CN111776475A - Rocket packaging method and manufacturing method of packaging box section - Google Patents
Rocket packaging method and manufacturing method of packaging box section Download PDFInfo
- Publication number
- CN111776475A CN111776475A CN202010660085.1A CN202010660085A CN111776475A CN 111776475 A CN111776475 A CN 111776475A CN 202010660085 A CN202010660085 A CN 202010660085A CN 111776475 A CN111776475 A CN 111776475A
- Authority
- CN
- China
- Prior art keywords
- rocket
- packaging
- section
- hollow
- pulling
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
- B65D81/00—Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents
- B65D81/02—Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents specially adapted to protect contents from mechanical damage
- B65D81/05—Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents specially adapted to protect contents from mechanical damage maintaining contents at spaced relation from package walls, or from other contents
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
- B65D25/00—Details of other kinds or types of rigid or semi-rigid containers
- B65D25/02—Internal fittings
- B65D25/10—Devices to locate articles in containers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
- B65D85/00—Containers, packaging elements or packages, specially adapted for particular articles or materials
- B65D85/68—Containers, packaging elements or packages, specially adapted for particular articles or materials for machines, engines or vehicles in assembled or dismantled form
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Buffer Packaging (AREA)
- Packaging Of Machine Parts And Wound Products (AREA)
Abstract
The invention discloses a packaging method for rockets and a preparation method for a packaging box section. The packaging method comprises the following steps: providing a packing box section, wherein the packing box section comprises a packing body part matched with the shape of the outer surface of the rocket to be packed, which extends along the axial direction, and a tension piece arranged on the body part; -arranging the packing box section on an axially extending outer surface of the rocket to be packed, and-pulling the tension member to cause the packing body portion to unfold along the outer surface. According to the embodiment of the invention, the packing box section is arranged on the rocket to be packed, and the packing body part is unfolded on the outer surface of the rocket through the tensioning piece, so that the packing flexibility of the rocket is improved, and the packing effect is improved.
Description
The application is filed on 27.2.2018 and is named as a division application of an invention patent with the application number of '201810160449.2', namely 'a packaging method for a rocket, a preparation method of a packaging box section and the packaging box section'.
Technical Field
The invention relates to the technical field of transportation of carrier rockets, in particular to a packaging method of a rocket and a preparation method of a packaging box section.
Background
During transport of the launch vehicle, special custom packaging boxes are often required. In general, in order to ensure the safety of the rocket, the packing case may have functions of water proofing, dust proofing, electricity proofing, and the like. In addition, the packing box can prevent the damage to the arrow body caused by uncontrollable unexpected factors such as broken stones splashed from the road surface or cargo throws.
The outer skin with the full-wrapping structure has high production difficulty and is inconvenient to operate. Therefore, a rocket packaging box which is convenient to operate and simple to prepare is needed to meet the requirements of transportation and storage of rockets.
Disclosure of Invention
Aiming at the technical problems in the related art, the invention provides a rocket packaging method, a packaging box section manufacturing method and a packaging box section. The rocket packaging method provided by the embodiment of the invention is simple to operate, so that the rocket packaging difficulty is obviously reduced while the transportation safety of the rocket is ensured.
One aspect of the present invention provides a method of packaging a rocket. The method comprises the following steps: providing a packing box section, wherein the packing box section comprises a packing body part matched with the shape of the outer surface of the rocket to be packed, which extends along the axial direction, and a tension piece arranged on the body part; -arranging the packing box section on an axially extending outer surface of the rocket to be packed, and-pulling the tension member to cause the packing body portion to unfold along the outer surface.
In one embodiment, the providing a packing box section comprises: providing a first packing box section and a second packing box section, wherein the first packing box section comprises a first packing body part and a first tensioning piece which are used for matching the shape of the outer surface of the rocket to be packed, and the second packing box section comprises a second packing body part and a second tensioning piece which are used for matching the shape of the outer surface of the rocket to be packed; the disposing the packing case section to an axially extending outer surface of the rocket to be packed and the expanding the packing body portion along the outer surface by pulling the tension member includes: disposing the first packing box section on a first axially extending outer surface of the rocket to be packed and pulling the first tensioning member to deploy the first packing body section along the first outer surface; and positioning the second package box section on a second axially extending outer surface of the rocket to be packaged, and pulling the second tensioning member to deploy the second package body portion along the second outer surface; wherein the first outer surface and the second outer surface are two surfaces that are close to each other in an axial direction thereof for a rocket to be packaged.
In one embodiment, said positioning said second package box section on a second outer surface of said rocket to be packaged extending in an axial direction and pulling said second tension member to deploy said second package body portion along said second outer surface further comprises: overlapping portions of the second section and the first section adjacent to each other.
In one embodiment, the providing a packing box section comprises: providing a plurality of packaging box sections; the disposing the packing case segment on the axially extending outer surface of the rocket to be packed and pulling the tension member to expand the packing body portion along the outer surface comprises: and overlapping and bonding a plurality of packing box sections along the axial outer surface of the rocket to be packed, wherein two packing box sections on the outermost side of the rocket to be packed in the axial direction are respectively arranged on the outer layer and the inner layer.
In one embodiment, the body portion includes a flexible packing layer and a plurality of buffer blocks arranged in sequence on at least one major surface side of the flexible packing layer in a first direction, and the tension member includes a plurality of hollow members provided to the body portion in the first direction and a pulling rope for passing through hollow portions of the plurality of hollow members; said unfolding the body portion of the package along the outer surface by pulling the tension member comprises: fixing one end of the pull rope, and pulling the other end of the pull rope to connect the plurality of hollow pieces end to form a shape matched with the axial section of the rocket to be packaged, so that the flexible packaging layer and the plurality of buffer blocks of the packaging body part are unfolded along the outer surface.
In one embodiment, the plurality of hollow members comprises a first hollow tube comprising a first connecting structure and a second hollow tube comprising a first mating structure adjacent to each other; the fixing one end of the pull rope to connect the plurality of hollow pieces end to combine into a shape matching the axial cross section of the rocket to be packaged, so that the flexible packaging layer and the plurality of buffer blocks of the packaging body part are spread along the outer surface comprises: combining the first connecting structure and the first mating structure with each other so that the combined first hollow tube and second hollow tube have a first shape matching a portion of the rocket shaft cross-sectional shape.
In one embodiment, the first shape is a portion of a circular ring or two sides of a polygonal structure.
Another aspect of the invention provides a method of making a packaging box section comprising: providing a flexible packaging layer, a cushion block and a tensioning piece, wherein the flexible packaging layer comprises two main surfaces and side surfaces connecting the two main surfaces; the method comprises the steps of arranging the buffer block on at least one main surface of the flexible packaging layer, and arranging the tension piece on at least one of the protective outer layer and the buffer block along a first direction, wherein the tension piece is used for pulling the flexible packaging layer and/or the buffer block so as to expand the flexible packaging layer and the buffer block on the outer surface of the rocket to be packaged, which extends along the axial direction.
In one embodiment, the cushion block includes a plurality, and the disposing the cushion block on at least one major surface of the flexible packaging layer includes: and fixing the plurality of buffer blocks on the at least one main surface of the flexible packaging layer in parallel along the first direction.
In one embodiment, the tension member comprises a plurality of hollow tubes and a pull cord, and the positioning the tension member in a first direction on at least one of the flexible packaging layer and the cushion block comprises: fixedly connecting the plurality of hollow tubes to at least one of the side surface or the two main surfaces in sequence along the first direction, and enabling the pull rope to penetrate through the plurality of hollow tubes, so that the plurality of hollow tubes are connected end to end by pulling the pull rope to be matched with the shaft section of the rocket to be packaged.
Yet another aspect of the invention provides a packing box section for a rocket, comprising: a packaging body portion and a tension member; the packing body part is used for being arranged on the outer surface of the rocket to be packed, which extends along the axial direction, and the tensioning piece is used for pulling the packing body part so as to enable the packing body part to be unfolded on the outer surface.
In one embodiment, the package body portion comprises a flexible package layer and a plurality of buffer blocks; wherein the flexible packaging layer comprises a first major surface and a second major surface opposite to each other and a side connecting the first major surface and the second major surface; the plurality of buffer blocks are arranged in order on the first main surface side in the first direction.
In one embodiment, the tension member includes a plurality of hollow members and a draw string for passing through hollow portions of the plurality of hollow members; wherein the plurality of hollow members are disposed in at least one of the flexible wrapping layer and the plurality of buffer blocks in the first direction so that the plurality of hollow members are connected end to form a shape matching an axial cross-section of the rocket to be wrapped when the pulling string is pulled.
In one embodiment, the plurality of hollow members comprises a first hollow tube and a second hollow tube adjacent to each other; the first and second hollow tubes include first connecting and mating structures, respectively, for connecting to each other.
In one embodiment, the first connection structure comprises a conical bore and the second mating structure comprises a truncated cone for mating with the conical bore, or the first connection structure comprises a ball head and the second mating structure comprises a socket for mating with the ball head.
In one embodiment, the hollow member is an elbow and both ends of the elbow have coupling structures that mate with adjacent elbows so that a plurality of elbows meet end to form a circular ring structure when the pull cord is pulled, or the hollow member is a straight tube and both ends of the straight tube have angled coupling faces for coupling with adjacent straight tubes so that a plurality of straight tubes meet end to form a polygonal ring structure when the pull cord is pulled.
In one embodiment, the buffer block is strip-shaped and has a circular arc-shaped or rectangular cross section.
In one embodiment, the flexible packaging layer is a fabric having water, dust, and static resistance.
The rocket packaging method provided by the embodiment of the invention can obviously reduce the rocket packaging difficulty and improve the rocket packaging effect by packaging the rocket in sections.
Those skilled in the art will recognize additional features and advantages upon reading the detailed description, and upon viewing the accompanying drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments 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 flow chart of a rocket wrapping method according to an embodiment of the present invention.
FIG. 2 is a schematic view of an unfolded configuration of a section of a packing box according to an embodiment of the present invention.
Fig. 3 is a schematic view showing a connection structure of two adjacent hollow tubes according to an embodiment of the present invention.
Fig. 4 is a flow chart of the preparation of a packaging box section according to an embodiment of the invention.
Fig. 5a is an expanded view of a section of a package according to an embodiment of the invention.
Fig. 5b and 5c are three-dimensional schematic views of the structure of a packaging box section according to an embodiment of the present invention.
Fig. 6a-6c are schematic views of the structure of a packaging box section according to an embodiment of the invention.
Fig. 7 is a schematic view showing the structure and connection of adjacent hollow tubes in a tension member according to an embodiment of the present invention.
Fig. 8 is a schematic view of the construction of a section of a packing box and its tension members according to an embodiment of the invention.
Fig. 9a-9b are schematic views of the structure of a packing box section provided with a buffer block in the embodiment of the invention.
Detailed Description
The technical scheme of the invention is further explained by the specific implementation mode in combination with the attached drawings. Spatially relative terms such as "below," "… below," "lower," "above," "… above," "upper," and the like are used for convenience in describing the positioning of one element relative to a second element and are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc. and should not be taken as limiting. Like terms refer to like elements throughout the description.
In accordance with standards relating to road transport vehicle management, it is generally required that the overall width of the vehicle be no greater than 2.55 meters, and that the width dimension of a standard container be 2.438 meters, which conditions generally cause the bulky launch vehicle to exceed the relevant transport regulations after packaging. Consequently, rocket cases often require special customization.
Conventional arrow-body packaging boxes take the form of a fully-wrapped outer skin made of metal. This form of coating has the following disadvantages: firstly, the requirements on the strength and the rigidity of the outer skin are strict, so that the production difficulty and the preparation cost are improved. Secondly, the packaging mode of the fully-coated outer skin usually needs to leave a certain safety gap between the rocket and the packaging box, thereby further increasing the packing size of the rocket and increasing the possibility that the outer side of the packaging box exceeds the height limit of road transportation. Thirdly, the box structure of the skin coated outside the all-metal is heavy in weight and large in overall dimension, so that the rocket body is inconvenient to hoist and pack and occupies a large storage space. Fourthly, the traditional arrow coat is not provided with a buffer material, so that the arrow body is easily damaged by mechanical impact during transportation and storage.
In view of the above, one aspect of the present invention provides a method of packaging a rocket. Referring to fig. 1, the packaging method includes: s100, providing a packing box section, wherein the packing box section comprises a packing body part and a tension piece, the packing body part is used for matching the shape of the outer surface of the rocket to be packed, and the outer surface of the rocket to be packed extends along the axial direction, and the tension piece is arranged on the body part. S200 sets the packing case section to the outer surface of the rocket to be packed extending in the axial direction, and S300 pulls the tension member to spread the packing body section along the outer surface of the rocket. According to the embodiment of the invention, the packing box section is arranged on the rocket to be packed, and the packing body part is unfolded on the outer surface of the rocket through the tensioning piece, so that the packing flexibility of the rocket is improved, and the packing effect is improved.
It should be noted that the term "rocket" as used in the preceding and subsequent sections of the present invention is intended to refer to a wide range of rockets, including both launch vehicles for carrying satellites or spacecraft or other detectors, and weapons such as missiles, rocket projectiles and the like of the type used to carry military loads. The term "rocket" as used in this patent is not to be construed restrictively by those skilled in the art.
In one embodiment, the S100 providing a packing box section includes: a plurality of packing box sections are provided. For example, each packing box section comprises a packing body portion and a tension member. And the packing body parts are arranged on the outer surface of the rocket to be packed, which extends along the axial direction, and the packing body parts are unfolded on the section of the rocket surface by pulling the tensioning piece arranged on the packing body parts, so that the packing of the section of the rocket is realized. The other axially extending outer surfaces of the rocket to be packaged can then be packaged in the same manner by other package box sections in order to achieve a segmented packaging of the entire rocket to be packaged. Two adjacent packing box sections can be overlapped through adhesive tapes. For example, the two end edges of one of the packing box sections may be provided with an annular or partially annular adhesive tape, and the edge of the other packing box section close to the packing box section may cover the outside of the adhesive tape, so as to fix the two packing box sections to each other and further prevent dust or other impurities from entering the inside of the packing box section to affect the rocket performance. The connection method of two adjacent packing box sections is not limited to overlapping, and may be sewing, clamping, binding, or the like. Alternatively, the adjacent portions of two adjacent packaging box sections can be provided with connecting structures for fitting with each other.
It should be noted that the sections may be wrapped sequentially from one end of the rocket to the other. The rocket to be packaged can also be packaged from the middle part to two sides of the rocket to be packaged. Alternatively, the wrapping sequence may be selected based on the relative positions of the rocket and the packing box sections, as the invention is not limited in this respect. In addition, the wrapping body portion may cover a part of the outer surface of the rocket or may cover the entire outer surface in the circumferential direction of the rocket. That is, after the rocket is packaged by the packaging box section, the outer surface of the rocket in the circumferential direction can be partially exposed or can be completely coated. The rocket packaging method provided by the embodiment of the invention can obviously reduce the packaging difficulty of the rocket and improve the packaging effect of the rocket by packaging the rocket in sections.
In addition, the tension member may be disposed along the direction of deployment of the body portion of the package. For example, when the wrapping body is designed in an expanding manner along the circumferential direction of the rocket to be wrapped, the tightening pieces may be provided at both ends of the wrapping body along the circumferential direction of the rocket after the wrapping body is expanded on the outer surface of the rocket to be wrapped. For example, the tension member may be a wire-like structure which may be snugly disposed along one surface of the packaging body portion, with both ends of the wire-like tension member protruding from both sides of the packaging body portion, for example. Therefore, after the packaging body part is arranged on the rocket to be packaged, the two end parts of the traction piece can be pulled, so that the packaging body part is completely unfolded on the surface of the rocket to be packaged, which extends along the axial direction, and the packaging of the section of the rocket to be packaged is realized.
In one embodiment, the S100 providing the packing box section comprises: providing a plurality of packaging box sections; the step of arranging the packing box section on the outer surface of the rocket to be packed, which extends along the axial direction, and the step of pulling the tension piece to enable the packing body part to be unfolded along the outer surface of the rocket comprises the following steps: and overlapping and bonding a plurality of packing box sections along the axial outer surface of the rocket to be packed, wherein the two packing box sections on the outermost side of the rocket to be packed in the axial direction are respectively arranged on the outer layer and the inner layer. For example, when a transport vehicle is used for transporting the rocket, the rocket end of the packing box section arranged on the inner layer faces the tail direction of the rocket, and the other end of the rocket is transported towards the head direction of the rocket, so that dust or sundries are better prevented from entering the packing box, and the transport safety of the rocket is improved.
In the embodiment of the invention, the box sections at two end parts of the rocket to be packaged are respectively arranged at the outer side and the inner side (for example, under the condition that two adjacent box sections are mutually overlapped, the packing box at one end part of the rocket to be packaged is arranged close to the rocket, the outer surface of the end part is provided with the adhesive layer, and the adjacent box section is adhered to the adhesive layer of the box section), so that the box section arranged at the inner side is outwards arranged and the box section arranged at the outer side is arranged close to the vehicle head when the rocket is transported, thereby better avoiding sundries from entering the interior of the packing box and preventing the performance of the rocket from being influenced.
In this embodiment, in order to better avoid the sundries from entering the rocket package box and avoid the increase of the external thickness difference of the package box, two edges of each package box section along the rocket axial direction can be alternately arranged on the inner side and the outer side respectively. That is, starting from one end of the rocket, a first packing box section is disposed on the inside, one side of a second packing box section adjacent thereto, which is close to the first packing box section, is disposed on the outside, and the other side of the second packing box section is disposed on the inside (e.g., disposed in close proximity to the outer surface of the rocket). Analogize in proper order, the third packing box section be close to second packing box section one side and set up in the outside, and the opposite side setting of third packing box section is in the inboard to the edge that adjacent packing box section was kept away from to last packing box section sets up in the inboard. According to the embodiment of the invention, the edges of the two packing box sections which are far away from each other along the outermost side of the rocket in the axial direction are arranged on the inner sides, so that dust and sundries can be prevented from entering the packing boxes from two directions, and the safety of rocket transportation is further improved.
Referring to fig. 2, in one embodiment, the body part 1 includes an outer layer fabric 11 and a plurality of buffer blocks 12 sequentially arranged in a first direction (a direction shown by an arrow in the drawing) on at least one major surface side of the outer layer fabric 11. The tension member 2 includes a plurality of hollow members 21 provided to the body portion 1 in the first direction and a string 22 for passing through the hollow portions of the plurality of hollow members 21. Unfolding the packaging body portion 1 along said outer surface by pulling the tension member 2 comprises: one end of the pulling rope 22 is fixed, and the other end of the pulling rope 22 is pulled so that the plurality of hollow members 21 are connected end to be combined into a shape matching the axial section of the rocket to be packaged, whereby the outer fabric 11 of the packaging body portion 1 and the plurality of cushion blocks 21 are spread along the outer surface. According to the embodiment of the invention, the buffer block and the tensioning piece for pulling the outer fabric and the buffer block are arranged, so that the packaging body part can be tightly attached to the outer surface of the rocket to be packaged, and on one hand, the gap between the rocket and an outer package can be reduced, thereby reducing the external size of the rocket during transportation and avoiding the influence of road transportation limitation; in addition, because the gap between the rocket and the outer package is small, the mechanical impact in the transportation process of the rocket to be packaged is reduced, and the safety of rocket transportation is improved.
In this embodiment, for example, the arrangement direction of the hollow members 21 may coincide with the arrangement direction of the buffer blocks 12. Specifically, the buffer blocks 12 may be disposed side by side in sequence on one main surface of the outer layer fabric 11, and both ends of the plurality of hollow members 21 may be disposed end to end. For example, the hollow members 21 may be sequentially stuck or bound on one surface of the plurality of cushion blocks 12 or the outer fabric 11, so that the plurality of hollow members 21 may be connected end to form a shape matching, for example, the circumference of the rocket when the pulling rope 22 is pulled. That is, the hollow members 21 are joined end to constitute a skeleton of the outer fabric 11 and the cushion block 12, and the outer fabric 11 and the cushion block 12 are supported in a shape similar to the rocket circumferential direction.
In this embodiment, for example, in order to make the packing effect of the packing case segments better, for example, a plurality of skeleton structures composed of hollow members 21 may be arranged at intervals in a direction perpendicular to the arrangement direction of the cushion blocks 12 (i.e., the direction indicated by the arrow in fig. 2). I.e. several parallel to the tension member shown in fig. 2. For example, two tension members may be disposed at both ends of the outer fabric perpendicular to the arrangement direction of the buffer blocks in the outer fabric 11, respectively, in the direction perpendicular to the arrangement direction of the buffer blocks 12, thereby improving the packing effect. For example, when the wrapping body portion provided with two skeletons composed of hollow members is expanded on the outer surface of the rocket extending in the axial direction, the two skeletons are located at both ends of the section in the axial direction of the rocket to be wrapped.
It should be noted that, after the outer layer fabric 11 and the cushion block 12 are unfolded by the pull rope 22, both ends of the pull rope 22 may be fixed to, for example, a vehicle, or fixed to the vehicle through a tensioner, respectively, thereby improving reliability of rocket packaging.
In the above embodiment, for example, the outer layer fabric 11 may be a flexible fabric. In particular, the flexible fabric may be a waterproof, dustproof and antistatic polymer material. The buffer block can be made of rubber, foam or plastic and the like, so that the outer surface of the rocket can be prevented from being scratched. The embodiment of the invention adopts the forms of the outer layer fabric and the buffer block, thereby not only greatly lightening the weight of the packing box section, but also reducing the storage space and facilitating the storage, transportation and packing of the outer package.
Referring to fig. 3, in one embodiment, the plurality of hollow members 21 includes a first hollow tube 23 and a second hollow tube 24 adjacent to each other. Wherein the first hollow tube 23 includes a first connecting structure 25 and the second hollow tube 24 includes a first mating structure 26. Fixing one end of the pulling rope 22 so that the plurality of hollow members 21 are connected end to be combined into a shape matching the axial section of the rocket to be packaged, whereby the deployment of the outer fabric 11 and the plurality of the bump stoppers 12 of the packaging body portion 1 along the outer surface of the rocket includes: the first connecting structure 25 and the first fitting structure 26 are joined to each other so that the joined first hollow tube 23 and second hollow tube 24 have a first shape matching a part of the sectional shape of the rocket shaft to be packaged. For example, the two hollow tubes 23, 24 may be bent tubes, so that the first shape may be a circular ring or a part of a circular ring. For example, the two hollow tubes may be straight tubes, and thus the first shape may be two sides of a polygon. For example, the two hollow tubes may be fitted through a conical bore and a truncated cone, or the two hollow tubes may be fitted through a ball and socket.
In the embodiment of the invention, for example, the front blocking cover and the rear blocking cover can be arranged at the front end and the rear end of the rocket outside the rocket body packaged with the rocket, so that the rocket is better protected.
Another aspect of the invention provides a method of making a packaging box section. Referring to fig. 4, the preparation method includes: s1000 provides a flexible packaging layer, a buffer block and a tensioning piece. Wherein the flexible package outer layer comprises two main surfaces and a side surface connecting the two main surfaces. S2000 disposing the cushion block to at least one major surface of the protective outer layer, and S3000 disposing a tension member to at least one of the flexible packaging layer and the cushion block in a first direction. Wherein the tensioning member is adapted to pull the flexible wrapping layer and/or the bumper block so as to spread the flexible wrapping layer and the bumper block apart on an axially extending outer surface of the rocket to be wrapped. According to the preparation method of the packing box section, the buffer block, the tensioning piece and the flexible packing layer are arranged, so that the packing box section which is easy to hoist and store and can conveniently pack the rocket can be obtained.
In one embodiment, the buffer block includes a plurality, and the S2000 disposing the buffer block to at least one major surface of the flexible packaging layer includes: and fixing the plurality of buffer blocks on the at least one main surface of the flexible packaging layer in parallel along the first direction. For example, the buffer block may be a foam, rubber, or the like. The first direction may, for example, be any direction along one of its major surfaces after the flexible packaging layer has been unfolded. For example, the first direction may be a straight line or a curved line or include both a straight line and a curved line. Further, the first direction may be a direction parallel to one side of the major surface of the unfolded flexible packaging layer. For example, if the protective outer layer is square after deployment, the first direction may be a direction parallel to one side of the square. Further, the length of the buffer block may be substantially equal to the length of the side length of the square. For example, the number of the buffer blocks arranged in the first direction may be 3 to 25.
It should be noted that, after the cushion block is provided to the flexible wrapping layer, when the rocket to be wrapped is wrapped with the packing case section, the cushion block and the flexible wrapping layer can be spread in the direction of the outer circumference of the rocket under the condition of pulling the tension member. That is, in the case where the flexible wrapping layer is unfolded, the arrangement direction of the plurality of cushion blocks coincides with the direction of the outer circumference of the rocket when the package box section is wrapped in the rocket. For example, the bumper may be an elongated structure that may be arcuate in cross-section so as to better match the axially extending outer surface of the rocket after the bumper is deployed on the outer surface of the rocket. In addition, the arrangement distance of the buffer blocks can be adjusted according to the peripheral dimension of the rocket to be packaged, the elasticity of the outer packaging layer and the size of the buffer blocks (for example, in the case that the outer packaging layer is made of elastic high polymer materials, the distance of the buffer blocks can be 0.5-1cm, and in the case of materials with poor elasticity, the distance of the buffer blocks can be 0.1-0.3 cm).
In one embodiment, the tension member comprises a plurality of hollow tubes and a pull cord. S300, disposing the tension member to at least one of the flexible packaging layer and the cushion block along the first direction includes: fixedly connecting a plurality of hollow tubes to at least one of the side surface and the two main surfaces in sequence along a first direction, and enabling the pull ropes to penetrate through the hollow tubes, so that the hollow tubes are connected end to end and matched into a shape matched with the shaft section of the rocket to be packaged by pulling the pull ropes. According to the preparation method of the packing box section provided by the embodiment of the invention, through the matching of the hollow pipes and the pull ropes, when the pull ropes are pulled, the hollow pipes are connected end to form a structure matched with the outer periphery of the rocket.
For example, a plurality of hollow tubes may be sequentially linearly disposed in a first direction on the deployed surface of the flexible packaging layer and/or the cushion block. For example, two rows of hollow tubes may be included, such that when the rocket is packaged, the two rows of hollow tubes may form an annular skeleton structure at the front and rear ends of the packing box section, respectively, thereby making the unfolding and tightening of the packing box section more reliable. For example, the hollow tubes can be arranged in multiple rows, so that after the hollow tubes in each row are pulled, the hollow tubes in the row can be connected end to form a shape matched with the periphery of the rocket to be packaged, so that the radial strength of the package box section is further improved, and the package reliability of the rocket box section is improved.
In yet another aspect of the invention, a packing box section for a rocket is provided. Referring to fig. 5a-5c, the packing box section comprises: the body portion 1 and the tension member 2 are packed. Wherein the body portion 1 is arranged on an outer surface of the rocket to be packaged extending along the axial direction, and the tension member 2 is used for pulling the body portion 1 to unfold the body portion on the outer surface. According to the packing box section, the body part and the tensioning piece are arranged, so that the rocket can be conveniently packaged in sections, and the packaging difficulty is reduced.
In this embodiment, for example, the body portion may be of foldable material. The body portion 1 is, for example, a material having waterproof, electricity-proof and dust-proof functions. Specifically, the body part 1 may include a polymer fabric material.
With continued reference to figures 5a-5c, for example, the tension member 2 may be a pull cord provided only at either end of the body portion 1 or extending in one direction through the interior of the body portion 1 or across at least one surface of the body portion 1. For example, the pull string may be sewn, adhered or tied to the body 1 so that when the rocket is packaged, the body 1 may be first placed on the outer surface of the rocket extending in the axial direction, and the body 1 is pulled tight and tightly attached to the outer surface of the rocket by pulling the portions of the pull string located at both ends of the body 1. For example, the ends of the pull cord may be tied directly to the vehicle or through a tensioner to the vehicle.
Referring to figure 6a, in one embodiment the packaging body portion 1 comprises a flexible packaging layer 11 and a plurality of cushioning blocks 12. Wherein the flexible packaging layer 11 comprises a side having a first and a second main surface opposite to each other and connecting the first and the second main surface. The plurality of buffer blocks 12 are arranged in order on the first main surface side in the first direction. That is, outer wrapper 11, after being unfolded, may include a first major surface and a second major surface, and a plurality of cushion blocks 12 may be disposed on one or both major surfaces, for example, in the first direction. For example, a plurality of buffer blocks 12 may be arranged side by side in the first direction. The embodiment of the invention provides the body part comprising the outer packaging layer and the plurality of buffer blocks, so that waterproof, dustproof and antistatic functions can be given to the rocket, and the plurality of buffer blocks can be directly contacted with the rocket to be packaged, thereby avoiding mechanical collision with the outer packaging when the rocket is moved, hoisted or transported, and improving the safety of rocket transportation.
Referring to fig. 6b, in one embodiment, the tension member 2 includes a plurality of hollow members 21 and a pull cord 22 for passing through the hollow portions of the hollow members 21. Wherein a plurality of hollow members 21 are provided in at least one of the flexible wrapping layer 11 and the plurality of buffer blocks 12 in the first direction so that the plurality of hollow members 21 are connected end to form a shape matching the axial section of the rocket to be wrapped when the pulling rope 22 is pulled. The tension member 2 of the embodiment of the invention is provided with the hollow member 21 and the pull rope 22 for penetrating through the hollow member 21, so that when the packaging body part 1 is arranged on the outer surface of the rocket to be packaged, the plurality of hollow members 21 can be conveniently connected end to end by pulling the pull rope 22 to form a framework which is matched with the outer surface of the rocket in the circumferential direction along the axial direction, and the packaging body part 1 is attached to the outer surface of the rocket.
For example, the hollow member may be a hollow tube as described in fig. 6a and 6 b. As mentioned above, the tension member 2 may have several rows in the case of unfolding the body portion 1 of the package. For example, as shown in figure 6c, a row may be provided at each of the flared front and rear ends F1 and F2 of the body portion 1 (i.e. the box section comprises the tension member shown in figures 6a and 6b and a tension member disposed at a position corresponding to the inner side as shown in the figures). For example, a plurality of rows of tension members may be spaced apart from one another. In particular, the number of rows of tension members may be determined by the length of the section of box, the material of the body portion of the package, etc. In general, in order to make the packing box section having the ring frame made of the hollow material stronger when packing the rocket, the longer the length of the packing box section is, the softer the material of the packing body portion is, the more the number of rows of the tension members is required. In order to provide the packaging box section with a certain strength, it is usually possible, for example, to provide the packaging box section with a row of tensioning elements at least at the front and rear ends of the packaging box section.
In the above embodiment, for example, the adjacent two hollow tubes 23, 24 may include the first connecting structure 25 and the first fitting structure 26 for connecting to each other. For example, as shown in fig. 7, the first connection structure 25 comprises a conical bore and the second mating structure 26 comprises a truncated cone for mating with the conical bore, or the first connection structure 25 comprises a ball head and the second mating structure 26 comprises a ball socket for mating with the ball head. The parts of the hollow pipes close to each other are respectively provided with the structures matched with each other, so that the hollow pipes can be conveniently connected with each other when the pull rope is pulled, and a framework for supporting the packaging body part is formed.
Referring to fig. 8, in one embodiment, the hollow member 21 may be an elbow, and the two ends of the elbow have mating connection structures with adjacent elbows, so that when the pull cord is pulled, the elbows meet end-to-end to form a partial circular ring structure as shown in fig. 8. Or the hollow part 21 is a straight pipe, and two ends of the straight pipe are provided with inclined connecting surfaces for connecting with adjacent straight pipes, so that when the pull rope is pulled, a plurality of straight pipes are connected end to form a polygonal annular structure. According to the invention, the hollow part is of a bent pipe or straight pipe structure, so that a circular ring or polygonal structure can be easily formed, the overall dimension of the packing box is reduced, and the packing effect of the rocket is improved.
In this embodiment, for example, a row of bent or straight tubes contains 3-13 bent or straight tubes (the number of bent tubes shown in fig. 8 is 11), so that when the same row of bent or straight tubes forms a skeleton, the outer dimension of the package box can be reduced, the package box section can be better attached to the outer surface of the rocket, and the package effect of the rocket can be improved.
As shown in fig. 8, for example, bent tubes (or straight tubes) may be arranged in the packaging body portion 1, the pull cord 22 may be passed through the bent tubes (or straight tubes) in the same row, and both ends may protrude from the bent tubes located on the outermost side, for example. The function of the pull cord 22 is to position the motion trajectory of the curved tubes (or straight tubes) so that when the pull cord 22 is pulled, the curved tubes (or straight tubes) in the same row are precisely butted against each other after the cord body of the pull cord 22 moves to form a desired shape (e.g., a circular ring, a partial circular ring, a polygonal shape, etc.). For example, the size of the pull cord 22 may match the size of the hollow member 21. For example, the internal dimensions of the hollow tubes 21 may be slightly larger than the external dimensions of the pull cord 22, thereby improving the accuracy of the butt joint of the hollow tubes to each other.
Referring to fig. 9a and 9b, in one embodiment, the bumper 12 is elongated and has a circular or rectangular cross-section (the bumper shown in fig. 9a and 9b has a circular cross-section with a smaller arc). For example, as shown in fig. 9a and 9b, the length of the elongated bumper 12 may be approximately equal to the width of the package section. Therefore, when the rocket to be packaged is packaged, the length direction of the buffer block 12 is consistent with the axial direction of the rocket to be packaged. As shown in the figure, in the case where the cross section of the elongated bump stopper 12 is circular arc, when the package body portion 1 is developed on the outer surface of the rocket extending in the circumferential direction, the side surfaces of the plurality of elongated bump stoppers 12 are in contact with each other to form a shape matching the outer periphery of the rocket. For example, after the plurality of elongated buffer blocks 12 are deployed on the outer surface of the rocket, the shape of the axial cross section of the structure formed by combining the plurality of buffer blocks is consistent with the shape of the rocket in the circumferential direction, i.e. the shape is an arc or a partial arc. For example, the inner diameter of the shaft section may be slightly larger than or equal to the outer diameter of the rocket.
For example, when the cross section of the elongated bumper 12 is rectangular, the cross section of the structure formed by the plurality of bumpers 12 may form a polygon when the plurality of bumpers 12 are deployed on the outer surface of the rocket. At this time, a certain gap is formed between the contacting portions of the side surfaces of the cushion block 12 and the outer surface of the rocket. The greater the number of the buffer blocks 12, the closer the shape of the polygon is to the circular shape. For example, when the cross section of the strip-shaped buffer block 12 is rectangular, the number of the buffer blocks can be 8-13, so that the buffer blocks can be better matched with the shape of the outer surface of the rocket, and the packaging effect is improved.
With continued reference to fig. 9a and 9b, in the above-described embodiment, the plurality of buffer blocks 12 may be in the form of an elongated flat plate. And the plate structure comprises a first main surface for contacting the rocket to be packaged (i.e. the side of the cushion block remote from the flexible packaging layer), a second main surface opposite to the first main surface (i.e. the side of the cushion block close to the flexible packaging layer), a first side 17 connecting the first main surface in the length direction, and a second side 18 connecting the first main surface and the second main surface in the thickness direction. Wherein the first sides 17 of two adjacent buffer blocks 12 for fitting to each other are respectively inclined surfaces, so that when the plurality of buffer blocks 12 are fitted to each other, the second sides 18 of the plurality of buffer blocks 12 may form a polygonal ring structure, for example. In this embodiment, in order to form the elongated buffer 12 into a polygon matching with the outer surface of the rocket, the adjacent sides of two adjacent buffer 12 may have a slope structure, so that the sides of the buffer 12 are combined more tightly, and the packing effect of the rocket is improved.
According to the embodiment of the invention, by setting the shape of the buffer blocks 12 or adjusting the number of the buffer blocks 12, the packing box section can be better attached to the ground outer surface of the rocket when packing the rocket projectile, and the safety of rocket packing is improved.
In one embodiment, the flexible packaging layer 11 is a fabric having waterproof, dustproof and antistatic properties. In particular, the body portion may be a polymer fabric material.
The above-described embodiments of the present invention may be combined with each other with corresponding technical effects.
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, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. A method of packaging a rocket, comprising:
providing a first packing box section and a second packing box section, wherein the first packing box section comprises a first packing body part and a first tensioning piece which are used for matching the shape of the outer surface of the rocket to be packed, and the second packing box section comprises a second packing body part and a second tensioning piece which are used for matching the shape of the outer surface of the rocket to be packed;
disposing the first packing box section on a first axially extending outer surface of the rocket to be packed and pulling the first tensioning member to deploy the first packing body section along the first outer surface; disposing the second wrapping case section to a second outer surface of the rocket to be wrapped extending in the axial direction, and pulling the second tensioning member to spread the second wrapping body section along the second outer surface; wherein the first outer surface and the second outer surface are two outer surfaces that are close to each other in an axial direction thereof; and
the first package body portion is deployed along the first outer surface by pulling the first tension member and the second package body portion is deployed along the second outer surface by pulling the second tension member.
2. The packaging method according to claim 1, wherein the first packaging body portion and the second packaging body portion each include a flexible packaging layer and a plurality of cushion blocks arranged in sequence in a first direction on at least one major surface side of the flexible packaging layer, and the tightening member includes a plurality of hollow members provided to the first packaging body portion and the second packaging body portion in the first direction, respectively, and a pulling rope for passing through hollow portions of the plurality of hollow members;
deploying the first package body portion along the first outer surface by pulling the first tension member, deploying the second package body portion along the second outer surface by pulling the second tension member comprises:
fixing one end of the pull cord, an
Pulling the other end of the pull rope to connect the plurality of hollow members end to form a shape matching the axial cross section of the rocket to be packaged, so that the flexible packaging layer and the plurality of buffer blocks of the first and second packaging body parts are respectively unfolded along the first and second outer surfaces.
3. The packaging method of claim 2, wherein the plurality of hollow pieces comprises a first hollow tube and a second hollow tube adjacent to each other, the first hollow tube comprising a first connecting structure, the second hollow tube comprising a first mating structure;
securing one end of the pull cord and pulling the other end of the pull cord to join the plurality of hollow members end-to-end to form a shape that matches an axial cross-section of the rocket to be packaged, whereby the flexible wrapping layers and the plurality of bumpers of the first and second package body portions are deployed along the first and second outer surfaces, respectively, comprising:
combining the first connecting structure and the first mating structure with each other so that the combined first hollow tube and second hollow tube have a first shape matching a portion of the rocket shaft cross-sectional shape.
4. A method of packaging according to claim 3, wherein the first shape is a portion of a circular ring or two sides of a polygonal structure.
5. The method of wrapping according to claim 1 wherein said positioning the second wrapping case section on a second outer surface of the rocket to be wrapped extending in an axial direction and pulling the second tension member to spread the second wrapping body portion along the second outer surface further comprises:
overlapping portions of the second section and the first section adjacent to each other.
6. The packaging method of claim 1, further comprising:
providing a plurality of packaging box sections; and
and overlapping and bonding a plurality of packing box sections along the axial outer surface of the rocket to be packed, wherein two packing box sections on the outermost side of the rocket to be packed in the axial direction are respectively arranged on the outer layer and the inner layer.
7. A method of making a packaging box section, comprising:
providing a flexible packaging layer, a cushion block and a tensioning piece, wherein the flexible packaging layer comprises two main surfaces and side surfaces connecting the two main surfaces;
disposing the buffer block on at least one major surface of the protective outer layer, an
And arranging the tension piece on at least one of the protective outer layer and the buffer block along a first direction, wherein the tension piece is used for pulling the flexible packaging layer and/or the buffer block so as to spread the flexible packaging layer and the buffer block on the outer surface of the rocket to be packaged, which extends along the axial direction.
8. A method of making a package section according to claim 7, wherein: the cushion block comprises a plurality of, the disposing the cushion block to at least one major surface of the flexible packaging layer comprises:
the plurality of buffer blocks are juxtaposed in the first direction on the at least one major surface of the flexible packaging layer.
9. A method of making a package section according to claim 8, wherein: the tensioning piece comprises a plurality of hollow tubes and a pull rope, and the step of arranging the tensioning piece on at least one of the flexible packaging layer and the buffer block along the first direction comprises the following steps:
fixedly connecting the plurality of hollow tubes to at least one of the side surface or the two main surfaces in sequence along the first direction, and enabling the pull rope to penetrate through the plurality of hollow tubes, so that the plurality of hollow tubes are connected end to end by pulling the pull rope to be matched with the shaft section of the rocket to be packaged.
10. A method of manufacturing a packaging box section according to claim 2, characterized in that: the flexible packaging layer is made of high polymer materials, and the buffer block is at least one of rubber, foam or plastic.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010660085.1A CN111776475B (en) | 2018-02-27 | 2018-02-27 | Rocket packaging method and manufacturing method of packaging box section |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010660085.1A CN111776475B (en) | 2018-02-27 | 2018-02-27 | Rocket packaging method and manufacturing method of packaging box section |
| CN201810160449.2A CN108482859B (en) | 2018-02-27 | 2018-02-27 | Rocket packaging method, packaging box section manufacturing method and packaging box section |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810160449.2A Division CN108482859B (en) | 2018-02-27 | 2018-02-27 | Rocket packaging method, packaging box section manufacturing method and packaging box section |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111776475A true CN111776475A (en) | 2020-10-16 |
| CN111776475B CN111776475B (en) | 2022-04-19 |
Family
ID=63340764
Family Applications (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010660085.1A Active CN111776475B (en) | 2018-02-27 | 2018-02-27 | Rocket packaging method and manufacturing method of packaging box section |
| CN202010660084.7A Active CN111874446B (en) | 2018-02-27 | 2018-02-27 | Rocket packing case section |
| CN201810160449.2A Active CN108482859B (en) | 2018-02-27 | 2018-02-27 | Rocket packaging method, packaging box section manufacturing method and packaging box section |
Family Applications After (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010660084.7A Active CN111874446B (en) | 2018-02-27 | 2018-02-27 | Rocket packing case section |
| CN201810160449.2A Active CN108482859B (en) | 2018-02-27 | 2018-02-27 | Rocket packaging method, packaging box section manufacturing method and packaging box section |
Country Status (1)
| Country | Link |
|---|---|
| CN (3) | CN111776475B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111776475B (en) * | 2018-02-27 | 2022-04-19 | 蓝箭航天技术有限公司 | Rocket packaging method and manufacturing method of packaging box section |
| CN114184097A (en) * | 2021-12-01 | 2022-03-15 | 上海航天设备制造总厂有限公司 | Protective clothing and protective method for large-diameter rocket body railway transportation |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB759133A (en) * | 1952-01-28 | 1956-10-17 | Heinrich Buddecke | Thread pack, and method of and means for preparing the same |
| CN1202862A (en) * | 1995-10-10 | 1998-12-23 | 维克托·曼纽尔·基尼奥内斯 | Method and system for wrapping steel |
| KR20040027851A (en) * | 2004-03-15 | 2004-04-01 | 정인천 | Packing case for model rocket kit |
| CN200964778Y (en) * | 2006-11-02 | 2007-10-24 | 林雅莹 | Curtain device |
| CN101117158A (en) * | 2007-01-08 | 2008-02-06 | 新康电脑科技（苏州）有限公司 | Method fro preventing foam block on the heat insulation layer of the shuttlecraft and the exterior fuel tank from falling |
| US20120223513A1 (en) * | 2011-03-02 | 2012-09-06 | King Iv Grady | Protective shield |
| US20120291616A1 (en) * | 2011-05-17 | 2012-11-22 | Andrewartha Michael I | Shield kits for projectile protection |
| CN104070975A (en) * | 2014-07-11 | 2014-10-01 | 中国人民解放军总参谋部工程兵科研三所 | Foldable hanging type protection structure |
| CN204172670U (en) * | 2014-09-15 | 2015-02-25 | 戴希 | Portable automobile protecting cover |
| CN106429061A (en) * | 2016-07-13 | 2017-02-22 | 上海宇航系统工程研究所 | Large spacecraft transportation protecting device |
| CN206053525U (en) * | 2016-08-25 | 2017-03-29 | 富士房车（江苏）有限公司 | Roof afterbody tent |
| CN206452901U (en) * | 2016-12-20 | 2017-09-01 | 深圳北林地景园林生态有限公司 | A kind of tree root transplants pretective sleeve pipe |
| CN206760780U (en) * | 2017-03-11 | 2017-12-19 | 芜湖元一航空科技有限公司 | A kind of sports type intelligence vest |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB612997A (en) * | 1946-06-13 | 1948-11-19 | Morton Smith | Improvements in or relating to transit boxes for rockets |
| CN2542491Y (en) * | 2002-06-07 | 2003-04-02 | 黄铭 | Car covering to be assembled and disassembled by single person |
| CN2712823Y (en) * | 2004-08-02 | 2005-07-27 | 阿布斯·班加纳 | External package with pulling rope |
| US20090183807A1 (en) * | 2007-08-16 | 2009-07-23 | Sadlier Claus E | More versatile flexible cover and method of manufacture |
| CN203889361U (en) * | 2014-04-11 | 2014-10-22 | 武钢实业印刷总厂 | Plastic textile sleeve for steel package |
| CN204453153U (en) * | 2015-01-14 | 2015-07-08 | 中国人民解放军海军航空工程学院 | Solid-rocket special-purpose assorted equipment storage transport integrative packaged design case |
| CN111776475B (en) * | 2018-02-27 | 2022-04-19 | 蓝箭航天技术有限公司 | Rocket packaging method and manufacturing method of packaging box section |
| CN208070450U (en) * | 2018-02-27 | 2018-11-09 | 蓝箭航天技术有限公司 | A kind of packing case section for rocket |
-
2018
- 2018-02-27 CN CN202010660085.1A patent/CN111776475B/en active Active
- 2018-02-27 CN CN202010660084.7A patent/CN111874446B/en active Active
- 2018-02-27 CN CN201810160449.2A patent/CN108482859B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB759133A (en) * | 1952-01-28 | 1956-10-17 | Heinrich Buddecke | Thread pack, and method of and means for preparing the same |
| CN1202862A (en) * | 1995-10-10 | 1998-12-23 | 维克托·曼纽尔·基尼奥内斯 | Method and system for wrapping steel |
| KR20040027851A (en) * | 2004-03-15 | 2004-04-01 | 정인천 | Packing case for model rocket kit |
| CN200964778Y (en) * | 2006-11-02 | 2007-10-24 | 林雅莹 | Curtain device |
| CN101117158A (en) * | 2007-01-08 | 2008-02-06 | 新康电脑科技（苏州）有限公司 | Method fro preventing foam block on the heat insulation layer of the shuttlecraft and the exterior fuel tank from falling |
| US20120223513A1 (en) * | 2011-03-02 | 2012-09-06 | King Iv Grady | Protective shield |
| US20120291616A1 (en) * | 2011-05-17 | 2012-11-22 | Andrewartha Michael I | Shield kits for projectile protection |
| CN104070975A (en) * | 2014-07-11 | 2014-10-01 | 中国人民解放军总参谋部工程兵科研三所 | Foldable hanging type protection structure |
| CN204172670U (en) * | 2014-09-15 | 2015-02-25 | 戴希 | Portable automobile protecting cover |
| CN106429061A (en) * | 2016-07-13 | 2017-02-22 | 上海宇航系统工程研究所 | Large spacecraft transportation protecting device |
| CN206053525U (en) * | 2016-08-25 | 2017-03-29 | 富士房车（江苏）有限公司 | Roof afterbody tent |
| CN206452901U (en) * | 2016-12-20 | 2017-09-01 | 深圳北林地景园林生态有限公司 | A kind of tree root transplants pretective sleeve pipe |
| CN206760780U (en) * | 2017-03-11 | 2017-12-19 | 芜湖元一航空科技有限公司 | A kind of sports type intelligence vest |
Non-Patent Citations (1)
| Title |
|---|
| 晏军: "影响天气火箭作业车弹药包装储运一体化", 《包装工程》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108482859B (en) | 2024-01-23 |
| CN111776475B (en) | 2022-04-19 |
| CN111874446B (en) | 2022-05-13 |
| CN111874446A (en) | 2020-11-03 |
| CN108482859A (en) | 2018-09-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111776475B (en) | Rocket packaging method and manufacturing method of packaging box section | |
| US10811759B2 (en) | Mesh antenna reflector with deployable perimeter | |
| US9160078B2 (en) | Corner reflector | |
| US8922456B2 (en) | Deployable antenna | |
| US20080111031A1 (en) | Deployable flat membrane structure | |
| US8167247B2 (en) | Space-based occulter | |
| US8550407B2 (en) | Large rigid deployable structures and method of deploying and locking such structures | |
| US20140232611A1 (en) | Deployable helical antenna for nano-satellites | |
| US8998535B2 (en) | Method and system of retriever systems for marine geophysical survey sensor streamers | |
| US8904937B2 (en) | Line charge | |
| CN106887714A (en) | Gas-filled unfolded cable mesh reflector antenna reflector | |
| US20030168248A1 (en) | Protective sleeving with support ribs | |
| CN208070450U (en) | A kind of packing case section for rocket | |
| KR20050115338A (en) | Composite biasable reflective sheet and sleeve | |
| US5463957A (en) | Inflatable nose fairing | |
| CN206134948U (en) | Light -duty deployable antenna of high rate of accomodating | |
| JP7459237B2 (en) | Deployable assembly for antenna | |
| FR2777118A1 (en) | Satellite launched folded reflector antenna | |
| JP7335122B2 (en) | Hose storage method, corner reflector, and manufacturing method thereof | |
| US6324957B1 (en) | Detonating cord stowage system | |
| CN114184097A (en) | Protective clothing and protective method for large-diameter rocket body railway transportation | |
| CN116234756A (en) | Transport device for transporting fragile articles | |
| US20050084220A1 (en) | Underwater vehicles | |
| JPH0358503A (en) | Expanded truss antenna | |
| JPH03189296A (en) | Developed structure for space |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |