CN112320681A - Guided missile hollow shell transport rack - Google Patents
Guided missile hollow shell transport rack Download PDFInfo
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- CN112320681A CN112320681A CN202011295122.XA CN202011295122A CN112320681A CN 112320681 A CN112320681 A CN 112320681A CN 202011295122 A CN202011295122 A CN 202011295122A CN 112320681 A CN112320681 A CN 112320681A
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- missile
- shell
- rod
- hollow shell
- guided missile
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- 230000007246 mechanism Effects 0.000 claims abstract description 43
- 230000000149 penetrating effect Effects 0.000 claims description 6
- 230000000670 limiting effect Effects 0.000 claims description 5
- 230000007306 turnover Effects 0.000 claims description 4
- 230000000694 effects Effects 0.000 abstract description 9
- 230000032258 transport Effects 0.000 description 28
- 230000009471 action Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66F—HOISTING, LIFTING, HAULING OR PUSHING, NOT OTHERWISE PROVIDED FOR, e.g. DEVICES WHICH APPLY A LIFTING OR PUSHING FORCE DIRECTLY TO THE SURFACE OF A LOAD
- B66F7/00—Lifting frames, e.g. for lifting vehicles; Platform lifts
- B66F7/10—Lifting frames, e.g. for lifting vehicles; Platform lifts with platforms supported directly by jacks
- B66F7/16—Lifting frames, e.g. for lifting vehicles; Platform lifts with platforms supported directly by jacks by one or more hydraulic or pneumatic jacks
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66F—HOISTING, LIFTING, HAULING OR PUSHING, NOT OTHERWISE PROVIDED FOR, e.g. DEVICES WHICH APPLY A LIFTING OR PUSHING FORCE DIRECTLY TO THE SURFACE OF A LOAD
- B66F7/00—Lifting frames, e.g. for lifting vehicles; Platform lifts
- B66F7/22—Lifting frames, e.g. for lifting vehicles; Platform lifts with tiltable platforms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66F—HOISTING, LIFTING, HAULING OR PUSHING, NOT OTHERWISE PROVIDED FOR, e.g. DEVICES WHICH APPLY A LIFTING OR PUSHING FORCE DIRECTLY TO THE SURFACE OF A LOAD
- B66F7/00—Lifting frames, e.g. for lifting vehicles; Platform lifts
- B66F7/28—Constructional details, e.g. end stops, pivoting supporting members, sliding runners adjustable to load dimensions
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- Life Sciences & Earth Sciences (AREA)
- Engineering & Computer Science (AREA)
- Geology (AREA)
- Mechanical Engineering (AREA)
- Structural Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides a missile hollow shell transport frame, which belongs to the technical field of transport and comprises a movable base, a bearing frame, an external pressure assembly and an internal support assembly. According to the missile vacant shell transport rack provided by the invention, the missile vacant shell is fixed on the bearing rack by adopting the external pressure component and the internal support component, so that the fixing effect is more stable. The jacking mechanism connected to the movable base controls the height of the bearing frame, the guided missile vacant shell is lifted to the guided missile transport vehicle from the ground, the movable base facilitates the movement of the guided missile vacant shell transport vehicle or under the condition of load, and convenience is provided for the transportation of the guided missile vacant shell. The missile empty shell transport rack provided by the invention has stable fixing effect, can finish the missile placement without manually aligning the missile and the bearing rack on the transport vehicle, and greatly reduces the labor intensity of workers.
Description
Technical Field
The invention belongs to the technical field of transportation, and particularly relates to a missile hollow shell transportation frame.
Background
At present, the missiles are transported on land by adopting the mode that the missiles are decomposed and then are loaded on a missile road transport vehicle in a classified mode. Because the guided missile empty shell is large in volume and heavy in weight, the guided missile empty shell is mostly installed on a guided missile road transport vehicle through cooperation of a crane and manpower at present, but the crane body is large, a crane arm cannot freely stretch out and draw back, limitation is too strong, the guided missile empty shell needs to be manually placed by a person in the hoisting process, and the labor intensity of the person is high.
Disclosure of Invention
The invention aims to provide a guided missile empty shell transport frame, and aims to solve the problems that guided missile empty shell loading is difficult, guided missile empty shells are manually placed by personnel, and the labor intensity is high.
In order to achieve the purpose, the invention adopts the technical scheme that: provided is a missile empty-shell transport carrier, comprising:
moving the base;
the bearing frame is arranged above the movable base through a jacking mechanism;
the external pressure assembly is arranged on the bearing frame through a connecting piece; and
the inner supporting assembly comprises a driving mechanism arranged on the connecting piece and a jacking piece connected with the driving mechanism, the driving mechanism is positioned below the outer pressure assembly, and the jacking piece abuts against the inner wall of the missile hollow shell and is used for supporting the missile hollow shell;
the outer pressure assembly is pressed downwards on the outer wall of the guided missile hollow shell supported by the top piece, so that the guided missile hollow shell is stably placed on the bearing frame.
As another embodiment of the present application, the driving mechanism includes:
the supporting tube is horizontally arranged on the connecting piece;
the draw bar is arranged in the supporting pipe in a penetrating way and is used for connecting the jacking piece;
the positioning piece is arranged on the traction rod and used for limiting the axial degree of freedom of the traction rod relative to the support pipe;
the traction rod moves along the axial direction of the supporting pipe, is limited by the positioning piece and is used for driving the jacking piece to abut against the inner wall of the guided missile hollow shell.
As another embodiment of the present application, the urging member includes:
the jacking rods are respectively hinged to one end, penetrating into the supporting pipe, of the traction rod, and correspondingly penetrate through a plurality of through holes formed in the circumferential direction of the supporting pipe, and are in clearance fit with the through holes;
the traction rod axially slides along the supporting tube, so that the jacking rods are abutted against the inner wall of the missile hollow shell under the limit of the corresponding through holes.
As another embodiment of the present application, the lateral direction of the through hole is provided with two obliquely arranged sliding guide surfaces, and the two sliding guide surfaces are sequentially arranged along the axial direction of the supporting tube.
As another embodiment of the application, the free end of the tightening rod is provided with a rubber ball, and the tightening rod is used for tightening the inner wall of the missile hollow shell through the rubber ball.
As another embodiment of the application, the connecting piece is a turnover plate hinged on the bearing frame, and the external pressure component and the supporting tube are connected to the turnover plate from top to bottom.
As another embodiment of the present application, the receiving frame includes two bearing rods that are transversely arranged and parallel to each other.
As another embodiment of the application, a telescopic mechanism for adjusting the length of the bearing rod is arranged inside the bearing rod.
As another embodiment of the application, a baffle is arranged at one end, far away from the connecting piece, of the bearing frame, and the baffle is matched with the connecting piece and used for transversely pressing the missile hollow shell.
As another embodiment of the present application, the baffle is hinged to the receiving frame.
The missile empty shell transport rack provided by the invention has the beneficial effects that: compared with the prior art, the missile vacant shell transport frame adopts the external pressure component and the internal support component to fix the missile vacant shell on the bearing frame, so that the fixing effect is more stable. The jacking mechanism connected to the movable base controls the height of the bearing frame, the guided missile vacant shell is lifted to the guided missile transport vehicle from the ground, the movable base facilitates the movement of the guided missile vacant shell transport vehicle or under the condition of load, and convenience is provided for the transportation of the guided missile vacant shell. The missile empty shell transport rack provided by the invention has stable fixing effect, can finish the missile placement without manually aligning the missile and the bearing rack on the transport vehicle, and greatly reduces the labor intensity of workers.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed for the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a missile empty-shell transport rack provided by an embodiment of the invention;
FIG. 2 is a top view of a missile empty-shell carrier provided by an embodiment of the invention;
FIG. 3 is a left side view of a missile empty shell carrier provided by an embodiment of the invention;
FIG. 4 is a right side view of a missile empty shell carrier provided by an embodiment of the invention;
FIG. 5 is a sectional view taken along line A-A of FIG. 1;
FIG. 6 is a cross-sectional view of the inner support assembly;
fig. 7 is a schematic structural view of the linkage mechanism.
In the figure: 100. moving the base; 101. a motor; 102. a first cylinder; 103. a stress plate; 104. a second cylinder; 110. a receiving frame; 111. a telescopic rod; 112. a connecting member; 113. a pressure lever; 114. an arc-shaped pressing plate; 115. a first transverse plate; 116. a second transverse plate; 120. supporting a tube; 121. a draw bar; 122. a tightening rod; 123. a rubber ball; 124. fastening a nut; 130. a baffle plate; 140. a first gear set; 141. a second gear set; 142. a rack; 143. a linkage rod.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects to be solved by the present invention more clearly apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Referring to fig. 1 to 7, the missile empty shell carrier provided by the invention will be described. The missile vacant shell transport rack comprises a movable base 100, a bearing rack 110, an external pressure component and an internal support component. The bearing frame 110 is arranged above the movable base 100 through a jacking mechanism; the external pressure component is arranged on the bearing frame 110 through a connecting piece 112; the inner support assembly comprises a driving mechanism arranged on the connecting piece 112 and a tightening piece connected with the driving mechanism, the driving mechanism is positioned below the outer pressure assembly, and the tightening piece is abutted against the inner wall of the missile hollow shell and used for supporting the missile hollow shell; the outer pressure component presses down on the outer wall of the guided missile hollow shell supported by the jacking piece, so that the guided missile hollow shell is stably placed on the bearing frame 110.
Compared with the prior art, the missile vacant shell transport rack provided by the invention has the advantages that the missile vacant shell is fixed on the bearing rack 110 by adopting the external pressure component and the internal support component due to the cylindrical structure of the missile vacant shell, and the fixing effect is more stable. The guided missile vacant shell is clamped by the outer pressure component and the inner support component together and is stabilized on the bearing frame 110, the height of the bearing frame 110 is controlled by the jacking mechanism connected to the moving base 100, the guided missile vacant shell is lifted to the guided missile transport vehicle from the ground, the bearing frame 110 can extend into the guided missile transport vehicle to position the guided missile vacant shell on a guided missile vacant shell support of the guided missile transport vehicle, and then the bearing frame 110 is moved out from the lower part of the guided missile vacant shell support. The movable base 100 is convenient to move under the condition that the guided missile empty shell is transported to an overhead vehicle or a load is carried, and convenience is provided for the transportation of the guided missile empty shell. The guided missile can be placed without manually aligning the guided missile and the bearing frame 110 on the transport vehicle, so that the labor intensity of workers is greatly reduced, and the guided missile empty shell transport frame provided by the invention has the advantages of small volume, simplicity in assembly and convenience in taking and placing.
Optionally, universal wheels are mounted at the lower part of the movable base 100, so that the guided missile hollow shell transport frame can move conveniently. The jacking mechanism is a first air cylinder 102 and a second air cylinder 104 which are hinged on the movable base 100, and the first air cylinder 102 is connected with the bearing frame 110 and the movable base 100 and used for jacking the bearing frame 110; the second cylinder 104 is hinged to a side wall of the first cylinder 102, and is used for supporting the first cylinder 102 and changing an included angle between the first cylinder 102 and the movable base 100, so that the horizontal movement of the receiving frame 110 in the X direction is realized. A motor 101 connecting a first cylinder 102 and a second cylinder 104 is located above the moving base 100. The bearing frame 110 is of two parallel rod-shaped structures in the X direction and vertically connected through a stress plate 103 arranged in the Y direction, the first air cylinder 102 is connected to the stress plate 103 and used for supporting the bearing frame 110, the missile hollow shell is cylindrical, the missile hollow shell is longitudinally placed between two rods of the bearing frame 110 in the X direction, and the two rods have a limiting effect on the missile hollow shell and prevent the missile hollow shell from rolling in the Y direction. The outer pressing assembly is an arc-shaped pressing plate, the pressing plate is located above the guided missile empty shell and presses the outer wall of the guided missile empty shell, the inner supporting assembly drives the jacking piece to stretch into the guided missile empty shell through the driving mechanism and supports the guided missile empty shell from inside to outside, and the guided missile empty shell is stressed inside and outside simultaneously, so that the effect of stable clamping is achieved. The internal supporting component and the external pressure component are connected through the linkage mechanism, when the internal supporting component drives the jacking piece to abut against the inner wall of the missile hollow shell through the driving mechanism, the external pressure component compresses the outer wall of the missile hollow shell from the top of the missile hollow shell, the internal part and the external part are fixed simultaneously, the clamping is more stable, the operation is convenient, and two actions of internal supporting and external pressure can be completed only by one manual operation.
Optionally, one end of the receiving frame 110 is provided with a first horizontal plate 115, and the first horizontal plate 115 connects the two rod-shaped structures. The connecting member 112 is fixed to the first cross plate 115.
As a specific embodiment of the missile empty-shell carrier provided by the present invention, please refer to fig. 1 and 6, the driving mechanism includes a supporting tube 120 horizontally installed on the connecting member 112, a pulling rod 121 penetrating the supporting tube 120 for connecting the fastening member, and a positioning member provided on the pulling rod 121 for limiting the axial degree of freedom of the pulling rod 121 relative to the supporting tube 120; the draw bar 121 moves along the axial direction of the support pipe 120 and is limited by a positioning piece for driving the jacking piece to abut against the inner wall of the missile hollow shell. In the embodiment, the driving mechanism can realize the tensioning and withdrawing states, the driving mechanism is in the tensioning state when the guided missile vacant shell needs to be fixed, and the traction rod 121 in the driving mechanism drives the jacking piece to prop against the inner wall of the guided missile vacant shell; when the missile hollow shell needs to be taken down, firstly, the driving mechanism is changed into a retraction state, at the moment, the draw bar 121 in the driving mechanism drives the puller part to retract, and the puller part is not contacted with the missile hollow shell any more. The draw bar 121 is positioned inside the support pipe 120, and the draw bar 121 controls the position of the jacking piece and the missile hollow shell by pushing and pulling. The support tube 120 is connected to the connection member 112, and the positioning member restricts the degree of freedom of the traction rod 121 in the X direction, thereby ensuring the stability of the traction rod 121.
Alternatively, the support tube 120 may move up and down along the connection 112 due to the different diameters of the different missile casings. The connecting member 112 is provided with a longitudinal connecting groove, a plurality of connecting holes are longitudinally arranged in the connecting groove, an external thread is arranged at the connecting end of the supporting tube 120 and the connecting member 112, an internal thread is arranged in the connecting hole, and the supporting tube 120 is connected in the connecting hole through a thread.
Optionally, the traction rod 121 penetrates through the support tube 120, one end of the traction tube is connected with the tightening member, the traction rod 121 is provided with threads, the inner side of the support tube 120 is provided with threads, and the traction rod 121 can move along the axial direction by rotating.
Optionally, the supporting tube 120 is a tube with a smooth inner wall, and the supporting tube 120 is fixed on the connecting member 112 by a thread; the outer wall of the traction rod 121 is provided with threads, the traction rod 121 penetrates through the supporting pipe 120 and extends out of the connecting piece 112, a fastening nut 124 is adopted on the outer side of the connecting piece 112 to position the traction rod 121, the traction rod 121 is prevented from falling out, and the extending length of the traction rod 121 is controlled so as to control the position relation between the jacking piece and the inner wall of the missile hollow shell.
As a specific embodiment of the missile empty-shell transportation frame provided by the present invention, please refer to fig. 1 and 6, the tightening member includes a plurality of tightening rods 122, the tightening rods 122 are respectively hinged to the traction rod 121 and penetrate one end of the support tube 120, the tightening rods 122 respectively penetrate a plurality of through holes provided in the circumferential direction of the support tube 120, and the tightening rods 122 are in clearance fit with the through holes; the traction rod 121 axially slides along the support pipe 120, so that a plurality of tightening rods 122 are abutted against the inner wall of the missile hollow shell under the limit of corresponding through holes. In this embodiment, the tightening member includes at least three tightening rods 122 for connecting the traction rod 121, one end of the traction rod 121 extends out of the support tube 120, the other end of the traction rod 121 is located inside the support tube 120, a through hole corresponding to the tightening rod 122 is circumferentially formed in a side surface of one end of the support tube 120, which is away from the connecting member 112, the tightening rod 122 is connected to the traction rod 121 through the corresponding through hole, the tightening rod 122 is hinged to the traction rod 121, and the tightening rod 122 can rotate around the hinge shaft.
Optionally, a sliding block is connected to an end of the traction rod 121 penetrating into one end of the support tube 120, the tightening rod 122 is hinged to the sliding block, and the sliding block drives the tightening rod 122 to move along with the traction rod 121 along the axial direction of the support tube 120.
Referring to fig. 1 and 6, as an embodiment of the missile hollow transportation frame provided by the present invention, two obliquely arranged guiding and sliding surfaces are provided laterally to the through hole, and the two guiding and sliding surfaces are sequentially arranged along the axial direction of the support tube 120. In this embodiment, the tightening rod 122 is hinged to the traction rod 121 through a corresponding through hole, the rotational radian of the tightening rod 122 around the hinge shaft is limited by the corresponding through hole, two inclined sliding guide surfaces are disposed on the side surfaces of the through hole, the sliding guide surfaces contact with the side walls of the tightening rod 122, and when the traction rod 121 draws the tightening rod 122 to retract, the tightening rod 122 moves into the support tube 120 along the sliding guide surfaces.
Optionally, the through hole on the support tube 120 is a circular through hole, and the tightening rod 122 is a cylindrical rod.
Referring to fig. 1 and 6, as an embodiment of the missile hollow shell transport rack provided by the present invention, a rubber ball 123 is disposed at a free end of the tightening rod 122, and the tightening rod 122 tightens against an inner wall of the missile hollow shell by means of the rubber ball 123. In this embodiment, the tightening member includes a tightening rod 122 and a rubber ball 123 connected to the tightening rod 122, and the rubber ball 123 contacts with the inner wall of the missile casing and is used for tightening the missile casing. The rubber ball 123 is pressed on the missile hollow shell under the action of the jacking rod 122, the rubber ball 123 deforms under the stress, the contact area of the rubber ball 123 and the missile hollow shell is increased, and the friction force is increased.
Referring to fig. 1 and 7, as an embodiment of the missile empty shell transportation frame provided by the present invention, the connecting member 112 is a turning plate hinged to the receiving frame 110, and the external pressure component and the supporting tube 120 are connected to the turning plate from top to bottom. In this embodiment, the connecting member 112 is hinged to the receiving frame 110, the connecting member 112 can rotate around the hinge shaft, after the guided missile hollow shell is placed, the inner supporting component extending into the guided missile hollow shell and the outer pressing component pressing on the outer wall of the guided missile hollow shell are simultaneously separated through the linkage mechanism, and then the connecting member 112 is rotated around the hinge shaft and placed down.
Optionally, both ends of the receiving frame 110 are connected to the connecting member 112 through hinge shafts, and both ends of the missile casing are fixed through the external pressure component and the internal support component. When the guided missile transport frame is mounted on the guided missile empty shell, the guided missile empty shell is fixed through the arc-shaped pressing plates 114, the jacking pieces and the receiving frame 110 at the two ends, the guided missile transport frame transports the guided missile to the transport vehicle, when the guided missile empty shell is placed on the receiving frame 110 on the guided missile transport vehicle, the arc-shaped pressing plates 114 and the jacking pieces at the two ends are separated, the connecting pieces 112 at the two ends are rotated and put down, the height of the receiving frame 110 is reduced, the receiving frame 110 is moved out from the lower part of the guided missile empty shell, and the transfer of the guided missile empty shell is completed.
Optionally, the linkage is located inside the connector 112. In order to reduce the influence of the environment on the linkage mechanism, the connecting piece 112 is provided with a hollow structure, and the linkage mechanism for connecting the external pressure component and the internal support component is arranged inside the connecting piece 112. The two ends of the linkage mechanism are respectively connected with the traction rod 121 and the external pressure component, the traction rod 121 penetrates through the connecting piece 112, the linkage mechanism is connected with the traction rod 121, and the linkage mechanism is arranged in the connecting piece 112, so that the safe operation of the linkage mechanism can be ensured, and the external space can be saved.
Optionally, the external pressure assembly includes a pressure rod 113 and an arc-shaped pressure plate 114, one end of the pressure rod 113 is connected to the linkage mechanism, and the other end is connected to the arc-shaped pressure plate 114. The connecting piece 112 is provided with a connecting hole, the draw bar 121 is positioned in the connecting hole, when the missile hollow shell does not need to be internally propped, the internal support component can be detached, only the external pressure component is reserved, and at the moment, the linkage mechanism can control the pressure rod 113 on the external pressure component to perform height adjustment.
Optionally, a linkage mechanism connects the drawbar 121 and the outer pressure assembly via a gear assembly and rack 142 and a linkage rod 143. In this embodiment, the linkage mechanism includes a first gear set 140, a second gear set 141, a rack 142 and a linkage rod 143, the first gear set 140 includes a first gear engaged with teeth on the traction rod 121 and a first bevel gear rotating synchronously with the first gear, and the first gear and the first bevel gear are connected to the inner wall of the connecting member 112 through a first fixed shaft; the second gear set 141 includes a second bevel gear engaged with the first bevel gear and a second gear rotating synchronously with the second bevel gear, the second bevel gear and the second gear are connected to the inner wall of the connecting member 112 by a second fixed shaft; the rack 142 is fixed in a longitudinal slide way arranged in the connecting piece 112 and meshed with the second gear, and the rack 142 slides longitudinally along the slide way along with the rotation of the second gear; the linkage rod 143 is fixed on the rack 142 and connected with the rack 142 and the external pressure assembly; when the linkage mechanism is in a working state, the traction rod 121 drives the first gear set 140 to rotate, and further drives the second gear set 141 to rotate, and further drives the rack 142 to slide up and down, and further drives the external pressure component to slide up and down through the linkage rod 143 fixed on the rack 142.
Referring to fig. 1, the receiving frame 110 includes two load-bearing rods disposed transversely and parallel to each other. In this embodiment, the receiving frame 110 is two parallel bearing rods, and the bearing rods are used for preliminarily fixing the missile hollow shell and preventing the missile hollow shell from rotating along the Y-axis direction, so as to achieve the effect of assisting the external pressure component and the internal support component to fix the missile hollow shell. The two bearing rods are connected with the first cylinder 102 through a stress plate 103.
Referring to fig. 1 and 5, as an embodiment of the missile empty shell transport rack provided by the invention, a telescopic mechanism for adjusting the length of the load-bearing rod is arranged inside the load-bearing rod. In this embodiment, the bearing rod is two hollow rods connected together through the telescopic rod 111, a sliding groove is arranged in an inner cavity of each hollow rod, the telescopic rod 111 is located in the inner cavity of each hollow rod, and each hollow rod can move along the direction of the corresponding sliding groove to achieve the change of the length of the bearing rod. Both the hollow rod and the telescoping rod 111 are rigid materials. The length of the bearing rod can be adjusted according to different lengths of the missile shells.
Optionally, the bearing bar includes two cavity poles and establishes telescopic link 111 in cavity pole inner chamber, sets up the screw thread on the inner chamber wall of cavity pole, and telescopic link 111 is the threaded rod, and telescopic link 111 accessible rotation control stretches out the length of cavity pole to reach the effect of control bearing bar length.
Referring to fig. 1 and 4, as an embodiment of the missile hollow shell transport rack provided by the invention, a baffle 130 is arranged at one end of the receiving rack 110 away from the connecting piece 112, and the baffle 130 is matched with the connecting piece 112 for transversely pressing the missile hollow shell. In this embodiment, one end of the receiving frame 110 is provided with a connecting member 112 through a first horizontal plate 115, and the other end is connected with a baffle 130 through a second horizontal plate 116, so as to limit the missile hollow shell along the X direction.
Referring to fig. 1 and 4, as an embodiment of the missile empty-shell carrier provided by the present invention, a baffle 130 is hinged to the receiving frame 110. In this embodiment, the baffle 130 is connected to the receiving frame 110 by a hinge shaft, and the baffle 130 is rotatable around the hinge shaft.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. Guided missile sky shell transportation frame, its characterized in that includes:
moving the base;
the bearing frame is arranged above the movable base through a jacking mechanism;
the external pressure assembly is arranged on the bearing frame through a connecting piece; and
the inner supporting assembly comprises a driving mechanism arranged on the connecting piece and a jacking piece connected with the driving mechanism, the driving mechanism is positioned below the outer pressure assembly, and the jacking piece abuts against the inner wall of the missile hollow shell and is used for supporting the missile hollow shell;
the outer pressure assembly is pressed downwards on the outer wall of the guided missile hollow shell supported by the top piece, so that the guided missile hollow shell is stably placed on the bearing frame.
2. The missile launcher system of claim 1, wherein the drive mechanism comprises:
the supporting tube is horizontally arranged on the connecting piece;
the draw bar is arranged in the supporting pipe in a penetrating way and is used for connecting the jacking piece;
the positioning piece is arranged on the traction rod and used for limiting the axial degree of freedom of the traction rod relative to the support pipe;
the traction rod moves along the axial direction of the supporting pipe, is limited by the positioning piece and is used for driving the jacking piece to abut against the inner wall of the guided missile hollow shell.
3. The missile launcher system of claim 2, wherein the top member comprises:
the jacking rods are respectively hinged to one end, penetrating into the supporting tube, of the traction rod, and correspondingly penetrate through a plurality of through holes formed in the circumferential direction of the supporting tube, and are in clearance fit with the through holes;
the traction rod axially slides along the supporting tube, so that the jacking rods are abutted against the inner wall of the missile hollow shell under the limit of the corresponding through holes.
4. The missile hollow carrier as claimed in claim 3, wherein the through hole is laterally provided with two obliquely arranged guide sliding surfaces, and the two guide sliding surfaces are sequentially arranged along the axial direction of the supporting pipe.
5. The missile hollow carrier of claim 3, wherein the free end of the tightening rod is provided with a rubber ball, and the tightening rod is used for tightening the inner wall of the missile hollow by means of the rubber ball.
6. The missile hollow carrier of claim 2, wherein the connecting member is a turnover plate hinged to the receiving frame, and the outer pressure component and the support tube are connected to the turnover plate from top to bottom.
7. The missile launcher of claim 1, wherein the adapter comprises two load bearing bars disposed transversely and parallel to each other.
8. The missile hollow carrier of claim 7, wherein the bearing rod is internally provided with a telescopic mechanism for adjusting the length of the bearing rod.
9. The missile casing transport rack of claim 1, wherein the end of the receiving rack remote from the connector is provided with a baffle plate, and the baffle plate is matched with the connector for transversely pressing the missile casing.
10. The missile launcher system of claim 9, wherein the skirt is hinged to the receiving rack.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011295122.XA CN112320681B (en) | 2020-11-18 | 2020-11-18 | Guided missile hollow shell transport rack |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011295122.XA CN112320681B (en) | 2020-11-18 | 2020-11-18 | Guided missile hollow shell transport rack |
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| Publication Number | Publication Date |
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| CN112320681A true CN112320681A (en) | 2021-02-05 |
| CN112320681B CN112320681B (en) | 2022-08-05 |
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| CN202011295122.XA Active CN112320681B (en) | 2020-11-18 | 2020-11-18 | Guided missile hollow shell transport rack |
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