Aerospace vehicle storage and transport container

Abstract

The application provides a gas bag type spacecraft storage and transportation container, which comprises a top cover, an upper flange of a box cover, a flexible container cover, a guide assembly, a lower flange of the box cover, a container bottom and a flexible film. The application has the beneficial effects that: the lifting operation of the flexible container cover is completed by using the power of air pressure and the self weight of the flexible cover, the lifting height limit of the factory building crane is avoided; the opening and closing operations of the container cover can be realized only by inflation and deflation, the hoisting and sleeving operation is cancelled, the operation process is simplified, and the operation risk is reduced; the regular and orderly folding storage of the container cover is realized, and the folding and unfolding are easy; the folding and unfolding ratio is greater than 10:1, the storage volume is greatly reduced; the hard metal is changed into the flexible film material, and the self weight of the container is greatly reduced.

Description

Technical Field

[0001] This invention belongs to the field of aerospace ground equipment, and in particular relates to an airbag-type spacecraft storage and transportation container. Background Technology

[0002] Spacecraft storage and transport containers are used for vertically transporting spacecraft between buildings and launch towers at space launch sites, providing high-quality local environmental conditions for spacecraft during transport in outdoor, non-clean environments.

[0003] The transfer of spacecraft between launch site facilities is done vertically. Before transport, the spacecraft is secured in a container inside the facility to create a partially sealed space, which is then inflated to create positive pressure before the transfer begins.

[0004] Traditional storage and transportation containers are rigid-shell cage-like structures. The bottom is a metal load-bearing container used to connect and secure vertically positioned spacecraft, while the upper part consists of multi-stage cage-like rigid-shell containers. During assembly, each stage of the container is lifted by an overhead crane, passed over the top of the satellite, and then lowered vertically to secure the spacecraft inside the container. A schematic diagram of the traditional rigid cage-like container structure and assembly operation can be found here. Figure 1 As shown.

[0005] With the rapid development of the aerospace field, the size and weight of spacecraft are increasing year by year. This has led to a corresponding increase in the size, height, and weight of containers used for transporting spacecraft at test ranges. Currently, the vertical height of many spacecraft is close to or exceeds half the height of overhead cranes in the factory. During lifting, the height of the lifting equipment itself cannot be achieved in a single operation, requiring more cumbersome procedures to open and close the containers. This not only results in low efficiency but also increases operational risks due to the complexity of the process. For valuable spacecraft, these risks translate into enormous costs.

[0006] Simultaneous deployment of multiple satellites to launch sites has become commonplace, leading to increasingly strained space resources at launch facilities. Launch containers are enormous, requiring significant storage space after use. Building or renovating launch facilities involves substantial investment and lengthy processes. Therefore, practical considerations necessitate innovative container designs that simplify operational procedures and reduce operational complexity, minimize space requirements, achieve product lightweighting, lower container costs, and adapt to the new demands of high-density aerospace launches.

[0007] Current problems with traditional rigid metal transport containers at spacecraft launch sites:

[0008] 1. For large spacecraft, the height of the factory is limited, which makes it impossible to complete the transfer of traditional rigid transfer containers with top-opening and closing boxes in one go. It is necessary to replace them with cumbersome opening and closing boxes, which reduces efficiency and increases operational risks.

[0009] 2. The storage of bulky rigid metal containers occupies a huge amount of factory space; with multiple satellites simultaneously entering the launch site, there is an urgent need to solve the problem of the huge amount of factory space occupied by container storage.

[0010] 3. Ultra-large rigid metal containers are large and incompressible, resulting in high material, processing, and transportation costs. Summary of the Invention

[0011] In view of this, the present invention aims to propose an airbag-type spacecraft storage and transportation container to solve the problems of limited factory hoisting height, large space occupation of storage facilities, difficult operation procedures and high operation risks, heavy weight and high cost.

[0012] To achieve the above objectives, the technical solution of the present invention is implemented as follows:

[0013] An airbag-type spacecraft storage and transportation container includes a top cover, an upper flange of the cover, a flexible container cover, guide components, a lower flange of the cover, a container bottom, and a flexible membrane. The top of the flexible container cover is connected to the top cover via the upper flange of the cover, and the bottom of the flexible container cover is connected to the container bottom via the lower flange of the cover. Several guide components are evenly distributed axially around the periphery of the flexible container cover. The top cover, the flexible container cover, and the container bottom together form a hollow sealed container, which is used to place the spacecraft.

[0014] Furthermore, the flexible container cover includes several airbag bodies, which are stacked vertically to form a hollow cylindrical structure, and adjacent airbag bodies are connected by a flexible membrane through thermal fusion.

[0015] Furthermore, the cross-section of the airbag body is circular, and the interior of the airbag body is a closed cavity; each airbag body is equipped with an airtight inflation / deflation port.

[0016] Furthermore, the guiding assembly includes a guide rod and several guide rings. The guide rod is axially mounted on the periphery of the flexible container cover, and several guide rings are axially distributed at equal intervals on the guide rod. Each guide ring is connected to a flexible membrane between two adjacent airbag bodies.

[0017] Furthermore, the guide rod is made of a rigid material.

[0018] Furthermore, the bottom of the container is made of metal.

[0019] Furthermore, the supporting frame of the top cover is made of a rigid material, either metal or non-metal, and the supporting frame of the top cover is connected to the flexible membrane to form the top cover structure.

[0020] Furthermore, the connection between the flexible container cover and the container bottom and top cover is a press-fit sealing method.

[0021] Furthermore, both the upper flange and the lower flange of the enclosure are made of rigid materials.

[0022] Furthermore, a sealing groove is provided inside the lower flange of the enclosure, and a sealing ring is placed inside the sealing groove.

[0023] Compared with existing technologies, the airbag-type spacecraft storage and transportation container of the present invention has the following advantages:

[0024] (1) The airbag-type spacecraft storage and transportation container of the present invention uses pneumatics and the weight of the flexible cover as power to complete the lifting and lowering operation of the flexible container cover, avoiding the height limit of the overhead crane in the factory; the opening and closing operations can be realized by simply inflating and deflating, eliminating the hoisting and fitting operation, simplifying the operation process and reducing the operation risk; the container cover can be folded and stored in a regular and orderly manner, which is easy to unfold; the unfolding ratio is greater than 10:1, which greatly reduces the storage volume; the hard metal is changed to a flexible membrane material, which greatly reduces the weight of the container.

[0025] (2) The airbag-type spacecraft storage and transportation container of the present invention uses a flexible membrane instead of rigid metal materials, which significantly reduces costs in terms of materials, processes, packaging, and transportation; the airbag-formed airtight cavity has good passive heat insulation function, replacing the rigid insulation layer to play a role in heat insulation. It achieves heat insulation function while reducing the weight of the container. Attached Figure Description

[0026] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0027] Figure 1 This is a schematic diagram of a traditional rigid steamer container and its closing operation as described in an embodiment of the present invention;

[0028] Figure 2 This is a schematic diagram of the overall structure according to an embodiment of the present invention;

[0029] Figure 3 This is a cross-sectional view of the overall structure as described in an embodiment of the present invention;

[0030] Figure 4 This is a partial cross-sectional view of the overall structure according to an embodiment of the present invention;

[0031] Figure 5 This is a cross-sectional view of the upper flange and lower flange of the box cover when folded, as described in an embodiment of the present invention.

[0032] Explanation of reference numerals in the attached figures:

[0033] 1. Top cover; 2. Upper flange of the enclosure; 3. Flexible container cover; 31. Airbag body; 4. Guide rod; 5. Guide ring; 6. Lower flange of the enclosure; 7. Container bottom; 8. Flexible membrane; 9. Sealing groove; 10. Sealing ring; 11. Spacecraft. Detailed Implementation

[0034] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other.

[0035] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0036] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art will understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0037] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0038] like Figures 1 to 5 As shown, an airbag-type spacecraft storage and transportation container includes a flexible inflatable airbag structure, which replaces the rigid metal container cover structure, while the bottom 7 of the container is still made of metal material.

[0039] The flexible airbag structure includes: a top cover 1, an upper flange of the housing 2, a flexible container cover 3, a guide rod 4, a guide ring 5, a lower flange of the housing 6, a container bottom 7, and a flexible membrane 8. The container bottom 7 is still made of rigid metal, while the flexible container cover 3 and the top cover 1 are primarily made of the flexible membrane 8. The guide rod 4 is made of rigid material.

[0040] The flexible container cover 3 includes an airbag body 31, which has a circular cross-section and a closed cavity inside. Each airbag body 31 is equipped with an airtight inflation / deflation port to meet inflation / deflation requirements. After inflation, the airbag body 31 has an overall shape that is circular or a near-circular regular polygon, similar to a "swimming ring" with a large inner diameter.

[0041] Multiple airbag bodies 31 are stacked vertically, and the airbag bodies 31 are connected to each other by thermal fusion with a flexible membrane 8 to form a large, airtight space for storing the spacecraft 11.

[0042] The top cover 1 is made of a metal or non-metal rigid material as a supporting frame, which is combined with the membrane assembly to form the top cover 1.

[0043] The container bottom 7, the flexible container cover 3, and the flexible top cover 1 constitute a large container with an internally sealed and airtight function.

[0044] The flexible membrane 8 connecting the airbag bodies 31 is made of composite materials such as high tensile strength fibers and airtight coatings, and has the characteristics of high tensile strength, good airtightness, rainproof, and aging resistance. Because the inside of the container needs to maintain positive pressure, the internal space enclosed by the entire flexible container cover 3 is circular (or a regular polygon that is close to a circle).

[0045] The flexible inflatable bladder structure has the following advantages:

[0046] a. Flexible membrane 8 replaces rigid materials and is foldable. The expansion-to-fold ratio of the inflatable bladder structure is greater than 10:1, allowing for foldable storage and greatly saving storage space.

[0047] b. The membrane material has a low density, which greatly reduces the weight of the product.

[0048] c. The use of an inflatable bladder structure optimizes the opening and closing process, changing the top-down locking process to a bottom-up locking process. The locking process does not require an overhead crane (thus eliminating height limitations); the container cover's raising or lowering is achieved by gradually inflating or deflating the bladder. This inflatable bladder structure optimizes the opening and closing operation, reducing operational risks.

[0049] d. The manufacturing process of flexible membrane structures mainly involves cutting and hot-melt processes. Not only are membrane materials cheaper than metal materials, but the manufacturing process is also cheaper than machining processes. This product solution significantly reduces product costs.

[0050] Advantages of this invention:

[0051] 1. Using pneumatics and the self-weight of the flexible cover as power, the lifting and lowering operation of the flexible container cover is completed, avoiding the height restrictions of the overhead crane in the factory.

[0052] 2. Opening and closing the container can be achieved simply by inflating and deflating the container, eliminating the need for hoisting and fitting, simplifying the operation process, and reducing operational risks.

[0053] 3. Enables containers to be folded and stored in a regular and orderly manner, making them easy to unfold.

[0054] 4. The unfolding ratio is greater than 10:1 (not limited to this ratio), which greatly reduces the storage volume.

[0055] 5. The change from rigid metal to flexible membrane material greatly reduces the container's weight.

[0056] 6. Flexible films replace rigid metal materials, significantly reducing costs in terms of materials, processes, packaging, and transportation.

[0057] 7. The airtight cavity formed by airbags provides good passive insulation, replacing rigid insulation layers to achieve thermal insulation while reducing the container's weight.

[0058] Example 1

[0059] The overall structure of the flexible container is as follows Figure 2 As shown.

[0060] Multiple airbag bodies 31 are stacked vertically, and the individual airbag bodies 31 are sealed together by a flexible membrane 8. See the specific structure below. Figure 4 When there is no gas inside, each airbag body 31 is inflated sequentially from top to bottom, causing the entire flexible container cover 3 to gradually rise and unfold. Conversely, during deflating, each airbag body 31 is deflated sequentially from bottom to top, causing the entire flexible container cover 3 to gradually lower, folding the airbag bodies 31 and reducing the overall height. The inflating and deflating pressures and the weight of the flexible container cover 3 serve as the power source for its unfolding and folding operations. During the rising and falling of the flexible container cover 3, the guide rod 4 provides guidance, with the guide ring 5 connected to the flexible membrane 8. The ratio of the unfolded to folded height of the flexible container cover 3 is greater than 10:1, which significantly reduces the space occupied.

[0061] The flexible container cover 3 is sealed to the container bottom 7 and top cover 1 through a press-fit sealing method. The upper flange 2 and lower flange 6 of the cover are made of rigid materials. The lower flange 6 has a sealing groove 9, and a sealing ring 10 is placed in the sealing groove 9. Figure 5 .

[0062] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A gasbag-type spacecraft storage and transportation container, characterized in that: It includes a top cover (1), an upper flange (2) of the box cover, a flexible container cover (3), a guide assembly, a lower flange (6) of the box cover, a container bottom (7) and a flexible membrane (8). The top of the flexible container cover (3) is connected to the top cover (1) through the upper flange (2), and the bottom of the flexible container cover (3) is connected to the container bottom (7) through the lower flange (6). Several guide assemblies are evenly distributed axially around the flexible container cover (3). The top cover (1), the flexible container cover (3) and the container bottom (7) together form a hollow sealed container. The hollow sealed container is used to place a spacecraft (11). The flexible container cover (3) includes several airbag bodies (31). Multiple airbag bodies (31) are stacked along the vertical direction to form a hollow cylindrical structure. Adjacent airbag bodies (31) are connected by a flexible membrane (8) through heat fusion. The flexible membrane (8) is made of fiber with high tensile strength and airtight coating material, and has high tensile strength, good airtightness, rainproof and aging resistance. Because the inside of the container needs to maintain positive pressure, the internal space enclosed by the entire flexible container cover (3) is circular or a regular polygon that is close to circular. The cross-section of the airbag body (31) is circular, and the interior of the airbag body (31) is a closed cavity; each airbag body (31) is equipped with an airtight inflation and deflation port. The guiding assembly includes a guide rod (4) and several guide rings (5). The guide rod (4) is axially mounted on the periphery of the flexible container cover (3). Several guide rings (5) are axially distributed at equal intervals on the guide rod (4). Each guide ring (5) is connected to the flexible membrane (8) between two adjacent airbag bodies (31). The connection between the flexible container cover (3) and the container bottom (7) and top cover (1) is a press-fit sealing method; Multiple airbag bodies (31) are stacked vertically, and the individual airbag bodies (31) are sealed together with a flexible membrane (8), forming a large, airtight space to store the spacecraft (11). When there is no gas inside, each airbag body (31) is inflated sequentially from top to bottom, and the entire flexible container cover (3) gradually rises and unfolds. After inflation, the overall shape of the airbag body (31) is a circular or nearly circular regular polygon, similar to a swimming ring with a large inner diameter. When deflation occurs, each airbag body (31) is inflated sequentially from bottom to top. As the airbag body (31) deflates, the entire flexible container cover (3) gradually lowers, the airbag body (31) folds, and the total height decreases; the inflation and deflation pressure and the weight of the flexible container cover (3) are used as power to complete the operation of unfolding and folding the flexible container cover (3); during the rising and falling of the flexible container cover (3), the guide rod (4) plays a guiding role, wherein the guide ring (5) is connected to the flexible membrane (8); the height ratio of the unfolded and folded flexible container cover (3) is greater than 10:1, which can greatly reduce the space occupied; The storage and transportation containers use pneumatic and flexible cover weight as power to complete the lifting and lowering of the flexible container cover, avoiding the height restrictions of the factory overhead crane; opening and closing operations can be achieved by simply inflating and deflating air, eliminating the lifting and fitting operation and simplifying the operation process; the rigid metal is replaced by a flexible membrane material, reducing the container weight; Flexible membranes replace rigid metal materials, significantly reducing costs in terms of materials, processes, packaging, and transportation; the airtight cavity formed by airbags provides good passive insulation, replacing rigid insulation layers to achieve thermal insulation; and the container's weight is reduced while achieving thermal insulation.

2. The airbag-type spacecraft storage and transportation container according to claim 1, characterized in that: The guide rod (4) is made of a hard material.

3. The airbag-type spacecraft storage and transportation container according to claim 1, characterized in that: The bottom (7) of the container is made of metal.

4. The airbag-type spacecraft storage and transportation container according to claim 1, characterized in that: The supporting frame of the top cover (1) is made of metal or non-metal rigid material, and the supporting frame of the top cover (1) is connected to the flexible membrane (8) to form the top cover structure.

5. A gasbag-type spacecraft storage and transportation container according to claim 1, characterized in that: Both the upper flange (2) and the lower flange (6) of the enclosure are made of rigid materials.

6. The airbag-type spacecraft storage and transportation container according to claim 1, characterized in that: A sealing groove (9) is provided in the lower flange (6) of the box cover, and a sealing ring (10) is placed in the sealing groove (9).

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