CN220018324U - Rocket erection arm and rocket erection device - Google Patents

Abstract

The embodiment of the utility model provides a rocket erection arm and a rocket erection device, wherein the rocket erection arm comprises an erection arm body, a holding arm, a bracket, a rear end locking mechanism, an oil cylinder upper support, a ladder and an operation platform; the vertical arm body is of a truss type splicing structure and comprises a front section, a middle section and a tail section which are sequentially connected; the connecting parts of the front section, the middle section and the tail section are respectively provided with a convex flange and a concave flange which are mutually inserted and used, and the convex flange is used for being inserted into the concave flange and fixedly connected with the concave flange; the tail section is far away from the one end of anterior segment is equipped with the gyration hole, the gyration hole is used for wearing to establish the gyration axle and makes the perpendicular arm of rising is around the gyration axle rotates. According to the rocket erection arm and the rocket erection device, the rocket erection arm body can be split into a plurality of groups of assembled structures, so that the rocket erection arm is convenient to transport and hoist independently, can be reused, and the connection structure between the section groups is stable and reliable.

Description

Rocket erection arm and rocket erection device

Technical Field

The utility model relates to the technical field of rocket launching equipment, in particular to a rocket erection arm and a rocket erection device.

Background

Currently, there are three main types of test patterns commonly used by carrier rockets in countries around the world: one flat two-fold (rocket horizontal transfer, vertical assembly, vertical test), three-fold (rocket vertical transfer, vertical assembly, vertical test), three-fold (rocket horizontal transfer, horizontal assembly, horizontal test).

Before launching, the rocket adopting the three-level test launching mode is erected on a launching pad by an erecting device from a horizontal state to a vertical state and is placed on a launching platform, so that the conversion of a rocket body from the horizontal state to the vertical state is completed. When the launching is canceled or the training is performed, the rocket is taken down from the launching platform and restored to a horizontal state. The equipment for erecting can be a vertical arm type, and the vertical arm type erecting equipment generally uses a multi-stage oil cylinder to jack the vertical arm carrying the rocket from a horizontal state to a vertical state. The erecting arm is a main stress part for supporting and supporting the rocket, one end of the erecting arm is connected with the foundation through a rotating shaft, the lower part of the arm is connected with the erecting oil cylinder, and the erecting and the lowering of the erecting arm with the rocket are realized through the extension and the retraction of the erecting oil cylinder.

For some medium and large rockets, when the rocket is in a three-level test mode and is wholly erected, the erection arm is required to limit and support the rocket in the erection process, so that an installation space is provided for rocket filling, air supply and air conditioning pipelines, a climbing channel is provided for realizing manned operation, and an operation platform is provided for personnel operation. The erection arm needs to be installed and debugged on site on the launching site in the using process. After the rocket launching task is executed once, the vertical arm body needs to be disassembled, the highway is transported to other launching stations, and the rocket launching station is installed and debugged again. Because the highway transportation has limitations on the length, the width and the height of the product, if the vertical arm adopts an integral structure, the size of the product on the vehicle can be increased, the transportation cost is increased sharply, and even the highway transportation cannot be realized. Because fixed hoisting equipment such as truss cranes, gantry cranes and the like are not arranged on the launching pad, the hoisting equipment is limited by the launching pad hoisting equipment, the crane with a truck can only be used for the disassembly and assembly of the hoisting arm, and if the weight of the body of the hoisting arm is overweight and the length is overlong, the hoisting is difficult.

Disclosure of Invention

In view of the above, an object of the embodiments of the present utility model is to provide a rocket erection arm and a rocket erection device, so as to solve the technical problem of inconvenient transportation and hoisting of the integral erection arm in the prior art.

In a first aspect, an embodiment of the present utility model provides a rocket erection arm, including: the lifting arm comprises a lifting arm body, a holding arm, a bracket, a rear end locking mechanism, an oil cylinder upper support, a personnel ladder and an operation platform which are respectively arranged on the lifting arm body; the vertical arm body is of a truss type splicing structure and comprises a front section, a middle section and a tail section which are sequentially connected; the connecting parts of the front section, the middle section and the tail section are respectively provided with a convex flange and a concave flange which are mutually inserted and used, and the convex flange is used for being inserted into the concave flange and fixedly connected with the concave flange; a rotary hole is formed in one end, far away from the front section, of the tail section, and is used for penetrating a rotary shaft and enabling the vertical arm to rotate around the rotary shaft; the oil cylinder upper support and the rear end locking mechanism are respectively arranged on the tail section.

Further, the holding arm comprises a first arm body and a second arm body which are symmetrically arranged, the first arm body is provided with a first holding block, and the second arm body is provided with a second holding block; the holding arm is used for holding or loosening the rocket through the first holding block and the second holding block.

Further, the number of the brackets is multiple, the brackets are arranged at intervals along the length direction of the erecting arm body, one side of each bracket is fixedly connected with the erecting arm body, a supporting plate is arranged at the end part of the other side of each bracket, the supporting plate is used for supporting an rocket body of a rocket, and the supporting wrap angle range of the supporting plate is between 70 degrees and 120 degrees.

Further, the rear end locking mechanism comprises a first locking piece and a second locking piece which are respectively arranged close to two ends of the tail section in the width direction; the first locking piece and the second locking piece respectively comprise a positioning plate and a telescopic lock hook; the positioning plate is used for guiding the rocket when the rocket is placed; the latch hook is used for tensioning the rocket body end journal after the rocket is placed.

Further, the number of the oil cylinder upper supports is two, the oil cylinder upper supports are respectively arranged on two sides of the tail section in the width direction, and each oil cylinder upper support comprises an oil cylinder upper support mounting seat, a support hole formed in the oil cylinder upper support mounting seat and an upper rotating shaft penetrating through the support hole; the upper rotating shaft is used for being connected with the driving end of the erection cylinder in a rotating mode.

Further, the personal ladder is used as a climbing tool and is formed by combining a plurality of groups of ladder sections, and the material of the personal ladder comprises aluminum materials.

Further, the operation platform is used for bearing objects or personnel and comprises a fixing frame, a bedplate and guardrails; the fixing frame is fixed on the vertical arm body, the bedplate is fixed on the fixing frame, and the guardrails are fixed on two sides of the bedplate; the peripheral edges of the bedplate are respectively provided with a turned-over edge turned towards one side of the bearing surface of the bedplate.

Further, the number of the middle sections is two or more, and every two adjacent middle sections are respectively connected through a concave flange and/or a convex flange.

Further, the material of the front section comprises aluminum.

In a second aspect, an embodiment of the present utility model provides a rocket erection device, including the rocket erection arm, a truss foundation and an erection cylinder; the erection cylinder is fixed on the truss foundation, and the driving end of the erection cylinder is rotationally connected with the upper support of the cylinder and used for driving the rocket erection arm to switch between a horizontal state and a vertical state.

The technical scheme has the following beneficial effects: the rocket erection arm provided by the utility model comprises an erection arm body, a holding arm, a bracket, a rear end locking mechanism, an oil cylinder upper support, a ladder and an operation platform, wherein the rocket can be limited and supported, an installation space is provided for rocket filling, air supply and air conditioning pipelines, and a climbing channel and an operation platform can be provided for operators. Meanwhile, the lifting arm body is of a split structure and at least comprises a front section and a tail section, the front section and the tail section of the lifting arm body can be disassembled and then independently loaded and transported, the transportation size and the weight can be reduced, the highway transportation can be conveniently realized, and meanwhile, the weight reduction is convenient for using a lorry-mounted crane to hoist the lifting arm body. The split type vertical arm body structure adopts concave-convex molded surface positioning between the sections, and the concave flange and the convex flange are connected in an opposite-plug manner, so that the shearing force and the torque of the vertical arm are born and transmitted through the two flanges which are in butt joint, and the stability and the bearing performance of the structure are enhanced.

Drawings

In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the utility model, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic view of the overall structure of a rocket erection device according to an embodiment of the present utility model;

FIG. 2 is a schematic view of the overall structure of a rocket erection arm according to embodiments of the present utility model;

FIG. 3 is a schematic view of the overall structure of the erection arm body according to the embodiment of the utility model;

FIG. 4 is a schematic structural view of a tail section of an embodiment of the present utility model;

FIG. 5 is a schematic illustration of the structure of a middle section of an embodiment of the present utility model;

FIG. 6 is a schematic structural view of the front section of an embodiment of the present utility model;

FIG. 7 is a schematic view of the arm according to an embodiment of the present utility model;

FIG. 8 is a schematic view of the structure of a bracket according to an embodiment of the present utility model;

FIG. 9 is a schematic view of the structure of the rear end locking mechanism (one of the locking members) according to the embodiment of the present utility model;

FIG. 10 is a schematic view of the structure of the cylinder upper support according to the embodiment of the present utility model;

FIG. 11 is a schematic view of the structure of a ladder (a group of sections) according to an embodiment of the utility model;

fig. 12 is a schematic structural diagram of an operation platform according to an embodiment of the present utility model.

The meaning of the various reference numerals in the drawings is as follows:

1. a rocket; 2. a transmitting station; 3. a deflector; 4. a rocket lifting vertical arm; 5. truss foundation; 6. a lifting oil cylinder; 40. a standing arm body;

41. a tail section; 411. a swivel hole; 412. a rear end locking mechanism mounting plate; 413. a first bracket mounting plate; 414. a first operating platform mounting plate; 415. the oil cylinder upper support mounting plate; 416. a first butt plate;

42. a middle section; 421. a second bracket mounting plate; 422. a second operating platform mounting plate; 423. arm holding mounting plates; 424. a second butt plate; 425. a third butt joint plate;

43. a front section; 431. a fourth butt plate; 432. a third operating platform mounting plate;

44. arm holding; 441. a first arm body; 442. the first holding block; 443. a second arm body; 444. a second holding block; 445. arm holding mounting seats;

45. a bracket; 451. a bracket butt joint plate; 452. a supporting plate; 453. a hoisting hook;

46. a rear end locking mechanism; 461. a first locking member; 462. a second locking member; 463. a latch hook; 464. a positioning plate; 465. a locking member mounting base;

47. an oil cylinder upper support; 471. a support hole; 472. an oil cylinder upper support mounting seat; 473. an upper rotating shaft;

48. a step; 481. ladder beams; 482. a pedal; 483. a column; 484. an armrest; 485. an upper butt plate; 486. a lower butt plate;

49. an operating platform; 491. a fixing frame; 492. a platen; 493. flanging; 494. guard bars;

51. a swivel support; 511. a rotating shaft; 52. and a lower support of the oil cylinder.

Detailed Description

Features and exemplary embodiments of various aspects of the utility model are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the utility model. It will be apparent, however, to one skilled in the art that the present utility model may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the utility model by showing examples of the utility model. In the drawings and the following description, at least some well-known structures and techniques have not been shown in detail in order not to unnecessarily obscure the present utility model; also, the dimensions of some of the structures may be exaggerated for clarity. Furthermore, the described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.

As shown in fig. 1, the embodiment of the utility model provides a rocket erection device, which comprises a rocket erection arm 4, a truss foundation 5 and a erection cylinder 6. The truss foundation 5 is used for being placed on a launching pad and carrying the rocket body of the horizontally placed rocket 1 when the rocket erection arm 4 is horizontally placed. The truss foundation 5 is also provided with a rotary support 51, a rotary shaft 511 is arranged on the rotary support 51 in a penetrating mode, and the rocket erection arm 4 is connected with the rotary shaft 511 in a rotary mode.

The erection cylinder 6 is fixed on the truss foundation 5, the driving end of the erection cylinder 6 is rotationally connected with the rocket erection arm 4, and the other end of the erection cylinder 6 is rotationally connected with the truss foundation 5. The rocket erecting arm 4 can rotate around the rotating shaft 511 under the drive of the erecting oil cylinder 6, and is erected upwards to drive the rocket 1 to complete erecting or falls downwards to drive the rocket 1 to restore the horizontal state. In this embodiment, the number of the erection cylinders 6 is two, and the two erection cylinders 6 are respectively and correspondingly arranged on the truss foundations 5 on two sides of the rocket erection arm 4 in the width direction.

As shown in fig. 2, the rocket erection arm 4 of the present embodiment includes an erection arm body 40, and a holding arm 44, a bracket 45, a rear end locking mechanism 46, an oil cylinder upper support 47, a step 48, and an operation platform 49 which are respectively provided on the erection arm body 40.

The erection arm body 40 is a truss type splicing structure welded by rectangular seamless steel pipes, and comprises a front section 43 and a tail section 41, and can also comprise one or more middle sections 42, wherein the number of the specific sections depends on actual hoisting and transportation. The erection arm body 40 of the present embodiment has the characteristics of good rigidity and light overall mass.

Specifically, the three-stage structure of the arm body 40 including the front stage 43, the middle stage 42 and the rear stage 41 is described.

As shown in fig. 3 and 4, the tail section 41 of the present embodiment is of a welded structure, and a rotation hole 411 is provided at the rear end of the tail section 41, i.e. the end far away from the middle section 42, and the rotation hole 411 is used for penetrating a rotation shaft 511, i.e. the rotation shaft 511 respectively penetrates the rotation hole 411 on the tail section 41 and the mounting hole on the rotation support 51, so that the lifting arm body 40 can rotate upwards around the rotation shaft 511 when the lifting cylinder 6 is lifted. The rear end upper surface (surface for loading rocket 1 side) of the tail section 41 is provided with a rear end locking mechanism mounting plate 412, a first bracket mounting plate 413 and a first operation platform mounting plate 414, respectively, cylinder upper bracket mounting plates 415 are mounted on both sides in the width direction of the tail section 41, respectively, a first butt plate 416 is provided at the front end portion of the tail section 41, that is, one end close to the middle section 42, and a first convex flange (not shown) having a square cross section is provided in the middle of the first butt plate 416. The rear locking mechanism mounting plate 412 is used for mounting the rear locking mechanism 46, the first bracket mounting plate 413 is used for mounting the bracket 45, the first operating platform mounting plate 414 is used for mounting the operating platform 49, the cylinder upper support mounting plate 415 is used for mounting the cylinder upper support 47, and the first butt plate 416 is used for butt joint with the middle section 42. The core of the tail section 41 is provided with a cavity for the placement of a ramp 48.

As shown in fig. 3 and 5, the middle section 42 of the present embodiment is a welded structure, and the upper surface of the middle section 42 is respectively provided with a second bracket mounting plate 421, a second operation platform mounting plate 422 and a arm holding mounting plate 423; a second abutment plate 424 is provided at the rear end portion of the middle section 42, a third abutment plate 425 is provided at the front end portion of the middle section 42, a first concave flange (not shown) corresponding to the first convex flange is provided at the middle portion of the second abutment plate 424, and a second concave flange (not shown) is provided at the middle portion of the third abutment plate 425. The second bracket mounting plate 421 is used for mounting the bracket 45, the second operating platform mounting plate 422 is used for mounting the operating platform 49, and the arm mounting plate 423 is used for mounting the arm 44. The second abutment plate 424 is for abutment with the first abutment plate 416. The first convex flange is inserted into the first concave flange, and is fixedly connected by a fastener, which may be a bolt, etc., so that the tail section 41 and the middle section 42 are fixed. The center portion of the middle section 42 is provided with a cavity for the step 48.

As shown in fig. 3 and 6, a fourth butt joint plate 431 is disposed on the rear end face of the front section 43 in the present embodiment, a second convex flange (not shown) corresponding to the second concave flange is disposed in the middle of the fourth butt joint plate 431, and the second convex flange is inserted into the second concave flange and fixedly connected by a fastener, so that the front section 43 and the middle section 42 are fixed. The upper surface of the front section 43 is also provided with a third operating platform mounting plate 432, the third operating platform mounting plate 432 being for mounting the operating platform 49. The core of the front section 43 is provided with a cavity for the step 48. To reduce the erection weight of rocket erection arm 4, front section 43 may be made of a lightweight material, such as aluminum.

As shown in fig. 3 and 7, the holding arm 44 includes a first arm body 441 and a second arm body 443 that are symmetrically arranged, the first arm body 441 is provided with a first holding block 442, and the second arm body 443 is provided with a second holding block 444; the arm 44 is used to hold or release the rocket wall of the rocket 1 by the first and second holding blocks 442 and 444. The clasping arm 44 is used for providing clasping force for the rocket 1, and has functions of clasping, loosening and fully opening. Arm holding mounting seats 445 are respectively arranged at the bottoms of the first arm body 441 and the second arm body 443, and the arm holding mounting seats 445 are fixedly connected with the arm holding mounting plates 423.

As shown in fig. 3 and 8, the number of brackets 45 is plural, and each bracket 45 has substantially the same or completely the same structure, and the brackets 45 are used for supporting the rocket 1 and matching the arms 44 to tightly hold the rocket 1. In this embodiment, the number of brackets 45 is three, and the brackets 45 are spaced apart along the length direction of the upright arm body 40, wherein one bracket 45 is disposed on the tail section 41, and two brackets 45 are disposed on the middle section 42. The bottom of the bracket 45 is provided with a bracket abutment plate 451, and the bracket abutment plate 451 is fixedly connected with the first bracket mounting plate 413 or the second bracket mounting plate 421. The upper surface of the bracket 45 is provided with a supporting plate 452, the supporting plate 452 is an arc-shaped plate and is used for supporting an arrow body of the rocket 1, the supporting wrap angle of the supporting plate 452 ranges from 70 degrees to 120 degrees, and the supporting width can range from 70mm to 120 mm. The portion of the bracket 45 that contacts the rocket body of the rocket 1 may be coated with a flexible material to protect the surface of the rocket body. A lifting hook 453 is arranged on the side surface of the bracket 45, and the lifting hook 453 is used for being matched with a lifting appliance, so that the bracket 45 is convenient to lift during assembly.

As shown in fig. 3 and 9, the rear end locking mechanism 46 includes a first locking member 461 and a second locking member 462 which are symmetrically disposed near both sides in the width direction of the tail section 41, respectively. The first locking member 461 and the second locking member 462 respectively include a positioning plate 464 and a telescopic locking hook 463. The positioning plate 464 is used for butt-jointing and guiding the end journal of the tail section 41 of the rocket 1 and the rear end locking mechanism 46 when the rocket 1 is horizontally transferred to the rocket erecting arm 4, and the lock hook 463 is used for tensioning the end journal of the rocket body after the rocket 1 is placed. The rear locking mechanism 46 is used as a main load bearing structure when the rocket 1 is in an erect state, and the bottoms of the first locking member 461 and the second locking member 462 are provided with locking member mounting seats 465, and the locking member mounting seats 465 are fixedly connected with the rear locking mechanism mounting plate 412.

As shown in fig. 3 and 10, the number of cylinder upper holders 47 is two, and they are symmetrically provided on both sides of the width direction of the tail section 41, respectively, for mounting rod rings of the piston rod of the erection cylinder 6. The cylinder upper support 47 includes a cylinder upper support mounting seat 472, a support hole 471 formed in the cylinder upper support mounting seat 472, and an upper rotating shaft 473 penetrating the support hole 471. The upper rotating shaft 473 is used for being rotationally connected with the driving end of the erection cylinder 6.

As shown in fig. 3 and 11, the ladder 48 is used as a climbing tool, and is formed by combining multiple groups of ladder sections, and the ladder 48 is made of a light material, such as aluminum. The multiple groups of ladder sections of the personal ladder 48 are arranged in a folding way, and the height of each group of ladder sections can be set between 2m and 3m by adopting a welding structure, and the inner side net width of the personal ladder 48 is set between 0.5m and 0.6 m. Each group of steps includes a ladder beam 481, a tread 482, a column 483 and a handrail 484, respectively, a lower abutment plate 486 is provided at the bottom of the ladder beam 481, and an upper abutment plate 485 is provided at the top of the ladder beam 481 for installation into a cavity in the center of the riser body 40 and fixedly connected by fasteners.

As shown in fig. 3 and 12, the operation platform 49 is used for carrying objects or personnel, and can provide an operation space for the operator to perform equipment inspection and maintenance operations, and also plays a role of safety protection. The operating platform 49 includes a mount 491, a platen 492, and a rail 494. The fixing frame 491 is fixed to the erecting arm body 40, the base plate 492 is fixed to the fixing frame 491, and the guard rail 494 is fixed to both sides of the upper surface of the base plate 492. The peripheral edges of the base plate 492 are provided with respective cuffs 493 which are folded over toward the bearing surface side of the base plate 492. The base plate 492 plays a bearing role, and the flange 493 is arranged at the edge of the base plate 492, so that the operator can be prevented from playing a role in preventing the tip of the foot from being kicked onto the rocket body of the rocket 1 during operation. The guard rail 494 is used for playing a safety protection role for an operator, and the operator should wear the area to limit the safety belt when ascending a height, and the guard rail 494 can also be used as a hanging point of the safety belt at the moment.

The installation method of the rocket erection device of the embodiment is as follows:

near the launching platform 2 of the rocket 1, a truss foundation 5 is installed, a deflector 3 is arranged at the bottom of the launching platform 2, and lower trunnions (not shown) of two erection cylinders 6 are respectively in butt joint with two cylinder lower supports 52 of the truss foundation 5. The two erection cylinders 6 are in a retracted state, the lengths are basically consistent, the blocking covers of the oil inlet and the oil outlet are screwed, and the erection cylinders 6 are in a locking state.

The rear end locking mechanism 46, the cylinder upper mount 47, the operation platform 49 of the tail section 41, the bracket 45 of the tail section 41, and the step 48 of the tail section 41 are attached to the tail section 41 of the boom body 40.

The bracket 45 of the middle section 42, the operating platform 49 of the middle section 42, the arm 44, and the step 48 of the middle section 42 are mounted to the middle section 42 of the arm body 40.

The operating platform 49 of the front section 43 and the ramp 48 of the front section 43 are mounted to the front section 43 of the riser arm body 40.

The swivel shaft 511 of the swivel support 51 of the truss foundation 5 is penetrated into the swivel hole 411 at the rear end of the tail section 41.

The tail section 41 is hoisted using a lorry-mounted crane, and the swivel shaft 511 is fitted into the bearing housing of the swivel support 51 of the truss foundation 5.

The head of the tail section 41 is supported by a jack, and the lorry-mounted crane is retracted.

The bearing caps of the slewing bearing 51 to which the truss foundation 5 is attached are attached using fasteners.

The head of the tail section 41 is lifted by a lorry-mounted crane, and slightly rotated about the pivot shaft 511 to adjust the position of the cylinder upper support 47. At the same time, the other truck-mounted crane lifts the rod portion of the right lift cylinder 6 (in the direction shown in the drawing) and slightly rotates around the lower lug (not shown) of the cylinder until the rod ring of the right lift cylinder 6 aligns with the axis of the support hole 471 of the cylinder upper support 47 on the right side, penetrating into the upper rotating shaft 473.

And loosening the blocking covers of the oil inlet and the oil return opening of the right vertical oil cylinder 6, wherein the right vertical oil cylinder 6 is in a freely telescopic state under external force.

The left lift cylinder 6 is installed using the same method. After the left vertical oil cylinder 6 is installed, the oil inlet and the oil return opening blanking cover of the right vertical oil cylinder 6 are screwed up, and the locking state is restored.

The truck crane hoist section 42, the first concave flange of the second interface plate 424 interfaces with the first convex flange of the first interface plate 416, and is connected using fasteners.

The second convex flange of the fourth abutment plate 431 abuts the second concave flange of the third abutment plate 425, and is attached using fasteners, to the front hoist section 43.

The erection arm is in the working state of figure 1, and the installation is completed.

After the rocket 1 is launched, the front section 43, the middle section 42, the erection cylinder 6 and the tail section 41 are respectively dismantled. The bracket 45, ramp 48 and operating platform 49 mounted on the riser body 40 need not be removed and the road truck can be loaded with each set of segments. The holding arm 44, the rear end locking mechanism 46 and the oil cylinder upper support 47 can be disassembled according to the condition according to whether the requirements of the width and the height of the road transportation are met or not, and are transported independently.

The length of the rocket erection arm is about 30-80 meters, the rocket erection arm can be used for the launching erection of medium-sized and large-sized rockets, is provided with a foldback ascending personal ladder and an operation platform, can meet the ascending and operation requirements of personnel after erection, and has the partial function of a launching tower. The components of the rocket lifting arm can be disassembled and can be transported to other launching stations for multiple use by a highway, and the rocket lifting arm has the characteristic of being movable. After the split erection arm body is transported to the launching site by a road, the assembly can be carried out on site on the launching site, and the split erection arm body can be used at different launching stations, so that the flexibility of the erection arm is enhanced. The butt joint interfaces of the sections of the vertical arm body are designed to be positioned by concave-convex profiles, and the concave flange and the convex flange are connected in an opposite-plug manner. The rocket erection arm and the rocket erection device of the embodiment can be assembled and disassembled by using general equipment during installation and disassembly, special facilities are not required to be built, the universality is high, and the investment cost of erection related equipment is reduced.

In the description of the present utility model, it should be noted that the orientation or positional relationship indicated by "upper, lower, inner and outer", etc. in terms are based on the orientation or positional relationship shown in the drawings, are merely for convenience of describing the present utility model and simplifying the description, and do not indicate or imply that the apparatus or element in question must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first, second, or third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

The terms "mounted, connected, and coupled" should be construed broadly in this disclosure unless otherwise specifically indicated and defined, such as: can be fixed connection, detachable connection or integral connection; it may also be a mechanical connection, an electrical connection, or a direct connection, or may be indirectly connected through an intermediate medium, or may be a communication between two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.

While the utility model has been described with reference to a preferred embodiment, various modifications may be made and equivalents may be substituted for elements thereof without departing from the scope of the utility model. In particular, the technical features mentioned in the respective embodiments may be combined in any manner as long as there is no structural conflict. The present utility model is not limited to the specific embodiments disclosed herein, but encompasses all technical solutions falling within the scope of the claims.

Claims (10)

1. A rocket erection arm, comprising: the lifting arm comprises a lifting arm body (40), and a holding arm (44), a bracket (45), a rear end locking mechanism (46), an oil cylinder upper support (47), a personnel ladder (48) and an operation platform (49) which are respectively arranged on the lifting arm body (40); the vertical arm body (40) is of a truss type splicing structure and comprises a front section (43), a middle section (42) and a tail section (41) which are sequentially connected; the connecting parts of the front section (43), the middle section (42) and the tail section (41) are respectively provided with a convex flange and a concave flange which are mutually spliced for use, and the convex flange is used for being inserted into the concave flange and fixedly connected with the concave flange; a rotary hole (411) is formed in one end, far away from the front section (43), of the tail section (41), and the rotary hole (411) is used for penetrating a rotary shaft (511) and enabling the vertical lifting arm to rotate around the rotary shaft (511); the oil cylinder upper support (47) and the rear end locking mechanism (46) are respectively arranged on the tail section (41).

2. Rocket erection arm according to claim 1, characterized in that the holding arm (44) comprises a first arm body (441) and a second arm body (443) which are symmetrically arranged, a first holding block (442) is arranged on the first arm body (441), and a second holding block (444) is arranged on the second arm body (443); the holding arm (44) is used for holding or loosening the rocket (1) through the first holding block (442) and the second holding block (444).

3. Rocket erection arm according to claim 1, characterized in that the number of brackets (45) is a plurality, the brackets are arranged at intervals along the length direction of the erection arm body (40), one side of each bracket (45) is fixedly connected with the erection arm body (40), a supporting plate (452) is arranged at the end part of the other side, the supporting plate (452) is used for supporting an rocket body of the rocket (1), and the supporting wrap angle range of the supporting plate (452) is between 70 and 120 degrees.

4. A rocket erection arm according to claim 1 wherein the rear-end locking mechanism (46) comprises a first locking member (461) and a second locking member (462) disposed near both widthwise ends of the tail section (41), respectively; the first locking member (461) and the second locking member (462) respectively comprise a positioning plate (464) and a telescopic locking hook (463); the positioning plate (464) is used for guiding the rocket (1) when the rocket (1) is placed; the latch hook (463) is used for tensioning the rocket body end journal after the rocket (1) is placed.

5. Rocket erection arm according to claim 1, characterized in that the number of the cylinder upper supports (47) is two, and the cylinder upper supports (47) are respectively arranged at two sides of the tail section (41) in the width direction, and the cylinder upper supports (47) comprise cylinder upper support mounting seats (472), support holes (471) formed in the cylinder upper support mounting seats (472), and upper rotating shafts (473) penetrating through the support holes (471); the upper rotating shaft (473) is used for being connected with the driving end of the erection cylinder (6) in a rotating mode.

6. Rocket erection arm according to claim 1 wherein the step (48) is used as climbing tool and is composed of a plurality of steps, the step (48) being made of aluminum.

7. Rocket erection arm according to claim 1 characterized in that the operating platform (49) is for carrying objects or persons, comprising a holder (491), a bedplate (492) and a railing (494); the fixing frame (491) is fixed on the erecting arm body (40), the bedplate (492) is fixed on the fixing frame (491), and the guardrails (494) are fixed on two sides of the bedplate (492); a flange (493) turned over towards one side of the bearing surface of the base plate (492) is respectively arranged at the peripheral edge of the base plate (492).

8. Rocket erection arm according to claim 1, wherein the number of intermediate sections (42) is two or more, each two adjacent intermediate sections (42) being connected by a concave flange and/or a convex flange, respectively.

9. Rocket-like boom according to claim 1, characterized in that the material of the front section (43) comprises aluminum.

10. A rocket erection device, characterized by comprising a rocket erection arm (4) according to any one of claims 1 to 9, a truss foundation (5) and a erection cylinder (6); the lifting oil cylinder (6) is fixed on the truss foundation (5), and the driving end of the lifting oil cylinder (6) is rotationally connected with the oil cylinder upper support (47) and used for driving the rocket lifting arm (4) to switch between a horizontal state and a vertical state.