CN112407638A - L-beam transporting device and transport packaging box suitable for large-bearing spacecraft - Google Patents
L-beam transporting device and transport packaging box suitable for large-bearing spacecraft Download PDFInfo
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- CN112407638A CN112407638A CN202011256992.6A CN202011256992A CN112407638A CN 112407638 A CN112407638 A CN 112407638A CN 202011256992 A CN202011256992 A CN 202011256992A CN 112407638 A CN112407638 A CN 112407638A
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- Prior art keywords
- bearing
- spacecraft
- frame
- shaped
- butt joint
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- 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
- B65D90/00—Component parts, details or accessories for large containers
- B65D90/004—Contents retaining means
- B65D90/0073—Storage racks
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- 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
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- 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
- B65D2585/00—Containers, packaging elements or packages specially adapted for particular articles or materials
- B65D2585/68—Containers, packaging elements or packages specially adapted for particular articles or materials for machines, engines, or vehicles in assembled or dismantled form
- B65D2585/6802—Containers, packaging elements or packages specially adapted for particular articles or materials for machines, engines, or vehicles in assembled or dismantled form specific machines, engines or vehicles
- B65D2585/6897—Containers, packaging elements or packages specially adapted for particular articles or materials for machines, engines, or vehicles in assembled or dismantled form specific machines, engines or vehicles others
-
- 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
- B65D2590/00—Component parts, details or accessories for large containers
- B65D2590/0041—Contents retaining means
- B65D2590/005—Contents retaining means adaptable to the size of the transport goods
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Buffer Packaging (AREA)
Abstract
The invention provides an L-shaped beam transporting device suitable for a large-bearing spacecraft, which comprises: the L-shaped main body structure frame comprises an L-shaped beam short side and an L-shaped beam long side, the L-shaped beam short side is perpendicular to the bottom surface of the packing box, and the L-shaped beam long side is parallel to the bottom surface of the packing box; the butt joint interface is arranged on the mounting center of the L-shaped main body structure frame; the lifting installation frame and the butt joint interface are arranged on the same side of the L-shaped main body structure frame; the height adjustment of the installation center of the L-beam transportation device can be realized through the lifting installation frame by the butt joint interface. According to the invention, the height of the installation center of the L-beam device can be adjusted by installing the lifting installation frame on the butt joint interface, so that the requirements of devices with different external dimensions are met.
Description
Technical Field
The invention relates to the technical field of spacecraft transportation equipment, in particular to an L-shaped beam transportation device and a transportation packaging box suitable for a large-bearing spacecraft.
Background
With the increasing development quantity and the shortening of the development period of the satellites, the whole satellite needs to be quickly transported to a launching site for final work before launching after the whole work of the final assembly and test stages of the satellites are completed. As the size of the satellite increases, the height direction limitation of the transportation process necessarily requires that the satellite be transported in a whole-satellite horizontal state.
The L-beam device is an important structural part for mounting the satellite in the transport packaging box, the use working condition of the L-beam device mainly comprises parking and lifting turning-over operation, the parking comprises vertical and horizontal different working conditions, the turning-over operation relates to three different working conditions of horizontal, 45 degrees and vertical, and the satellite is fixedly connected with the L-beam device through a process ring.
At present, an L-beam device of a whole satellite transport packaging box is suitable for the requirement of a size device of a satellite aiming at a large satellite, along with the increase of the number of the satellites, the demand of the transport packaging box is increased, and the research and development manufacturing cost is increased. Therefore, it is a very important task to develop a universal L-beam device to realize the universal matching of the packing box and the L-beam.
Through the retrieval, patent document CN109516003A discloses an equipment transportation frock of jumbo size cabin cover product, including bottom frame, vertical bearing structure, horizontal bearing structure and slide rail device, vertical bearing structure is including locating the first mullion and the second mullion of bottom frame both ends top side by side, horizontal bearing structure includes many crossbeams, the crossbeam level is fixed in between the vertical bearing structure, slide rail device includes first slide rail and second slide rail, first slide rail and second slide rail are vertical respectively and locate the frock both sides, all be equipped with the spout of opening towards the frock outside on first slide rail and the second slide rail. Although the prior art has strong overall structure stability and can be disassembled and put into a common container for transportation, the assembly and transportation tool can only meet the requirement of a size device of one satellite and can not realize the quantitative matching work.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an L-beam transporting device and a transport packaging box suitable for a large-bearing spacecraft, and aims to overcome the defect that the L-beam transporting device in the prior art cannot meet the requirements of devices with different satellite sizes, so that a novel L-beam device with vibration reduction efficiency, universality and light weight is provided.
The invention provides a transportation L-shaped beam device suitable for a large-load-bearing spacecraft, which comprises: an L-shaped main body structure frame, a butt joint interface and a lifting installation frame,
the L-shaped main structure frame comprises an L-shaped beam short edge and an L-shaped beam long edge, the L-shaped beam short edge is perpendicular to the bottom surface of the packing box, and the L-shaped beam long edge is parallel to the bottom surface of the packing box; the butt joint interface is arranged on an installation center of the L-shaped main body structure frame, and the installation center is positioned on one side of the short side of the L-shaped beam and is used for arranging the butt joint interface and the lifting installation frame; the lifting installation frame and the butt joint interface are arranged on the same side of the L-shaped main body structure frame; the height adjustment of the installation center of the L-beam transportation device can be realized through the lifting installation frame by the butt joint interface.
Preferably, the docking device further comprises a damping block, and the damping block is mounted on the inner ring of the docking interface.
Preferably, the lifting device further comprises a particle-vibration absorbing box, and the particle-vibration absorbing box is arranged below the lifting and mounting frame.
Preferably, the docking interfaces are mounted on the L-beam short sides by a liftable mounting frame.
Preferably, still include the auxiliary stay crossbeam, the auxiliary stay crossbeam sets up on L roof beam long limit side, and the auxiliary stay crossbeam can be dismantled with L roof beam long limit and be connected, and the auxiliary stay crossbeam can be adjusted along L roof beam long limit horizontal direction.
Preferably, the L-shaped main structure frame is provided with a cavity filled with polyurethane foam.
Preferably, the joint further comprises a pitch circle, the joint interface and the mounting surface of the spacecraft are the pitch circle, and the hole positions of the through holes on the pitch circle are symmetrical relative to the quadrant line.
Preferably, the high-damping spring shock absorber and the standard shock absorption unit are further included and arranged on the long edge of the L-shaped beam.
Preferably, the lifting device further comprises a connecting bracket, and the connecting bracket is arranged between the lifting and mounting frames.
The invention provides a transport package box which comprises the transport L-beam device suitable for a large-bearing spacecraft.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the invention, the height of the installation center of the L-beam device can be adjusted by installing the lifting installation frame on the butt joint interface, so that the requirements of devices with different external dimensions are met.
2. According to the invention, the L-shaped main structure frame adopts a hollow structure design, polyurethane foam is filled in the cavity, the rigidity of thin-wall steel is enhanced, and the damping characteristic of the whole structure is improved.
3. The vibration absorption device can absorb vibration energy in the transportation process by installing the damping block and the particle vibration absorption box, and effectively improves the vibration absorption efficiency.
4. The invention can fully improve the damping efficiency by adopting the high-damping spring damper and the standard damping unit.
5. The L-beam device adopted by the invention has the characteristics of good vibration reduction efficiency, generalization and light weight, and can realize the generalized matching of the packing box and the L-beam.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic overall structure diagram of a transportation L-beam device suitable for a large-load-bearing spacecraft in the invention;
FIG. 2 is a schematic illustration of the installation of a transport L-beam apparatus suitable for use in a large-capacity spacecraft of the present invention;
fig. 3 is a schematic perspective view of a docking interface according to the present invention.
In the figure:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, fig. 2 and fig. 3, the L-beam transportation device suitable for large-load spacecraft provided by the invention comprises an L-shaped main structure frame 1, a docking interface 2, a liftable installation frame 3, a damping block 4, a pitch circle part 6, a particle vibration absorption box 7, an auxiliary support beam 8, a screw 10, an upper support plate 11, a high damping spring vibration absorber 12, a standard vibration absorption unit 13 and a connecting bracket 14,
the L-shaped main structure frame 1 comprises an L-shaped beam short edge 5 and an L-shaped beam long edge 9, wherein the L-shaped beam short edge 5 is vertical to the bottom surface of the packing box, and the L-shaped beam long edge 9 is parallel to the bottom surface of the packing box; the butt joint interface 2 is arranged on the installation center of the L-shaped main body structure frame 1; the lifting installation frame 3 and the butt joint interface 2 are arranged on the same side of the L-shaped main body structure frame 1; the height adjustment of the installation center of the L-beam transportation device can be realized through the lifting installation frame 3 by the butt joint interface 2.
Further, the damping block 4 is mounted on the inner ring of the docking interface 2; the particle vibration absorption box 7 is arranged below the liftable installation frame 3; the butt joint interface 2 is arranged on the L-shaped beam short side 5 through a lifting installation frame 3; the auxiliary supporting beam 8 is arranged on the side of the L-shaped beam long edge 9, the auxiliary supporting beam 8 is detachably connected with the L-shaped beam long edge 9, and the auxiliary supporting beam 8 can be adjusted along the L-shaped beam long edge direction.
Still further, the pitch circle part 6 is arranged on the butt joint interface 2, and the hole sites of the through holes on the pitch circle part 6 are symmetrical relative to the quadrant line; the high-damping spring shock absorber 12 and the standard shock absorption unit 13 are arranged on the long side 9 of the L-shaped beam; the connecting bracket 14 is mounted between the liftable mounting frames 3.
Hair brushClear and obviousPreferred example 1For further explanation.
Based on above-mentioned basic embodiment, but butt joint interface 2 installs in L roof beam minor face 5 through lifting installation frame 3, and butt joint interface 2 department installation round rubber damping piece, L roof beam long limit 9 sets up two auxiliary stay crossbeams 8, and butt joint interface is to large-scale satellite standard technology ring.
According to the inventionPreferred example 2For further explanation.
Based on the basic embodiment and the preferred embodiment 1, the L-shaped main structure frame 1 is made of Q345 steel materials, the surface of the L-shaped main structure frame is treated by zinc spraying, a hollow structure design is adopted, polyurethane foaming is filled in the cavity, the rigidity of thin-wall steel materials is enhanced, and the damping characteristic of the whole structure is improved.
According to the inventionPreferred example 3For further explanation.
Based on the basic embodiment, the installation surface of the butt joint interface 2 and the spacecraft is a phi 1224mm pitch circle 6, 48 phi 9 through holes are uniformly distributed in the pitch circle 6, the pitch circle 6 is divided into four quadrants, no hole is arranged on each quadrant line, hole positions on two sides of each quadrant line are symmetrical relative to the quadrant lines, and the distance between the standard process ring of the large satellite and the installation surface of the pitch circle 6 of the butt joint interface 2, namely the L-beam short side 5, is 395 mm.
According to the inventionPreferred example 4For further explanation.
Based on above-mentioned basic embodiment, but butt joint interface 2 is installed in liftable installation frame 3 through linking bridge 14, can realize transporting the adjustable of installation center height of L roof beam device, and the relative packing box bottom surface of L roof beam center installation height is adjusted at 1625mm-1865mm within range every interval 60mm to adapt to different satellite overall dimension device requirements.
The long side 9 of the L-shaped beam is provided with two auxiliary supporting beams 8 which can be adjusted along the long side direction, so that the L-shaped beam can support satellite stars of different types. In order to improve the supporting capacity of the L-beam device on a satellite platform in the transportation process and avoid local damage caused by vibration or damage to the connection root caused by additional moment generated at the connection part of a lower end frame of a satellite in the transportation process of the satellite, the auxiliary support and the satellite are connected through an integral structure reinforcing plate, and the vibration isolation adopts a bidirectional spring to realize vibration isolation so as to realize fixed-force auxiliary support on the satellite structure. When the auxiliary support is used, the auxiliary support connecting rod is connected with the star body, the spring vibration isolation device is installed after the star body is in butt joint with the L-shaped beam, and the quick connection is realized by using the pin shaft. In order to avoid the support resonance phenomenon at the auxiliary support part, in the auxiliary support parallel damping structure, an HB type bidirectional damper developed by ACE company is firstly adopted to effectively control the amplitude of the auxiliary support parallel damping structure, and the damper has a continuous adjustable function and has a continuous adjustable function of 30N-10000N under the condition of 0.8m/s movement speed.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A transport L-beam apparatus suitable for large-capacity spacecraft, comprising: an L-shaped main body structure frame (1), a butt joint interface (2) and a lifting installation frame (3),
the L-shaped main structure framework comprises an L-shaped beam short edge (5) and an L-shaped beam long edge (9), the L-shaped beam short edge (5) is perpendicular to the bottom surface of the packing box, and the L-shaped beam long edge (9) is parallel to the bottom surface of the packing box;
the butt joint interface (2) is arranged on the installation center of the L-shaped main body structure frame (1);
the lifting installation frame (3) and the butt joint interface (2) are arranged on the same side of the L-shaped main body structure frame (1);
the height adjustment of the installation center of the L-beam transportation device can be realized through the lifting installation frame (3) by the butt joint interface (2).
2. A transport L-beam arrangement suitable for a large load-bearing spacecraft according to claim 1, characterized by further comprising a damping block (4), said damping block (4) being mounted to the inner ring of the docking interface (2).
3. A transport L-beam arrangement suitable for large load-bearing spacecraft according to claim 1, characterized in that it further comprises a particle-shock absorber tank (7), said particle-shock absorber tank (7) being arranged below said liftable mounting frame (3).
4. A transporting L-beam arrangement suitable for a large load-bearing spacecraft according to claim 1, characterized in that the docking interface (2) is mounted on the L-beam short side (5) by means of the liftable mounting frame (3).
5. A transport L-beam arrangement suitable for a large-capacity spacecraft according to claim 1, characterized in that it further comprises auxiliary support beams (8), said auxiliary support beams (8) being arranged on the side of the long side (9) of the L-beam.
6. A transporting L-beam device for large load-bearing spacecraft according to claim 1, characterized in that the L-shaped main structural frame (1) is provided with a cavity filled with polyurethane foam.
7. The L-shaped beam device for transporting large-load-bearing spacecraft of claim 1, further comprising a pitch circle (6), wherein the joint (2) and the mounting surface of the spacecraft are the pitch circle (6), and the hole positions of the through holes on the pitch circle (6) are symmetrical relative to a quadrant line.
8. A transport L-beam arrangement suitable for large load-bearing spacecraft according to claim 1, characterized in that it further comprises high damping spring dampers (12) and standard damping units (13), said high damping spring dampers (12) and said standard damping units (13) being arranged on the L-beam long side (9).
9. A transporting L-beam arrangement suitable for large load-bearing spacecraft according to claim 1, characterized in that it further comprises connecting brackets (14), said connecting brackets (14) being mounted between said liftable mounting frames (3).
10. A transport package comprising a transport L-beam arrangement suitable for large load-bearing spacecraft of any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011256992.6A CN112407638A (en) | 2020-11-11 | 2020-11-11 | L-beam transporting device and transport packaging box suitable for large-bearing spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011256992.6A CN112407638A (en) | 2020-11-11 | 2020-11-11 | L-beam transporting device and transport packaging box suitable for large-bearing spacecraft |
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| Publication Number | Publication Date |
|---|---|
| CN112407638A true CN112407638A (en) | 2021-02-26 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011256992.6A Pending CN112407638A (en) | 2020-11-11 | 2020-11-11 | L-beam transporting device and transport packaging box suitable for large-bearing spacecraft |
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07291384A (en) * | 1994-04-20 | 1995-11-07 | Fujitsu General Ltd | Package for antenna for satellite broadcasting |
| US20040197165A1 (en) * | 2003-04-03 | 2004-10-07 | Simmons Robert J. | Building-erection structural member transporter |
| CN102774576A (en) * | 2012-07-31 | 2012-11-14 | 北京卫星环境工程研究所 | Universal transport packing case for remote sensing satellite |
| CN106134494B (en) * | 2011-09-22 | 2014-08-27 | 北京卫星制造厂 | A kind of device for the integration test of satellite Compact Range |
| CN106515902A (en) * | 2016-11-09 | 2017-03-22 | 上海卫星装备研究所 | Novel satellite single-axial rotation parking device |
| CN106596010A (en) * | 2016-11-09 | 2017-04-26 | 上海卫星装备研究所 | Ground vibration test clamp used for large-scale spacecraft |
| CN109129349A (en) * | 2018-09-19 | 2019-01-04 | 燕山大学 | Six degree of freedom posture adjustment docking platform |
| CN110641527A (en) * | 2019-09-09 | 2020-01-03 | 安徽坤源铝业有限公司 | Aluminum plate coil placing and transporting integrated device |
| CN211352590U (en) * | 2019-11-08 | 2020-08-25 | 深圳市嘉立创科技发展有限公司 | PCB power circuit device based on particle damping |
| CN211860848U (en) * | 2019-10-09 | 2020-11-03 | 句容市翔茂机箱厂 | Durable panel beating rack that shocks resistance |
-
2020
- 2020-11-11 CN CN202011256992.6A patent/CN112407638A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07291384A (en) * | 1994-04-20 | 1995-11-07 | Fujitsu General Ltd | Package for antenna for satellite broadcasting |
| US20040197165A1 (en) * | 2003-04-03 | 2004-10-07 | Simmons Robert J. | Building-erection structural member transporter |
| CN106134494B (en) * | 2011-09-22 | 2014-08-27 | 北京卫星制造厂 | A kind of device for the integration test of satellite Compact Range |
| CN102774576A (en) * | 2012-07-31 | 2012-11-14 | 北京卫星环境工程研究所 | Universal transport packing case for remote sensing satellite |
| CN106515902A (en) * | 2016-11-09 | 2017-03-22 | 上海卫星装备研究所 | Novel satellite single-axial rotation parking device |
| CN106596010A (en) * | 2016-11-09 | 2017-04-26 | 上海卫星装备研究所 | Ground vibration test clamp used for large-scale spacecraft |
| CN109129349A (en) * | 2018-09-19 | 2019-01-04 | 燕山大学 | Six degree of freedom posture adjustment docking platform |
| CN110641527A (en) * | 2019-09-09 | 2020-01-03 | 安徽坤源铝业有限公司 | Aluminum plate coil placing and transporting integrated device |
| CN211860848U (en) * | 2019-10-09 | 2020-11-03 | 句容市翔茂机箱厂 | Durable panel beating rack that shocks resistance |
| CN211352590U (en) * | 2019-11-08 | 2020-08-25 | 深圳市嘉立创科技发展有限公司 | PCB power circuit device based on particle damping |
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Application publication date: 20210226 |
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