A satellite structure and assembly method thereof

Abstract

The invention relates to the field of spacecraft technology, in particular to a satellite structure and an assembly method thereof; the satellite structure comprises a cabin panel assembly, a positioning mechanism and a fastening mechanism; the positioning mechanism is used for positioning and resetting the cabin panel assembly, and comprises a precise positioning structure and an adjustable positioning structure, the precise positioning structure comprises an interference fixing pin hole, a clearance fixing pin hole and a cylindrical pin, one end of the cylindrical pin is interference-fitted with the interference fixing pin hole, and the other end is clearance-fitted with the clearance fixing pin hole; the adjustable positioning structure comprises a clearance movable pin hole, a movable pin countersunk hole and a movable pin, one end of the movable pin is clearance-fitted with the clearance movable pin hole, and the other end is bonded to the movable pin countersunk hole as a whole; the left cabin panel, the right cabin panel, the upper cabin panel, the lower cabin panel and the rear cabin panel are assembled and positioned by cylindrical pins; the front cabin panel and the lower cabin panel are assembled and positioned by cylindrical pins; the front cabin panel and the upper cabin panel, the left cabin panel and the right cabin panel are assembled and positioned by movable pins; the assembly precision is high, and the assembly and positioning can be precisely performed.

Description

Technical Field

[0001] The invention belongs to the technical field of spacecraft, and in particular to a satellite structure and an assembly method thereof. Background Art

[0002] The satellite structure is the main body of the satellite platform. A good satellite structure should meet the mechanical vibration resistance of the satellite on the carrier and ensure the installation and heat dissipation requirements of the equipment on the satellite. At present, small and above satellites mainly use aluminum honeycomb panel structures. The center of the aluminum honeycomb panel is an aluminum hexagonal honeycomb structure, and the outer surface is covered with a skin. It is a composite plate, which is lighter than the full aluminum plate of the same thickness. However, the strength of the aluminum honeycomb panel along the honeycomb arrangement direction is poor, and the mechanical continuity is inferior to the full aluminum plate; the satellite structure may deform, and the deformation will lead to inconsistency with the state during design and assembly, resulting in the failure of the on-board coordinate system; how to ensure that the on-board coordinate system is consistent during and after the system is established, especially during flight, is a difficult point in satellite structure design. The thermal conductivity of the aluminum honeycomb panel is poor. In order to ensure the thermal control and heat dissipation requirements of the internal equipment of the satellite, heat pipes are usually embedded in the aluminum honeycomb panel to enhance heat dissipation. Although the aluminum honeycomb panel is light in weight and can save the launch cost to a certain extent, the cost of embedding heat pipes is high, and its overall cost is also high. Summary of the invention

[0003] The technical problem to be solved by the present invention is: to overcome the above-mentioned deficiencies of the prior art, to provide a satellite structure and an assembly method thereof, to improve the mechanical properties of the satellite structure as a whole, and at the same time to ensure continuous high-intensity heat dissipation, without the need to adopt other means to enhance the thermal control and heat dissipation of the satellite's internal equipment, and the overall cost is low; at the same time, the precise assembly method simplifies the assembly process and the assembly error is adjustable and controllable, ensuring the accuracy of the on-board coordinate system, and can provide reliable input for satellite attitude and orbit control.

[0004] To solve the above technical problems, the technical solution of the present invention is: a satellite structure, including a cabin panel assembly, a positioning mechanism and a fastening mechanism;

[0005] The cabin panel components together constitute the cabin body of the satellite; the cabin panel components at least include a front cabin panel, a rear cabin panel, a left cabin panel, a right cabin panel, an upper cabin panel and a lower cabin panel;

[0006] The positioning mechanism is used for positioning the cabin panel assembly and resetting the open and closed cabin panels; the positioning mechanism includes a precise positioning structure and an adjustable positioning structure, the precise positioning structure includes an interference fixing pin hole, a clearance fixing pin hole and a cylindrical pin, one end of the cylindrical pin is interference-fitted with the interference fixing pin hole, and the other end is clearance-fitted with the clearance fixing pin hole; the adjustable positioning structure includes a clearance movable pin hole, a movable pin countersunk hole and a movable pin, one end of the movable pin is clearance-fitted with the clearance movable pin hole, and the other end is bonded to the movable pin countersunk hole as a whole;

[0007] The rear left connecting surface, the rear right connecting surface, the rear upper connecting surface and the rear lower connecting surface of the rear deck are all provided with interference fixing pin holes;

[0008] The front lower connecting surface of the front deck is provided with an interference fixing pin hole, and the front left connecting surface, the front right connecting surface and the front upper connecting surface are all provided with clearance movable pin holes;

[0009] The lower front connecting surface and the lower rear connecting surface of the lower cabin plate are both provided with gap fixing pin holes;

[0010] The upper rear connection surface of the upper deck plate is provided with a gap fixing pin hole, and the upper front connection surface is provided with a movable pin countersunk hole;

[0011] The left front connection surface of the left cabin plate is provided with a movable pin countersunk hole, and the left rear connection surface is provided with a gap fixing pin hole;

[0012] The right front connection surface of the right cabin plate is provided with a movable pin countersunk hole, and the right rear connection surface is provided with a gap fixing pin hole;

[0013] The left cabin plate, the right cabin plate, the upper cabin plate, the lower cabin plate and the rear cabin plate are positioned for assembly by cylindrical pins; the front cabin plate and the lower cabin plate are positioned for assembly by cylindrical pins; the front cabin plate and the upper cabin plate, the left cabin plate and the right cabin plate are positioned for assembly by movable pins.

[0014] In the above-mentioned satellite structure, the fastening mechanism includes a fixed connector and a corner box, and the cabin panel assembly is fastened by the fixed connector during assembly; the corner box has two mutually perpendicular connecting surfaces, which are respectively used to connect two mutually perpendicular cabin panels.

[0015] In the above-mentioned satellite structure, the cabin panel assembly also includes a plurality of partitions located inside the cabin.

[0016] In the above-mentioned satellite structure, the front cabin plate, the rear cabin plate, the left cabin plate, the right cabin plate, the upper cabin plate and the lower cabin plate are all made of lightweight metal plates. The lightweight metal plates are all metal plates. One side of the lightweight metal plate is a plane, and the other side is provided with a lightweight groove, and the groove wall of the lightweight groove forms a grid.

[0017] In the above satellite structure, the outer side surface of one end where the movable pin and the movable pin hole in the gap cooperate is a cylindrical surface, and the outer side surface of one end where the movable pin and the movable pin countersunk hole cooperate is provided with a glue groove.

[0018] The above-mentioned satellite structure assembly method comprises performing the following steps in sequence:

[0019] Step 1: Install the lower deck;

[0020] Step 2: Install the front deck and the rear deck on the lower deck respectively and complete the positioning of the front deck, the rear deck and the lower deck through cylindrical pins;

[0021] Step 3: Install the upper deck plate to the front deck plate and the rear deck plate; realize the positioning of the rear deck plate and the upper deck plate by cylindrical pins; realize the positioning of the front deck plate and the upper deck plate by movable pins;

[0022] Step 4: Tighten the upper deck, front deck, rear deck and lower deck; after the fastening is completed, the colloid is poured into the countersunk hole of the movable pin of the upper deck to solidify the position of the movable pin;

[0023] Step 5: The left and right deck panels are respectively installed and positioned on the front and rear deck panels, and the rear deck panel is positioned with the left and right deck panels by cylindrical pins, and the front deck panel is positioned with the left and right deck panels by movable pins;

[0024] After positioning is completed, fasten the left and right cabin panels to the upper, front, rear and lower cabin panels; after fastening is completed, inject colloid into the countersunk holes of the movable pins of the left and right cabin panels to solidify the positions of the movable pins.

[0025] In the above-mentioned assembly method, the satellite structure is assembled using a support vehicle, and the support vehicle is provided with an adapter seat and an adjustable height seat, and the top surface of the adjustable height seat and the top surface of the adapter seat together form a reference support surface; in step one, the lower cabin plate is installed on the reference support surface.

[0026] In the above-mentioned assembly method, before installing the lower deck, the coplanarity of the top surface of the adjustable cushion seat of the support vehicle and the top surface of the adapter seat is precisely measured and adjusted until the design requirements are met.

[0027] In the above-mentioned assembly method, in step one, after the installation of the lower deck is completed, the coplanarity of the lower front connecting surface and the lower rear connecting surface of the lower deck is precisely measured; if the coplanarity does not meet the design requirements, the lower deck is disassembled for rework.

[0028] In the above assembly method, in step 4, after the front deck, rear deck, upper deck, and lower deck are fastened and before the active pin countersunk holes of the upper deck are glued,

[0029] Accurately measure the coplanarity of the front left connection surface, front right connection surface, rear left connection surface, rear right connection surface, lower left connection surface, lower right connection surface, upper left connection surface, and upper right connection surface to determine whether the coplanarity meets the design requirements;

[0030] At the same time, the rear surface of the rear deck and the upper surface of the upper deck are dotted and precisely measured for flatness to determine whether the precisely measured values ​​are within the requirements for the processing flatness of the rear deck and the upper deck.

[0031] Compared with the prior art, the present invention has the following advantages:

[0032] 1) The satellite structure of the present invention adopts a metal lightweight plate, which is a full metal plate. One side of the metal lightweight plate is a plane, and the other side is provided with a lightweight groove. The groove wall of the lightweight groove forms a grid, which has both a continuous plane and an orthogonal cross rib grid. Compared with the aluminum honeycomb structure, it has good mechanical continuity, high rigidity and strength, good resistance to random vibration, good flatness and continuity of the installation surface; good thermal conductivity, can save the embedded heat pipe, and can save the overall cost;

[0033] 2) Compared with the prior art, the assembly method provided by the present invention can achieve high-precision assembly and measurement, ensuring accurate repeated disassembly, assembly and reset of the satellite platform structure;

[0034] 3) Ensure the mechanical vibration resistance of the satellite on the carrier, ensure the installation and heat dissipation requirements of the equipment on the satellite, reduce the overall cost, and enhance the reliability of the satellite platform; it can not only make the satellite platform meet the mechanical performance requirements of each single device, provide a safe and reliable connection and fixing platform that meets the stiffness and strength requirements for each single device, but also meet the mechanical response requirements of the launch vehicle to the satellite, and avoid the satellite from being damaged and failed in the mechanical environment of the launch vehicle;

[0035] 4) The satellite structures have high assembly accuracy, which can effectively reduce the reduction of cabin plate mechanical properties and equipment position accuracy caused by adverse assembly stress and strain in ground environment, transportation environment and aerospace environment, so that the satellite platform structure can be accurately and repeatedly disassembled and positioned. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 Install exploded diagrams for satellite structures;

[0037] Figure 2 Provide an exploded rear view of the satellite structure;

[0038] Figure 3 Provide stereograms of satellite structural parts;

[0039] Figure 4 This is a three-dimensional picture of the satellite with the cabin panel opened after the structural parts are installed;

[0040] Figure 5 This is a front cross-sectional view of the front deck connection;

[0041] Figure 6 is a front cross-sectional view of the first partition connection;

[0042] Figure 7 is a front cross-sectional view of the second partition connection;

[0043] Figure 8 It is a front cross-sectional view of the connection of the rear deck;

[0044] Fig. 9It is a structural schematic diagram of a movable pin;

[0045] Fig.10 This is a schematic diagram of the movable pin connection.

[0046] Reference numerals:

[0047] 1-front cabin board; 2-rear cabin board; 3-left cabin board; 4-right cabin board; 5-upper cabin board; 6-lower cabin board; 7-first partition board; 8-second partition board; 9-corner box; 10-fastening screw; 11-cylindrical pin; 12-movable pin;

[0048] 13-carriage support; 131-adjustable cushion seat; 132-carriage support side panel;

[0049] 14- adapter; 15- colloid. DETAILED DESCRIPTION

[0050] The present invention will be further described below in conjunction with the embodiments.

[0051] The present invention proposes a satellite structure and an assembly method. The satellite structure adopts an all-metal lightweight structure. At the same time, a precision assembly measurement method is proposed for the lightweight structure. The precision assembly measurement method can realize flexible positioning of the entire satellite structure assembly, accurate measurement of the system, and accurate resetting of the opening and closing panels.

[0052] like Figure 1 , 2 As shown, the present invention lists a satellite structure, including a cabin panel assembly, which together constitutes the cabin body of the satellite; the cabin panel assembly includes a front cabin panel 1, a rear cabin panel 2, a left cabin panel 3, a right cabin panel 4, an upper cabin panel 5, and a lower cabin panel 6. The front cabin panel 1, the rear cabin panel 2, the left cabin panel 3, the right cabin panel 4, the upper cabin panel 5, and the lower cabin panel 6 are all made of metal lightweight plates, which are all-metal plates, and 7 series aluminum alloy materials can be selected, or other alloy materials. One side of the metal lightweight plate is a plane, and the other side is provided with a lightweight groove. The specific size and arrangement of the lightweight groove can be designed differently according to different applications; the groove wall of the lightweight groove forms a grid, and the grid is designed to have a certain regularity; for example, in this embodiment, the lightweight groove adopts a uniformly distributed square groove, and the interval between two phase lightweight grooves is 2mm, which naturally forms an orthogonal 2mm thick grid. The lightweight groove can also adopt irregular grooves or irregular arrangement according to different application requirements. Among them, the installation surface thickness of the metal lightweight plate can be designed according to the thermal control requirements, and the thinnest is 1mm.

[0053] The metal lightweight plate of the above structure has high mechanical continuity, overall stiffness and strength, and at the same time has local strength reinforcement at specific locations, which can ensure the overall reliability of the satellite structure; in terms of thermal control, the all-metal continuous structure can ensure good heat dissipation of the satellite and provide a good thermal conduction environment for the on-board equipment.

[0054] It also includes several partitions, which divide the space inside the cabin into several areas; the satellite structure shown in the figure includes two parallel partitions, namely the first partition 7 and the second partition 8; the first partition 7, the second partition 8, the front cabin board 1, and the rear cabin board 2 are parallel to each other. According to design requirements, the partition can also be set in other forms, such as parallel to the left cabin board 3.

[0055] A positioning mechanism is provided between the cabin panel components for component positioning and opening and closing of the cabin panels for resetting. The positioning mechanism includes a precise positioning structure and an adjustable positioning structure. The precise positioning structure includes an interference fixing pin hole, a clearance fixing pin hole and a cylindrical pin 11; the adjustable positioning structure includes a clearance movable pin hole, a movable pin countersunk hole and a movable pin 12.

[0056] The clearance fixing pin hole and the interference fixing pin hole are connected by a cylindrical pin 11, that is, one end of the cylindrical pin 11 must be embedded in the interference fixing pin hole by an interference fitting method. This fitting method can be regarded as the cylindrical pin 11 and the interference fixing pin hole tightly fitting without a gap, that is, the position of the cylindrical pin 11 in the interference fixing pin hole is accurately known. The other end of the cylindrical pin 11 is embedded in the clearance fixing pin hole by a clearance fitting method, that is, there is a gap between the cylindrical pin 11 and the clearance fixing pin hole, and they can be directly manually aligned and inserted during assembly. The cylindrical pin 11, the clearance fixing pin hole and the interference fixing pin hole are all commonly used pin connection structures, so their structures are not described in detail here. The clearance fit between the cylindrical pin 11 and the clearance fixing pin hole can be designed according to the actual needs of the application. In this implementation case, the maximum clearance of the clearance fit is 0.02mm.

[0057] The connection structure of the gap movable pin hole, the movable pin countersunk hole and the movable pin 12 is as follows Fig. 9 and Fig.10 As shown, the surface where the movable pin 12 and the clearance movable pin hole match is a cylindrical surface, and the two are clearance matched; the clearance match can be designed according to the actual needs of the application. In this embodiment, the maximum clearance of the clearance match is 0.02mm. The outer diameter of the movable pin 12 is smaller than the inner diameter of the movable pin countersunk hole, so the movable pin 12 can be adjusted in position in the movable pin countersunk hole. After the adjustment is completed, the colloid 15 is poured into the movable pin countersunk hole. The colloid 15 is bonded and cured more firmly, and a long screw can be screwed in at the same time, which is convenient for installation and disassembly. In this embodiment, the diameter of the movable pin countersunk hole is 0.5mm larger than the outer diameter of the movable pin 12. The surface where the movable pin 12 and the movable pin countersunk hole match has an inwardly concave glue groove, and the end face has a screw hole; the contact area of ​​the colloid 15 is increased. The movable pin 12 can also be a cylindrical pin, a pin shaft, etc.

[0058] The movable pin 12 can realize flexible positioning and can cooperate with the clearance of the cabin board or the partition board. After the overall structural assembly is completed, the movable pin countersunk hole can be filled with glue and cured to achieve the purpose of accurate resetting of the cabin board opening and closing.

[0059] The connection surfaces of the rear deck 2 and the left deck 3, the right deck 4, the upper deck 5, and the lower deck 6 are set as the rear left connection surface, the rear right connection surface, the rear upper connection surface, and the rear lower connection surface respectively; interference fixing pin holes are set on the rear left connection surface, the rear right connection surface, the rear upper connection surface, and the rear lower connection surface. To ensure accurate positioning, the number of interference fixing pin holes on the rear left connection surface, the rear right connection surface, the rear upper connection surface, and the rear lower connection surface should be greater than or equal to two.

[0060] It is set that the connecting surfaces of the front cabin plate 1 and the left cabin plate 3, the right cabin plate 4, the upper cabin plate 5 and the lower cabin plate 6 are respectively set as the front left connecting surface, the front right connecting surface, the front upper connecting surface and the front lower connecting surface; the front lower connecting surface is provided with interference fixing pin holes, the number of which is greater than or equal to two; the front left connecting surface, the front right connecting surface and the front upper connecting surface are all provided with clearance movable pin holes, the number of which is at least one.

[0061] It is assumed that the connection surfaces of the lower deck 6 and the front deck 1, the rear deck 2, the left deck 3, and the right deck 4 are respectively the lower front connection surface, the lower rear connection surface, the lower left connection surface, and the lower right connection surface. The lower front connection surface and the lower rear connection surface are both provided with gap fixing pin holes, the number of which is greater than or equal to two.

[0062] It is assumed that the connection surfaces of the upper deck 5 with the front deck 1, the rear deck 2, the left deck 3, and the right deck 4 are the upper front connection surface, the upper rear connection surface, the upper left connection surface, and the upper right connection surface respectively; the connection surface of the upper deck 5 with the partition is the upper partition connection surface. The upper rear connection surface is provided with a gap fixing pin hole, the number of which should be greater than or equal to two; the upper front connection surface and the upper partition connection surface are provided with a movable pin countersunk hole, the number of which is at least one.

[0063] It is assumed that the connection surfaces of the left deck 3 and the front deck 1, the rear deck 2, the upper deck 5, and the lower deck 6 are respectively the left front connection surface, the left rear connection surface, the left upper connection surface, and the left lower connection surface. The left front connection surface is provided with a movable pin countersunk hole, the number of which is at least one; the left rear connection surface is provided with a gap fixing pin hole, the number of which should be greater than or equal to two.

[0064] It is assumed that the connection surfaces of the right deck 4 and the front deck 1, the rear deck 2, the upper deck 5, and the lower deck 6 are the right front connection surface, the right rear connection surface, the right upper connection surface, and the right lower connection surface. The right front connection surface is provided with a movable pin countersunk hole, the number of which is at least one; the right rear connection surface is provided with a gap fixing pin hole, the number of which should be greater than or equal to two.

[0065] Specifically, Figure 5-8As shown, the left deck 3, the right deck 4, the upper deck 5, the lower deck 6 and the rear deck 2 are positioned by the cylindrical pin 11. The cylindrical pin 11 is interference fit with the rear deck 2, and the left deck 3, the right deck 4, the upper deck 5, and the lower deck 6 can be positioned with the rear deck 2 by the clearance fit with the cylindrical pin 11. The front deck 1 and the lower deck 6 are positioned by the cylindrical pin 11, and the cylindrical pin 11 is interference fit with the front deck 1, and the lower deck 6 can be positioned with the front deck 1 by the clearance fit with the cylindrical pin 11. The front deck 1 and the upper deck 5, the left deck 3, and the right deck 4 are positioned by the movable pin 12.

[0066] A fastening mechanism is provided between each cabin panel assembly, and the fastening mechanism includes a fixed connector and a corner box 9. The fixed connector can be a fastening screw 10; the front cabin panel 1, the rear cabin panel 2, the left cabin panel 3, the right cabin panel 4, the upper cabin panel 5, and the lower cabin panel 6 are all fixedly connected by fastening screws 10. The corner box 9 has two mutually perpendicular connecting surfaces, which are respectively used to connect two mutually perpendicular cabin panels. Specifically, corner boxes 9 are respectively provided at the upper and lower ends of the front cabin panel 1 and the rear cabin panel 2, which are used to strengthen and fix the upper cabin panel 5 and the lower cabin panel 6; because the two connecting surfaces of the corner box 9 in contact with the cabin panel have a high degree of verticality, the overall structure can be strengthened and shaped.

[0067] It also includes several partitions, which divide the space inside the cabin into several areas; the satellite structure shown in the figure includes two parallel partitions, namely the first partition 7 and the second partition 8; the first partition 7, the second partition 8, the front cabin board 1, and the rear cabin board 2 are parallel to each other. According to design requirements, the partition can also be set in other forms, such as parallel to the left cabin board 3.

[0068] The partition and the upper deck 5 are positioned by an adjustable positioning structure, a clearance movable pin hole is set on the upper connection surface of the partition, and a movable pin countersunk hole is set on the upper deck 5 at the corresponding position; the partition and the lower deck 6 are positioned by a precise positioning structure, an interference fixing pin hole is set on the lower connection surface of the partition, and a clearance fixing pin hole is set on the lower deck 6 at the corresponding position. The partition and the upper deck 5 and the partition and the lower deck 6 are fixedly connected by fixed connectors and corner boxes 9.

[0069] The satellite structure is assembled using the support vehicle 13, which can be regarded as a reference platform. Figure 3-4 As shown, a transfer seat 14 and an adjustable cushion seat 131 are installed on the support vehicle 13, and the height of the adjustable cushion seat 131 is adjustable; the top surface of the adjustable cushion seat 131 and the top surface of the transfer seat 14 together form a reference support surface. The transfer seat 14 and the adjustable cushion seat 131 can achieve support, so the existing known structure can be adopted. The support vehicle 13 is equipped with three adjustable height feet and an adjustable tilting top rod, which can cooperate with the feet and the top rod to ensure that the top surface of all adjustable cushion seats 131 is level with the top surface of the transfer seat 14.

[0070] The satellite structure assembly method comprises the following steps:

[0071] Step 1: Install the lower deck 6;

[0072] Before the lower deck 6 is installed on the reference support surface, the coplanarity of the top surface of the adjustable height-raising seat 131 of the support vehicle 13 and the top surface of the adapter seat 14 is precisely measured and adjusted until the design requirements are met. The coplanarity of the top surfaces of all adjustable height-raising seats 131 and adapter seats 14 is precisely measured by using a theodolite and a horizontal bubble meter. In this embodiment, the coplanarity accuracy is better than 0.1mm / 600mm.

[0073] After the adjustment is completed, the lower deck plate 6 is installed on the adapter seat 14 , and the lower surface of the lower deck plate 6 contacts the top surface of the adjustable cushion seat 131 and the top surface of the adapter seat 14 .

[0074] In the actual assembly process, the front cabin panel 1, the rear cabin panel 2, the left cabin panel 3, the right cabin panel 4, and the upper cabin panel 5 are installed based on the lower cabin panel 6; therefore, the lower cabin panel 6 is first installed on the support vehicle 13, and the top surface of the adjustable cushion seat 131 on the support vehicle 13 and the top surface of the adapter seat 14 support the lower cabin panel 6.

[0075] After the lower deck 6 is installed on the support vehicle 13, the coplanarity of the lower front connecting surface and the lower rear connecting surface of the lower deck 6 is precisely measured; if the coplanarity does not meet the design requirements, the lower deck 6 is disassembled and reworked.

[0076] Specifically, a laser tracker is used to precisely measure the lower front connection surface and the lower rear connection surface to measure their coplanarity; that is, the coplanarity of the lower deck plate 6 and the front deck plate 1 and the rear deck plate 2 is precisely measured. The coplanarity should be within the flatness requirement of the lower deck plate 6. If it is higher than this value, the lower deck plate 6 should be disassembled and reworked, and the flatness of the lower deck plate 6 should be remeasured, and the coplanarity of the top surface of the adjustable pad seat 131 and the top surface of the adapter seat 14 should be remeasured and adjusted.

[0077] Step 2: Install the front deck 1 and the rear deck 2 onto the lower deck 6 respectively and complete the positioning of the front deck 1 and the rear deck 2.

[0078] Specifically, the cylindrical pin 11 is first installed in the interference fixing pin holes of the front deck plate 1 and the rear deck plate 2, and then the front deck plate 1 and the rear deck plate 2 are installed to the lower deck plate 6, and the front deck plate 1 and the rear deck plate 2 are positioned by the cooperation of the cylindrical pin 11 and the clearance fixing pin holes.

[0079] Step 3: Install the upper deck 5 onto the front deck 1 and the rear deck 2 and complete the positioning.

[0080] Specifically, the upper deck plate 5 is first installed on the front deck plate 1 and the rear deck plate 2, and the cylindrical pin 11 on the rear deck plate 2 is inserted into the gap fixing pin hole on the upper deck plate 5 to achieve the positioning of the rear deck plate 2 and the upper deck plate 5; then, the movable pin 12 is inserted from the movable pin countersunk hole on the upper deck plate 5 until the movable pin 12 is in place and extends into the gap movable pin hole to achieve the positioning of the front deck plate 1 and the upper deck plate 5.

[0081] Step 4: Tighten the upper deck 5, the front deck 1, the rear deck 2 and the lower deck 6; after the fastening is completed, the colloid 15 is poured into the movable pin countersunk hole of the upper deck 5 to solidify the position of the movable pin 12.

[0082] Corner boxes 9 are used to strengthen the fixing shape of the upper deck 5, the lower deck 6, the front deck 1 and the rear deck 2, and fastening screws 10 are used to fasten the upper deck 5, the front deck 1, the rear deck 2, the lower deck 6 and the corner boxes 9 to each other.

[0083] After the front deck 1, rear deck 2, upper deck 5, and lower deck 6 are fastened by fastening screws 10 and corner boxes 9 and before the movable pin countersunk holes of the upper deck 5 are glued, the coplanarity of the front left connection surface, front right connection surface, rear left connection surface, rear right connection surface, lower left connection surface, lower right connection surface, upper left connection surface, and upper right connection surface are precisely measured to determine whether the coplanarity meets the design requirements. At the same time, the rear surface of the rear deck 2 and the upper surface of the upper deck 5 are precisely measured for flatness to determine whether the precisely measured values ​​are within the processing flatness requirements of the rear deck 2 and the upper deck 5.

[0084] If any of the coplanarity of the front left connecting surface, the front right connecting surface, the rear left connecting surface, the rear right connecting surface, the lower left connecting surface, the lower right connecting surface, the upper left connecting surface, the upper right connecting surface, the flatness of the rear deck 2 and the flatness of the upper deck 5 do not meet the requirements, loosen the fastening mechanism, re-fine-tune the positions of the front deck 1, the rear deck 2 and the upper deck 5 and execute step six.

[0085] The design requirements for the coplanarity of the front left connecting surface, front right connecting surface, rear left connecting surface, rear right connecting surface, lower left connecting surface, lower right connecting surface, upper left connecting surface, and upper right connecting surface are that the coplanarity should be within the requirements of the sum of the dimensional accuracy, pin hole position accuracy, and maximum clearance between the pin and the hole of each cabin plate in the left-right direction. The laser tracker is used to precisely measure the contact surfaces of the front cabin plate 1, rear cabin plate 2, upper cabin plate 5, and lower cabin plate 6 for installation with the left cabin plate 3 and the right cabin plate 4, and measure their coplanarity. The coplanarity should be within the requirements of the sum of the dimensional accuracy, pin hole position accuracy, and maximum clearance between the pin and the hole of each cabin plate and partition in the left-right direction.

[0086] In this implementation case, the left and right dimensional accuracy is better than 0.05mm, the pin hole position accuracy is better than 0.02mm, and the maximum matching clearance is 0.02mm, so the measured coplanarity should be within 0.09mm. If it is higher than this value, the fastening screws 10 should be loosened, and the positions of the front deck 1, the rear deck 2, and the upper deck 5 should be fine-tuned again, and then tightened and precisely measured. If the coplanarity is still not met after repeated precision measurement, the front deck 1, the rear deck 2, and the upper deck 5 should be completely disassembled, and the dimensional accuracy and pin hole position accuracy should be re-measured. If it exceeds the requirements, rework should be carried out.

[0087] Use a laser tracker to measure the rear surface of the rear deck 2 and the upper surface of the upper deck 5 respectively, and judge whether the measured value is within the processing flatness requirements of the rear deck 2 and the upper deck 5. If it exceeds this value, the fastening screws 10 should be loosened, and the front deck 1, the rear deck 2, and the upper deck 5 should be adjusted. After the adjustment is completed, use the laser tracker to measure the rear surface of the rear deck 2 and the upper surface of the upper deck 5 respectively; if the flatness cannot meet the requirements after repeated precise measurements, the front deck 1, the rear deck 2, and the upper deck 5 should be completely disassembled, and the flatness of the rear deck 2 and the upper deck 5 should be remeasured. If it exceeds the requirements, rework should be carried out.

[0088] Step 5: Load the left and right deck panels 3, 4 onto the support vehicle side panels 132, and then position the left and right deck panels 3, 4 onto the front and rear deck panels 1, 2 respectively, and then fasten the left and right deck panels 3, 4 to the upper and rear deck panels 5, the front and rear deck panels 1, 2 and the lower and rear deck panels 6.

[0089] Specifically, the left cabin plate 3 and the right cabin plate 4 are positioned with the rear cabin plate 2 by two cylindrical pins 11, and are positioned with the front cabin plate 1 by a movable pin 12; then the left cabin plate 3 and the right cabin plate 4 are fastened with the upper cabin plate 5, the front cabin plate 1, the rear cabin plate 2 and the lower cabin plate 6 respectively by using the fastening screws 10; after the fastening is completed, the colloid 15 is poured into the movable pin countersunk holes of the left cabin plate 3 and the right cabin plate 4 to solidify the position of the movable pin 12.

[0090] When the satellite structure includes a partition, in step 2, the partition is installed on the lower cabin plate 6 and positioned. A cylindrical pin 11 is installed in the interference fixing pin hole of the first cabin plate 7 and the second cabin plate 8, and then the first cabin plate 7 and the second cabin plate 8 are installed on the lower cabin plate 6, and the first cabin plate 7 and the second cabin plate 8 are positioned by the cooperation of the cylindrical pin 11 and the gap fixing pin hole. In step 3, the upper cabin plate 5 is positioned with the partition; the movable pin 12 is inserted from the movable pin countersunk hole on the upper cabin plate 5 until the movable pin 12 is in place and extends into the gap movable pin hole of the partition to achieve the positioning of the partition with the upper cabin plate 5; in step 4, the partition is fastened to the upper cabin plate 5 and the lower cabin plate 6; the corner box 9 is used to strengthen the fixing dimension of the upper cabin plate 5, the lower cabin plate 6 and the partition, and the fastening screws 10 are used to fasten the upper cabin plate 5, the partition, the lower cabin plate 6, and the corner box 9 to each other.

[0091] The satellite structural assembly described above is easy to install and operate, has accurate positioning, and high assembly precision. The reset deviation after disassembly and reassembly can be controlled within a relatively small range.

[0092] According to the measured values, simulated space construction is performed to provide an accurate on-board coordinate system benchmark for the satellite, and the on-board coordinate system is established for the assembled structure; the position accuracy of the opening, closing and resetting of the satellite cabin panel can be guaranteed. For example, combined with the surface values ​​of the front left connecting surface, rear left connecting surface, lower left connecting surface, upper left connecting surface, rear surface of the rear cabin panel 2, and upper surface of the upper cabin panel 5 precisely measured in step 4, the coordinate axis of the satellite can be fitted to precisely measure and establish the on-board coordinate system of the satellite. After the coordinate axis of the on-board coordinate system is determined, a laser tracker is used to mark the four corner points on the rear surface of the entire satellite structure. After the position is measured, the corresponding coordinate origin position of the system construction can be calculated according to the measurement value software of the space plane. At this point, the precise measurement of the entire satellite is completed, and the on-board coordinate system is established.

[0093] The thickness, rib thickness, flatness, coplanarity, position accuracy, and dimensional accuracy mentioned above should all be listed as an implementation case for clear expression. The present invention focuses on the structural form, assembly method, and precision measurement method rather than specific values.

[0094] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A satellite structure, characterized in that: It includes a cabin panel assembly, a positioning mechanism and a fastening mechanism; The cabin panel assembly together constitutes the cabin body of the satellite; the cabin panel assembly at least comprises a front cabin panel (1), a rear cabin panel (2), a left cabin panel (3), a right cabin panel (4), an upper cabin panel (5) and a lower cabin panel (6); The positioning mechanism is used for positioning the cabin panel assembly and resetting the open and closed cabin panels; the positioning mechanism comprises a precise positioning structure and an adjustable positioning structure, the precise positioning structure comprises an interference fixing pin hole, a clearance fixing pin hole and a cylindrical pin (11), one end of the cylindrical pin (11) is interference-fitted with the interference fixing pin hole, and the other end is clearance-fitted with the clearance fixing pin hole; the adjustable positioning structure comprises a clearance movable pin hole, a movable pin countersunk hole and a movable pin (12), one end of the movable pin (12) is clearance-fitted with the clearance movable pin hole, and the other end is bonded to the movable pin countersunk hole as a whole; The rear left connecting surface, the rear right connecting surface, the rear upper connecting surface and the rear lower connecting surface of the rear deck plate (2) are all provided with interference fixing pin holes; The front lower connecting surface of the front deck plate (1) is provided with an interference fixing pin hole, and the front left connecting surface, the front right connecting surface and the front upper connecting surface are all provided with clearance movable pin holes; The lower front connecting surface and the lower rear connecting surface of the lower cabin plate (6) are both provided with gap fixing pin holes; The upper rear connection surface of the upper deck plate (5) is provided with a gap fixing pin hole, and the upper front connection surface is provided with a movable pin countersunk hole; The left front connection surface of the left cabin plate (3) is provided with a movable pin countersunk hole, and the left rear connection surface is provided with a gap fixing pin hole; The right front connection surface of the right cabin plate (4) is provided with a movable pin countersunk hole, and the right rear connection surface is provided with a gap fixing pin hole; The left cabin plate (3), the right cabin plate (4), the upper cabin plate (5), the lower cabin plate (6) and the rear cabin plate (2) are assembled and positioned by means of cylindrical pins (11); the front cabin plate (1) and the lower cabin plate (6) are assembled and positioned by means of cylindrical pins (11); and the front cabin plate (1) and the upper cabin plate (5), the left cabin plate (3) and the right cabin plate (4) are assembled and positioned by means of movable pins (12).

2. A satellite structure according to claim 1, characterized in that: The fastening mechanism comprises a fixed connecting piece and a corner box (9), and the cabin panel assembly is fastened by the fixed connecting piece when being assembled; the corner box (9) has two mutually perpendicular connecting surfaces, which are respectively used to connect two mutually perpendicular cabin panels.

3. A satellite structure according to claim 2, characterized in that: The cabin panel assembly also includes a plurality of partitions located inside the cabin body.

4. A satellite structure according to claim 1, characterized in that: The front cabin plate (1), the rear cabin plate (2), the left cabin plate (3), the right cabin plate (4), the upper cabin plate (5), and the lower cabin plate (6) are all made of lightweight metal plates. The lightweight metal plates are all metal plates. One side of the lightweight metal plate is a plane, and the other side is provided with a lightweight groove, and the groove wall of the lightweight groove forms a grid.

5. A satellite structure according to claim 1, characterized in that: The outer side surface of one end of the movable pin (12) that cooperates with the clearance movable pin hole is a cylindrical surface, and the outer side surface of one end of the movable pin (12) that cooperates with the movable pin countersunk hole is provided with a glue groove.

6. The satellite structure assembly method according to any one of claims 1 to 5, characterized in that: It includes executing the following steps in sequence: Step 1: Install the lower deck (6); Step 2: Install the front deck (1) and the rear deck (2) onto the lower deck (6) respectively and position the front deck (1), the rear deck (2) and the lower deck (6) by using cylindrical pins (11); Step 3: Install the upper deck (5) onto the front deck (1) and the rear deck (2); realize the positioning of the rear deck (2) and the upper deck (5) by means of the cylindrical pin (11); realize the positioning of the front deck (1) and the upper deck (5) by means of the movable pin (12); Step 4: Tighten the upper deck (5), the front deck (1), the rear deck (2) and the lower deck (6); after the fastening is completed, the colloid (15) is poured into the movable pin countersunk hole of the upper deck (5) to solidify the position of the movable pin (12); Step 5: The left deck (3) and the right deck (4) are respectively installed and positioned on the front deck (1) and the rear deck (2), and the rear deck (2) is positioned with the left deck (3) and the right deck (4) by means of the cylindrical pin (11), and the front deck (1) is positioned with the left deck (3) and the right deck (4) by means of the movable pin (12); After positioning is completed, the left cabin plate (3) and the right cabin plate (4) are fastened to the upper cabin plate (5), the front cabin plate (1), the rear cabin plate (2) and the lower cabin plate (6); after fastening is completed, the colloid (15) is poured into the movable pin countersunk holes of the left cabin plate (3) and the right cabin plate (4) to solidify the position of the movable pin (12).

7. The assembly method according to claim 6, characterized in that: The satellite structure is assembled using a support vehicle (13), the support vehicle (13) is provided with an adapter seat (14) and an adjustable height-raising seat (131), the top surface of the adjustable height-raising seat (131) and the top surface of the adapter seat (14) jointly form a reference support surface; in step 1, the lower cabin plate (6) is installed on the reference support surface.

8. The assembly method according to claim 7, characterized in that: Before installing the lower deck (6), the coplanarity between the top surface of the adjustable pad (131) of the support vehicle (13) and the top surface of the adapter (14) is precisely measured and adjusted until the design requirements are met.

9. The assembly method according to claim 6, characterized in that: In step 1, after the installation of the lower deck (6) is completed, the coplanarity of the lower front connecting surface and the lower rear connecting surface of the lower deck (6) is precisely measured; if the coplanarity does not meet the design requirements, the lower deck (6) is disassembled for rework.

10. The assembly method according to claim 6, characterized in that: In step 4, after the front deck (1), the rear deck (2), the upper deck (5), and the lower deck (6) are fastened and before the active pin countersunk holes of the upper deck (5) are glued, Accurately measure the coplanarity of the front left connection surface, front right connection surface, rear left connection surface, rear right connection surface, lower left connection surface, lower right connection surface, upper left connection surface, and upper right connection surface to determine whether the coplanarity meets the design requirements; At the same time, the rear surface of the rear deck (2) and the upper surface of the upper deck (5) are dotted to precisely measure the flatness, and it is determined whether the precisely measured values ​​are within the processing flatness requirements of the rear deck (2) and the upper deck (5).

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