A cloth patch method and tooling for OSR pasting on spacecraft surface

Abstract

The present invention discloses a patch method and tooling for pasting OSR on the surface of a spacecraft, the patch method comprising the following steps: dividing the surface of the spacecraft into a plurality of patch areas of predetermined sizes for standardized patching; providing a patch tooling consistent with the patch area, the patch tooling array having a plurality of recessed grid areas for accommodating OSR sheets; arranging the OSR sheets in the recessed grid areas of the patch tooling; providing a patch board with a surface adhesive treatment and flexibility; positioning the patch board and the patch tooling, and pressing the OSR sheet array surface on the patch tooling, transferring the OSR sheet array to the patch board by utilizing the adhesiveness of the surface of the patch board; pasting the OSR sheet array on the patch board to the surface of the spacecraft by using patch adhesive. The above-mentioned patch method can reduce the workload and difficulty of patching, improve the uniformity and efficiency of patching, and reduce the dependence on the technical ability of the operator.

Description

Technical Field

[0001] The invention relates to the technical field of aerospace thermal control coating manufacturing, and in particular to a method and tooling for pasting OSR on the surface of a spacecraft. Background Art

[0002] Antistatic cerium glass silver-coated secondary surface mirror, also known as optical solar reflector (OSR), is one of the most commonly used thermal control materials for satellites and other spacecraft, and is increasingly widely used in the field of spacecraft thermal control. The OSR specification is generally 40mm×40mm, and the thickness is less than 0.2mm. When applied, it is directly pasted on the outer heat dissipation surface of the satellite with conductive adhesive. When pasting OSR, it is necessary to evenly arrange the single-piece packaged OSR sheets on the surface of the spacecraft in advance. In order to ensure the total area of ​​the heat dissipation mirror, the gap between each OSR sheet must not be greater than 0.2mm, and they must be evenly arranged.

[0003] Therefore, the existing cloth pieces have a large workload and difficulty, low efficiency, and are highly dependent on the operating level of the operator. Summary of the invention

[0004] In view of this, the present invention provides a method and tooling for pasting OSR on the surface of a spacecraft, which can reduce the workload and difficulty of pasting, improve the uniformity and efficiency of pasting, and reduce the dependence on the technical ability of the operator.

[0005] The present invention adopts the following specific technical solutions:

[0006] The present invention provides a method for pasting OSR on the surface of a spacecraft, the method comprising the following steps:

[0007] Step 1: Divide the spacecraft surface into a number of patch areas of predetermined sizes for standardized patching;

[0008] Step 2, providing a fabric tooling that is consistent with the patch area, wherein the fabric tooling array is provided with a plurality of recessed grid areas for accommodating the OSR sheet;

[0009] Step 3, arranging the OSR sheets in the recessed grid area of ​​the fabric tooling;

[0010] Step 4, providing a cloth sheet with a flexible surface and treated with adhesive;

[0011] Step 5: Position the cloth sheet and the cloth sheet fixture, and press them onto the surface of the OSR sheet array on the cloth sheet fixture, and transfer the OSR sheet array to the cloth sheet by utilizing the stickiness of the surface of the cloth sheet;

[0012] Step six: stick the OSR array on the cloth board to the surface of the spacecraft using patch adhesive.

[0013] Furthermore, in step one, the surface of the spacecraft is divided into a number of rectangular patch areas of predetermined sizes.

[0014] Furthermore, the cloth sheet is made of epoxy glass fiber cloth sheet with a thickness of 0.5 mm.

[0015] Furthermore, the surface adhesive treatment is achieved by coating the adsorption surface of the epoxy glass fiber cloth board with a rubber film.

[0016] In addition, the present invention also provides a cloth piece tooling used in the above cloth piece method, the cloth piece tooling comprises a base plate;

[0017] A plurality of recessed lattice regions matching the shape of the OSR sheet are distributed in an array on the upper surface of the substrate, and the depth of the recessed lattice regions is equal to the thickness of the OSR sheet.

[0018] Furthermore, the upper surface of the substrate is provided with retaining edges around it, and the upper surface is provided with lattice walls that cross in a vertical and horizontal direction, and the lattice walls divide the area inside the retaining edges into a plurality of the recessed lattice areas.

[0019] Furthermore, positioning platforms are provided on the top surfaces of two adjacent retaining edges;

[0020] The retaining edge is provided with arc grooves at the four corners of the base plate and at the positions opposite to the ends of the lattice walls.

[0021] Beneficial effects:

[0022] The sheet laying method of the present invention first arranges the OSR sheets on the sheet laying tooling, and then utilizes the viscosity of the sheet laying plate to transfer and stick the OSR sheet array on the sheet laying tooling to the surface of the spacecraft; the sheet laying tooling can be used to pre-arrange the OSR sheets, and the sheet laying tooling can efficiently complete the arrangement of the OSR sheet array; the viscosity of the sheet laying plate can be used to transfer the pre-arranged OSR sheet array as a whole and quickly to the surface of the spacecraft; therefore, the above-mentioned sheet laying method can reduce the workload and difficulty of sheet laying, improve the uniformity and efficiency of sheet laying, and reduce the dependence on the technical ability of the operator. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 is a flow chart of the cloth patch method of the present invention;

[0024] Figure 2 It is a schematic diagram of the structure of transferring the OSR array from the cloth tooling using the cloth plate;

[0025] Figure 3 It is a schematic structural diagram of the cloth piece tooling of the present invention.

[0026] Among them, 1-cloth piece tooling, 2-cloth piece board, 11-base plate, 12-recessed lattice area, 13-retaining edge, 14-lattice wall, 15-positioning platform, 16-arc groove DETAILED DESCRIPTION

[0027] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0028] Embodiment 1

[0029] This embodiment provides a method for applying OSR to the surface of a spacecraft. Figure 1 As shown, the cloth piece method comprises the following steps:

[0030] Step 1 S1, divide the spacecraft surface into a number of patch areas of predetermined sizes for standardized patching; the patch area of ​​predetermined size can be a rectangular patch area; in the actual patching process, the surface of a spacecraft of any shape can be pre-divided into a number of rectangular areas of standard sizes; taking the standard OSR sheet size of 40mm×40mm×0.2mm as an example, the patch area can be divided into 5×6 arrays, 5×8 arrays, etc., and the pre-divided patch area facilitates the arrangement of OSR sheets in advance according to the design drawings before the formal bonding construction on the spacecraft surface, thereby improving the on-site construction efficiency;

[0031] Step 2 S2, providing a cloth piece tooling 1 consistent with the patch area, the cloth piece tooling 1 array is distributed with a plurality of recessed grid areas 12 for accommodating OSR sheets; the size of each recessed grid area 12 is just the size of a single OSR sheet, and the spacing between OSR sheets is determined by the width of the grid wall 14 between the recessed grid areas 12 (generally less than 0.2 mm); the OSR sheet can easily fall into the recessed grid area 12 when placed or slid, so as to realize the arrangement of the OSR sheet; the specific structure of the cloth piece tooling 1 can refer to Figure 2 and Figure 3 , the patch tooling 1 is consistent with the patch area divided on the surface of the spacecraft. When the patch area is divided into a 5×6 array, the patch tooling 1 can also arrange the OSR sheets in a 5×6 array; the depth of the concave grid area 12 is equal to the thickness of the OSR sheet;

[0032] Step three S3, arranging the OSR sheets in the recessed grid area 12 of the cloth sheet tooling 1; when arranging the OSR sheets in the recessed grid area 12 of the cloth sheet tooling 1, a vacuum pen or other tool may be used to place the OSR sheets into the grid of the cloth sheet tooling 1;

[0033] Step 4 S4, providing a cloth sheet 2 with a flexible and bendable surface treated with adhesive; the cloth sheet 2 can be made of an organic material board such as an epoxy glass fiber cloth sheet with a thickness of 0.5 mm; the surface adhesive treatment is achieved by coating a rubber film on the adsorption surface of the epoxy glass fiber cloth sheet; the bending is facilitated by the deflection of the cloth sheet 2, and the pasting and transfer of the OSR sheet are facilitated by the bending; the size of the cloth sheet 2 is consistent with the size of the square area of ​​the cloth sheet fixture 1, and the surface adhesive treatment can be achieved by coating a self-adhesive film on one of the surfaces, and the adhesion and transfer of the arranged OSR sheet array on the cloth sheet fixture 1 to the cloth sheet 2 are achieved by using the surface adhesive; the cloth sheet 2 can be curved to achieve the gradual pressing of the OSR sheet on the cloth sheet 2 into the adhesive glue;

[0034] Step five S5, positioning the cloth sheet plate 2 and the cloth sheet fixture 1, and pressing the surface of the OSR sheet array on the cloth sheet fixture 1, transferring the OSR sheet array to the cloth sheet plate 2 by using the stickiness of the surface of the cloth sheet plate 2, and transferring the OSR sheet array to the cloth sheet plate 2 by using the stickiness of the surface of the cloth sheet plate 2 to form a separate standard OSR "block";

[0035] Step six S6, sticking the OSR array on the cloth plate 2 to the surface of the spacecraft by using patch adhesive.

[0036] The above-mentioned laying method first arranges the OSR sheets on the cloth tooling 1, and then uses the viscosity of the cloth plate 2 to transfer and stick the OSR sheet array on the cloth tooling 1 to the surface of the spacecraft; the cloth tooling 1 can be used to arrange the OSR sheets in advance, and the cloth tooling 1 can efficiently complete the arrangement of the OSR sheet array; the viscosity of the cloth plate 2 can be used to transfer the pre-arranged OSR sheet array as a whole and quickly to the surface of the spacecraft; therefore, the above-mentioned laying method can reduce the workload and difficulty of laying, improve the uniformity and efficiency of laying, and reduce the dependence on the technical ability of the operator.

[0037] Embodiment 2

[0038] This embodiment provides a cloth piece tool 1 used in the above cloth piece method, such as Figure 2 and Figure 3As shown, the cloth piece tooling 1 includes a base plate 11; a plurality of recessed lattice areas 12 matching the shape of the OSR sheet are arranged in an array on the upper surface of the base plate 11, and the depth of the recessed lattice area 12 is equal to the thickness of the OSR sheet; a retaining edge 13 is arranged around the upper surface of the base plate 11, and a lattice wall 14 is arranged on the upper surface in a vertical and horizontal manner, and the lattice wall 14 divides the area inside the retaining edge 13 into a plurality of recessed lattice areas 12; a positioning platform 15 or a positioning groove is arranged on the top surface of two adjacent retaining edges 13, and correspondingly, on the cloth piece plate 2 A positioning hole that matches the shape of the positioning platform 15 or a positioning column that matches the shape of the positioning groove is provided. In order to facilitate the positioning of the cloth plate 2 and the cloth tooling 1, both the corresponding positioning platform 15 and the positioning hole, as well as the corresponding positioning groove and the positioning column, have the same setting position, shape and size; the positioning platform or the positioning groove can provide a positioning reference for the standard-sized cloth plate 2 to adhere and transfer the OSR sheet array; the retaining edge 13 is provided with arc grooves 16 at the four corners of the base plate 11 and at the position opposite to the end of the lattice wall 14.

[0039] The above-mentioned cloth piece tooling 1 can realize the pre-arrangement of OSR sheets, and can improve the quality and efficiency of the arrangement. The OSR sheets can be quickly transferred between the cloth piece tooling 1 and the surface of the spacecraft by gluing the cloth piece board 2.

[0040] In summary, the above are only preferred embodiments of the present invention and are not intended to limit the protection scope of the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for pasting OSR on the surface of a spacecraft, characterized in that: The following steps are involved: Step 1, dividing the spacecraft surface into a number of patch areas of predetermined sizes; Step 2: Provide a fabric tooling that is consistent with the patch area, wherein the fabric tooling array is provided with a plurality of recessed grid areas for accommodating OSR sheets; the size of each recessed grid area is exactly the size of a single OSR sheet, and the spacing size between OSR sheets is determined by the width of the grid wall between the recessed grid areas; Step 3, arranging the OSR sheets in the recessed grid area of ​​the fabric tooling; Step 4, providing a cloth sheet with a flexible surface after being treated with adhesiveness; the cloth sheet is made of an epoxy glass fiber cloth sheet with a thickness of 0.5 mm; the surface adhesiveness treatment is achieved by coating a rubber film on the adsorption surface of the epoxy glass fiber cloth sheet; Step 5: Position the cloth sheet and the cloth sheet fixture, and press them onto the surface of the OSR sheet array on the cloth sheet fixture, and transfer the OSR sheet array to the cloth sheet by utilizing the stickiness of the surface of the cloth sheet; Step six: stick the OSR array on the cloth board to the surface of the spacecraft using patch adhesive.

2. The cloth method according to claim 1, characterized in that: In step one, the spacecraft surface is divided into a number of rectangular patch areas of predetermined sizes.

3. A cloth piece tooling for use in the cloth piece method as claimed in claim 1 or 2, characterized in that: The cloth piece tooling comprises a base plate; The upper surface of the substrate is arrayed with a plurality of recessed lattice regions matching the shape of the OSR sheet, and the depth of the recessed lattice regions is equal to the thickness of the OSR sheet; The upper surface of the substrate is provided with retaining edges around the edges, and the upper surface is provided with lattice walls that cross in a vertical and horizontal direction, and the lattice walls divide the area inside the retaining edges into a plurality of the recessed lattice areas; Positioning platforms are provided on the top surfaces of two adjacent retaining edges; The retaining edge is provided with arc grooves at the four corners of the base plate and at the positions opposite to the ends of the lattice walls.

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