Multi-section expansion type automobile carrier orientator for cluster launching of small missiles

Abstract

The utility model discloses a multi-section expansion type automobile carrier orientator for cluster launching of small missiles, which comprises an orientator main body, the orientator main body comprises a bearing tube, support constraint bases are arranged at the bottom and in the middle of the bearing tube, an upper side support is rotatably arranged at the top of each support constraint base, and a lower side support is rotatably arranged at the bottom of each support constraint base. The upper side supports, the transverse side supports and the lower side supports are rotationally connected with the corresponding support restraining bases, and the middles of the upper side supports, the transverse side supports and the lower side supports are connected with bearing pipes through hydraulic pipes. The utility model relates to the technical field of missile launchers, missiles with different purposes can be launched on the same rack, the missiles can be loaded in a mixed mode according to task requirements, the comprehensive and cooperative combat ability of a combat system is improved, the missiles are allowed to point to a target after being lifted to a certain height, and the missile launchers are more convenient to use. And all-directional launching and striking are realized.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the technical field of missile launcher, concretely is a kind of multi-section unfolding formula car carrier directional device for small missile cluster launch. BACKGROUND

[0002] Missile launcher is the special device for aircraft suspension and launch missile, the existing missile launcher mostly adopts the way of oblique launch missile, is composed of pedestal, bracket, directional device and aiming mechanism.The directional device of the existing missile launcher has launch rail, launch cylinder or launch container form, these directional devices can only load the same specification missile, and only face one direction when launching, and the reaction is not very timely for the target on the side and suddenly appearing directly above launch rack. INVENTION CONTENTS

[0003] The utility model is to provide a kind of multi-section unfolding formula car carrier directional device for small missile cluster launch, to solve the problems presented in the above background technique.

[0004] The technical scheme adopted by the utility model is as follows:

[0005] A kind of multi-section unfolding formula car carrier directional device for small missile cluster launch, including directional device main body, the directional device main body includes load-bearing pipe, the load-bearing pipe bottom and middle part are equipped with support constraint base, the support constraint base top is rotatably provided with upper side support, the support constraint base both sides are rotatably provided with horizontal side support, the support constraint base bottom is rotatably provided with lower side support, the upper side support, horizontal side support, lower side support lower end are rotatably connected with its corresponding support constraint base, and the middle part is connected with load-bearing pipe by hydraulic pipe, for control upper side support, horizontal side support, lower side support are retracted.

[0006] Preferably, the support constraint base includes limit pier, the outer side of the limit pier adopts arc structure, and the four sides are provided with rotating groove, and the upper side of the rotating groove is provided with pivot.

[0007] Preferably, the upper side support, horizontal side support, lower side support bottom are equipped with side support bearing, and the pivot sleeve of support constraint base is connected, when side support bearing is rotated to a certain angle along pivot, support bottom is limited by limit pier outer end.

[0008] Preferably, the upper side support adopts L-shaped structure, including hydraulic pipe piston connection side wall and missile mounting plate, the inner side of the missile mounting plate is equipped with missile mounting slide rail, and the side of the hydraulic pipe piston connection side wall away from the missile mounting plate is close to load-bearing pipe.

[0009] Preferably, the lateral side support adopts an L-shaped structure, comprising a hydraulic pipe piston connecting side wall and a missile mounting plate, the inside of the missile mounting plate is provided with a missile mounting slide rail, and the outside of the hydraulic pipe piston connecting side wall is arranged close to the load bearing pipe.

[0010] Preferably, the lower side support comprises a hydraulic pipe piston connecting side wall, the outside of the hydraulic pipe piston connecting side wall is provided with a missile mounting slide rail, and the inside of the hydraulic pipe piston connecting side wall is arranged close to the load bearing pipe.

[0011] Preferably, the hydraulic pipe comprises a hydraulic pipe cylinder and a hydraulic pipe piston, the hydraulic pipe cylinder is rotationally connected with the load bearing pipe through a hydraulic pipe cylinder hinge fastener, the hydraulic pipe piston is rotationally connected with the corresponding support through a hydraulic pipe piston hinge fastener, and an oval hole is formed in the side wall of the load bearing pipe.

[0012] Preferably, the top of the load bearing pipe is provided with a top load.

[0013] As described above, due to the adoption of the above technical solutions, the present application has the following beneficial effects:

[0014] In the present application, different missiles can be launched in a shared frame, the missiles can be mixed and loaded according to task requirements, the comprehensive and cooperative combat capability of the combat system is improved, meanwhile, the missiles are allowed to be aimed at targets after being lifted to a certain height, the problem of blind area in the traditional launching mode is effectively avoided, omnidirectional launching and attack are realized, the same series of launching devices can be assembled into different forms according to the use requirements, the reliability of the system is improved, and the maintenance workload is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 is a state diagram when the launcher orientation device of the present application is lifted;

[0016] Figure 2 is a state diagram when the lateral side support of the launcher orientation device of the present application is completely unfolded under the pushing of the hydraulic pipe piston;

[0017] Figure 3 is a main structure schematic diagram of the lateral side support of the present application;

[0018] Figure 4 is a back structure schematic diagram of the lateral side support of the present application;

[0019] Figure 5 is a main structure schematic diagram of the lower side support of the present application;

[0020] Figure 6 is a side schematic diagram of the lower side support of the present application;

[0021] Figure 7 is a schematic view of the main structure of the upper side support of the utility model;

[0022] Figure 8 is a schematic view of the support constraint base of the utility model;

[0023] Figure 9 is a schematic view of the second section support constraint base on the load-bearing tube of the utility model;

[0024] Figure 10 is a sectional view of the side support closely adhering to the load-bearing tube of the directional device of the utility model;

[0025] Figure 11 is a schematic view of the arrangement of the hydraulic tube observed from the inside of the load-bearing tube of the utility model;

[0026] Figure 12 is a sectional view of the load-bearing tube when the side support is unfolded of the utility model;

[0027] Figure 13 is a schematic view of the safety state of the directional device installed on the automobile carrier of the utility model;

[0028] Figure 14 is a schematic view of the safety state of the directional device connected with the launching rack and hanging the sample missile on the side support of the utility model;

[0029] Figure 15 is a schematic view of the overall installation of the directional device of the utility model;

[0030] Figure 16 is a schematic view of the unfolded style of the directional device of the utility model;

[0031] Figure 17 is a schematic view of the unfolded style of the directional device of the utility model;

[0032] In the figure: 1, directional device main body; 2, support constraint base; 3, upper side support; 4, horizontal side support; 5, lower side support, 6, top load; 7, hydraulic tube piston; 8, oval hole; 9, missile hanging slide rail; 10, hydraulic tube piston connecting side wall; 11, side support bearing; 12, pivot; 13, limit pier; 14, load-bearing tube; 15, hydraulic tube; 16, hydraulic tube cylinder; 18, hydraulic tube cylinder hinge fastener; 19, oval hole; 20, hydraulic tube piston hinge fastener; 21, step; 22, sample missile; 23, launching rack. DETAILED DESCRIPTION

[0033] The specific implementation of the utility model is described in detail below.

[0034] The range is limited in the form of a lower limit and an upper limit, and the given range is limited by selecting a lower limit and an upper limit, and the selected lower limit and upper limit limit the boundary of the specific range. The range limited in this way can include end values or not include end values, and can be arbitrarily combined, that is, any lower limit can be combined with any upper limit to form a range. For example, if a range of 10-50 is listed for a specific parameter, it is understood that the ranges of 10-40 and 20-50 are also expected. In addition, if the minimum range values 1 and 2 are listed, and if the maximum range values 3, 4 and 5 are listed, the following ranges can all be expected: 1-3, 1-4, 1-5, 2-3, 2-4 and 2-5. In this application, unless otherwise stated, the range of values "a-b" represents a shorthand representation of any real number combination between a and b, where a and b are both real numbers. For example, the value range "0-5" indicates that all real numbers between "0-5" have been listed in this document, and "0-5" is only a shorthand representation of these value combinations.

[0035] Unless otherwise specified, all embodiments and optional embodiments of the present application can be combined with each other to form new technical solutions.

[0036] Unless otherwise specified, all technical features and optional technical features of the present application can be combined with each other to form new technical solutions.

[0037] Unless otherwise specified, all steps of the present application can be performed in sequence or randomly, and preferably in sequence. For example, the method comprises steps (a) and (b), which means that the method can comprise steps (a) and (b) in sequence, or steps (b) and (a) in sequence. For example, the method also comprises step (c), which means that step (c) can be added to the method in any order, for example, the method can comprise steps (a), (b) and (c), or steps (a), (c) and (b), or steps (c), (a) and (b), etc.

[0038] Unless otherwise specified, the "includes" and "contains" mentioned in the present application mean open-ended, and can also be closed. For example, the "includes" and "contains" can mean that other components not listed can also be included or contained, or only the listed components can be included or contained.

[0039] Unless otherwise specified, the reaction is carried out under normal temperature and pressure conditions.

[0040] Unless otherwise specified, all parts or percentages are weight parts or weight percentages.

[0041] In the utility model, the used substances are all known substances, which can be purchased or synthesized by known methods.

[0042] In the utility model, the used devices or equipment are all conventional devices or equipment known in the field, which can be purchased.

[0043] In order to make the utility model purposes, technical scheme and advantages more clearly, the following will be combined with the drawings and examples, and the utility model will be further described in detail. It should be understood that the specific examples described here are only used to explain the utility model, and are not used to limit the utility model.

[0044] Embodiment:

[0045] A kind of for small missile cluster launch's multi-section unfolding type automobile carrier director, as shown in Figures 1-17 The director main body 1 includes load-bearing tube 14, the bottom and middle part of load-bearing tube 14 are equipped with support constraint base 2, the top of support constraint base 2 is rotatably provided with upper side support 3, the both sides of support constraint base 2 are rotatably provided with horizontal side support 4, the bottom of support constraint base 2 is rotatably provided with lower side support 5, the lower end of upper side support 3, horizontal side support 4 and lower side support 5 is rotatably connected with its corresponding support constraint base 2, and the middle part is connected with load-bearing tube 14 by hydraulic pipe 15, for controlling the expansion of upper side support 3, horizontal side support 4 and lower side support 5.

[0046] In a possible implementation, the support constraint base 2 includes a limiting block 13, the outer side of the limiting block 13 adopts an arc structure, and a rotating groove is formed in each of the four sides of the limiting block 13, and a pivot 12 is arranged on the upper side of the rotating groove.

[0047] In a possible implementation, the bottom of the upper side support 3, the horizontal side support 4 and the lower side support 5 is provided with a side support bearing 11, which is sleeved with the pivot 12 of the support constraint base 2, and when the side support bearing 11 is rotated to a certain angle along the pivot 12, the bottom of the support is limited by the outer end of the limiting block 13.

[0048] In a possible implementation, the upper side support 3 adopts an L-shaped structure, includes a hydraulic pipe piston connecting side wall 10 and a missile mounting plate, the inner side of the missile mounting plate is provided with a missile mounting slide rail 9, and the side of the hydraulic pipe piston connecting side wall 10 away from the missile mounting plate is arranged close to the load-bearing tube 14.

[0049] In a possible implementation, the horizontal side support 4 adopts an L-shaped structure, includes a hydraulic pipe piston connecting side wall 10 and a missile mounting plate, the inner side of the missile mounting plate is provided with a missile mounting slide rail 9, and the outer side of the hydraulic pipe piston connecting side wall 10 is arranged close to the load-bearing tube 14.

[0050] In a possible implementation, the lower side bracket 5 comprises a hydraulic tube piston connection side wall 10, the outer side of which is provided with a missile mounting slide rail 9, and the inner side of which is arranged close to the load-bearing tube 14.

[0051] In a possible implementation, the hydraulic tube 15 comprises a hydraulic tube cylinder 16 and a hydraulic tube piston 7, the hydraulic tube cylinder 16 is rotationally connected with the load-bearing tube 14 through a hydraulic tube cylinder hinge fastener 18, and the hydraulic tube piston 7 is rotationally connected with its corresponding bracket through a hydraulic tube piston hinge fastener 20, and an oval hole 19 is formed in the side wall of the load-bearing tube 14.

[0052] In a possible implementation, the top load 6 is arranged on the top of the load-bearing tube 14.

[0053] In a possible implementation, the number of nodes of the director body 1 can be determined by the carrying capacity of the vehicle.

[0054] In a possible implementation, a single-node director is composed of a load-bearing tube 14, accessories, a bracket-constrained base 2, and a top load 6, wherein the accessories mainly include a hydraulic tube 15 and a side bracket, a missile is mounted on the side bracket, and the hydraulic tube 15 comprises a cylinder and a piston.

[0055] Among them, the main function of the load-bearing tube 14 is to bear the accessories, the end of the hydraulic tube cylinder is fixed on the load-bearing tube, the piston is connected with the side bracket through a fastener, and the side bracket can rotate around the bracket-constrained base, and the rotation power comes from the hydraulic tube piston.

[0056] Further, the load-bearing tube 14 is a hollow metal tube with a rectangular cross section, so four side brackets can be placed on the side. According to the direction of movement and the direction of gravity, the cross section of the side bracket is different, but there is a slide rail for the missile to be mounted and launched.

[0057] Further, when the side bracket is pushed by the hydraulic tube 15, the hydraulic tube 15 will rotate around the fixed end, the side wall of the load-bearing tube 14 is provided with an oval opening, and the hydraulic tube itself is a solid body, which is designed to prevent collision and stagger.

[0058] Further, the top load 6 is used to support the director in the non-working state to prevent long-term deformation of the director.

[0059] In a possible implementation, as shown in Figure 13 , the safety state of the director installed on the vehicle carrier, eight side brackets each mount a sample missile 22, and the top load 6 is pressed on a step 21;

[0060] Further, as shown in Figure 14As shown, the hidden car carrier rear and launcher 23 connected to the side bracket mounted on the example missile 22 orientation safety state;

[0061] Further, as Figure 15 As shown, when the target is found, the launcher 23 slowly rises with the help of other hydraulic equipment, tilted at an angle.

[0062] Further, the hydraulic tube 16 pushes the hydraulic tube piston 7, and since the piston is connected to the hydraulic tube piston fastener 20 fixed on the upper side bracket 3, the horizontal side bracket 4, and the lower side bracket 5 through the hinge, the upper side bracket 3, the horizontal side bracket 4, and the lower side bracket 5 are pushed by the piston 20 to form an unfolded style, as shown. Figure 16 As shown, the missile begins to enter the standby state, as shown. Figure 17

[0063] By adopting the above technical scheme:

[0064] The present application has the following advantages:

[0065] 1. Improve combat capability: different purpose missiles realize common launcher, and can be mixed according to the task demand, improve the comprehensive and cooperative combat capability of the combat system.

[0066] 2. All-round launch: allows the missile to point to the target after rising to a certain height, effectively avoids the blind area problem of the traditional launch mode, and realizes all-round launch.

[0067] 3. Facilitate modularization and generalization design: according to the different functions, it is divided into several standard modules, and the same series is assembled into different forms according to the use demand, which improves the reliability of the system and reduces the maintenance workload.

[0068] 4. Increase the missile orientation range: the movable range of the side bracket in the launcher similar to the flower blooming type can make up for the limited orientation range of the orientation device, thereby reducing the requirement for the carrying tool.

[0069] The above is only a preferred embodiment of the present application, and does not limit the present application, and any modification, equivalent replacement and improvement made within the spirit and principle of the present application shall be included in the protection scope of the present application.​

Claims

1. A multi-section deployable vehicle-mounted launcher for launching small missile clusters, characterized in that: The device includes a main body (1), which includes a load-bearing tube (14). The load-bearing tube (14) has a support constraint base (2) at its bottom and middle. The support constraint base (2) has an upper side support (3) rotatably mounted on its top. The support constraint base (2) has a horizontal side support (4) rotatably mounted on both sides. The support constraint base (2) has a lower side support (5) rotatably mounted on its bottom. The lower ends of the upper side support (3), the horizontal side support (4), and the lower side support (5) are rotatably connected to their corresponding support constraint base (2). The middle part of the support is connected to the load-bearing tube (14) through a hydraulic pipe (15) to control the opening and closing of the upper side support (3), the horizontal side support (4), and the lower side support (5).

2. The multi-section deployable vehicle-mounted launcher for launching small missile clusters as described in claim 1, characterized in that: The bracket constraint base (2) includes a limiting block (13). The outer side of the limiting block (13) adopts an arc-shaped structure, and a rotating groove is provided on all four sides. A pivot (12) is provided on the upper side of the rotating groove.

3. The multi-section deployable vehicle-mounted launcher for small missile cluster launch as described in claim 2, characterized in that: The bottom of the upper side bracket (3), the horizontal side bracket (4), and the lower side bracket (5) are all provided with side bracket bearings (11), which are sleeved with the pivot (12) of the bracket constraint base (2). When the side bracket bearing (11) rotates along the pivot (12) to a certain angle, the bottom of the bracket is limited by the outer end of the limiting block (13).

4. A multi-section deployable vehicle-mounted launcher for launching small missile clusters as described in claim 2, characterized in that: The upper side support (3) adopts an L-shaped structure, including a hydraulic pipe piston connecting side wall (10) and a missile mounting plate. The missile mounting plate is provided with a missile mounting slide rail (9) on its inner side. The side of the hydraulic pipe piston connecting side wall (10) away from the missile mounting plate is located close to the load-bearing pipe (14).

5. A multi-section deployable vehicle-mounted launcher for launching small missile clusters as described in claim 2, characterized in that: The transverse side support (4) adopts an L-shaped structure, including a hydraulic pipe piston connecting side wall (10) and a missile mounting plate. The inner side of the missile mounting plate is provided with a missile mounting slide rail (9), and the outer side of the hydraulic pipe piston connecting side wall (10) is located near the load-bearing pipe (14).

6. A multi-section deployable vehicle-mounted launcher for launching small missile clusters as described in claim 2, characterized in that: The lower side support (5) includes a hydraulic pipe piston connection sidewall (10), and a missile mounting rail (9) is provided on the outer side of the hydraulic pipe piston connection sidewall (10), and the inner side of the hydraulic pipe piston connection sidewall (10) is located close to the load-bearing pipe (14).

7. A multi-section deployable vehicle-mounted launcher for launching small missile clusters as described in claim 1, characterized in that: The hydraulic pipe (15) includes a hydraulic pipe cylinder (16) and a hydraulic pipe piston (7). The hydraulic pipe cylinder (16) is rotatably connected to the load-bearing pipe (14) through a hydraulic pipe cylinder hinge fastener (18). The hydraulic pipe piston (7) is rotatably connected to its corresponding bracket through a hydraulic pipe piston hinge fastener (20). An elliptical hole (19) is provided on the side wall of the load-bearing pipe (14).

8. A multi-section deployable vehicle-mounted launcher for launching small missile clusters as described in claim 1, characterized in that: The top of the load-bearing pipe (14) is provided with a top weight (6).

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