicles Tanks, 4*4s and Trucks

combat.

launch equipment. The device includes a box-like structure with missile receiver cylinders.

The housing shall be axial between a position in which the cylinders have a longitudinal geometric axis parallel to the plane of the 0 support surface and a position in which the lower surface of the housing structure is at an acute or right angle to a surface

bracing” with the axle generally arranged near the rear end of the vehicle.

Therefore, according to the type and weight of the weapons used; The box body and the device must be set aaa

The hinge to support the weight of the pivot structure and the missiles to be launched. stereotyped; The greater the weight

missiles are higher; The amount that could be packed into the box body was smaller. For heavy weapons; like missiles; The box-like structure is generally smaller in size; And you will understand who

Two to four missiles at the same time.

The weight of the weapons affects both the capacity of the box-like structure and the structure of the pivot hinge system.

Since the handling of weapons must be done with a large margin of safety, the system must be

aly Ugh the pivot joint

Another disadvantage associated with launching equipment is the need for a vehicle that is completely dedicated to the launch as the vehicle must be modified to incorporate the pivot hinge system and to form a flat support surface. In addition to the cade issues, there are also known firing equipment limitations related to the J-guidance of ¢ weapons as the box-shaped Jeg has limited movement of the pivot joint. There are some solutions in the technical field to provide greater flexibility for launching equipment.

EP document No. 1,739,382 shows 4,338 projectiles comprising a vehicle with a coaxial launch platform with several launch hulls arranged side by side. European patent document No. 2 754 989 presents a missile launch container that is received by a device with a side guidance part and a vertical guidance part.

Japanese patent document No. 056997/2003 describes a rocket launcher that allows more freedom in adjusting the launch angle. The adjustment system includes a pneumatic system with pivoting arms. US Patent No. 0282150/2010 discloses Lge hall janie specifically for use on ships. The ramp has a collapsible structure where the shell supports are attached. The foldable structure includes; on articulated arms.

5 US Patent No. 3,316,809 shows a retractable rocket launcher for an armored vehicle. A shell containing the shells is mounted on a ring protected by a track offset system and a rack and gear system is used to shrink the shell. US Patent No. 79001367 describes a system for propelling arms in a support cage; A mobile platform that holds a retractable Big Weapon that covers the weapon.

0 day EP No. 969 612 612 describes an all-terrain vehicle with a pivot chassis on a “Jagat” platform in which the chassis pivots between a transport position and an operating position.

With cell these known solutions fail; In providing the resistance needed to support a projectile or artillery assembly

of the missile type or incorporating extremely complex structures; And require the use of systems out

Several mechanical arms that are hydraulically or pneumatically actuated.

And therefore; There is a need in the field for a solution that allows for stable, robust, yet simple missile launches

It allowed the use of a stand-alone or vehicle-mounted module model.

The present invention is intended to provide a fixed modular missile launch unit; And powerful and versatile.

The present invention also aims to provide a modular missile launch unit that can be operated separately or

It can be installed on the vehicle body.

The present invention also aims to provide a modular missile launch unit with a protected design when arranged in a towed design in a vehicle body.

The present invention also aims to provide a modular missile launch unit that is towed and guided

Its movement is by electric actuators.

General description of the invention

The present invention achieves the above objectives by means of a modular missile launch unit comprising 5 base frame comprising at least one rail; Sliding table designed to slide vertically

large on said rod when pushed by at least one electric ad actuator; aig installation

A targeting device comprising a rotating table with a pivoting body to support a gla missile. include

The sliding table is on a platform designed to receive the rotating table of the aiming device.

preferred; The frame of the base includes a frame in the form of a rectangular pediment; Each of the four columns is defined by a rod; The sliding table includes a support structure to support the flat platform to the platform

to a big limit; The sliding table support structure includes several lugs designed to slide into rails

the frame; The sliding table of the substantially flat platform has a slot that receives the table

Rotary aiming device.

to provide a stable displacement of the sliding table; The module also includes two linear actuators arranged at opposite ends of the frame where the actuators are driven by an eS motor and connected to the sliding table by a transition piece. preferentially The body of the pivot aiming device shall be designed so that the position of its pivot is in line with the axial motion of the rotary table and the pivot motion of the pivot body is driven preferably by the module may include an external cage that can be used for transportation or; when supplied with a stand; Allows the module to run independently.

0 The present invention also describes a missile launch vehicle comprising a body with an upper hatch that can be selectively opened or closed and the launch module of the present invention; so that when the upper opening of the body is closed; The sliding table is pulled out from the frame; When opening the upper body hatch; The sliding table slides vertically on the frame rails to an extended position in which the J targeting device is exposed outside the body of the vehicle.

BRIEF EXPLANATION OF THE DRAWINGS Figure 1 is a frontal view of a firing module according to an embodiment of the present invention; The module is illustrated in a drawn design; Figure 2 is a perspective projection of the rear portion of a firing module according to an embodiment of J of the present invention ¢ The design shown for the module is the towed design ¢

Fig. 3 is a perspective projection of a firing module housing according to one of the z alas of the present invention ¢ Figure 4 is a perspective internal gall projection of a firing module housing Wy of an embodiment of the present invention;

Fig. 5 is an upper and lower perspective view of a modular space firing unit according to an embodiment of the present invention; Fig. 6 Ble is of a perspective view of the forward part of a firing module according to an embodiment of the present invention; The module design is illustrated in a towed design with modular missile receiver pods; Fig. 7 is a rear view galll projection from a firing module according to an embodiment of the present invention; The module design is illustrated in a drawn-out design with modular missile receiver pods; Figure 8 is a perspective view of a firing module according to an embodiment of the present invention; 0 Module design is demonstrated in an extended layout with modular missile receiver pods; Figure 9 is a second perspective view of a firing module according to an embodiment of the present invention; Module design is articulated in an extended layout with modular missile receiver pods; Fig. 10 is a schematic projection showing the main components of a firing module linear actuator according to an embodiment of the present invention; 5 Fig. 11 is a perspective view of a firing module according to a second embodiment of the present invention; The module is illustrated in an extended design; Fig. 12 is a side view of the firing module according to the second embodiment of the invention (Ja) The module is shown in an extended design with ein firing hinge; Fig. 13 is a perspective view of a firing module according to the second embodiment of the present invention; The module is illustrated in the drawn design; Fig. 14 is a perspective projection of the frame base of the firing module according to a second embodiment of the present invention;

Fig. 15 is a perspective projection of a sliding launch platform module according to the second model of

the present invention;

Figure 16 is a perspective view of the firing module's sliding table according to a second embodiment

of the present invention;

Figure 17 is a perspective projection of the firing module target device according to a second embodiment

of the present invention;

Figure 18 is an external perspective [abd] projection of the firing module according to one of z ala

the present invention; And

Figure 19 is a perspective projection of the external shear Bas ol a firing modular according to one of the z ala of the present invention; receives abel) a support post.

Detailed description:

The present invention is described herein based on two embodiments of the invention described in

Figures 1 to 19.

The J of Figures 1 and 2 shows a front viewfinder and a rear viewfinder of the firing module according to 5 of the preferred embodiment of the present invention.

The launch module includes a base frame 1 and a platform 3 that is designed to slide fairly vertically.

on the rails of the base frame 1.

The base frame 1 preferably comprises a frame in the form of a rectangle with four columns 2 arranged at

corners of the rectangular shape. forms part of the inner surface of each column—i.e.; Part of the surface of each column facing in the frame- Rod 2a.

The sliding table 3 is designed to accommodate the aiming device 4. Therefore; In the preferred embodiment of the invention (rain gall) the sliding table 3 comprises an opening for receiving the rotating table of the aiming device 4. Preferably; the sliding table 3 comprises a substantially flat platform 8 (with hole) and a support structure 9 in which the support structure 9 includes GUST designed to attach the rails 2a of the base frame. In a ume (ume) shape the base frame has 8 brackets; two spaced, aligned shoulders are arranged to match each rail 2a. With this design in frame 1 and sliding table 3 the base can be safely and securely Stationary The flat 0 platform moves you to support the aiming device 4 vertically + where the platform is slidably supported on the 4 columns 2 of the base frame 1. A linear actuator 11 driven by an electric motor 12 preferentially achieves the more or less vertical displacement of the sliding table 3. In the unit Typically shown in Figures 1, 2 and 6 to 9; two linear actuators 11 are provided that are actuated by a single electric motor 12. 5 as shown in Figures » preferably the linear actuators are arranged at opposite ends of the frame 1 so that the vertical movement of the sliding table 3 is carried out in a consistent manner. The connection between each actuator 11 and the sliding table is formed by a related transition piece 13 connected to the table. The upper (ial) of each actuator 11 is attached to frame 1 by means of a fixture 14 connected to the upper beam 15 of frame 1. The lower part of each actuator 11 is attached to the frame by means of a fitting 0-lower 16. As is best illustrated in Figures 8 and 9; Targeting means 4 preferably includes a turntable 5 SH gle pivot body 6 to support ga missile support 7.

The pivot body 6 is preferably designed so that the position of the pivot axis corresponds to the center of mass/

It contains the support section 7 that receives the modular missile chamber.

Preferably ¢ the axial movement of the rotary table 5 and the axial movement of the pivot body 6 are driven

by an electric actuator which can; For example; Connect it to the bottom side of the flat platform 8 of the sliding table 3.

The gga 7 reinforcement preferably includes a substantially flat upper oda on which a chamber is supported.

The missile module and installed.

Figures 3 to 5 show a typical M-rocket chamber that is attached to a support part 7 means

4. Targeting

0 as can be seen from these figures; A modular housing comprises an outer fascia 20 in which a positioner 12 is arranged. Figure 5 shows two upper (a) and lower (b) sights of the positioner. The outer fascia may include streamlined surfaces 22 in the form of longitudinal shoulders. In the preferred z embodiment of 1 of the present invention “the outer fascia 8 receives a position adjusting device 4 in

5 on the upper wall and 4 on the lower wall.

the inner part is formed; shown in Figure 4 where the housing is shown without a roll 20; By many tubes 23 with tires 24 act as struts and spacers. The tubes act as a missile receiver. In the model shown in the figures, each modular chamber includes 16 tubes that receive a missile.

0 With this ddl Ji can easily store and store modules. in addition to; Installing and replacing the M chambers in the Sls launch module is quick and safe.

— 0 1 — as shown in Figures 6 and 7) Support 7 of the launch module 4 targeting means gia can receive more than one modular missile pod (in the figure, module 3 receives module pods). Figures 8 and 9 show the launch module In an extended design, that is, after sliding the sliding table 3 on the rails 2 in the columns of the frame 2.

As can be seen from these figures; With this design the modular chambers of can be oriented by rotary table orientation 5 and pivot body 6 orientation axially. Whereas the positioning of the pivot body axis 6 with the center of gravity on the basis of gia support 7 corresponds to the modular compartments M; Electrical operation of aiming device 4 is possible; Which reduces the weight of the assembly and eliminates the use of operating systems

0 hydraulic and pneumatic. Figure 9 shows a preferred embodiment of a linear actuator 11 according to the present invention. in the preferred form; A linear actuator includes the following elements: (a) an object; (b) cover; (c) male connector; (d) flange; (e) 3 spacers (f) flange-to-body connection 3 (g) cylinder-rod connection with ¢ connector (ii) body-compassion gasket; (i) bushing; (j) cylinder-rod; (k) tube stator and (l) orbital roller mounting; Figures 11 to 17 show a second embodiment of the launching module of the present invention.In this embodiment the launch module receives a set of receiver tubes for a missile or an F-missile.Figs 11 and 1 and 2 show a perspective and side projection of the launching module according to the second embodiment of the present invention; Illustration of the module in the extended design Figure 13 illustrates

0 Perspective projection of the ag module of the second embodiment of the invention all in a drawn design. Similar characteristics to the first model are represented by the same reference numbers. So » The launch module includes a base frame 1 and a table 3 designed to slide largely vertical on the rails of the base frame 1.

— 1 1 —

WS is better illustrated in Figure 14; The base frame 1 preferably comprises a frame in rectangular form with four columns 2 arranged at the corners of the rectangular shape. gia forms from the inner surface of each column- ie 3 ey from the surface of each column facing in the frame _ rod 2 . The sliding table 3 is designed to receive the aiming device 4.

5 therefore; In the form shown in Figure 16; The sliding table 3 includes a slot 13 for receiving the rotating table of the aiming device 4. Also as shown in Fig. 6; The sliding table 3 includes a substantially flat platform 8 Jam a hole 13 and a support structure 9. The support structure 9 includes lugs 10 designed day) bars 12 the base frame. in this form;

0 Base frame has 8 shoulders 0 Two spaced shoulders aligned to match each rod 2a are arranged. Having this design in frame 1 and sliding table 3; The flat platform can be moved to support the aiming device 4 securely and stably. The clad platform is slidably supported on the four columns 2 of the base frame 1.

5 The vertical displacement is largely achieved of the sliding table 3 by a linear actuator 110; It is driven by an electric motor 120 (electric piston shown schematically in the figures). Subsequently; As illustrated best in Figures 11; 13, 15; The firing module preferably includes two linear actuators 110 driven by two electric motors 120.

As shown in the figure; Preferably linear actuators are arranged at opposite ends

0 for frame 1; So that the vertical movement of the sliding table 3 is stable. The connection between each actuator 0 and the sliding table is made by a related transition piece 13 connected to the table.

— 1 2 —

The upper part of each actuator 110 is fixed to the frame 1 by means of a fixture 14 connected to a girder

Upper 15 of the frame 1. The lower part of each actuator 110 is fixed to the frame by means of a lower fitting.

16

As illustrated better in Figure 17; Targeting device 4 preferably includes a table

Rotary 5 on which a pivot body 6 is installed to support the ga support of the missile 7.

The axial body 6 is preferably designed so that the position of the axial axis 17 coincides with the center of the

Mass/weight of the support part 7 that receives the missile that receives the F assembly.

Preferably ¢ the axial movement of the rotary table 5 and the axial movement of the pivot body 6 are driven

by means of an electric starter Sa connected to it; For example; On the bottom side of the flat platform 8 0 of the sliding table 3.

The bracing gia 7 preferably includes a flat top gia to as large as bracing

The F assembly that receives a missile and installs it.

As shown in Figure 18; The launch module may also include a cage

ext 18; It can arrange frame/sliding table/target assembly and drive device for transportation. 5 The upper part of the outer cage 18 shall be preferably open to allow the passage of the assembly.

As shown in Figure 19; The brace 19 can be attached to the cage 18. Thus; maybe

Use cage 18 as a supporting structure for the module.

In this regard; It should be noted that the firing module of the present invention; with triggers

Baha's electric vehicle can operate completely autonomously in any vehicle. Subsequently; 0 cage 18 can act as a chassis in the independent operation state.

Instead of that; The firing module of the present invention can be installed in a vehicle; even it's happen

Connecting the frame 1 to the vehicle's internal structure.

— 1 3 —

The firing module of the present invention provides a compact solution; Safe and stable to launch the rocket

(preferably 70 mm rockets).

As shown in Figures 11 and 12; When the sliding table 3 is in an extended design

for frame 1; The aiming device 4 can be rotated and the support surface 7 can be pivoted to adjust both direction and angle of launch.

On the other hand; As shown in Figure 3; When the sliding table 3 is present in the design

withdrawn»; The assembly becomes very compact. Thus » the module can be installed in a configured vehicle

4 so that the module is fully inside the vehicle when pulled (Sag) extended through a slot

It is projected onto the roof of a vehicle (if the targeting device 4 is outside the body of the vehicle).

0 In addition as the sliding table 3 slides on the rails 2 in the frame columns 2 the flat platform 8 with aiming device 4 can be safely and stably moved vertically by linear actuator operation without tilt hazards (png) the need for hydraulic or pneumatic actuating systems; which reduce In the end, the risk of failure, taking into account the operating conditions in sand or gravel in particular dag, ensures the use of the rotary table 5 and the positioning of the axial shaft 17 of the axial body 6 as well

5 Possibility of electrical operation of the aiming device 4; which reduces the weight of the assembly and eliminates the use of hydraulic or pneumatic operating systems. After describing two examples which are a preferred embodiment of the present invention, it should be recognized that the scope of the present invention includes various other possible forms of the inventive concept described herein; That is, it is limited only to the terminology of the Claims; Including possible equivalents.

Claims (8)

protection elements 1. A missile launch module; Comprises: (1) base frame comprising at least one rail (12) a sliding table (3) designed to slide substantially vertical on said rail (12) when pushed here by at least one electric linear actuator (11); and Target (4) comprising a rotating table (5) on which a pivot body (6) is mounted to support ei a missile (7); Cua sliding table (3) comprising one substantially flat platform (8) designed to receive Rotary table (5) of aiming device (4). 0 2. A missile launch module of claim 1; where: the base frame (1) includes a rectangular frame with four columns (2)» each of the columns (das) defines a rod (2a); The sliding table (3) includes a support structure (19) to support the largely flat platform (8); the support frame (9) of the sliding table (3) has several lugs (10) designed to slide into the 5 rails (2a) of the frame ( 1); the substantially flat platform (8) of the sliding table includes a slot (13) that receives the rotating table (5) of the aiming device (4). 3. A missile launch module of claim 2; It also includes two 0 linear actuators (11) arranged at opposite ends of the frame (1). 4 a missile launch module in accordance with claim No. 3; The actuators (11) are driven by an electric motor (12). — 5 1 — 5. A module for launching a missile according to claim No. 3) where each launcher (110) is driven by an electric motor (120) and connected to the sliding table (3) by means of a transition piece (13). 6. A missile launch module of claim 1; The load includes at least one modular missile receiver unit (M) designed to be attached to the missile support part (7). 7. A missile launch module of claim No. 6 comprising 3 missile receiver units (/a); The three units are for receiving missiles (M) that can be linked together (gia) supporting the missile (7). 8. Module for launching a missile in accordance with Claim 6) in which the pivot body (6) of the targeting device (4) is designed such that the position and its pivot axis (17) correspond to the center of mass gy reinforcement (7) of the missile receiver units (M ) 5 1 9 A missile launch module of claim 8 in which the axial movement of the rotary table (5) and the axial movement of the pivot body (6) are driven by an electric actuator. 0. A missile launch module of claim 1; Also includes an outdoor cage (18). 0 11. Module for launching a missile according to claim No. 10) The load includes a stand (19) for a separate support independent of the outer cage (8 1). or close it; and 5 a module in accordance with any of claims 1 through 9, wherein: — 6 1 — Sliding table (3) placed in a position retracted relative to the frame (1) ¢ at aod the opening of the upper body; the sliding table (3) slides vertically on the rails (12) of the frame (1) to an extended position; It detects the targeting device (4) outside the body of the vehicle when the hatch of the upper part of the body is open. RN 8 gt B a Ho BUR b a l hi i oo Cos Fr RS Be. ¥ I So =, RR FE ra FE RQ. 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