CN111634793A - Hoisting device and hoisting method for satellite - Google Patents
Hoisting device and hoisting method for satellite Download PDFInfo
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- CN111634793A CN111634793A CN202010339086.6A CN202010339086A CN111634793A CN 111634793 A CN111634793 A CN 111634793A CN 202010339086 A CN202010339086 A CN 202010339086A CN 111634793 A CN111634793 A CN 111634793A
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- hoisting
- lifting
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- satellite
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C1/00—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles
- B66C1/10—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles by mechanical means
Abstract
A hoisting device and a hoisting method for a satellite belong to the technical field of mechanical structures, and the satellite universal cross-shaped hoisting frame is adapted to eight hoisting points of the whole satellite by adopting an eight-point hoisting mode and finally combining a one-to-two switching support into a four-point hoisting state. The hanging points are uniformly distributed on the structural plate, the distance is moderate, the edge effect at the hanging points at four corners and the stress interference between the adjacent hanging points are avoided, and the bearing capacity of the hanging points is fully exerted. The hoisting point and the switching bracket are connected without additional bending moment by using a ball pad. The hoisting points are connected through lateral threads of the large embedded part, the embedded part adopts an ellipse-like structure, the bearing stress concentration area is covered and reinforced, multiple thickness changes are used, and the effective diffusion of concentrated load is ensured.
Description
Technical Field
The invention relates to a hoisting device and a hoisting method for a satellite, in particular to a multi-hoisting-point large-bearing light-weight hoisting device suitable for a large-mass satellite (the maximum mass of which exceeds 9000kg), and belongs to the technical field of mechanical structures.
Background
The weight of the former satellite is usually less than 5000kg, the lifting point of the whole satellite is positioned at the top of the whole satellite, and the number of the lifting points is usually 4. In a satellite in the form of a honeycomb sandwich structure plate, a hoisting joint is usually pre-embedded in the honeycomb sandwich structure plate near a hoisting point, the hoisting joint transmits hoisting load to a panel of the honeycomb sandwich structure plate, and finally the load is spread on the panel, so that the transmission of the whole satellite hoisting load is realized. However, by adopting the lifting joint, most of the load of the honeycomb sandwich structure plate near the lifting point is borne by one side panel in contact with the lifting tool, the other side panel is stressed less, and large additional bending moment is generated on the honeycomb sandwich plate, so that the bearing of the honeycomb sandwich plate of the lifting point accessory is not facilitated. The whole star has small weight (not more than 1000kg), and the hoisting and bearing requirements can be met by adopting larger design margin. For the condition that the weight of the whole satellite exceeds 1000kg and is not more than 5000kg, the whole satellite is hoisted by adopting a hoisting connector pre-buried on the angular point of an outer side plate, the outer side of the plate is connected with a reinforcing strip through glue joint and a screw, hoisting load is transmitted to a panel through shearing of a glue layer between a reinforcing embedded part and the panel, and the load is spread through the reinforcing strip; by adopting the hoisting embedded part, the problem of uneven bearing of the side panels at two sides of the honeycomb sandwich plate near the hoisting point caused by the hoisting joint of the small satellite can be avoided; but the axial line of the lifting hole is vertical to the honeycomb sandwich structure plate and the lifting direction and is positioned in the center of the embedded part, so that more structural materials are required to bear the upper part of the lifting hole, and the weight of the embedded part is increased; in addition, as the reinforcing strips which are connected by gluing and threads are adopted, the connection relationship between the reinforcing strips and the honeycomb sandwich structure plate is complex, the corresponding production process is complex, and simultaneously, the load transfer link and the weight of the lifted embedded part are increased.
In the prior art, aiming at the whole satellite weight of 5000kg, the bearing limit of the existing lightweight hoisting connector is 28.9kN, the bearing efficiency (the bearing capacity of gram number of the connector at a unit hoisting point) reaches 0.12kN/g, the hoisting requirement can be met, and a certain safety margin can be ensured. However, for satellites with a weight of 9000kg and above, in order to adapt to a large lifting load and ensure sufficient lifting strength, the weight of a lifting appliance connection point which cannot be separated is not too large in a spacecraft structure using the honeycomb sandwich plate, and a high bearing mass ratio of a lifting point is ensured, and the conventional lifting connector cannot meet the use requirement.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, and the hoisting device and the hoisting method for the satellite are provided. The hanging points are uniformly distributed on the structural plate, the distance is moderate, the edge effect at the hanging points at four corners and the stress interference between the adjacent hanging points are avoided, and the bearing capacity of the hanging points is fully exerted. The hoisting point and the switching bracket are connected without additional bending moment by using a ball pad. The hoisting points are connected through lateral threads of the large embedded part, the embedded part adopts an ellipse-like structure, the bearing stress concentration area is covered and reinforced, multiple thickness changes are used, and the effective diffusion of concentrated load is ensured.
The purpose of the invention is realized by the following technical scheme:
a hoisting device for a satellite comprises a plurality of hoisting points, a plurality of switching brackets and a hoisting frame;
the hoisting point is embedded in a cabin plate of the satellite and is connected with one side of the switching bracket; the other side of the switching bracket is connected with the hanging bracket;
each lifting point has the same structure, comprises two symmetrical metal sheets and a solid metal structure positioned between the two symmetrical metal sheets, and is integrally processed and formed; the solid metal structure is positioned at one end of the two symmetrical metal sheets and is close to the switching bracket; the metal sheet is oval-like.
Preferably, in the hoisting device for a satellite, the metal sheet is an ellipse-like shape composed of a trapezoid, a rectangle and an arc.
Preferably, the end face of the solid metal structure protrudes out of the end faces of the two symmetrical metal sheets, so that the switching bracket is prevented from contacting with a panel of the satellite deck.
In the hoisting device for the satellite, preferably, the thickness of the metal sheet is reduced in steps, the thickness of the metal sheet at the joint with the solid metal structure is the thickest, and the surface in contact with the panel of the satellite deck is kept flat.
In the hoisting device for the satellite, preferably, two support columns are further arranged in each hoisting point, are used for connecting two symmetrical metal sheets and are located at the thinnest part of the metal sheets.
In the above-described hoisting device for a satellite, it is preferable that the distance between two adjacent hoisting points is greater than 2 times the contour of the yield stress of the structural panel 1/2 caused by the hoisting load, and the distance between two adjacent hoisting points on each of the deck plates is the same, and all the hoisting points on each of the deck plates are centered on the panel as a whole.
The hoisting device for the satellite preferably has an ultimate load carrying capacity of 50kN for each hoisting point.
Preferably, the hoisting point and the adapting bracket are connected by a ball pad.
In the hoisting device for the satellite, preferably, each adapter bracket is connected with two hoisting points; the switching support is isosceles triangle.
A hoisting method for a satellite adopts the hoisting device for the satellite, and comprises the following steps:
s1, determining the number of lifting points according to the weight of the satellite and the limit bearing capacity of each lifting point, wherein the number of the lifting points is an integral multiple of 4; then determining the number of the switching brackets; finally, selecting a hanging bracket;
s2, equally dividing all hoisting points into two parts, and respectively embedding the two parts in two opposite cabin plates of the satellite; the spacing between two adjacent suspension points on each deck is greater than 2 times the contour of the yield stress of the deck panel 1/2 resulting from the lifting load, and the spacing between two adjacent suspension points on each deck is the same, with all suspension points on each deck being centered as a unit on the deck.
S3, connecting the lifting point with one side of the switching bracket; the other side of the switching bracket is connected with the hanging bracket; each switching bracket is connected with two hoisting points, and the hoisting points and the switching bracket are connected in a ball pad mode;
and S4, connecting the lifting frame with a lifting mechanism to lift the lifting frame, the switching support, the lifting point and the satellite.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention provides an eight-point hoisting device which is suitable for hoisting a whole satellite of a large-mass satellite (5000kg to 9000 kg); the bearing capacity of the hoisting point can be further improved by further optimizing the parameters such as the structural shape, the thickness and the like of the hoisting point;
(2) according to the hoisting device, the bearing pressure of a single hoisting point is effectively relieved by increasing the number of the hoisting points; meanwhile, stress concentration of the traditional scheme at the angular point of the star body is avoided through the optimized layout of the positions of the lifting points;
(3) the hoisting points are connected through lateral threads of the large embedded part, and the configuration of the embedded part is designed according to the size and the shape of a stress diffusion area of a hoisting load on the honeycomb sandwich panel, so that the stress concentration area near the hoisting points is covered and reinforced, and the effective diffusion of the hoisting load is ensured;
(4) eight-point hoisting is combined into four-point hoisting through the switching bracket, so that the problem of multi-hoisting-point hoisting of a large-mass satellite is solved; the ball pad is used between the lifting point screw and the switching support, the switching support is reasonably stiffened, and meanwhile, the long round hole is used to adapt to the mode that the deformation of the support causes the distance between the lifting point connecting points to change, so that the problem that the lifting point bears additional bending moment load due to large span between the lifting points and serious limitation of the height of the switching support is solved.
Drawings
FIG. 1 is a schematic view of the whole star crane of the present invention.
Fig. 2 is a cross-sectional view (a-a, B-B, C-C) of the suspension point of the present invention embedded in a structural panel.
Fig. 3 is a schematic view of an adapter bracket of the present invention.
Fig. 4 is a schematic view of the connection between the suspension point and the adapter bracket of the present invention.
Fig. 5 is a schematic view of the suspension point of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail with reference to the accompanying drawings.
A hoisting device for a satellite comprises a plurality of hoisting points 1-8, a plurality of switching supports 9-12 and a hoisting frame;
the hoisting points 1-8 are embedded in a cabin plate of the satellite and connected with one sides of the switching brackets 9-12; the other sides of the switching brackets 9-12 are connected with the hanging bracket;
each lifting point 1-8 is identical in structure, comprises two symmetrical metal sheets and a solid metal structure positioned between the two symmetrical metal sheets, and is integrally machined and formed; the solid metal structure is positioned at one end of the two symmetrical metal sheets and is close to the transfer brackets 9-12; the metal sheet is oval-like.
The metal sheet is in an ellipse-like shape consisting of a trapezoid, a rectangle and an arc. The thickness of the metal sheet is reduced in a step mode, the thickness of the joint of the metal sheet and the solid metal structure is the thickest, and the surface of the metal sheet, which is in contact with the panel of the satellite deck, is kept flat. And two support columns are further arranged in each lifting point 1-8 and used for connecting two symmetrical metal sheets and located at the thinnest part of the metal sheets. The end face of the solid metal structure protrudes out of the end faces of the two symmetrical metal sheets, so that the switching supports 9-12 are prevented from contacting with a panel of the satellite cabin plate.
The distance between two adjacent suspension points 1-8 is greater than 2 times the contour of the yield stress of the structural panel 1/2 caused by the lifting load, and the distance between two adjacent suspension points on each deck is the same, and all suspension points on each deck are centered on the panel as a whole. The ultimate bearing capacity of each lifting point 1-8 is 50 kN.
The hoisting points 1-8 and the switching brackets 9-12 are connected by ball pads. Each transfer support 9-12 is connected with two hoisting points 1-8; the switching support 9-12 are isosceles triangles.
A hoisting method for a satellite adopts the hoisting device for the satellite, and comprises the following steps:
s1, determining the number of lifting points 1-8 according to the weight of the satellite and the limit bearing capacity of each lifting point, wherein the number of the lifting points 1-8 is an integral multiple of 4; then determining the number of the transfer brackets 9-12; finally, selecting a hanging bracket;
s2, equally dividing all hoisting points 1-8 into two parts, and respectively embedding the two parts in two opposite cabin plates of the satellite; on each deck, the distance between two adjacent suspension points 1-8 is more than 2 times of the contour of the yield stress of the deck panel 1/2 caused by the hoisting load, the distance between two adjacent suspension points on each deck is the same, and all the suspension points on each deck are centered on the deck as a whole.
S3, connecting the hoisting points 1-8 with one sides of the transfer brackets 9-12; the other sides of the switching brackets 9-12 are connected with the hanging bracket; each transfer support 9-12 is connected with two lifting points 1-8, and the lifting points 1-8 are connected with the transfer supports 9-12 through ball pads;
and S4, connecting the lifting frame with a lifting mechanism, and lifting the lifting frame, the switching supports 9-12, the lifting points 1-8 and the satellite.
Example (b):
a large-bearing light-weight lifting device is shown in figure 1, namely a lifting device for a satellite, and comprises lifting points 1-8 and switching supports 9-12. The lifting points 1-8 are laterally embedded at the upper edges of the satellite north and south cabin plates, and are respectively arranged in 4 numbers as shown in figure 2. One side of each switching support 9-12 is connected with the universal cross-shaped hanging bracket of the satellite, and the other side of each switching support is connected with the two hanging points 1-8. The bearing weight of a single lifting point is reduced to be less than 1500kg by increasing the number of 1-8 lifting points. And the two-in-one switching brackets 9-12 are combined into a final four-point hoisting state, as shown in fig. 3. The method has the advantages that the traditional cross-shaped hanging bracket is adapted to the eight hanging point 1-8 interfaces of the whole satellite, and the problem of multi-hanging point 1-8 lifting of the large-mass satellite is solved.
The hoisting points 1-8 on each cabin plate are arranged in the middle and at equal intervals on the upper edges of the north and south cabin plates to form a complete stress diffusion area, so that the edge effect at the hoisting points at four corners and the stress interference between the adjacent hoisting points 1-8 are avoided, and the bearing capacity of the hoisting points 1-8 is fully exerted.
For the condition that the hoisting weight is 1500kg in the distribution of 1-8 single hoisting points, in order to ensure the strength of 1-8 hoisting points, the distance between 1-8 adjacent hoisting points needs to be larger than 2 times of the yield stress contour of a deck panel 1/2 caused by the hoisting load with a honeycomb panel, in this embodiment, for an aluminum panel with 0.3mm, the distance between 1-8 hoisting points should be larger than 500mm, for a star width of 2500mm, 600mm is selected as the distance between 1-8 hoisting points, after the suspension points are arranged in the middle, the loads of 1-8 hoisting points and the internal stress of the deck panel are uniformly distributed, and the star width is effectively utilized.
Under the condition that the single-point hoisting weight is not more than 1500kg, under the conditions that the overall height is 150mm and the span is 600mm, the inclined sides of the sections of the switching supports 9-12 are 44 multiplied by 40mm, the deformation of the joints of the hoisting points 1-8 is controlled, meanwhile, the hoisting points 1-8 are connected with the switching supports 9-12 through ball pads in a mode of connection, no additional bending moment is achieved, and the strength of the embedded parts of the satellite hoisting points 1-8 is ensured. In order to further ensure that no additional bending moment exists, slotted holes are used for connecting holes of 1-8 hanging points on one sides of the switching supports 9-12, so that the influence of the change of the distance between holes on two sides caused by the lifting deformation of the switching supports 9-12 is adapted, as shown in fig. 4.
As shown in fig. 5, the lifting points 1-8 are fixedly connected with the star body, and the lifting points 1-8 are connected through lateral threads of the large embedded part; hoisting points 1-8 are pre-embedded in the cabin plate of the honeycomb sandwich structure, the hoisting points 1-8 are in an ellipse-like shape, and are integrally formed by a solid metal structure and two symmetrical metal sheet structures, and the hoisting point metal sheets cover a yield stress affected area caused by the hoisting of the cabin plate panel; the end face of the embedded piece solid metal structure is provided with a lifting threaded hole with the axis parallel to the lifting direction, and lifting load is transferred to the solid metal structure from the threaded hole and is transferred to the deck plate panel of the honeycomb sandwich structure cabin plate through the metal sheet; in order to ensure uniform stress and good processing manufacturability, the lifting point flanging (namely the metal sheet) changes the thickness by 2 steps, and the thickness is gradually thinned outwards from the 1-8 screw threads of the lifting point, so that the quality of the embedded part structure is further optimized, the bearing efficiency of the embedded part structure is improved, and the steps are arranged on the inner side of the metal sheet to ensure that the outer side of the sheet is tightly attached to the deck plate panel of the honeycomb sandwich structure; the lifting point flanging is additionally provided with a cylindrical support at the far position of the cantilever, so that the composite manufacturability of the embedded part and the deck plate is improved; the major axis of the 1-8 ellipse of the lifting point is about 140mm, the minor axis is about 130mm, the ultimate bearing capacity of the corresponding lifting point 1-8 reaches 50kN, and the lifting requirement of a single point with the weight of 1500kg is met.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. A hoisting device for a satellite is characterized by comprising a plurality of hoisting points (1-8), a plurality of switching brackets (9-12) and a hoisting frame;
the hoisting points (1-8) are embedded in a cabin plate of the satellite and connected with one sides of the switching brackets (9-12); the other side of the switching support (9-12) is connected with the hanging bracket;
each lifting point (1-8) is identical in structure, comprises two symmetrical metal sheets and a solid metal structure positioned between the two symmetrical metal sheets, and is integrally machined and formed; the solid metal structure is positioned at one end of the two symmetrical metal sheets and is close to the switching bracket (9-12); the metal sheet is oval-like.
2. The lifting device for the satellite according to claim 1, wherein the metal sheet is in an ellipse-like shape consisting of a trapezoid, a rectangle and an arc.
3. The lifting device for the satellite is characterized in that the end face of the solid metal structure protrudes out of the end faces of the two symmetrical metal sheets to avoid the contact between the adapter bracket (9-12) and the panel of the satellite deck.
4. The lifting device for satellites as claimed in claim 1, wherein the thickness of the metal sheet is reduced in steps, the thickness of the metal sheet is the thickest at the joint with the solid metal structure, and the surface in contact with the panels of the satellite deck is kept flat.
5. A lifting device for satellites as claimed in claim 4 wherein two support columns are also provided in each lifting point (1-8) for connecting two symmetrical metal sheets at the thinnest of the metal sheets.
6. A lifting device for a satellite according to any one of claims 1 to 5, wherein the distance between two adjacent lifting points (1 to 8) is greater than 2 times the contour of the yield stress of the structural panel 1/2 caused by the lifting load, and the distance between two adjacent lifting points on each deck is the same, all lifting points on each deck being centered on the panel as a whole.
7. A lifting installation for satellites as claimed in any of claims 1 to 5 wherein the ultimate load carrying capacity of each lifting point (1 to 8) is 50 kN.
8. A lifting device for a satellite according to any one of claims 1 to 5, wherein the lifting points (1 to 8) and the transfer brackets (9 to 12) are connected by ball pads.
9. A lifting device for satellites as claimed in any of claims 1 to 5 wherein each adapter bracket (9 to 12) is connected to two lifting points (1 to 8); the switching support (9-12) is in the shape of an isosceles triangle.
10. A hoisting method for a satellite, characterized in that the hoisting device for the satellite as claimed in any one of claims 1 to 5 is adopted, and comprises the following steps:
s1, determining the number of lifting points (1-8) according to the weight of the satellite and the limit bearing capacity of each lifting point, wherein the number of the lifting points (1-8) is an integral multiple of 4; then determining the number of the switching supports (9-12); finally, selecting a hanging bracket;
s2, equally dividing all hoisting points (1-8) into two parts, and respectively embedding the two parts in two opposite cabin plates of the satellite; on each deck plate, the distance between two adjacent hoisting points (1-8) is more than 2 times of the contour line of the yield stress of the deck plate panel 1/2 caused by the hoisting load, the distance between two adjacent hoisting points on each deck plate is the same, and all the hoisting points on each deck plate are centered on the deck plate as a whole;
s3, connecting the hoisting points (1-8) with one sides of the switching brackets (9-12); the other side of the switching support (9-12) is connected with the hanging bracket; each transfer support (9-12) is connected with two lifting points (1-8), and the lifting points (1-8) are connected with the transfer supports (9-12) by adopting a ball pad connection mode;
and S4, connecting the lifting frame with a lifting mechanism, and lifting the lifting frame, the switching supports (9-12), the lifting points (1-8) and the satellite.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010339086.6A CN111634793B (en) | 2020-04-26 | 2020-04-26 | Hoisting device and hoisting method for satellite |
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| CN202010339086.6A CN111634793B (en) | 2020-04-26 | 2020-04-26 | Hoisting device and hoisting method for satellite |
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| CN111634793B CN111634793B (en) | 2022-08-12 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112875486A (en) * | 2021-01-12 | 2021-06-01 | 航天科工空间工程发展有限公司 | Satellite hoisting equipment |
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| CN112875486B (en) * | 2021-01-12 | 2023-03-24 | 航天科工空间工程发展有限公司 | Satellite hoisting equipment |
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| Publication number | Publication date |
|---|---|
| CN111634793B (en) | 2022-08-12 |
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