CN114750981A - Transition structure between frame structure and plate structure for spacecraft - Google Patents
Transition structure between frame structure and plate structure for spacecraft Download PDFInfo
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- CN114750981A CN114750981A CN202210476030.4A CN202210476030A CN114750981A CN 114750981 A CN114750981 A CN 114750981A CN 202210476030 A CN202210476030 A CN 202210476030A CN 114750981 A CN114750981 A CN 114750981A
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- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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Abstract
The transition structure is characterized in that at least one four-direction limiting transition joint structure is fixed on the frame structure of the spacecraft, a first blind hole is arranged on a first body and extends along the horizontal direction, the first blind hole is detachably connected with the horizontal tube structure, a frustum is arranged on the top wall, and the frustum has a first taper and a first height; at least one embedded transition joint of three-dimensional structure is fixed in on the plate structure of spacecraft, plate structure includes a plurality of curb plate structures, first lateral wall upwards extends perpendicularly from the diapire, the second lateral wall upwards extends perpendicularly and perpendicular first lateral wall from the diapire, second lateral wall, first lateral wall and diapire constitute triangular structure, the basal surface is located to the taper hole, the taper hole has second taper and second height, the frustum can be dismantled in the taper hole, first lateral wall and second lateral wall are located in order to dismantle the corresponding curb plate structure of connection to a plurality of connecting pieces. The transition structure has high assembly precision and strong bearing capacity.
Description
Technical Field
The invention relates to the technical field of spacecrafts, in particular to a transition structure between a frame structure and a plate type structure of a spacecraft.
Background
The main structure of the spacecraft platform can be divided into a frame type (truss type) structure form, a box plate type structure form, a plate cylinder type structure form and the like. Although the load bearing and force transmission modes of different main structure forms are slightly different, the operation of the main function of the structure, namely the installation of equipment or effective load and the cheap general assembly process, is an important factor for determining the main structure form in the structural design. If the overall required structure does not need to be disassembled and reassembled in the final assembly stage, the main structure can consider to select a box plate type or plate cylinder type structure form, and the box plate type or plate cylinder type structure is mainly characterized in that the main structure is formed by mutually overlapping and stacking plate plates and plate cylinders, and has the main advantages of simple and visual equipment installation and high structure bearing efficiency, but the reassembling precision is low after the structure is disassembled, and the accurate control cannot be realized. If the overall structure is required for mounting or dismounting the equipment, the main structure may be considered to be selected in the form of a frame-like structure in order to improve the operating efficiency and the cheapness. The frame structure is mainly characterized in that a frame rod and a joint are connected to form a frame type dimensional structure. According to bearing and equipment fixing demand, the honeycomb sandwich structure board is assisted in the frame-type outside, further promotes frame-type structure's bearing efficiency. The main advantages are good structure dimension, can realize the cabin design, and can be disassembled and reassembled for many times for each cabin. After the composite structure is reassembled, the high-precision assembly of the structure can be guaranteed, but the mass is relatively large, and the bearing efficiency of the structure is relatively low.
However, with the increasing demands of spacecraft on structural lightweight and load-bearing efficiency, the requirements of lightweight and load-bearing have not been satisfied by using a single traditional main structural form. Meanwhile, in order to meet the requirements of final assembly efficiency and reduction of the final assembly period of the spacecraft, certain spacecraft structural requirements are designed into a form that the final assembly stage can be separated according to functions, can be disassembled in a single cabin and can be reassembled with high precision. Under the current technical condition, the structure capable of realizing subdivision, single-cabin disassembly and reassembly is generally in a frame type structural form. However, the frame structure has relatively large mass, and thus, the frame structure does not meet the requirements of light structure and high bearing efficiency. Therefore, according to the problems brought by the traditional single main structure form, the combination form of the frame type or plate type structure adopted by the single cabin of the main structure is a main technical approach for solving the problems of light weight, high bearing efficiency, detachability and high precision of the existing structure.
According to the current technical level, if a propulsion cabin structure at the lower part of the main structure is prepared by adopting a frame structure, and a load cabin or platform cabin structure at the upper part of the main structure is prepared by adopting a plate structure, the problems caused by the combined structure are also obvious: (1) the design of the transition joint structure form between the frame type structure and the plate type structure (two cabins) is difficult, and risks such as overlarge local stress of the frame or the plate structure, insufficient bearing of the structure and the like are easily caused; (2) the precision of the plate-type structure (a load cabin or a platform cabin) after being reassembled cannot be accurately controlled, and some extra-cabin equipment and the like cannot be installed with high precision easily; (3) because the main structure has realized the subdivision design, and the mechanical load is mostly all transmitted through the joint design, and local load is too big, needs the enhancement or the reinforcement to frame or plate structure to the quality of structure has been increased to a certain extent.
The above information disclosed in this background section is only for enhancement of understanding of the background of the invention and therefore it may contain information that does not form the prior art that is already known to a person of ordinary skill in the art.
Disclosure of Invention
The invention aims to provide a transition structure between a frame structure and a plate type structure of a spacecraft, which can realize reliable transition type combination between the frame and the plate structure, avoid overlarge local stress and further improve the bearing capacity of a joint structure between the frame and the plate; the precision of the plate type structure (or a single cabin) after disassembly and reassembly in the final assembly stage can be accurately controlled, and the high precision of the reassembled structural plate is ensured; the stress level of the multi-reading joint structure between the cabins of the frame type and plate type combined structure is reduced through the lap joint transition structure between the cabins.
In order to achieve the above purpose, the invention provides the following technical scheme:
the invention relates to a transition structure between a frame structure and a plate structure for a spacecraft, comprising:
at least one four-way limiting transition joint structure fixed on a frame structure of the spacecraft, wherein the frame structure comprises a plurality of horizontal pipe structures and a plurality of vertical pipe structures, the four-way limiting transition joint structure comprises,
A first body having a horizontal top wall,
a first blind hole which is arranged on the first body and extends along the horizontal direction, the first blind hole is detachably connected with the horizontal tube structure,
a second blind hole which is arranged on the first body and extends along the horizontal direction, the second blind hole is vertical to the first blind hole, the second blind hole is detachably connected with the horizontal tube structure,
a third blind hole which is arranged on the first body and extends along the vertical direction, the third blind hole is vertical to the first blind hole and the second blind hole, the third blind hole is detachably connected with the vertical pipe structure,
a frustum disposed at the top wall, the frustum having a first taper and a first height;
at least one three-way embedded transition joint structure fixed on a plate structure of the spacecraft, wherein the plate structure comprises a plurality of side plate structures, the three-way embedded transition joint structure comprises,
a second body which is a triangular structure comprising,
a bottom wall having a horizontal bottom surface,
a first side wall extending vertically upward from the bottom wall,
a second side wall extending vertically upward from the bottom wall and perpendicular to the first side wall, the second side wall, the first side wall and the bottom wall forming a triangular structure,
A tapered bore disposed in the bottom surface, the tapered bore having a second taper and a second height, the tapered bore being detachably connected to the frustum,
and the connecting pieces are arranged on the first side wall and the second side wall so as to be detachably connected with corresponding side plate structures.
The transition structure used between the frame structure and the plate structure of the spacecraft is characterized in that the plate structure comprises a platform cabin plate structure and a load cabin plate structure, the platform cabin plate structure and the load cabin plate structure both comprise a plurality of side plate structures, and the side plate structures are side plates of a honeycomb sandwich structure.
The transition structure used between the frame structure and the plate structure of the spacecraft further comprises a lap joint strap transition structure used for connecting the plate structure of the platform cabin and the plate structure of the load cabin, wherein the lap joint strap transition structure is a horizontal plate and is provided with a plurality of connecting holes.
In the transition structure between the frame structure and the plate structure of the spacecraft, the second blind hole is in clearance fit with the horizontal tube structure, and the third blind hole is in clearance fit with the vertical tube structure.
In the transition structure between the frame structure and the plate structure of the spacecraft, a glue layer is coated between the second blind hole and the horizontal tube structure, and a glue layer is coated between the third blind hole and the vertical tube structure.
In the transition structure between the frame structure and the plate structure of the spacecraft, the connecting piece comprises an embedded taper hole structure which is matched with a taper pin of the side plate structure, and the embedded taper hole structure is in clearance fit with the taper pin.
In the transition structure between the frame structure and the plate structure of the spacecraft, the connecting piece comprises a threaded hole which is matched with a bolt of the side plate structure.
In the transition structure between the frame structure and the plate structure of the spacecraft, the first taper is the same as the second taper, the first height is the same as the second height, and the two three-way embedded transition joint structures are vertically and fixedly connected through corresponding taper holes.
In the transition structure between the frame structure and the plate structure of the spacecraft, the top wall and the bottom wall are respectively provided with aligned through holes for installation.
A transition structure for between frame construction and the plate structure of spacecraft in, all be equipped with the strengthening rib between first blind hole, second blind hole and the third blind hole, all be equipped with the strengthening rib between second lateral wall, first lateral wall and the diapire.
In the technical scheme, the transition structure between the frame structure and the plate type structure for the spacecraft, provided by the invention, has the following beneficial effects: compared with the prior art, the four-direction limiting type transition joint structure is in large-area glue joint with structures such as a frame horizontal pipe and a frame vertical pipe, and stability and reliability of the frame structure are achieved. The frustum with a certain height is designed at the upper end of the four-way limiting type transition joint structure and is in clearance fit with the taper hole of the three-way embedded type transition joint structure of the plate type structure. The transverse deformation control of the lower end frame type propulsion cabin joint and the upper end plate type load cabin joint is realized through the design of the gap size, and the problems that the inter-cabin precision cannot be controlled and the main structure precision is reduced after the cabin is assembled in a final assembly stage in a sub-cabin manner are solved. Two local position design screw connections and frustum/taper hole cooperation between embedded transition joint design of three-dimensional and the curb plate structure have solved the anti peel performance between transition joint design and the curb plate structure and have hanged down or curb plate structure repacking precision can't guarantee the scheduling problem. The anti-stripping performance between the transition joint structure and the side plate structure is greatly improved through the screw connection of the transition joint structure and the side plate structure; the transverse bearing performance is guaranteed through the matching of the frustum and the taper hole, and meanwhile the reassembling precision of the side plate is greatly improved, so that the precision of the side plate structure is controllable during reassembling. The design through faying strap transition structure realizes the partial reposition of redundant personnel of joint design local load, has solved the higher problem of the local stress level of four-way spacing formula transition joint design, the embedded transition joint design of three-dimensional, avoids local structure such as joint design and curb plate to strengthen or the reinforcement measure, further reduces joint design local quality, promotes the bearing efficiency of joint design.
Drawings
In order to more clearly illustrate the embodiments of the present application or technical solutions in the prior art, the drawings required in the embodiments will be briefly described below, it is obvious that the drawings in the following description are only some embodiments described in the present invention, and other drawings can be obtained by those skilled in the art according to these drawings.
Fig. 1 is a schematic installation diagram of a transition structure between a frame structure and a plate-type structure for a spacecraft, provided by an embodiment of the present invention.
Fig. 2 is a partially enlarged schematic view of a partial view 1 between a frame structure and a plate structure for a spacecraft according to the embodiment of the present invention in fig. 1.
Fig. 3 is a partially enlarged schematic view of a partial view 2 between a frame structure and a plate structure for a spacecraft, provided by an embodiment of the invention of fig. 1.
Fig. 4 is a schematic structural diagram of a four-way limiting type transition joint structure for a transition structure between a frame structure and a plate structure of a spacecraft, according to an embodiment of the present invention.
Fig. 5 is a schematic cross-sectional view of a four-way limiting type transition joint structure for a transition structure between a frame structure and a plate-type structure of a spacecraft, according to an embodiment of the present invention.
Fig. 6 is a schematic structural diagram of a three-way embedded transition joint structure for a transition structure between a frame structure and a plate structure of a spacecraft according to an embodiment of the present invention.
Fig. 7 is a schematic structural diagram of a three-way embedded transition joint structure for a transition structure between a frame structure and a plate structure of a spacecraft according to an embodiment of the present invention.
Fig. 8 is a schematic structural diagram of a three-way embedded transition joint structure for a transition structure between a frame structure and a plate structure of a spacecraft according to an embodiment of the present invention.
Fig. 9 is a schematic structural diagram of a transition structure of a strap for use in a transition structure between a frame structure and a plate-type structure of a spacecraft, according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings of the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
Thus, the following detailed description of the embodiments of the present invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be obtained by a person skilled in the art without inventive efforts based on the embodiments of the present invention, are within the scope of protection of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined or explained in subsequent figures.
In the description of the present invention, it is to be understood that the terms center, longitudinal, transverse, length, width, thickness, upper, lower, front, rear, left, right, vertical, horizontal, top, bottom, inner, outer, clockwise, counterclockwise and the like refer to the orientation or positional relationship illustrated in the drawings only for the convenience of description and simplicity of description, and do not indicate or imply that the apparatus or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be considered limiting.
Furthermore, the terms first and second are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, the first and second features defined may explicitly or implicitly include one or more of the features. In the description of the invention, a plurality means two or more unless specifically defined otherwise.
In the present invention, unless otherwise explicitly specified or limited, the terms mounted, connected, fixed and the like are to be understood broadly, e.g. as being fixedly connected, detachably connected or integrated; they may be directly connected or indirectly connected through intervening media, or may be connected through the use of two elements or the interaction of two elements. The specific meanings of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
In the present invention, unless expressly stated or limited otherwise, the first feature may be located above or below the second feature and may comprise both the first and second features in direct contact, or may comprise the first and second features not being in direct contact but being in contact via another feature therebetween. Also, the first feature may be over, above or on the second feature including the first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is at a higher level than the second feature. A first feature being below, beneath or beneath a second feature includes the first feature being directly below and obliquely below the second feature or simply indicating that the first feature is at a lesser level than the second feature.
In order to make those skilled in the art better understand the technical solution of the present invention, the present invention will be further described in detail with reference to the accompanying drawings.
Referring to fig. 1-9, in one embodiment, a transition structure between a frame structure and a panel structure for a spacecraft of the present invention comprises,
at least one four-way limiting transition joint structure 6 fixed on a frame structure 1 of the spacecraft, wherein the frame structure 1 comprises a plurality of horizontal pipe structures 4 and a plurality of vertical pipe structures 5, the four-way limiting transition joint structure 6 comprises,
a first body having a horizontal top wall 17,
a first blind hole 18, which is arranged on the first body and extends along the horizontal direction, the first blind hole 18 is detachably connected with the horizontal pipe structure 4,
a second blind hole 19, which is arranged on the first body and extends along the horizontal direction, the second blind hole 19 is perpendicular to the first blind hole 18, the second blind hole 19 is detachably connected with the horizontal pipe structure 4,
a third blind hole 20, which is disposed on the first body and extends along a vertical direction, the third blind hole 20 is perpendicular to the first blind hole 18 and the second blind hole 19, the third blind hole 20 is detachably connected to the vertical pipe structure 5,
a frustum 11 disposed on the top wall 17, the frustum 11 having a first taper and a first height;
At least one three-way embedded transition joint structure 7 fixed to a plate structure of the spacecraft, the plate structure comprising a plurality of side plate structures 8, the three-way embedded transition joint structure 7 comprising,
a second body which is a triangular structure comprising,
a bottom wall 21 having a horizontal bottom surface,
a first side wall 22 extending vertically upward from the bottom wall 21,
a second side wall 23 extending vertically upward from the bottom wall 21 and perpendicular to the first side wall 22, the second side wall 23, the first side wall 22 and the bottom wall 21 forming a triangular structure,
a taper hole 14 provided on the bottom surface, the taper hole 14 having a second taper and a second height, the taper hole 14 being detachably connected to the frustum 11,
a plurality of connectors provided to the first and second side walls 22, 23 for detachable connection to respective side panel structures.
The transition structure used between the frame structure and the plate structure of the spacecraft can realize effective, reliable and high-precision interbay installation or reassembly of the propulsion cabin frame structure and the platform cabin (load cabin) plate structure; the side plate structure 8 is controlled in the reassembly precision, and the reassembly precision is ensured; the reduction of the local stress level of the inter-cabin transition joint structure is realized, and the lightweight level of the transition joint structure is further improved.
In the preferred embodiment of the transition structure between the frame structure and the plate structure for the spacecraft, the plate structure comprises a platform cabin plate structure 2 and a load cabin plate structure 3, the platform cabin plate structure 2 and the load cabin plate structure 3 both comprise a plurality of side plate structures 8, and the side plate structures 8 are side plates of a honeycomb sandwich structure.
In the preferred embodiment of the transition structure between the frame structure and the plate structure of the spacecraft, the transition structure further comprises a strap transition structure 9 for connecting the platform cabin plate structure 2 and the load cabin plate structure 3, wherein the strap transition structure 9 is a horizontal plate and is provided with a plurality of connecting holes 24.
In a preferred embodiment of the transition structure between a frame structure and a plate structure for a spacecraft, the second blind holes 19 are in clearance fit with the horizontal tube structures 4, and the third blind holes 20 are in clearance fit with the vertical tube structures 5.
In the preferred embodiment of the transition structure between the frame structure and the plate structure for a spacecraft, a glue layer is coated between the second blind holes 19 and the horizontal tube structure 4, and a glue layer is coated between the third blind holes 20 and the vertical tube structure 5.
In a preferred embodiment of the transition structure between a frame structure and a plate structure for a spacecraft described above, the connecting element comprises an embedded taper hole structure 12 adapted to a taper pin of the side plate structure 8, the embedded taper hole structure 12 being in clearance fit with the taper pin.
In a preferred embodiment of the described transition structure between a frame structure and a plate structure for a spacecraft, the connection comprises threaded holes 13 adapted to the bolts of the side plate structures 8.
In the preferred embodiment of the transition structure between the frame structure and the plate structure for a spacecraft, the first taper is the same as the second taper, the first height is the same as the second height, and two three-way embedded transition joint structures 7 are fixedly connected vertically through corresponding taper holes 14.
In a preferred embodiment of the described transition between a frame structure and a plate structure for a spacecraft, the top wall 17 and the bottom wall 21 are provided with aligned through holes for mounting, respectively.
In the preferred embodiment of the transition structure between the frame structure and the plate structure for a spacecraft, reinforcing ribs 25 are arranged among the first blind hole 18, the second blind hole 19 and the third blind hole 20, and reinforcing ribs are arranged among the second side wall 23, the first side wall 22 and the bottom wall 21.
In one embodiment, the four-way limiting transition joint structure 6 and the three-way embedded transition joint structure 7 are made of carbon nanotube reinforced aluminum matrix composite.
In one embodiment, in order to solve the problem of transition connection between the propulsion chamber frame structure 1 and the platform chamber (or load chamber) plate structure, a four-way limiting type transition joint structure 6 is designed at four corners of the upper end of the frame propulsion chamber structure, the joint structure is designed into first to third blind holes 20 with certain depths in the left, right and lower directions, and is designed into a frustum 11 with a certain height at the top end (on). The first to third blind holes 20 are respectively connected with the horizontal tube structure 4 and the vertical tube structure 5 of the frame structure 1 by clearance fit, and the horizontal tube or the vertical tube is inserted into the blind hole of the joint structure after the outer layer is coated with structural adhesive, so that the stable propulsion cabin frame structure 1 is formed. The upper end of the four-direction limiting type transition joint structure 6 is designed to be a frustum 11 with a certain cone angle and height, the lower end of the plate type structure of the platform cabin (or the load cabin) is designed to be a three-direction embedded type transition joint structure 7, the lower end face of the three-direction embedded type transition joint structure 7 is designed to be a corresponding cone hole 14 to be matched with the frustum 11 of the four-direction limiting type transition joint structure 6, and high-precision resetting between the cabins is guaranteed while transverse loads between the cabins are borne. Corresponding through holes or threaded holes 13 are circumferentially designed on the outer sides of the four-way limiting type transition joint structure 6 and the three-way embedded type transition joint structure 7, and longitudinal connection between cabins is achieved through screw connection. In order to solve the problems of uncontrollable precision, low precision and the like of the upper plate type structure after disassembly and reassembly in the final assembly stage, four three-way embedded transition joint structures 7 are designed at the lower end of the plate type structure, and the lower end surfaces of the transition joint structures are designed into embedded taper holes 14 and are in embedded fit with upper end frustum 11 of the four-way limiting joint structure of the lower frame structure 1. Two other sides of transition joint design are connected with corresponding honeycomb sandwich structure curb plate respectively, and in order to guarantee the precision of curb plate in the installation, the position design that transition joint design and corresponding curb plate are connected is screw hole 13 with embedded taper hole structure 12 form to form whole and be the embedded joint structure of three-dimensional triangle structure form three-dimensional. The threaded hole 13 on the joint structure is connected with the screw passing through the side plate structure 8, and the main function is to transversely connect the side plate and the transition joint structure into a whole, so that the longitudinal anti-stripping capability between the side plate and the joint structure is improved. The embedded taper hole structure 12 on the transition joint structure is connected with a corresponding taper pin in the side plate structure 8, and the embedded taper hole structure is mainly used for limiting the transverse displacement of the plate structure or the single cabin in the bearing process and improving the transverse shear resistance. Meanwhile, the lower end of the side plate is designed through a gap between the embedded taper hole structure 12 and the taper pin in the side plate, so that high-precision control of installation or reassembly between the side plate and the joint structure is realized, and the requirement on the precision of side installation or reassembly is met.
In order to reduce the bearing stress of the transition joint structure between the cabins and avoid the problem that the transition joint structure is locally buckled, which is possibly caused by the fact that loads are mainly transmitted through the joint, a lap joint transition structure 9 is designed between the two cabins, and a connecting and force transmission channel between the two cabins is increased through the lap joint transition structure 9. The design of the lap joint transition structure 9 can reduce the local stress concentration level of the joint structure to a certain extent, and avoids the reinforcement or reinforcement measure of the side plate in the local structure. The lap joint piece structure through the small mass has realized the structure lightweight design of transition joint design, curb plate local structure, further reduces the construction quality. A transition structure for between frame construction and the plate structure of spacecraft realizes being connected between frame construction 1 and the plate structure, has guaranteed the horizontal high accuracy reinstallation between the cabin, and three-dimensional embedded transition joint design 7 compromises connection and curb plate reinstallation precision and guarantees 8 high accuracy reinstallations of curb plate structure between the cabin, and the overlap joint structure increases mechanical load dispersion passageway, reduces the local stress of three-dimensional embedded transition joint design 7.
In one embodiment, the strap transition structure 9 is a high strength carbon nanotube reinforced aluminum matrix composite.
In one embodiment, as shown in fig. 1, the lower part of the spacecraft is a propulsion bay frame structure 1 and the upper part is a platform bay plate structure 2 and a load bay plate structure 3, respectively. Frame construction 1 mainly comprises horizontal tubular structure 4, riser structure 5 and the spacing formula transition joint design 6 of quadriversal, and horizontal tubular structure 4, riser structure 5 are through inserting in the blind hole 13 of the spacing formula transition joint design 6 of quadriversal behind the outer surface coating glue film, connect after the solidification and form reliable stable frame construction 1. The upper platform cabin structure 2 or the load cabin is a plate type structure 3, and the stable platform cabin plate type structure 2 and the load cabin plate type structure 3 are formed by connecting the side plate structure 8, other plate type structures 10 and the inter-cabin transition lap joint structure 9 in a screwed mode. The connection between the cabins is realized between the frame structure 1 and the platform cabin plate type structure 2 through a four-way limiting type transition joint structure 6 and a three-way embedded type transition joint structure 7, and meanwhile, the reinstallation precision between the cabins is guaranteed.
As shown in fig. 2 and 3, in order to achieve the inter-deck connection between the propulsion-deck frame structure 1 and the platform deck plate structure 2 and to ensure the reassembly accuracy. The four-way spacing type transition joint structure 6 is provided with 3 blind holes at the corresponding positions of the horizontal tube structure 4 and the vertical tube structure 5, and the horizontal tube structure 4 and the vertical tube structure 5 are fixedly connected with the 3 blind holes through glue joint. The 4 four-way limiting transition joint structures 6 are respectively glued and fixed with the horizontal pipe structure 4 and the vertical pipe structure 5, so that the stability of the propulsion cabin frame structure 1 is ensured. On this basis, the position that single spacing formula transitional coupling structure of quadriversal 6 is connected with platform cabin plate structure 2 designs 1 frustum 11 that has a take the altitude and tapering, correspond position design three-dimensional embedded transitional coupling structure 7 at platform cabin plate structure 2's lower extreme and four-way spacing formula transitional coupling structure 6, and design 1 taper hole 14 that has certain given degree of depth and tapering on single three-dimensional embedded transitional coupling structure 7, through the clearance size between design frustum 11 and taper hole 14, guarantee to impel the horizontal precision of being connected between cabin frame construction 1 and the platform cabin plate structure 2, realize impelling the high accuracy repacking between cabin frame construction 1 and the platform cabin plate structure 2. Meanwhile, in order to realize the longitudinal fixed connection of the propulsion cabin frame structure 1 and the platform cabin plate type structure 2, 3 frame transition joint structure through holes 15 and single plate type transition joint structure through holes 16 are respectively designed at the corresponding positions of the single four-way limiting type transition joint structure 6 and the single three-way embedded type transition joint structure 7, and after the two cabins are butted, the longitudinal connection and the fixation of the two cabins are ensured by nailing a nut.
As shown in fig. 3, except for the longitudinal connection between the three-way embedded transition joint structure 7 and the four-way limiting transition joint structure 6, in order to ensure the accuracy of the side plate structure 8 after final assembly, the three-way embedded transition joint structure 7 is designed to be integrally in a three-dimensional triangular structure form, a double connection mode of a 2-position taper hole structure 12 and a threaded hole 13 is designed between the single three-way embedded transition joint structure 7 and the side plate structure 8, the taper hole structure 12 is matched with a corresponding taper pin in the side plate structure 8, and by designing the gap size between the two, the accuracy of the side plate structure 8 during final assembly is ensured to be controllable, so that high-accuracy final assembly of the side plate structure 8 is realized. The threaded hole 13 is matched with a corresponding through hole in the side plate structure 8, and the through-nail is screwed into the threaded hole 13, so that the anti-stripping performance of lateral connection between the side plate 8 and the three-way embedded transition joint structure 7 is greatly improved.
As shown in fig. 4, in order to reduce the local stress level of the three-way embedded transition joint structure 7, an interbay transition lap joint structure 9 is designed between the bays, the platform deck slab structure 2 and the load deck slab structure 3 are connected through the interbay transition lap joint structure 9, the mechanical load is dispersed and gathered at the three-way embedded transition joint structure 7, the local reinforcement post-reinforcement measure of the three-way embedded transition joint structure 7 is avoided, and the lightweight design of the three-way embedded transition joint structure 7 is realized.
Finally, it should be noted that: the embodiments described are only a part of the embodiments of the present application, and not all embodiments, and all other embodiments obtained by those skilled in the art without making creative efforts based on the embodiments in the present application belong to the protection scope of the present application.
While certain exemplary embodiments of the present invention have been described above by way of illustration only, it will be apparent to those of ordinary skill in the art that the described embodiments may be modified in various different ways without departing from the spirit and scope of the invention. Accordingly, the drawings and description are illustrative in nature and should not be construed as limiting the scope of the invention.
Claims (10)
1. A transition structure between a frame structure and a plate structure for a spacecraft, characterized in that it comprises:
at least one four-way limiting transition joint structure fixed on a frame structure of the spacecraft, wherein the frame structure comprises a plurality of horizontal pipe structures and a plurality of vertical pipe structures, the four-way limiting transition joint structure comprises,
a first body having a horizontal top wall,
a first blind hole which is arranged on the first body and extends along the horizontal direction, the first blind hole is detachably connected with the horizontal tube structure,
A second blind hole which is arranged on the first body and extends along the horizontal direction, the second blind hole is vertical to the first blind hole, the second blind hole is detachably connected with the horizontal tube structure,
a third blind hole arranged on the first body and extending along a vertical direction, the third blind hole being perpendicular to the first blind hole and the second blind hole, the third blind hole being detachably connected to the vertical pipe structure,
a frustum disposed at the top wall, the frustum having a first taper and a first height;
at least one three-way embedded transition joint structure fixed on a plate structure of the spacecraft, wherein the plate structure comprises a plurality of side plate structures, the three-way embedded transition joint structure comprises,
a second body which is a triangular structure comprising,
a first side wall extending vertically upward from the bottom wall,
a second side wall extending vertically upward from the bottom wall and perpendicular to the first side wall, the second side wall, the first side wall and the bottom wall forming a triangular structure,
a tapered bore disposed in the bottom surface, the tapered bore having a second taper and a second height, the tapered bore being detachably connected to the frustum,
a plurality of connectors provided to the first and second side walls for detachable connection to respective side panel structures.
2. A transition structure between a frame structure and a plate structure for a spacecraft as claimed in claim 1, wherein the plate structure comprises a platform deck structure and a load deck structure, each comprising a plurality of side plate structures, the side plate structures being side plates of a honeycomb sandwich structure.
3. The transition structure between a frame structure and a plate structure for a spacecraft of claim 2, further comprising a strap transition structure for connecting the platform deck structure and the load deck structure, wherein the strap transition structure is a horizontal plate having a plurality of connection holes formed therein.
4. A transition structure between a frame structure and a plate structure for a spacecraft according to claim 1, wherein the second blind hole is clearance-fitted to a horizontal tube structure and the third blind hole is clearance-fitted to a riser structure.
5. A transition structure between a frame structure and a plate structure for a spacecraft as claimed in claim 1, wherein a glue layer is applied between the second blind holes and the horizontal structure and a glue layer is applied between the third blind holes and the riser structure.
6. A transition structure between a frame structure and a plate structure for a spacecraft as claimed in claim 1, wherein the connection comprises an embedded taper hole structure adapted to a taper pin of the side plate structure, the embedded taper hole structure being clearance fitted with the taper pin.
7. A transition structure between a frame structure and a plate structure for a spacecraft as claimed in claim 1, wherein the connection comprises threaded holes adapted to bolts of the side plate structure.
8. The transition structure between a frame structure and a panel structure for a spacecraft of claim 1, wherein the first taper is the same as the second taper, the first height is the same as the second height, and the two three-way embedment joint structures are fixedly connected vertically through corresponding tapered holes.
9. A transition structure between a frame structure and a panel structure for a spacecraft as claimed in claim 1, wherein the top and bottom walls are each provided with aligned through holes for mounting.
10. A transition structure between a frame structure and a plate structure for a spacecraft as claimed in claim 1, wherein reinforcing ribs are provided between said first, second and third blind holes, and reinforcing ribs are provided between said second, first and bottom walls.
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| CN202210476030.4A CN114750981B (en) | 2022-04-29 | 2022-04-29 | Transition structure between frame structure and plate structure for spacecraft |
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|---|---|---|---|---|
| US4395004A (en) * | 1980-03-24 | 1983-07-26 | Rca Corporation | Modular spacecraft structures |
| CN104401508A (en) * | 2014-10-27 | 2015-03-11 | 北京空间飞行器总体设计部 | Cross bracing main structure for spacecraft |
| CN109484673A (en) * | 2018-12-24 | 2019-03-19 | 深圳航天东方红海特卫星有限公司 | A kind of payload platform separate type remote sensing micro satellite configuration and its assembly method |
| CN111542198A (en) * | 2020-04-28 | 2020-08-14 | 中国科学院空间应用工程与技术中心 | Load adapter with heat conduction structure |
| CN113562195A (en) * | 2021-08-17 | 2021-10-29 | 北京微纳星空科技有限公司 | Box board frame combined satellite configuration |
| CN214738825U (en) * | 2020-12-21 | 2021-11-16 | 袁志林 | Adjustable frame connecting piece |
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2022
- 2022-04-29 CN CN202210476030.4A patent/CN114750981B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4395004A (en) * | 1980-03-24 | 1983-07-26 | Rca Corporation | Modular spacecraft structures |
| CN104401508A (en) * | 2014-10-27 | 2015-03-11 | 北京空间飞行器总体设计部 | Cross bracing main structure for spacecraft |
| CN109484673A (en) * | 2018-12-24 | 2019-03-19 | 深圳航天东方红海特卫星有限公司 | A kind of payload platform separate type remote sensing micro satellite configuration and its assembly method |
| CN111542198A (en) * | 2020-04-28 | 2020-08-14 | 中国科学院空间应用工程与技术中心 | Load adapter with heat conduction structure |
| CN214738825U (en) * | 2020-12-21 | 2021-11-16 | 袁志林 | Adjustable frame connecting piece |
| CN113562195A (en) * | 2021-08-17 | 2021-10-29 | 北京微纳星空科技有限公司 | Box board frame combined satellite configuration |
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| CN114750981B (en) | 2022-12-09 |
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