CN112848363A - Unfolding design method for spacecraft thermal control multilayer model - Google Patents
Unfolding design method for spacecraft thermal control multilayer model Download PDFInfo
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- CN112848363A CN112848363A CN202110008863.3A CN202110008863A CN112848363A CN 112848363 A CN112848363 A CN 112848363A CN 202110008863 A CN202110008863 A CN 202110008863A CN 112848363 A CN112848363 A CN 112848363A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C69/00—Combinations of shaping techniques not provided for in a single one of main groups B29C39/00 - B29C67/00, e.g. associations of moulding and joining techniques; Apparatus therefore
- B29C69/001—Combinations of shaping techniques not provided for in a single one of main groups B29C39/00 - B29C67/00, e.g. associations of moulding and joining techniques; Apparatus therefore a shaping technique combined with cutting, e.g. in parts or slices combined with rearranging and joining the cut parts
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Abstract
The application provides a method for unfolding and designing a thermal control multilayer model of a spacecraft, wherein a three-dimensional model with edges is unfolded: cutting along one edge or a plurality of edges of the three-dimensional model, and enabling the sum of cutting lengths to be minimum; unfolding the conical surface model: dividing the conical surface model into a plurality of sub conical surfaces in the circumferential direction, and flattening by taking the central line of the sub conical surfaces as a central axis; unfolding the cylindrical surface model: the cylindrical surface model is circumferentially divided into a plurality of sub-arc surfaces, and one side edge parallel to the central line of the cylindrical surface model along the sub-arc surfaces is used as a central axis for flattening; unfolding the spherical model: the spherical model is divided into a plurality of subspheres in the circumferential direction, and triangular surface patch cutting is carried out on a plurality of positions on the subspheres, so that the breaking times of the subspheres during unfolding are minimum. The beneficial effect of this application is: according to the shape, the category and the installation mode of the three-dimensional multi-layer model, the three-dimensional multi-layer model is unfolded into a plane structure according to the set rules, so that the installation difficulty of the three-dimensional multi-layer model is reduced, and the multi-layer thermal control effect is ensured.
Description
Technical Field
The disclosure relates to the technical field of spacecraft thermal control multilayer manufacturing, in particular to a spacecraft thermal control multilayer model unfolding design method.
Background
The thermal control multilayer is a flexible product on the spacecraft, is arranged on the surfaces of the spacecraft and equipment, and directly influences the temperature control and on-orbit operation effect of the spacecraft. The surface of the spacecraft is provided with a plurality of curved surfaces, protruding products such as equipment, brackets and the like, and the multilayer models covered on the products have different shapes according to the shapes of the products to be covered. The shapes and the installation modes of the multi-layer models of different equipment, supports and the like are different, and the unfolding methods of the multi-layer models are required to be unified, so that the installation difficulty of the multi-layer models is reduced, and the thermal control effect is not influenced.
In order to solve the problem of unfolding of the thermal control multilayer model of the spacecraft, the method for unfolding the thermal control multilayer model is developed, the unfolding mode is determined, and the convenience for installing the thermal control multilayer of the spacecraft and the coating effect of the thermal control multilayer are ensured.
Disclosure of Invention
The application aims to solve the problems and provides a spacecraft thermal control multilayer model expansion design method.
In a first aspect, the application provides a method for unfolding and designing a thermal control multilayer model of a spacecraft,
unfolding the three-dimensional model with edges: cutting along one edge or a plurality of edges of the three-dimensional model, and enabling the sum of cutting lengths to be minimum;
unfolding the conical surface model: dividing the conical surface model into a plurality of sub conical surfaces in the circumferential direction, and flattening by taking the central line of the sub conical surfaces as a central axis;
unfolding the cylindrical surface model: the cylindrical surface model is circumferentially divided into a plurality of sub-arc surfaces, and one side edge parallel to the central line of the cylindrical surface model along the sub-arc surfaces is used as a central axis for flattening;
unfolding the spherical model: the spherical model is divided into a plurality of subspheres in the circumferential direction, and triangular surface patch cutting is carried out on a plurality of positions on the subspheres, so that the breaking times of the subspheres during unfolding are minimum.
According to the technical scheme provided by the embodiment of the application, when the three-dimensional model with the edges is a three-dimensional model with openings at two ends, the three-dimensional model is cut along the shortest edges, and 20mm overlapping edges are additionally arranged on the cut single-edge edges.
According to the technical scheme provided by the embodiment of the application, when the three-dimensional model with the edges is a three-dimensional model with an opening at one end, the three-dimensional model is unfolded by cutting a plurality of edges so as to take the surface with the largest area as the center.
According to the technical scheme that this application embodiment provided, work as when one end open-ended three-dimensional model is the cuboid, cut along many edges of cuboid for cut length sum is minimum.
According to the technical scheme that this application embodiment provided, work as when one end open-ended three-dimensional model is the non-cuboid, add 20mm overlap joint limit on the unilateral edge of cutting.
According to the technical scheme provided by the embodiment of the application, a 20mm overlap edge is added on a single side at the fracture position of the subsphere.
The invention has the beneficial effects that: the application provides a method for unfolding and designing a thermal control multilayer model of a spacecraft, the three-dimensional multilayer models with different shapes are designed and manufactured according to the difference between the shapes and the installation modes of different products, and the three-dimensional multilayer models are installed after being unfolded into a plane structure when being installed, so that the installation difficulty of the three-dimensional multilayer models is reduced, and the multilayer thermal control effect is ensured. The three-dimensional multi-layer models with different types, shapes and installation modes are unfolded according to different rules, so that the efficiency of unfolding the multi-layer models is improved.
Drawings
FIG. 1 is a schematic view of an expanded multi-layer model of an equipment rack;
FIG. 2 is a schematic diagram of an engine mount in a multi-layer model deployment;
FIG. 3 is an expanded view of a rectangular parallelepiped multi-layer model;
FIG. 4 is an expanded view of a conical multi-layer mold;
FIG. 5 is a schematic diagram of the cylindrical multi-layer mold expanded;
fig. 6 is an expanded view of the spherical multi-layer model.
Detailed Description
In order that those skilled in the art will better understand the technical solutions of the present invention, the following detailed description of the present invention is provided in conjunction with the accompanying drawings, and the description of the present section is only exemplary and explanatory, and should not be construed as limiting the scope of the present invention in any way.
The application provides a method for unfolding and designing a spacecraft thermal control multilayer model, which is characterized in that the type, shape and installation mode of a product arranged on the surface of a spacecraft are various, so that the shape of a thermal control multilayer covering the outer layer of the surface of the product is various, and the thermal control multilayer manufactured according to the shape of the product needs to be unfolded into a plane for installation and then is installed, as shown in figures 1-6:
unfolding the three-dimensional model with edges: and cutting along one edge or a plurality of edges of the three-dimensional model, and minimizing the sum of cutting lengths. As shown in fig. 1-3.
Unfolding the conical surface model: and the conical surface model is circumferentially divided into a plurality of sub conical surfaces, and the sub conical surfaces are flattened by taking the central line of the sub conical surfaces as the central axis. As shown in fig. 4.
Unfolding the cylindrical surface model: the cylindrical surface model is circumferentially divided into a plurality of sub-arc surfaces, and one side edge parallel to the central line of the cylindrical surface model along the sub-arc surfaces is used as a central axis for flattening. As shown in fig. 5.
Unfolding the spherical model: the spherical model is divided into a plurality of subspheres in the circumferential direction, and triangular surface patch cutting is carried out on a plurality of positions on the subspheres, so that the breaking times of the subspheres during unfolding are minimum. As shown in fig. 6. Preferably, a 20mm overlapping edge is added on one side of the fracture part of the subsphere surface to ensure that no seam is missed during multilayer installation.
In a preferred embodiment, when the three-dimensional model with the edges is a three-dimensional model with openings at two ends, the three-dimensional model is cut along the shortest edge, and a 20mm overlapping edge is additionally arranged on the cut single-side edge.
In the preferred embodiment, as shown in fig. 1, a cylindrical three-dimensional multi-layer model of an equipment support with two open ends is shown, when the model is unfolded, one edge needs to be cut, the surfaces are connected together, the shortest edge is selected for cutting on the premise that the connection of each surface is not overlapped, and the single edge at the cut part is increased by 20mm for overlapping when the model is installed in multiple layers.
In a preferred embodiment, when the edged three-dimensional model is an open-ended three-dimensional model, the opening is performed by cutting a plurality of edges so as to center on a surface having the largest area.
In the preferred embodiment described above, the edged three-dimensional model is a three-dimensional model with one open end, and may be a multi-layer model of a device, a battery cover, an engine mount, or the like, for example. As shown in FIG. 2, the three-dimensional multi-layer model of the engine bracket is unfolded towards the periphery by taking an engine injection hole as the center, and the single edge at the edge cutting part is increased by 20mm after the unfolding for overlapping during multi-layer installation.
In the above preferred embodiment, preferably, when the one-end-opened three-dimensional model is a rectangular parallelepiped, as shown in fig. 3, the three-dimensional model is cut along a plurality of edges of the rectangular parallelepiped, so that the sum of the cutting lengths is minimized.
The principles and embodiments of the present application are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts of the present application. The foregoing is only a preferred embodiment of the present application, and it should be noted that there are objectively infinite specific structures due to the limited character expressions, and it will be apparent to those skilled in the art that a plurality of modifications, decorations or changes may be made without departing from the principle of the present application, and the technical features described above may be combined in a suitable manner; such modifications, variations, combinations, or adaptations of the invention using its spirit and scope, as defined by the claims, may be directed to other uses and embodiments, or may be learned by practice of the invention.
Claims (6)
1. A method for unfolding and designing a thermal control multilayer model of a spacecraft is characterized in that,
unfolding the three-dimensional model with edges: cutting along one edge or a plurality of edges of the three-dimensional model, and enabling the sum of cutting lengths to be minimum;
unfolding the conical surface model: dividing the conical surface model into a plurality of sub conical surfaces in the circumferential direction, and flattening by taking the central line of the sub conical surfaces as a central axis;
unfolding the cylindrical surface model: the cylindrical surface model is circumferentially divided into a plurality of sub-arc surfaces, and one side edge parallel to the central line of the cylindrical surface model along the sub-arc surfaces is used as a central axis for flattening;
unfolding the spherical model: the spherical model is divided into a plurality of subspheres in the circumferential direction, and triangular surface patch cutting is carried out on a plurality of positions on the subspheres, so that the breaking times of the subspheres during unfolding are minimum.
2. The method for unfolding design of a thermal control multilayer model of a spacecraft as claimed in claim 1, wherein when the three-dimensional model with edges is a three-dimensional model with openings at two ends, the three-dimensional model is cut along the shortest edge, and a 20mm overlapping edge is additionally arranged on the cut single-side edge.
3. The method for unfolding design of a thermal control multilayer model of a spacecraft of claim 1, wherein when the three-dimensional model with edges is a three-dimensional model with an opening at one end, the three-dimensional model with edges is unfolded by cutting off a plurality of edges so as to take the surface with the largest area as a center.
4. The method for unfolding design of the thermal control multilayer model of the spacecraft of claim 3, wherein when the three-dimensional model with the opening at one end is a cuboid, the three-dimensional model is cut along a plurality of edges of the cuboid, so that the sum of the cutting lengths is minimum.
5. The method for unfolding design of a thermal control multilayer model of a spacecraft as claimed in claim 3, wherein when the three-dimensional model with the one open end is non-cuboid, a 20mm overlapping edge is additionally arranged on the cut single-side edge.
6. The method for unfolding design of a multi-layer spacecraft thermal control model according to claim 1, wherein a 20mm lap edge is added on one side of a fracture of the subsphere.
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Citations (9)
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| CN102541109A (en) * | 2011-12-14 | 2012-07-04 | 北京卫星环境工程研究所 | Method for manufacturing satellite star surface temperature-control multilayer |
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| CN102541109A (en) * | 2011-12-14 | 2012-07-04 | 北京卫星环境工程研究所 | Method for manufacturing satellite star surface temperature-control multilayer |
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