CN219279236U - Missile lifting appliance loading tool for test - Google Patents
Missile lifting appliance loading tool for test Download PDFInfo
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- CN219279236U CN219279236U CN202320810325.0U CN202320810325U CN219279236U CN 219279236 U CN219279236 U CN 219279236U CN 202320810325 U CN202320810325 U CN 202320810325U CN 219279236 U CN219279236 U CN 219279236U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The utility model relates to a missile sling loading tool for a test. Comprises a frame structure which is a cuboid structure; the front mounting vertical frame, the middle mounting vertical frame and the rear mounting vertical frame are symmetrically arranged about the middle mounting vertical frame; the device also comprises a plurality of counterweight support rods fixedly connected between two adjacent installation vertical frames, and each counterweight support rod extends along the length direction of the frame structure; the front double-hole lifting lug unit and the rear double-hole lifting lug unit are fixedly connected with the frame structure and are symmetrically arranged about the central line of the frame structure; and a weight column structure mounted at the bottom of the frame structure. The method can test the vertical load of the missile sling, check the fatigue life of the missile sling, and provide reliable test data for structural optimization of the missile sling in time.
Description
Technical Field
The utility model belongs to the technical field of load test equipment, and particularly relates to a missile sling loading tool for a test.
Background
Missiles (missiles) are aircraft which carry warheads, are propelled by self-powered devices, are guided by a guidance system to control a flight path, guide a target and destroy the target. The missile can be expanded into a case missile, a barrel missile or a missile packaging module. In the military and aerospace fields, a missile is often required to be hoisted by using a lifting appliance to realize the transportation or installation of products, so that the missile lifting appliance is an essential hoisting tool in the missile transportation and hoisting process, and after taking materials, the missile lifting appliance starts to have a vertical or vertical and horizontal working stroke, and after reaching a destination, the missile lifting appliance unloads, and then the missile lifting appliance has an idle stroke to a material taking place to complete a working cycle, and then carries out second hoisting. Generally, missile slings for cartridges are often horizontally hoisted slings.
In the actual working process, the missile sling for hoisting the cylindrical shell mainly comprises a cross beam, wherein a steel wire rope connecting piece is arranged on the cross beam, the steel wire rope connecting piece is hung on a lifting hook of a crane through a steel wire rope, at least two lifting pieces are arranged on the cross beam, and the lifting pieces are connected with lifting points on the missile. After the lifting tool is manufactured, in order to improve the safety performance of the lifting tool, the whole lifting tool needs to be subjected to overload test, so that the lifting tool is inspected to have no abnormal conditions such as fracture, loosening and the like in set weight and time, and the welding seam of the cross beam and all bearing parts cannot be cracked, so that the lifting tool is judged to be qualified, or else, the lifting tool is judged to be unqualified.
At present, no load test tool specially aiming at a missile sling exists on the market, the existing load tool of the crane sling mainly comprises a main frame structure, a main lifting ring positioned in the middle and an auxiliary lifting ring surrounding the main lifting ring are arranged above the main frame structure, and a plurality of balancing weights can be placed on the main frame structure. The existing crane sling load tool has the following defects in the missile sling load test process: firstly, the load test tool is simple in structure, the shape of the missile and the mass condition of the missile cannot be simulated, and only the mass center of the load test tool is simply assumed to be located right below a main hanging point; secondly, rings arranged above the main frame structure can not meet the distribution requirement of hanging points of the missile sling. Therefore, the load test of the missile sling cannot be carried out by utilizing the existing crane sling load tool, and the design of the missile sling load tool for test is needed to meet the load test requirement of the missile sling.
Disclosure of Invention
The utility model provides a missile sling loading tool for a test, which is reasonable in structural design and aims to solve the technical problems in the prior art. The utility model can simulate the shape of the missile and the quality condition of the missile, and meets the load test requirement of the missile sling.
The utility model adopts the technical proposal for solving the technical problems in the prior art that: the missile sling loading tool for the test comprises a frame structure, wherein the frame structure is of a cuboid structure; the front mounting vertical frame, the middle mounting vertical frame and the rear mounting vertical frame are symmetrically arranged about the middle mounting vertical frame; the device also comprises a plurality of counterweight support rods fixedly connected between two adjacent installation vertical frames, and each counterweight support rod extends along the length direction of the frame structure; the front double-hole lifting lug unit and the rear double-hole lifting lug unit are fixedly connected with the frame structure and are symmetrically arranged about the central line of the frame structure; and a weight column structure mounted at the bottom of the frame structure.
The utility model has the advantages and positive effects that: the utility model provides a missile sling loading tool for a test, which can simulate the shape and the size of a cylindrical shell lifted by a missile sling by arranging a frame structure with a cuboid structure; the vertical load of the frame structure in the vertical direction is realized through the counterweight column structure arranged on the frame structure, so that the quality condition of the cartridge is simulated, and when the loading tool is hoisted on the missile sling, the load born in the vertical direction in the process of hoisting and transferring the cartridge product of the missile sling can be simulated through the arrangement; through the front double-hole lifting lug unit and the rear double-hole lifting lug unit which are arranged on the top surface of the frame structure, the distribution condition of lifting points of the cylindrical shell can be simulated, and then the loading tool can be lifted on the missile lifting appliance according to the lifting mode of the cylindrical shell on the missile lifting appliance.
Preferably: the frame structure comprises an upper rectangular mounting frame and a lower rectangular mounting frame which are distributed up and down, and a plurality of mounting frame connecting rods which are used for connecting the upper rectangular mounting frame and the lower rectangular mounting frame into a whole are fixedly connected between the upper rectangular mounting frame and the lower rectangular mounting frame; the counterweight column structure is connected with the lower rectangular mounting frame.
Preferably: the front mounting vertical frame, the middle mounting vertical frame and the rear mounting vertical frame are all arranged between the upper rectangular mounting frame and the lower rectangular mounting frame and are fixedly connected with the upper rectangular mounting frame and the lower rectangular mounting frame.
Preferably: the weight column structure is arranged in parallel along the length direction of the frame structure, and is fixedly connected with a front bracket and a rear bracket of the bottom surface of the weight column structure, a plurality of groups of middle brackets which are arranged in parallel along the length direction of the frame structure and are fixedly connected with the bottom surface of the frame structure are arranged between the front bracket and the rear bracket, the middle bracket and the front bracket are all U-shaped structures with the same structure; the device also comprises column limiting blocks fixedly connected on the front bracket and the rear bracket respectively, wherein the rear bracket, the plurality of groups of middle brackets, the front bracket and the two groups of column limiting blocks jointly function to form an installation area capable of placing the weight column.
Preferably: the front double-hole lifting lug unit comprises a first front cross beam, a second front cross beam and a third front cross beam which are fixedly connected to the top of the frame structure, and the first front cross beam, the second front cross beam and the third front cross beam are arranged in parallel and extend along the width direction of the frame structure; the two front double-hole lifting lugs are fixedly connected between the two adjacent front cross beams and are distributed in parallel along the width direction of the frame structure, and the two front double-hole lifting lugs located on the same side in the width direction are correspondingly arranged.
Preferably: the rear double-hole lifting lug unit comprises a first rear cross beam, a second rear cross beam and a third rear cross beam which are fixedly connected to the top of the frame structure, and the first rear cross beam, the second rear cross beam and the third rear cross beam are arranged in parallel and extend along the width direction of the frame structure; the two rear double-hole lifting lugs are fixedly connected between the two adjacent rear cross beams and are distributed in parallel along the width direction of the frame structure, and the two rear double-hole lifting lugs located on the same side in the width direction are correspondingly arranged.
Drawings
FIG. 1 is a schematic perspective view of the present utility model;
fig. 2 is a schematic perspective view of a weight column structure according to the present utility model.
In the figure: 1. a weight column structure; 1-1, a rear bracket; 1-2, a counterweight column; 1-3, middle bracket; 1-4, front bracket; 1-5, a column limiting block; 2. a lower rectangular mounting frame; 3. installing a frame connecting rod; 4. a rectangular mounting frame is arranged; 5. a first front cross member; 6. front double-hole lifting lugs; 7. a second front cross member; 8. a third front cross member; 9. a front mounting vertical frame; 10. a middle mounting vertical frame; 11. mounting a vertical frame at the rear; 12. a first rear cross member; 13. rear double-hole lifting lugs; 14. a second rear cross member; 15. a third rear cross member; 16. a counterweight supporting rod.
Detailed Description
For a further understanding of the utility model, its features and advantages, the following examples are set forth in detail:
referring to fig. 1, the missile sling loading tool for test according to the present utility model includes a frame structure, in this embodiment, the frame structure is in a cuboid structure, wherein the size of the frame structure simulates the shape and size of a missile which is to be lifted and transferred by a missile sling for load test, and in view of the fact that the cylindrical structure of a shell is inconvenient to simulate, the cylindrical structure of the shell is simulated by adopting a cuboid structure with the same size and box.
The frame structure comprises an upper rectangular mounting frame 4 and a lower rectangular mounting frame 2 which are distributed up and down and are in rectangular structures, wherein the upper rectangular mounting frame 4 and the lower rectangular mounting frame 2 are formed by mutually perpendicular long sectional materials and short sectional materials which are mutually perpendicular and welded and fixedly connected. A plurality of mounting frame connecting rods 3 which are used for connecting the upper rectangular mounting frame 4 and the lower rectangular mounting frame 2 into a whole are fixedly connected between the two; in addition, in order to further increase the strength of the frame structure, the present embodiment includes a plurality of sets of reinforcing bars mounted on four outer peripheral surfaces of the frame structure.
In addition, a middle mounting vertical frame 10 is fixedly connected to the middle part of the frame structure in the length direction, and the front mounting vertical frame 9 and the rear mounting vertical frame 11 which are symmetrically arranged relative to the middle mounting vertical frame 10 are further arranged between the upper rectangular mounting frame 4 and the lower rectangular mounting frame 2 and fixedly connected with the upper rectangular mounting frame 4, the middle mounting vertical frame 10 and the rear mounting vertical frame 11. The strength of the frame structure can be improved by providing the front mounting stile 9, the middle mounting stile 10 and the rear mounting stile 11.
The front mounting vertical frame 9, the middle mounting vertical frame 10 and the rear mounting vertical frame 11 are basically consistent in structure, and comprise two transverse sectional materials which are correspondingly arranged up and down, are respectively welded and fixedly connected with the upper rectangular mounting frame 4 and the lower rectangular mounting frame 2 and extend along the width direction of the mounting frame, and further comprise two vertical sectional materials which are distributed left and right, wherein the two vertical sectional materials are respectively positioned at two sides of the transverse sectional materials, the upper end parts of the vertical sectional materials are respectively welded and fixedly connected with the upper rectangular mounting frame 4, and the lower end parts of the vertical sectional materials are respectively welded and fixedly connected with the lower rectangular mounting frame 2; the reinforced section bars are welded and fixedly connected in a rectangular area surrounded by the two vertical section bars and the two transverse section bars.
In order to meet the lifting point distribution requirement of the missile lifting appliance, the embodiment further comprises a front double-hole lifting lug unit and a rear double-hole lifting lug unit, wherein the front double-hole lifting lug unit and the rear double-hole lifting lug unit are fixedly connected with the upper rectangular mounting frame 4 and are symmetrically arranged about the central line of the frame structure, and the front double-hole lifting lug unit and the rear double-hole lifting lug unit are respectively positioned on the outer sides of the front mounting vertical frame 9 and the rear mounting vertical frame 11.
As shown in fig. 1, the front double-hole lifting lug unit comprises a first front cross beam 5, a second front cross beam 7 and a third front cross beam 8 which are fixedly connected to the top of the frame structure, wherein the first front cross beam 5, the second front cross beam 7 and the third front cross beam 8 are arranged in parallel and extend along the width direction of the frame structure; the two front double-hole lifting lugs 6 are welded and fixedly connected between the two adjacent front cross beams, the two front double-hole lifting lugs 6 are distributed in parallel along the width direction of the frame structure, and the two front double-hole lifting lugs 6 positioned on the same side in the width direction are correspondingly arranged.
The rear double-hole lifting lug unit comprises a first rear cross beam 12, a second rear cross beam 14 and a third rear cross beam 15 which are fixedly connected to the top of the frame structure, and the first rear cross beam 12, the second rear cross beam 14 and the third rear cross beam 15 are arranged in parallel and extend along the width direction of the frame structure; the two rear double-hole lifting lugs 13 are fixedly connected between two adjacent rear cross beams, the two rear double-hole lifting lugs 13 are distributed in parallel along the width direction of the frame structure, and the two rear double-hole lifting lugs 13 positioned on the same side in the width direction are correspondingly arranged.
In the embodiment, two hanging holes are formed in each of the four front double-hole lifting lugs 6 and the four rear double-hole lifting lugs 13, and the central lines of the two hanging holes are located in different horizontal planes; it is noted that the corresponding hanging holes of the front double-hole hanging lug 6 and the rear double-hole hanging lug 13 which are positioned on the same side are coaxially arranged. Through the arrangement, the position of the lifting point of the missile can be simulated, and further the lifting requirement of the missile lifting appliance is met.
Through setting up preceding diplopore lug unit and back diplopore lug unit, can satisfy the hoist and mount requirement of a plurality of hoisting points of distributing on the guided missile hoist, and then make this embodiment hoist and mount on the guided missile hoist of waiting to carry out load test according to guided missile hoist and mount missile's mode to follow-up test operation is convenient for carry out.
In order to simulate the mass distribution of the missile, as shown in fig. 1, the embodiment further comprises a weight column structure 1 mounted at the bottom of the lower rectangular mounting frame 2. Referring further to fig. 2, the weight column structure 1 is arranged in parallel along the length direction of the frame structure and is fixedly connected with the front bracket 1-4 and the rear bracket 1-1 of the bottom surface thereof, and a plurality of groups of middle brackets 1-3 which are arranged in parallel along the length direction of the frame structure and are fixedly connected with the bottom surface of the frame structure are arranged between the front bracket 1-4 and the rear bracket 1-1; the rear bracket 1-1, the middle bracket 1-3 and the front bracket 1-4 are all of U-shaped structures with the same structure, and two supporting legs of the U-shaped structures of the brackets are respectively welded and fixedly connected with two long sections of the lower rectangular mounting frame 2.
The counterweight column structure 1 further comprises column limiting blocks 1-5 fixedly connected to the front bracket 1-4 and the rear bracket 1-1 respectively, wherein the rear bracket 1-1, the plurality of groups of middle brackets 1-3, the front bracket 1-4 and the two groups of column limiting blocks 1-5 jointly function to enclose a mounting area capable of placing the counterweight column 1-2, and the counterweight column 1-2 is a columnar counterweight; the number of the weight columns 1-2 can be increased or decreased according to the mass of the missile in actual work, and in order to avoid rolling of the weight columns 1-2 in the hoisting process, each weight column 1-2 can be welded on a bracket after the number of the weight columns 1-2 is determined. It is noted that in the present embodiment, the weight column structure 1 is disposed symmetrically with respect to the center line of the frame structure. In addition, in order to facilitate the loading and unloading of the weight column 1-2, a gap through which the weight column 1-2 passes is left between the top of each column stopper 1-5 and the bottom surface of the lower rectangular mounting frame 2.
As shown in the figure, the device also comprises a plurality of counterweight support rods 16 fixedly connected between two adjacent installation vertical frames, wherein each counterweight support rod 16 extends along the length direction of the frame structure; when the weight post structure 1 is insufficient to meet the mass of the simulated missile in the embodiment, the weight block can be hoisted to the frame structure to make up for the mass gap, and in the actual working process, the weight block can be placed on the weight support rod 16, and in addition, the weight block can be welded on the weight support rod 16 for safety.
Working principle:
the utility model utilizes the frame structure with a cuboid structure, and can simulate the shape and the size of a cartridge hoisted by a missile sling; the vertical load of the frame structure in the vertical direction is realized through the counterweight column structure 1 arranged on the frame structure, so that the quality condition of the cartridge is simulated, and when the loading tool is hoisted on the missile sling, the load born in the vertical direction in the process of hoisting and transferring the cartridge product of the missile sling can be simulated through the arrangement; through the front double-hole lifting lug unit and the rear double-hole lifting lug unit which are arranged on the top surface of the frame structure, the distribution condition of lifting points of the cylindrical shell can be simulated, and then the loading tool can be lifted on the missile lifting appliance according to the lifting mode of the cylindrical shell on the missile lifting appliance.
Claims (6)
1. A missile sling loading tool for test is characterized in that:
comprises a frame structure which is a cuboid structure;
the front mounting vertical frame (9), the middle mounting vertical frame (10) and the rear mounting vertical frame (11) are symmetrically arranged about the middle mounting vertical frame (10), and the middle mounting vertical frame (10) is arranged in the middle of the frame structure;
the device also comprises a plurality of counterweight support rods (16) fixedly connected between two adjacent installation vertical frames, and each counterweight support rod (16) extends along the length direction of the frame structure;
the front double-hole lifting lug unit and the rear double-hole lifting lug unit are fixedly connected with the frame structure and are symmetrically arranged about the central line of the frame structure;
and a counterweight column structure (1) arranged at the bottom of the frame structure.
2. The test missile sling loading fixture as recited in claim 1, wherein: the frame structure comprises an upper rectangular mounting frame (4) and a lower rectangular mounting frame (2) which are distributed up and down, and a plurality of mounting frame connecting rods (3) which are connected into a whole are fixedly connected between the upper rectangular mounting frame (4) and the lower rectangular mounting frame (2); the weight column structure (1) is connected with the lower rectangular mounting frame (2).
3. The test missile sling loading fixture as recited in claim 2, wherein: the front mounting vertical frame (9), the middle mounting vertical frame (10) and the rear mounting vertical frame (11) are all arranged between the upper rectangular mounting frame (4) and the lower rectangular mounting frame (2) and fixedly connected with the upper rectangular mounting frame and the lower rectangular mounting frame.
4. The test missile sling loading fixture as recited in claim 1, wherein: the weight column structure (1) is provided with a plurality of groups of middle brackets (1-3) which are distributed in parallel along the length direction of the frame structure and are fixedly connected with the bottom surface of the frame structure, and U-shaped structures with the same structure are arranged between the front brackets (1-4) and the rear brackets (1-1), wherein the front brackets (1-4) and the rear brackets (1-1) are respectively provided with the middle brackets (1-3) which are distributed in parallel along the length direction of the frame structure and are fixedly connected with the bottom surface of the frame structure, and the rear brackets (1-1), the middle brackets (1-3) and the front brackets (1-4); the device also comprises column limiting blocks (1-5) fixedly connected on the front bracket (1-4) and the rear bracket (1-1) respectively, wherein the rear bracket (1-1), the middle brackets (1-3) in multiple groups, the front bracket (1-4) and the two groups of column limiting blocks (1-5) jointly function to form a mounting area capable of placing the weight column (1-2).
5. The test missile sling loading fixture as recited in claim 1, wherein: the front double-hole lifting lug unit comprises a first front cross beam (5), a second front cross beam (7) and a third front cross beam (8) which are fixedly connected to the top of the frame structure, wherein the first front cross beam (5), the second front cross beam (7) and the third front cross beam (8) are arranged in parallel and extend along the width direction of the frame structure; the frame structure is characterized by further comprising two front double-hole lifting lugs (6) fixedly connected between two adjacent front cross beams, wherein the two front double-hole lifting lugs (6) are distributed in parallel along the width direction of the frame structure, and the two front double-hole lifting lugs (6) positioned on the same side in the width direction are correspondingly arranged.
6. The test missile sling loading fixture as recited in claim 1, wherein: the rear double-hole lifting lug unit comprises a first rear cross beam (12), a second rear cross beam (14) and a third rear cross beam (15) which are fixedly connected to the top of the frame structure, and the first rear cross beam (12), the second rear cross beam (14) and the third rear cross beam (15) are arranged in parallel and extend along the width direction of the frame structure; the two rear double-hole lifting lugs (13) are fixedly connected between two adjacent rear cross beams, the two rear double-hole lifting lugs (13) are distributed in parallel along the width direction of the frame structure, and the two rear double-hole lifting lugs (13) positioned on the same side in the width direction are correspondingly arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320810325.0U CN219279236U (en) | 2023-04-13 | 2023-04-13 | Missile lifting appliance loading tool for test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320810325.0U CN219279236U (en) | 2023-04-13 | 2023-04-13 | Missile lifting appliance loading tool for test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219279236U true CN219279236U (en) | 2023-06-30 |
Family
ID=86931765
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320810325.0U Active CN219279236U (en) | 2023-04-13 | 2023-04-13 | Missile lifting appliance loading tool for test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219279236U (en) |
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2023
- 2023-04-13 CN CN202320810325.0U patent/CN219279236U/en active Active
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