CN114919777A - High-bearing double-star series structure - Google Patents

High-bearing double-star series structure Download PDF

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Publication number
CN114919777A
CN114919777A CN202210639138.0A CN202210639138A CN114919777A CN 114919777 A CN114919777 A CN 114919777A CN 202210639138 A CN202210639138 A CN 202210639138A CN 114919777 A CN114919777 A CN 114919777A
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CN
China
Prior art keywords
satellite
bearing cylinder
bearing
load
flange
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202210639138.0A
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Chinese (zh)
Inventor
陈鸿程
蒋桂忠
沈苑
刘佳伟
程泽崧
曹冬冬
田艳
解放
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shanghai Engineering Center for Microsatellites
Innovation Academy for Microsatellites of CAS
Original Assignee
Shanghai Engineering Center for Microsatellites
Innovation Academy for Microsatellites of CAS
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Publication date
Application filed by Shanghai Engineering Center for Microsatellites, Innovation Academy for Microsatellites of CAS filed Critical Shanghai Engineering Center for Microsatellites
Priority to CN202210639138.0A priority Critical patent/CN114919777A/en
Publication of CN114919777A publication Critical patent/CN114919777A/en
Pending legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/645—Separators
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/641—Interstage or payload connectors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/641—Interstage or payload connectors
    • B64G1/643—Interstage or payload connectors for arranging multiple satellites in a single launcher

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Radio Relay Systems (AREA)

Abstract

The invention belongs to the technical field of aerospace, and provides a high-bearing double-star series structure, which comprises: an upper bearing cylinder; an inter-satellite separation device connecting the upper and lower messenger drums, wherein the inter-satellite separation device is configured to transfer the load of an upper satellite from the upper messenger drum to the lower messenger drum; and a lower bearing cylinder arranged below the upper bearing cylinder, wherein the lower bearing cylinder is configured to bear the load of the upper satellite and the lower satellite.

Description

High-bearing double-star series structure
Technical Field
The present invention relates generally to the field of aerospace technology. Particularly, the invention relates to a high-bearing double-star series structure.
Background
With the development of satellite technology, simultaneous multi-satellite transmission has become a trend to reduce the cost of satellite transmission. However, the following problems still exist if a newly-researched satellite with high functional density and high bearing ratio in China needs to carry out one-arrow two-satellite launching: because the single-star mass is close to the conditions of large mass of the assembly, high longitudinal mass center, large bending moment and the like, and the rigidity loss is large in the process of inter-star unlocking and separation of the double stars, the traditional double-star structure cannot meet the requirement on carrying rigidity; in addition, the impact magnitude is larger in the inter-satellite unlocking process of the double satellites, and the impact resistance of the traditional double-satellite structure is difficult to meet the requirement.
Disclosure of Invention
To at least partially solve the above problems in the prior art, the present invention provides a high-load dual-star series structure, comprising:
an upper bearing cylinder;
an inter-satellite separation device connecting the upper bearing cylinder and the lower bearing cylinder, wherein the inter-satellite separation device is configured to transfer the load of the upper satellite from the upper bearing cylinder to the lower bearing cylinder; and
a lower messenger cylinder disposed below the upper messenger cylinder, wherein the lower messenger cylinder is configured to carry the load of an upper satellite and a lower satellite.
In one embodiment of the invention, the overall rigidity of the inter-satellite separation device is configured to be equivalent to the rigidity of the lower bearing cylinder and the upper bearing cylinder.
In one embodiment of the invention, the upper bearing cylinder and the lower bearing cylinder comprise honeycomb sandwich bearing cylinders.
In one embodiment of the invention, it is provided that the lower buoyant tube is connected to the launch vehicle, wherein the lower buoyant tube comprises:
a lower bearing cylinder body;
the first upper end frame is arranged above the lower bearing cylinder body and is connected with the inter-satellite separation device; and
a first lower end frame disposed below the lower messenger barrel, the first lower end frame configured to connect the lower satellite with the launch vehicle.
In one embodiment of the present invention, it is provided that the lower bearing cylinder further comprises a lower bearing cylinder flange, a first bottom plate, a first middle plate, a first tank system, a first top plate and a first adjusting module, wherein the lower bearing cylinder flange comprises:
a first floor flange connected to the first floor;
the first middle-layer plate flange is connected with the first middle-layer plate;
a first tank flange connected to the first tank system;
a first top plate flange connected with the first top plate; and
a first conditioning module flange connected with the first conditioning module.
In one embodiment of the invention, it is provided that the lower bearing cylinder further comprises a connecting layer, and the connecting layer is arranged on a connecting surface of the lower bearing cylinder and the first top plate.
In one embodiment of the invention, it is provided that the upper force bearing cylinder comprises:
an upper bearing cylinder body;
the second top plate is arranged above the upper bearing cylinder body;
the second upper end frame connects the upper bearing cylinder body with the second top plate; and
and the second lower end frame is arranged below the lower bearing cylinder body and connects the upper bearing cylinder body with the satellite-rocket separation device.
In one embodiment of the present invention, it is provided that the upper force-bearing cylinder further includes an upper force-bearing cylinder flange and a second bottom plate, wherein the upper force-bearing cylinder flange further includes:
a second floor flange connected to the second floor;
a second mid-deck flange connected to the second mid-deck;
a second tank flange connected to the second tank system;
a second top plate flange connected to the second top plate;
the cylinder inner bottom plate flange is connected with the cylinder inner top plate; and
a second conditioning module flange connected with the second conditioning module flange.
In one embodiment of the invention, the satellite and rocket separation device comprises:
an inter-satellite separation device is arranged on the frame;
a lower frame of the inter-satellite separation device; and
a point type separation device connecting the inter-satellite separation device upper frame and the inter-satellite separation device lower frame.
In one embodiment of the invention, the satellite-rocket separation device further comprises a positioning pin, and the positioning pin is configured to enable the lower bearing cylinder and the upper bearing cylinder to be coaxial.
The invention has at least the following beneficial effects: the invention solves the problems of large rigidity loss of a high-bearing point type separation main structure and overlarge inter-satellite point type separation impact magnitude of the traditional double-satellite structure, can realize one-arrow double-satellite series emission with the combined body more than or equal to 5.0T, has simple interfaces of an inter-satellite separation device, and is convenient for factory building and launch site final assembly tests.
Drawings
To further clarify advantages and features that may be present in various embodiments of the present invention, a more particular description of various embodiments of the present invention will be rendered by reference to the appended drawings. It is appreciated that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting of its scope. In the drawings, the same or corresponding parts will be denoted by the same or similar reference numerals for clarity.
Fig. 1 shows a schematic diagram of a high-load dual-star tandem structure according to an embodiment of the present invention.
FIG. 2 shows a force transfer logic diagram for a high load bearing tandem double star configuration in one embodiment of the present invention.
Fig. 3 is a schematic diagram illustrating the structural logic of a high-load dual-star serial structure according to an embodiment of the present invention.
Fig. 4 shows a schematic view of a lower force-bearing cylinder in one embodiment of the invention.
Fig. 5 shows a schematic view of an upper force-bearing cylinder in one embodiment of the invention.
Fig. 6 shows a schematic view of an inter-satellite separation apparatus in an embodiment of the invention.
FIG. 7 shows a schematic view of one locating pin in one embodiment of the present invention.
Detailed Description
It should be noted that the components in the figures may be exaggerated and not necessarily to scale for illustrative purposes. In the figures, identical or functionally identical components are provided with the same reference symbols.
In the present invention, "disposed on …," "disposed over …," and "disposed over …" do not exclude the presence of an intermediate therebetween, unless specifically noted. Further, "disposed on or above …" merely indicates the relative positional relationship between two components, and may also be converted to "disposed below or below …" and vice versa in certain cases, such as after reversing the product direction.
In the present invention, the embodiments are only intended to illustrate the aspects of the present invention, and should not be construed as limiting.
In the present invention, the terms "a" and "an" do not exclude the presence of a plurality of elements, unless otherwise specified.
It is further noted herein that in embodiments of the present invention, only a portion of the components or assemblies may be shown for clarity and simplicity, but those of ordinary skill in the art will appreciate that, given the teachings of the present invention, required components or assemblies may be added as needed in a particular scenario. Furthermore, features from different embodiments of the invention may be combined with each other, unless otherwise indicated. For example, a feature of the second embodiment may be substituted for a corresponding or functionally equivalent or similar feature of the first embodiment, and the resulting embodiments are likewise within the scope of the disclosure or recitation of the present application.
It is also noted herein that, within the scope of the present invention, the terms "same", "equal", and the like do not mean that the two values are absolutely equal, but allow some reasonable error, that is, the terms also encompass "substantially the same", "substantially equal". By analogy, in the present invention, the terms "perpendicular", "parallel" and the like in the directions of the tables also cover the meanings of "substantially perpendicular", "substantially parallel".
In the present invention, the term "temperature characteristic" refers to a deviation of an analog module of a semiconductor device caused by an influence of a change in an external temperature.
The numbering of the steps of the methods of the present invention does not limit the order in which the method steps are performed. Unless specifically stated, the method steps may be performed in a different order.
The invention is further elucidated with reference to the following description, in conjunction with the detailed description, and with reference to the accompanying drawings.
Fig. 1 shows a schematic diagram of a high-load dual-star tandem structure according to an embodiment of the present invention. As shown in fig. 1, the high-load-bearing double-star series structure may include a lower bearing cylinder 101, an inter-star separation device 102, and an upper bearing cylinder 103.
FIG. 2 shows a force transfer logic diagram for a high load bearing tandem double star configuration in one embodiment of the present invention. As shown in fig. 2, the lower messenger cylinder 101 and the upper messenger cylinder 103 are connected by the inter-satellite separation device 102. The inter-satellite separation device 102 has a docking interface and a separation mechanism, which can ensure the safety and operability of inter-satellite separation. The upper star load is transferred to the lower bearing cylinder 101 through the inter-star separation device 102 by the load of the upper bearing cylinder 103, and the lower star load is also transferred to the lower bearing cylinder 101. The lower bearing cylinder 101 is provided with a star-arrow interface, and the lower bearing cylinder 101 bears the carrying load.
Fig. 3 is a schematic diagram illustrating the structural logic of a high-load dual-star serial structure according to an embodiment of the present invention. As shown in fig. 3, the high-load-bearing tandem structure may adopt a stiffness design priority principle, wherein the lower bearing cylinder 101 and the upper bearing cylinder 103 may be honeycomb sandwich bearing cylinders. The barrel skins of the lower bearing barrel 101 and the upper bearing barrel 103 can be high-modulus carbon fiber and epoxy M55J/AG-80. The barrel skin can bear axial tension and compression loads as well as transverse shear loads. Through reasonable skin laying design, the barrel skin can obtain required mechanical properties. In addition, sensitivity analysis and optimal design can be performed on the laying angle, sequence, thickness, proportion and the like of the carbon fibers according to the conditions such as the load and the configuration of the satellite, the diameter-length ratio of the cylinder and the like. Because the load change of the barrel skin in the height direction of the barrel is large, the barrel skin can adopt a variable-thickness section design in order to reduce the structural mass.
The lower bearing cylinder 101 has the largest contribution to the rigidity of the high-bearing double-star series structure. The larger the aspect ratio of the lower carrier cylinder 101. For example, according to the constraint envelope of a single satellite and the constraint conditions of the carrying mechanics, a taping interface with the diameter of 1666mm can be selected, and the section moment of the root of the lower bearing cylinder 101 is increased, so as to improve the bending resistance of the root of the lower bearing cylinder 101 to the maximum extent. Under the space and weight constraints of the satellite, the appearance of the lower bearing cylinder 101 is divided into a column section part and a cone section part, wherein the diameter of the column section part can be 1194mm, and the overall height of the lower bearing cylinder 101 can be 2093 mm.
Fig. 4 shows a schematic view of a lower force-bearing cylinder in one embodiment of the invention. As shown in fig. 4, the lower force-bearing cylinder 101 may include a lower force-bearing cylinder body 401, a first upper end frame 402, a first lower end frame 403, a first bottom plate flange 404, a first middle plate flange 405, a first tank flange 406, a first top plate flange 407, and an adjusting module flange 408. The first upper end frame 402 can be embedded with glue above the lower bearing cylinder 401, and the first upper end frame 402 is connected with the inter-satellite separation device 102. The first lower end frame 403 may be embedded under the lower bearing cylinder body 402, the first lower end frame 403 is integrated with the skin of the lower bearing cylinder 101, and the first lower end frame 403 is used for connecting a satellite and a launch vehicle below. The lower bearing cylinder 401 may be adhesively connected to the first bottom plate flange 404, the first middle plate flange 405, the first storage tank flange 406, and the first top plate flange 407, and the lower bearing cylinder 101 may be provided with a first bottom plate, a first middle plate, a first storage tank system, a first top plate, and a first adjustment module by the first bottom plate flange 404, the first middle plate flange 405, the first storage tank flange 406, the first top plate flange 407, and the first adjustment module flange 408. The first top plate flange 407 can enhance the top end of the lower bearing cylinder 101 to bear the concentrated load of an upper satellite, and a connecting layer can be arranged on the connecting surface of the lower bearing cylinder 101 and the first top plate to reduce the impact load.
The upper bearing cylinder 103 can adopt a variable thickness section design, the overall height of the upper bearing cylinder 103 can be 1980mm, and the diameter of the column section of the upper bearing cylinder 103 can be 1194 mm.
Fig. 5 shows a schematic view of an upper force-bearing cylinder in one embodiment of the invention. As shown in fig. 5, the upper force-bearing cylinder 103 may include an upper force-bearing cylinder body 501, a second upper end frame 502, a second lower end frame 503, a second bottom plate flange 504, a second middle plate flange 505, a second tank flange 506, a second top plate flange 507, an in-cylinder bottom plate flange 508, and a second adjusting module flange 509. The upper end of the upper bearing cylinder body 501 may be embedded with the second upper end frame 502, and the second upper end frame 502 may be connected with a second top plate. The lower end of the upper bearing cylinder 501 may be embedded with the second lower end frame 503, and the second lower end frame 503 may be connected to the inter-satellite separation device 102. The upper bearing cylinder 501 may be glued to the second bottom plate flange 504, the second middle layer plate flange 505, the second storage tank flange 506, and the second top plate flange 507, and the upper bearing cylinder 103 may be provided with a second bottom plate, a second middle layer plate, a second storage tank system, and a second top plate through the second bottom plate flange 504, the second middle layer plate flange 505, the second storage tank flange 506, and the second top plate flange 507.
The inter-satellite separation device 102 has a dual-satellite docking interface and a separation mechanism, which can ensure the safety and operability of inter-satellite separation between the upper satellite and the lower satellite. The inter-satellite separation device 102 is constructed by adopting an equal rigidity design principle, that is, the overall rigidity of the inter-satellite separation device 102 is equivalent to the rigidity of the lower bearing cylinder 101 and the upper bearing cylinder 103, so that the rigidity loss is reduced. The inter-satellite separating device 102, the lower bearing cylinder 101 and the upper bearing cylinder 103 can be connected through 96M 6 screws, so that the load of the upper bearing cylinder 101 is directly transmitted to the lower bearing cylinder 103 through the inter-satellite separating device 102, and the rigidity loss of inter-satellite connection is reduced.
Fig. 6 shows a schematic diagram of an inter-satellite separation device according to an embodiment of the present invention, and as shown in fig. 6, the inter-satellite separation device 102 may include an inter-satellite separation device upper frame 601, an inter-satellite separation device lower frame 602, and a point separation device 603. The inter-satellite separation device upper frame 601 and the inter-satellite separation device lower frame 602 are connected through the point type separation device 603, and unlocking and separation can be achieved by exploding the point type separation device 603.
Locating pins may also be disposed on the inter-satellite spacing apparatus 102. FIG. 7 shows a schematic view of one locating pin in one embodiment of the present invention. The coaxiality of the lower bearing cylinder 101 and the upper bearing cylinder 103 can be ensured through the positioning pin, so that the unification of mechanical references is realized.
The high-bearing double-star series structure can adjust the height and the diameter of the lower bearing cylinder 101 and the upper bearing cylinder 103 according to different satellite tasks and load configurations. The high-bearing double-star series structure shown in the figure 3 is a 2.5T single-star and 5.0T combined body main structure, a lower bearing cylinder adopts a conical column bearing cylinder structure, the diameter of the cylinder is phi 1194mm, the stars are connected through an inter-star separation device, the load is transferred from the upper bearing to the lower bearing and the unlocking separation is realized, an upper bearing cylinder adopts a variable-thickness cylinder section bearing cylinder (phi 1194mm) design, and a main structure with the envelope of phi 1666mm multiplied by 4353mm is finally formed and is suitable for one-arrow double-star series transmission of small GEO communication satellites. In addition, the invention can increase the bearing mass of the lower star to be more than or equal to 3.0T by increasing the height of the lower bearing cylinder, is restrained by the carrying envelope, reduces the height of the upper bearing cylinder and the bearing mass to be less than or equal to 2.0T, ensures the mass of the assembly to be more than or equal to 5.0T, connects the stars through the inter-star separation device, supports the upper and lower transmission loads and realizes the unlocking separation. And realizing one-arrow two-satellite series emission of satellites with different large masses.
While various embodiments of the present invention have been described above, it should be understood that they have been presented by way of example only, and not limitation. It will be apparent to persons skilled in the relevant art that various combinations, modifications, and changes can be made thereto without departing from the spirit and scope of the invention. Thus, the breadth and scope of the present invention should not be limited by any of the above-described exemplary embodiments, but should be defined only in accordance with the following claims and their equivalents.

Claims (10)

1. The utility model provides a high two stars series connection structure that bear which characterized in that includes:
an upper bearing cylinder;
an inter-satellite separation device connecting the upper and lower messenger drums, wherein the inter-satellite separation device is configured to transfer the load of an upper satellite from the upper messenger drum to the lower messenger drum; and
a lower messenger cylinder disposed below the upper messenger cylinder, wherein the lower messenger cylinder is configured to carry the load of an upper satellite and a lower satellite.
2. The high load bearing dual star tandem structure of claim 1 wherein the overall stiffness of the inter-star separation apparatus is configured to be equivalent to the stiffness of the lower messenger tube and the upper messenger tube.
3. The high-load-bearing dual-satellite series structure of claim 1, wherein the upper bearing cylinder and the lower bearing cylinder comprise honeycomb sandwich bearing cylinders.
4. The high load bearing tandem structure of claim 1, wherein the lower buoyant barrel is connected to a launch vehicle, wherein the lower buoyant barrel comprises:
a lower bearing cylinder body;
the first upper end frame is arranged above the lower bearing cylinder body and is connected with the inter-satellite separation device; and
a first lower end frame disposed below the lower messenger barrel, the first lower end frame configured to connect the lower satellite with the launch vehicle.
5. The high-load-bearing dual-satellite series structure according to claim 4, wherein the lower load-bearing cylinder further comprises a lower load-bearing cylinder flange, a first bottom plate, a first middle-layer plate, a first tank system, a first top plate and a first adjusting module, wherein the lower load-bearing cylinder flange comprises:
a first floor flange connected to the first floor;
a first mid-deck flange connected to the first mid-deck;
a first tank flange connected to the first tank system;
a first top plate flange connected with the first top plate; and
a first conditioning module flange connected with the first conditioning module.
6. The high-load-bearing double-star series structure according to claim 5, wherein the lower bearing cylinder further comprises a connecting layer, and the connecting layer is arranged on the connecting surface of the lower bearing cylinder and the first top plate.
7. The high load bearing dual star series connection structure of claim 6, wherein the upper bearing cylinder comprises:
an upper bearing cylinder body;
the second top plate is arranged above the upper bearing cylinder body;
the second upper end frame connects the upper bearing cylinder body with the second top plate; and
and the second lower end frame is arranged below the lower bearing cylinder body and connects the upper bearing cylinder body with the satellite-rocket separation device.
8. The high-load-bearing dual-star series structure of claim 7, wherein the upper bearing cylinder further comprises an upper bearing cylinder flange and a second bottom plate, wherein the upper bearing cylinder flange further comprises:
a second floor flange connected to the second floor;
a second mid-deck flange connected to the second mid-deck;
a second tank flange connected to the second tank system;
a second top plate flange connected to the second top plate;
the cylinder inner bottom plate flange is connected with the cylinder inner top plate; and
a second conditioning module flange connected to the second conditioning module flange.
9. The high load bearing tandem structure of claim 8, wherein said satellite-rocket separation device comprises:
an inter-satellite separation device is arranged on the frame;
a lower frame of the inter-satellite separation device; and
a point type separating device connecting the inter-satellite separating device upper frame with the inter-satellite separating device lower frame.
10. The high load bearing dual star tandem structure of claim 9 wherein the star-arrow separation device further comprises a positioning pin configured to make the lower bearing cylinder coaxial with the upper bearing cylinder.
CN202210639138.0A 2022-05-31 2022-05-31 High-bearing double-star series structure Pending CN114919777A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210639138.0A CN114919777A (en) 2022-05-31 2022-05-31 High-bearing double-star series structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210639138.0A CN114919777A (en) 2022-05-31 2022-05-31 High-bearing double-star series structure

Publications (1)

Publication Number Publication Date
CN114919777A true CN114919777A (en) 2022-08-19

Family

ID=82813612

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210639138.0A Pending CN114919777A (en) 2022-05-31 2022-05-31 High-bearing double-star series structure

Country Status (1)

Country Link
CN (1) CN114919777A (en)

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