Flexible solar wing combined pressing structure and forming method

Abstract

According to the flexible solar wing combined pressing structure and the forming method, a carbon fiber composite material curing tool is adopted, and thermal expansion matching in the heating and curing process is guaranteed; certain machining allowance is reserved in the important interface part state, and the high-precision requirement of the flexible solar wing combined pressing structure interface is guaranteed through combined machining; a multi-surface interface embedded part is optimized into a combined embedded part structure form, so that the interface bearing performance of the combined compression structure of the flexible solar wing structure is ensured; the machining height tolerance of all the embedded parts is finely controlled, a special combined embedded part gluing positioning tool is designed, and the flatness of a reference working face is guaranteed; and a pressing state evaluation tool is designed, so that the stable long-period rebound mechanical performance is ensured. The problems that in the forming process of an existing flexible solar wing combined pressing structure, the interface precision is out of tolerance, the bearing capacity of a local interface is insufficient, the flatness of a reference working face is insufficient, and the flexible pressing state cannot be quantitatively evaluated are solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of composite material molding, and in particular relates to a flexible solar wing combined pressing structure and a high-precision molding method. Background Art

[0002] Compared with traditional rigid and semi-rigid solar wings, flexible solar wings have the advantages of small folding envelope, high storage ratio, light weight, and high specific power, which can meet the high power requirements of future ultra-high-power spacecraft. The circular flexible solar wing is the carrier platform of the solar cell array. It is a flexible and foldable structure that is folded during the launch phase and unfolded like an umbrella during the in-orbit phase. The circular flexible solar wing combined compression structure is one of the important components of the circular solar wing of the spacecraft. It is equivalent to the "umbrella handle" of the circular solar wing and is the only rigid reference for the assembly of the entire flexible solar wing. The flexible solar wing combined compression structure is formed by a combination of a rigid support structure and a flexible compression structure, which can simultaneously realize the rigid support of the solar wing structure and the flexible compression of the solar cell. The launch section compresses the solar wing on the side of the probe, and after entering orbit, the solar wing is unfolded and tensioned to form a circular solar wing array, realizing the functions of assembly and folding of the solar wing array, compression and buffering of the cell, unfolding and release, and load transfer. In order to ensure that the solar wing combined clamping structure and other components are assembled, clamped, unfolded and locked in place, high requirements are placed on the position of the installation interface of the combined clamping structure and the flatness of the clamping reference working surface; in order to ensure that the flexible clamping state matches the bearing capacity of the battery cell, long-term rebound mechanical performance stability requirements are placed on the combined clamping structure.

[0003] The flexible solar wing combined clamping structure is a 1 / 20 arc-shaped nearly fan-shaped structure with an envelope size of (2800±0.5)mm×(900±0.5)mm×35mm, including a rigid support structure and a flexible clamping structure. The rigid support structure is a full-carbon composite sandwich structure, mainly composed of two layers of carbon fiber composite panels inside and outside, an aluminum honeycomb core in the middle, and 23 types of carbon fiber composite embedded parts pre-embedded inside, a total of 92 pieces. The whole is assembled and positioned by adhesive composite, and then cured to form the rigid support structure body. The flexible clamping structure is a flexible buffer material and structure set on the side where the rigid support structure contacts the solar blanket solar cell array, which is used to realize the clamping and buffering functions of the solar cell array. At present, the commonly used process methods for rigid support and flexible clamping are to place all parts on the bonding and curing tooling for one-time positioning and compounding, and then glue the flexible structure to form a combined clamping structure assembly. This method currently has the following disadvantages:

[0004] (1) Due to the long length of the flexible solar wing assembly compression structure (2800mm±0.5mm), the large number of parts, and the large number of assembly positioning positions, it is very easy for the thermal expansion of the side positioning tooling at both ends and the embedded parts interface to not match during the composite heating and curing process, causing the side interface embedded parts to be delaminated or the interface accuracy to exceed the tolerance.

[0005] (2) The flexible solar wing combination compression structure needs to provide multiple interfaces in multiple directions, such as with the solar blanket, central deployment mechanism, compression release mechanism, deployment locking mechanism, tension control mechanism, compression carbon strips, drive motors, whole device interfaces, and ground assembly tooling. Since the bearing capacity of carbon fiber composite materials in non-thickness direction openings is weak, the local interface bearing capacity of the flexible solar wing combination compression structure is insufficient, resulting in problems such as delamination and splitting.

[0006] (3) There are many types and quantities of parts in the flexible solar wing combination clamping structure. The surface quality and height uniformity matching of any part will have a coupling effect on the flatness of the reference working surface after one-time positioning and compounding, which can easily cause the problem of insufficient flatness of the reference working surface of the flexible solar wing combination clamping structure.

[0007] (4) The post-bonded flexible structure uses flexible open-cell foam whose size corresponds to the area occupied by the solar cells and is bonded to the rigid support structure. The foam pre-deformation is used to achieve uniform loading and buffering of the solar cell array under vibration conditions. Currently, only its role and function can be qualitatively evaluated, and it is impossible to quantitatively evaluate the flexible compression state and confirm whether the requirements for stable long-term rebound mechanical properties can be achieved. Summary of the invention

[0008] In order to overcome the deficiencies in the prior art, the inventors have conducted intensive research and provided a flexible solar wing combination compression structure and a high-precision molding method to solve at least one technical problem that occurs during the molding process of the existing flexible solar wing combination compression structure, such as excessive interface accuracy, insufficient local interface bearing capacity, insufficient reference working surface flatness, and inability to quantitatively evaluate the flexible compression state.

[0009] The technical solution provided by the present invention is as follows:

[0010] In a first aspect, a flexible solar wing combined compression structure includes a rigid support structure and a flexible compression structure, wherein the rigid support structure includes two layers of carbon fiber composite panels, an intermediate sandwich honeycomb core material, and an internal carbon fiber composite embedded part; the flexible compression structure is a flexible buffer layer provided on a side of the rigid support structure in contact with a solar blanket solar cell array;

[0011] The multi-faceted interface embedded parts in the carbon fiber composite material embedded parts adopt a combined embedded part structure. The multi-faceted interface embedded parts are assembled by gluing multiple parts. The punching direction on each part is consistent with the thickness direction of the carbon fiber composite material ply of the part. The parts are assembled by overall gluing to form a combined embedded part with interfaces on multiple surfaces.

[0012] In a second aspect, a method for forming a flexible solar wing assembly compression structure includes:

[0013] The rigid support structure of the flexible solar wing combined compression structure is formed into an integrated structure by one-time gluing and curing. Specifically:

[0014] Assemble the structural parts of the rigid support structure in the flexible solar wing assembly compression structure, and apply adhesive to the contact surfaces of adjacent structural parts;

[0015] A full carbon fiber composite material cured bottom plate and a full carbon fiber composite material equalizing plate are arranged on the outsides of the inner and outer carbon fiber composite material panels respectively;

[0016] The carbon fiber composite panel of the rigid support structure, the all-carbon fiber composite cured bottom plate, and the all-carbon fiber composite equalizing plate are expanded and cured synchronously to form a flexible solar wing combined compression structure;

[0017] After the rigid support structure of the flexible solar wing combined compression structure is cured by one-time bonding, the flexible compression structure is bonded to the side of the rigid support structure in contact with the solar blanket solar cell array.

[0018] Furthermore, the flexible clamping structure uses a clamping state evaluation tool to evaluate the long-cycle rebound mechanical properties. The clamping state evaluation tool includes a test table, a pressure equalizing tool plate, a constant pressure counterweight and two limit screws. The evaluation method includes the following steps:

[0019] (1) Place the flexible compression structure on the test work surface;

[0020] (2) Place the limit screws on the test work surface in a low displacement state;

[0021] (3) evenly placing the pressure-equalizing tooling plate on the upper surface of the flexible pressing structure;

[0022] (4) Place the constant pressure counterweight on the pressure equalizing tooling plate, and the flexible clamping structure begins to compress. The pressure generated by the constant pressure counterweight is P 定 ;

[0023] (5) After the constant pressure counterweight is loaded and the compression state of the flexible clamping structure is stable, the limit screw is screwed out upward until it just contacts the lower plate surface of the pressure equalizing tooling plate, and the limit screw is fixed;

[0024] (6) Every other week, all the constant pressure counterweights are unloaded. After the flexible compression structure is fully restored at room temperature, the fixed counterweight is used as the step difference to load in stages until the pressure equalizing tooling plate touches the limit screw. Then the loading is stopped and the loading pressure P at this time is recorded. The attenuation pressure is P 定 -P;

[0025] During the entire test period, when P 定-P≤2.25kPa, indicating that the long-term rebound performance of the compressed state is stable; within the entire test cycle, P 定 - When P>2.25kPa, it indicates that the long-term rebound performance in the compressed state is unstable.

[0026] A flexible solar wing assembly compression structure and a high-precision molding method provided by the present invention have the following beneficial effects:

[0027] (1) The present invention provides a flexible solar wing combined clamping structure and a high-precision molding method, which adopts a carbon fiber composite material curing tooling to ensure thermal expansion matching during the heating and curing process. The flexible solar wing structure combined clamping structure rigid support structure innovatively adopts a full carbon fiber composite material curing base plate and a full carbon fiber composite material equalizing plate for gluing and curing positioning during the heating and curing process of the rigid support structure. During the heating and curing process of the rigid support structure, the carbon fiber composite material panel of the rigid support structure and the full carbon fiber composite material curing base plate and the equalizing plate are expanded and cured synchronously. After the curing is completed and the temperature is lowered, they are cooled and contracted synchronously. Since the thermal expansion coefficients of the rigid support structure and the gluing and curing tooling match each other, each structure expands and contracts synchronously, thereby effectively ensuring the molding quality and interface accuracy of the product during the one-time positioning and composite process.

[0028] (2) The present invention provides a flexible solar wing combined compression structure and a high-precision molding method, in which multi-faceted interface embedded parts are optimized into a combined embedded part structure to ensure the bearing performance of the interface of the combined compression structure of the flexible solar wing structure. In view of the problem that the bearing capacity of the central mechanism interface embedded parts, hinge interface embedded parts, compression point interface embedded parts, etc. is weak due to the opening bearing capacity of the carbon fiber composite material in the non-thickness direction, resulting in insufficient bearing capacity of the final combined compression interface, the present invention innovatively optimizes the multi-faceted interface embedded parts into a combined embedded part structure, according to the characteristics of the corresponding embedded part punching direction, based on the principle that "the punching direction of the carbon fiber composite material is consistent with the thickness direction of the ply", the multi-faceted interface is optimized into a plurality of parts glued together and assembled, and finally assembled into a combined embedded part through overall gluing, which can ensure the bearing performance of the flexible solar wing combined compression structure.

[0029] (3) The present invention provides a flexible solar wing combination clamping structure and a high-precision molding method. The machining height tolerances of all embedded parts are finely controlled, and a special combination embedded part gluing and positioning tooling is designed to ensure the flatness of the reference working surface. For the clamping point interface combined embedded parts, the machining tolerance is guaranteed by gluing assembly. According to the structural characteristics of the clamping point interface combined embedded parts, a special gluing assembly tooling is designed. The gluing assembly tooling can ensure the symmetrical gluing of the clamping point combined embedded parts through the gluing tooling bottom plate, discretely arranged gluing tooling positioning blocks, and the gluing tooling top clamping plate. The total height tolerance of the clamping point interface combined embedded parts meets the gluing assembly tolerance requirements.

[0030] (4) The present invention provides a flexible solar wing combined clamping structure and a high-precision molding method. Important embedded parts such as the center mechanism interface embedded parts, the clamping point interface embedded parts, and the hinge interface embedded parts are reserved with a certain machining margin in the state of parts. In the state of rigid support structure components, all spatial dimensions are machined in place at one time with reference to a unified machining reference, thereby ensuring high-precision molding of the combined clamping structure.

[0031] (5) The present invention provides a flexible solar wing assembly clamping structure and a high-precision molding method, and designs a clamping state evaluation tool to ensure stable long-cycle rebound mechanical properties. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 Schematic diagram of the use state of the flexible solar wing combined compression structure when the flexible solar wing is unfolded;

[0033] Figure 2 A schematic diagram of the flexible solar wing assembly compression structure of the present invention;

[0034] Figure 3 Schematic diagram of the assembly of the flexible solar wing combined compression structure curing tooling of the present invention;

[0035] Figure 4 Schematic diagram of the position of the embedded parts of the combined compression structure of the flexible solar wing of the present invention;

[0036] Figure 5 A schematic diagram of the structure of the central mechanism interface assembly embedded parts of the flexible solar wing assembly compression structure of the present invention;

[0037] Figure 6 A schematic diagram of the structure of the hinge interface assembly embedded parts of the flexible solar wing assembly compression structure of the present invention;

[0038] Figure 7 A schematic diagram of the structure of the pre-embedded parts of the compression point interface combination of the flexible solar wing combination compression structure of the present invention;

[0039] Figure 8 Schematic diagram of the adhesive joint tooling of the compression point interface combination embedded parts of the flexible solar wing combination compression structure of the present invention;

[0040] Fig. 9 Schematic diagram of the clamping state evaluation tooling of the flexible solar wing assembly clamping structure of the present invention, (a) is a schematic diagram of the free state; (b) is a schematic diagram of the constant displacement state. DETAILED DESCRIPTION

[0041] The following detailed description of the present invention will make the features and advantages of the present invention more clear and explicit.

[0042] The word “exemplary” is used exclusively herein to mean “serving as an example, example, or illustration.” Any embodiment described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments.

[0043] The invention provides a flexible solar wing combined pressing structure and a high-precision forming method. Figure 1 This is the usage state of the flexible solar wing combined clamping structure when the flexible solar wing is unfolded. At this time, the flexible solar wing combined clamping structure 1 and its mirror image 2 are locked at the back to realize the 360° unfolding and assembly of the flexible solar wing. At this time, the solar wing area is the largest; in the ground state, the flexible solar wing structure 1 and its mirror image 2 are locked at the front to compress the entire folded solar wing battery array to the side of the detector, greatly reducing the occupied space in the rocket fairing. During the rocket launch phase, the pre-deformation of the flexible clamping structure can be used to achieve uniform loading of the solar battery array and stress maintenance in a vibration environment, ensuring the safety of the solar battery array structure during the launch phase. During the on-orbit operation phase, the flexible solar wing combined clamping structure 1 gradually unfolds, releases, and locks the solar wing to form a circular array surface. As a whole wing force transmission structure, it transmits the dynamic load of the solar blanket and related components to the root hinge, and then to the whole device structure, ensuring the overall structural safety of the solar wing.

[0044] like Figure 2 As shown, the flexible solar wing combined compression structure is a 1 / 20 arc-surface nearly fan-shaped structure, including a carbon fiber composite material panel 1-1, a honeycomb core material 1-2, 23 types of 92 carbon fiber composite material embedded parts 1-3 and a flexible compression structure 1-4.

[0045] like Figure 3 As shown, during the one-time gluing and curing of the rigid support structure of the flexible solar wing combined compression structure, an innovative all-carbon fiber composite material curing base plate 1-5 and an all-carbon fiber composite material equalizing pressure plate 1-6 are used for gluing and curing positioning. During the heating and curing process of the rigid support structure, the carbon fiber composite material panel 1-1 of the rigid support structure and the all-carbon fiber composite material curing base plate 1-5 and the all-carbon fiber composite material equalizing pressure plate 1-6 are expanded and cured synchronously. After the curing is completed and the temperature is lowered, they are cooled and contracted synchronously. Since the thermal expansion coefficients of the rigid support structure and the gluing and curing tooling match each other, each structure expands and contracts synchronously, thereby effectively ensuring the product molding quality and interface accuracy of the one-time positioning composite process.

[0046] Furthermore, during the primary adhesive curing of the flexible solar wing combined compression structure, in order to prevent the carbon fiber composite embedded part 1-3 from moving, the positioning pin / screw 1-7 is used to penetrate the inherent through hole in the carbon fiber composite embedded part 1-3 and the avoidance hole on the carbon fiber composite panel 1-1, the all-carbon fiber composite cured bottom plate 1-5 and the all-carbon fiber composite equalizing plate 1-6, and the clamping nut 1-9 is used in conjunction with the positioning pin / screw 1-7 to lock the flexible solar wing combined compression structure to be cured, thereby improving the product molding quality and interface accuracy. If the aperture of the avoidance hole on the all-carbon fiber composite cured bottom plate 1-5 and the all-carbon fiber composite equalizing plate 1-6 is larger than the positioning pin / screw 1-7, then the annular positioning gasket 1-8 is processed, the outer diameter of the gasket matches the avoidance hole of the all-carbon fiber composite cured bottom plate 1-5 and the all-carbon fiber composite equalizing plate 1-6, and the inner diameter is equivalent to the inner diameter of the positioning pin / screw 1-7.

[0047] Figure 4 The distribution of the center mechanism interface embedded parts, hinge interface embedded parts, and compression point interface embedded parts are shown. The above three interface embedded parts are multi-faceted interface embedded parts of carbon fiber composite materials, that is, interfaces are processed on multiple faces of the embedded parts. Since the bearing capacity of the openings in the non-thickness direction of the carbon fiber composite materials is relatively weak, it may cause insufficient bearing capacity of the final combined compression structure. The present invention innovatively optimizes the multi-faceted interface embedded parts into a combined embedded part structure. According to the characteristics of the punching direction of the corresponding embedded parts and based on the principle that "the punching direction of the carbon fiber composite material is consistent with the thickness direction of the layer", the multi-faceted interface embedded parts are optimized into a plurality of parts glued together and assembled. The punching direction on each part is consistent with the thickness direction of the carbon fiber composite material layer of the part. Finally, the combined embedded parts are assembled through overall gluing, which can ensure the bearing performance of the flexible solar wing combined compression structure.

[0048] Figure 5 The schematic diagram of the structure of the central mechanism interface combined embedded parts is an integrated central mechanism interface embedded part. The central mechanism interface combined embedded part 1-3-1 provides an interface for the central deployment mechanism pressing surface, the central deployment mechanism guide wheel positioning pin, the tension control mechanism deployment rope fixing pin, etc., and includes a first square sleeve structure 1-3-1-1 and a plurality of interface sub-embedded parts (1-3-1-2, 1-3-1-3, 1-3-1-4); the first square sleeve structure 1-3-1-1 is a carbon fiber composite material structural part prepared by a winding process of carbon fiber prepreg, such as the carbon fiber prepreg is wound on the surface of a rectangular model and cured, and a plurality of through holes are distributed on the four faces of the first square sleeve structure 1-3-1-1 according to the interface layout; the interface sub-embedded parts are arranged in the first square sleeve structure 1-3-1-1 and fit the inner wall, and each interface sub-embedded part provides an interface in one direction, and the interface direction is consistent with the thickness direction of the sub-embedded carbon fiber composite material layer, and coincides with the through holes on the first square sleeve structure 1-3-1-1.

[0049] The central mechanism interface assembly embedded parts can be pre-cured into an integrated structure. After the mating surfaces of the first square sleeve structure and the plurality of interface sub-embedded parts are bonded with an adhesive, the adhesive is cured according to a corresponding curing system to complete the assembly.

[0050] Figure 6 Schematic diagram of hinge interface combination embedded parts structure composed of hinge interface embedded parts. Hinge interface combination embedded parts 1-3-2 provide interfaces for drive motors, root clamping and releasing mechanisms, solar wing connection frames, etc., and include a second square sleeve structure 1-3-2-3 and multiple interface sub-embedded parts (1-3-2-1, 1-3-2-2); the second square sleeve structure 1-3-2-3 is a carbon fiber composite material structural part prepared by a winding process of carbon fiber prepreg, such as the carbon fiber prepreg is wound on the surface of a rectangular model and cured, and multiple through holes are distributed on the four faces of the second square sleeve structure 1-3-2-3 according to the interface layout; the interface sub-embedded parts are arranged in the second square sleeve structure 1-3-2-3 and fit the inner wall, and each interface sub-embedded part provides an interface in one direction, and the interface direction is consistent with the thickness direction of the sub-embedded carbon fiber composite material ply, and coincides with the through holes on the second square sleeve structure 1-3-2-3.

[0051] The hinge interface assembly embedded parts can be pre-cured into an integrated structure, and the second square sleeve structure and the mating surfaces of the plurality of interface sub-embedded parts are bonded with an adhesive, and then cured according to a corresponding curing system of the adhesive to complete the assembly.

[0052] Figure 7 The schematic diagram of the structure of the combined pre-embedded parts of the clamping point interface is formed by integrating the embedded parts of the clamping point interface. The combined pre-embedded parts of the clamping point interface 1-3-3 provide interfaces for the support ribs to clamp the carbon strips, the guide blocks for the whole device to clamp and gather, the reinforcing connecting screws of the clamping point, etc. It is composed of the bottom panel 1-3-3-1 of the combined pre-embedded parts of the clamping point interface, the bottom reinforcing panel 1-3-3-2 of the combined pre-embedded parts of the clamping point interface, the center pre-embedded parts of the clamping point interface 1-3-3-3, the top reinforcing panel 1-3-3-4 of the combined pre-embedded parts of the clamping point interface and the top panel 1-3-3-5 of the combined pre-embedded parts of the clamping point interface, and provides interfaces in the direction perpendicular to the thickness of the carbon fiber composite material plies of each structural component.

[0053] like Figure 8As shown, the present invention designs a bonding assembly tooling according to the structural characteristics of the combined embedded parts of the pressing point interface, and the bonding assembly tooling includes a bonding tooling bottom plate 3-1, discretely arranged bonding tooling positioning blocks 3-2, and a bonding tooling top pressing plate 3-3; wherein the discretely arranged bonding tooling positioning blocks 3-2 include a bonding tooling middle positioning block 3-2-1 for the combined embedded parts of the pressing point interface, at least two bonding tooling front positioning blocks 3-2-2 for the combined embedded parts of the pressing point interface, and at least two bonding tooling side positioning blocks 3-2-3 for the combined embedded parts of the pressing point interface; the bonding tooling middle positioning block 3-2-1 for the combined embedded parts of the pressing point interface, at least two bonding tooling front positioning blocks 3-2-2 for the combined embedded parts of the pressing point interface, and at least two bonding tooling side positioning blocks 3-2-3 for the combined embedded parts of the pressing point interface; The upper positioning block 3-2-1 is a U-shaped structure, and the U-shaped surfaces on both sides thereof are in contact with the bottom panel and the top panel of the clamping point interface combined embedded parts; the front positioning block 3-2-2 of the clamping point interface combined embedded parts gluing tooling and the side positioning blocks 3-2-3 of the clamping point interface combined embedded parts gluing tooling are respectively arranged at the front end and both sides of the middle positioning block 3-2-1 of the clamping point interface combined embedded parts gluing tooling, and cooperate with the gluing tooling bottom plate 3-1 and the gluing tooling top clamping plate 3-3, and the discretely arranged gluing tooling positioning blocks 3-2 in the middle and the clamping point interface combined embedded parts are clamped and fixed by threaded fasteners.

[0054] When the bonding tool is used, first place the bonding tool bottom plate 3-1 on the platform, then place the bottom panel 1-3-3-1 of the pressing point interface combined embedded part 1-3-3 on the bonding tool bottom plate 3-1, then press the middle positioning block 3-2-1 of the bonding tool on the bottom panel 1-3-3-1 of the pressing point interface combined embedded part, then place the bottom reinforcement panel 1-3-3-2 of the pressing point interface combined embedded part on the bottom panel 1-3-3-1 of the pressing point interface combined embedded part, and then place the front positioning block 3-2-1 of the bonding tool in sequence. -2-2, glue the side positioning blocks 3-2-3 of the tooling and the center embedded parts 1-3-3-3 of the clamping point interface to ensure the accuracy of the positioning blocks, and then place the top reinforcement panel 1-3-3-4 of the clamping point interface combined embedded parts and the top panel 1-3-3-5 of the clamping point interface combined embedded parts in sequence, and finally place the top clamping plate 3-3 of the glue tooling, arrange them symmetrically and tighten all the fastening screws and positioning pins to ensure the symmetrical bonding of the clamping point combined embedded parts, and the total height tolerance of the clamping point interface combined embedded parts meets the bonding assembly tolerance requirements.

[0055] like Fig. 9 As shown, the present invention innovatively designs a clamping state evaluation tool to measure the long-period rebound pressure attenuation under constant displacement compression conditions, with the attenuation pressure ≤ 15% as a standard for evaluating the stability of the long-period rebound mechanical properties of the flexible clamping structure. The clamping state evaluation tool of the present invention includes a test table 4-1, a pressure equalizing tool plate 4-2, a constant pressure counterweight 4-3, and two limit screws 4-4.

[0056] The steps for using the clamping status evaluation tool are as follows:

[0057] (1) Place the flexible pressing structure 1-4 on the test work surface 4-1;

[0058] (2) Place the limit screw 4-4 on the test work surface 4-1 in a low displacement state;

[0059] (3) evenly placing the pressure-equalizing tooling plate 4-2 on the upper surface of the flexible pressing structure 1-4;

[0060] (4) Set the constant pressure counterweight, such as 15 kPa nominal pressure, to calculate the constant pressure counterweight 4-3, place the constant pressure counterweight 4-3 on the pressure equalizing tooling plate 4-2, and the flexible clamping structure begins to compress; preferably, the size of the counterweight block is consistent with the size of the flexible clamping structure, which can ensure the pressure equalization loading of the counterweight;

[0061] (5) After the constant pressure counterweight loading is completed and the compression state of the flexible clamping structure 1-4 is stable, the limit screw 4-4 is screwed out upward until it just contacts the lower plate surface of the pressure equalizing tooling plate 4-2. At this time, the displacement is the compression displacement corresponding to the foam pressure of 15 kPa. At this time, the limit screw 4-4 is fixed;

[0062] (6) Every other week, unload all the constant pressure weights. After the flexible compression structure recovers to room temperature for at least 24 hours (considered to be fully recovered), start loading in stages with a fixed weight such as a fixed weight equivalent to 1 kPa as a step difference until the pressure equalizing tooling plate 4-2 touches the limit screw 4-4. Stop loading and record the loading pressure P at this time. The attenuation pressure is 15-P.

[0063] During the entire test cycle, when 15-P≤2.25kPa, it indicates that the long-period rebound performance in the compressed state is stable; during the entire test cycle, when 15-P>2.25kPa, it indicates that the long-period rebound performance in the compressed state is unstable.

[0064] The rigid support structure of a flexible solar wing combined compression structure of the present invention is the only rigid assembly reference for the entire flexible solar wing. Therefore, the rigid support structure requires that the three-dimensional spatial relationship of the interface, side interface and height interface within the support structure surface is relatively fixed, and the precision requirement is high. The spatial dimensions cannot be fully guaranteed by relying solely on the molding process. Therefore, important interface parts such as the center mechanism interface embedded parts, the compression point interface embedded parts, and the hinge interface embedded parts are reserved with machining allowances in the part state. In the rigid support structure assembly state, all spatial dimensions are processed in place at one time with reference to a unified processing reference, which can ensure high-precision molding of the combined compression structure.

[0065] According to the flatness requirement of the reference working surface of the combined pressing structure, the present invention decomposes the processing indicators of all parts. The panel processing thickness tolerance is H1±0.05, the honeycomb core processing tolerance is H2 (0.2, +0.25), the non-combined embedded parts height processing tolerance is H3 (-0.02, +0.02), and the combined embedded parts bonding assembly tolerance is H3 (-0.02, +0.02). All embedded parts are processed according to the above processing tolerances to ensure the flatness of the reference working surface of the final formed flexible solar wing combined pressing structure.

[0066] The high-precision molding method of a flexible solar wing combined compression structure of the present invention aims at the original molding process, and solves the problems of excessive interface accuracy, insufficient local interface bearing capacity, insufficient reference working surface flatness, and inability to quantitatively evaluate the flexible compression state in the current molding process of the flexible solar wing combined compression structure. The interface accuracy of the combined compression structure formed by the present invention is improved from 0.5mm to 0.1mm, and the local interface accuracy is improved to 0.05mm; there are no problems such as delamination and splitting caused by insufficient local interface bearing capacity; the reference surface flatness is improved from 2.7mm to 0.6mm; the compression state of the flexible compression structure is improved from only qualitative evaluation to quantitative evaluation. At present, the flexible combined compression structure has successfully passed the assessment of completing the whole wing assembly of the solar wing, multiple unfolding compression and release tests, vibration tests, and thermal vacuum tests.

[0067] The present invention has been described in detail above in conjunction with specific implementations and exemplary examples, but these descriptions cannot be understood as limiting the present invention. Those skilled in the art understand that, without departing from the spirit and scope of the present invention, a variety of equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its implementation methods, all of which fall within the scope of the present invention. The scope of protection of the present invention shall be subject to the attached claims.

[0068] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A flexible solar wing assembly compression structure, characterized in that: The invention comprises a rigid support structure and a flexible pressing structure (1-4), wherein the rigid support structure comprises two layers of carbon fiber composite material panels (1-1) and an inner and outer layer of a honeycomb core material (1-2) and an inner carbon fiber composite material embedded part (1-3); the flexible pressing structure (1-4) is a flexible buffer layer provided on the side of the rigid support structure in contact with the solar blanket solar cell array; The multi-faceted interface embedded parts in the carbon fiber composite material embedded parts (1-3) adopt a combined embedded part structure. The multi-faceted interface embedded parts are assembled by gluing multiple parts. The punching direction on each part is consistent with the thickness direction of the carbon fiber composite material ply of the part. The parts are assembled by gluing as a whole to form a combined embedded part with interfaces on multiple surfaces.

2. The flexible solar wing assembly compression structure according to claim 1 is characterized in that: The central mechanism interface combined embedded part (1-3-1) in the carbon fiber composite material embedded part (1-3) provides an interface for the central deployment mechanism pressing surface, the central deployment mechanism guide wheel positioning pin, and the tension control mechanism deployment rope fixing pin, and comprises a first square sleeve structure (1-3-1-1) and a plurality of interface sub-embedded parts; the first square sleeve structure (1-3-1-1) is a carbon fiber composite material structural part prepared by a winding process of carbon fiber prepreg, and a plurality of through holes are distributed on four surfaces of the first square sleeve structure (1-3-1-1) according to the interface layout; the interface sub-embedded parts are arranged in the first square sleeve structure (1-3-1-1) and fit the inner wall, and each interface sub-embedded part provides an interface in one direction, the interface direction is consistent with the thickness direction of the sub-embedded part carbon fiber composite material ply, and coincides with the through holes on the first square sleeve structure (1-3-1-1).

3. The flexible solar wing assembly compression structure according to claim 1 is characterized in that: The hinge interface combined embedded part (1-3-2) in the carbon fiber composite material embedded part (1-3) provides an interface for a drive motor, a root pressing and releasing mechanism, and a solar wing connecting frame, and comprises a second square sleeve structure (1-3-2-3) and a plurality of interface sub-embedded parts; the second square sleeve structure (1-3-2-3) is a carbon fiber composite material structural part prepared by a winding process of carbon fiber prepreg, and a plurality of through holes are distributed on four surfaces of the second square sleeve structure (1-3-2-3) according to the interface layout; the interface sub-embedded parts are arranged in the second square sleeve structure (1-3-2-3) and fit the inner wall, and each interface sub-embedded part provides an interface in one direction, the interface direction is consistent with the thickness direction of the sub-embedded part carbon fiber composite material ply, and coincides with the through holes on the second square sleeve structure (1-3-2-3).

4. The flexible solar wing assembly compression structure according to claim 1, characterized in that: The compression point interface combined embedded part in the carbon fiber composite material embedded part (1-3) provides an interface for the support ribs to compress the carbon strips, the whole device to compress the guide block, and the compression point reinforcement connection screws. It is composed of a compression point interface combined embedded part bottom panel (1-3-3-1), a compression point interface combined embedded part bottom reinforcement panel (1-3-3-2), a compression point interface center embedded part (1-3-3-3), a compression point interface combined embedded part top reinforcement panel (1-3-3-4) and a compression point interface combined embedded part top panel (1-3-3-5) which are stacked in sequence, and provides an interface in a direction perpendicular to the thickness of the carbon fiber composite material plies of each structural part.

5. A method for forming a flexible solar wing assembly compression structure according to any one of claims 1 to 4, characterized in that: include: The rigid support structure of the flexible solar wing combined compression structure is formed into an integrated structure by one-time gluing and curing. Specifically: Assemble the structural parts of the rigid support structure in the flexible solar wing assembly compression structure, and apply adhesive to the contact surfaces of adjacent structural parts; A full carbon fiber composite material cured bottom plate and a full carbon fiber composite material equalizing plate are arranged on the outsides of the inner and outer carbon fiber composite material panels respectively; The carbon fiber composite panel of the rigid support structure is expanded and cured synchronously with the all-carbon fiber composite cured bottom plate and the all-carbon fiber composite equalizing plate to form a flexible solar wing combined compression structure; After the rigid support structure of the flexible solar wing combined compression structure is cured by one-time bonding, the flexible compression structure is bonded to the side of the rigid support structure in contact with the solar blanket solar cell array.

6. The method for forming the flexible solar wing combined compression structure according to claim 5, characterized in that: When the rigid support structure of the flexible solar wing combined compression structure is cured by one-time adhesive bonding, positioning pins or screws (1-7) are used to penetrate the inherent through holes in the carbon fiber composite embedded parts (1-3) and the avoidance holes on the carbon fiber composite panel (1-1), the all-carbon fiber composite curing bottom plate (1-5) and the all-carbon fiber composite equalizing plate (1-6), and the clamping nuts (1-9) are used in conjunction with the positioning pins or screws (1-7) to lock the flexible solar wing combined compression structure to be cured.

7. The method for forming the flexible solar wing combined compression structure according to claim 6, characterized in that: When the diameter of the avoidance hole on the all-carbon fiber composite material cured bottom plate (1-5) and the all-carbon fiber composite material equalizing plate (1-6) is larger than the positioning pin / screw (1-7), an annular positioning gasket (1-8) is provided at the avoidance hole, and the outer diameter of the positioning gasket matches the avoidance hole of the all-carbon fiber composite material cured bottom plate (1-5) and the all-carbon fiber composite material equalizing plate (1-6), and the inner diameter is equivalent to the inner diameter of the positioning pin or screw (1-7).

8. The method for forming the flexible solar wing combined compression structure according to claim 5, characterized in that: The central mechanism interface combination embedded parts, hinge interface combination embedded parts and compression point interface combination embedded parts are pre-cured into an integrated structure, and then assembled, glued and cured with other structural parts in the rigid support structure of the flexible solar wing combination compression structure.

9. The method for forming the flexible solar wing combined compression structure according to claim 5, characterized in that: The molding of the pressing point interface combined embedded part adopts a bonding assembly tool, which comprises a bonding tool bottom plate (3-1), discretely arranged bonding tool positioning blocks (3-2), and a bonding tool top clamping plate (3-3); when the bonding tool is used, the bonding tool bottom plate (3-1) is first placed on the platform, and then the bottom panel (1-3-3-1) of the pressing point interface combined embedded part (1-3-3) is placed on the bonding tool bottom plate (3-1), and then the bonding tool middle positioning block (3-2-1) is pressed on the bottom panel (1-3-3-1) of the pressing point interface combined embedded part, and then the bottom reinforcement panel (1-3- 3-2) is placed on the bottom panel (1-3-3-1) of the clamping point interface combined embedded part, and then the front positioning block (3-2-2) of the bonding tool, the side positioning block (3-2-3) of the bonding tool and the center embedded part (1-3-3-3) of the clamping point interface are placed in sequence, and then the top reinforcement panel (1-3-3-4) of the clamping point interface combined embedded part and the top panel (1-3-3-5) of the clamping point interface combined embedded part are placed in sequence, and finally the top clamping plate (3-3) of the bonding tool is placed, and all the fastening screws and positioning pins are tightened symmetrically, so that the clamping point interface combined embedded parts are symmetrically bonded, and the total height tolerance of the clamping point interface combined embedded parts meets the bonding assembly tolerance requirements.

10. The method for forming a flexible solar wing assembly compression structure according to claim 5, characterized in that: The flexible clamping structure uses a clamping state evaluation tool to evaluate the long-period rebound mechanical properties. The clamping state evaluation tool includes a test table (4-1), a pressure equalizing tool plate (4-2), a constant pressure counterweight (4-3) and two limit screws (4-4). The evaluation method includes the following steps: Placing the flexible pressing structure (1-4) on the test work surface (4-1); Place the limit screw (4-4) on the test work surface (4-1) in a low displacement state; Evenly placing the pressure-equalizing tooling plate (4-2) on the upper surface of the flexible pressing structure (1-4); The constant pressure counterweight (4-3) is placed on the pressure equalizing tooling plate (4-2), and the flexible pressing structure begins to compress. The pressure generated by the constant pressure counterweight (4-3) is P 定 ; After the constant pressure counterweight loading is completed and the compression state of the flexible clamping structure (1-4) is stabilized, the limit screw (4-4) is screwed out upward until it just contacts the lower plate surface of the pressure equalizing tooling plate (4-2), and the limit screw (4-4) is fixed; Every other week, all the constant pressure counterweights are unloaded. After the flexible compression structure is fully restored at room temperature, the fixed counterweight is used as the step difference for graded loading. After the pressure equalizing tooling plate (4-2) touches the limit screw (4-4), the loading is stopped and the loading pressure P at this time is recorded. The attenuation pressure is P 定 -P; During the entire test period, when P 定 -P≤2.25kPa, indicating that the long-term rebound performance of the compressed state is stable; within the entire test cycle, P 定 - When P>2.25kPa, it indicates that the long-term rebound performance in the compressed state is unstable.

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