CN212605900U - Multi-layer assembly of satellite propulsion system - Google Patents
Multi-layer assembly of satellite propulsion system Download PDFInfo
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- CN212605900U CN212605900U CN202021779101.0U CN202021779101U CN212605900U CN 212605900 U CN212605900 U CN 212605900U CN 202021779101 U CN202021779101 U CN 202021779101U CN 212605900 U CN212605900 U CN 212605900U
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Abstract
The utility model provides a satellite propulsion system's multilayer assembly, first material layer and second material layer including the interval is laid, wherein: the second material layer is removed at a ground end and a lap end of the multilayer assembly, exposing the first material layer; and the first material layers are in direct contact at the grounding end part and the lap joint end part of the multilayer assembly and/or are connected through the conductive parts, so that a simple grounding structure of the multilayer heat insulation assembly between the first material layers is realized, and the manufacturing and assembling processes of multiple layers are simplified. The multilayer manufacturing and assembling process can be simplified, the problem that the grounding sheet is not easy to rivet due to the shape of the multilayer heat insulation assembly of the long-strip pipeline is solved, the multilayer grounding flow of the pipeline is simplified, and the full and effective grounding of the multilayer heat insulation assembly of the pipeline is ensured, so that the charging and discharging risks of a satellite propulsion system are effectively reduced.
Description
Technical Field
The utility model relates to an aerospace technical field, in particular to satellite propulsion system's multilayer subassembly.
Background
The propulsion system is an actuating mechanism of a satellite attitude and orbit control subsystem, is used for providing speed damping, keeping an orbit, keeping an attitude, adjusting an attitude, changing an orbit and the like, and is an extremely important component of a satellite. The propulsion system comprises a storage tank, a pipeline, a pressure sensor, a self-locking valve, an adding and discharging valve, an electromagnetic valve and the like, in order to meet the on-orbit flight requirement, the temperature of the propulsion system needs to be controlled in a higher range, heaters need to be adhered to all the components, and a plurality of layers of heat insulation assemblies are coated outside the components, so that the heating efficiency is improved, and the influence of the temperature of other single units in the cabin is reduced.
In order to prevent the satellite from generating static electricity accumulation and static electricity discharge, protect the satellite from electric shock caused by any electromagnetic pulse effect in the environment, reduce electromagnetic interference and discharge pollution generated by electromagnetic fields or other forms of inductive coupling and the like, all conductive parts inside and outside the satellite are grounded as required. The multilayer heat insulation assembly is also lapped with the satellite structure nearby according to a specified process, the grounding resistance between the multilayer grounding reference point and the structure grounding pile is less than 1.0 omega, and the grounding connection is as short as possible.
The design of traditional storage box multilayer thermal-insulated subassembly is mostly the multiple-sheet type, in order to laminate globular, divide into it more than 8 at least, and not only technology is complicated, and assembly and ground connection process are also very loaded down with trivial details. Due to the slender shape of the propulsion pipeline, the propulsion pipeline needs to be wound by using long-strip-shaped multiple layers along the pipeline, and the problems of overlapping and grounding of the multiple layers are faced. At present, for the propulsion pipeline, the more common treatment methods are as follows: without the multi-layer insulation assembly and with or without grounding by conventional grounding tabs. The disadvantage of not coating the multi-layer heat insulation assembly is obvious, the temperature of the pipeline is easily influenced by the change of the temperature of a single machine around, and the stability is reduced; if the coating is multi-layer but not grounded, the static accumulation capacity is weak, but the static accumulation capacity is still an isolated conductor, so that the risk exists; the traditional multilayer grounding structure is characterized in that a grounding rivet is arranged on a multilayer, double-sided aluminum plated polyester films in each unit of the multilayer are lapped and led out for grounding through the grounding rivet, and the size of a traditional grounding sheet is equivalent to that of a pipeline multilayer heat insulation assembly, so that the grounding structure is particularly heavy, large in manufacturing difficulty and difficult to fix.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a satellite propulsion system's multilayer assembly to the multilayer assembly structure of solving current satellite propulsion system is complicated, the big problem of the assembly degree of difficulty.
In order to solve the technical problem, the utility model provides a satellite propulsion system's multilayer assembly, including the first material layer and the second material layer of interval laying, wherein:
the second material layer is removed at a ground end and a lap end of the multilayer assembly, exposing the first material layer; and
the first material layers are in direct contact at the ground and lap ends of the multilayer assembly and/or are connected by a conductive member.
Optionally, in the multi-layer assembly of the satellite propulsion system, the satellite propulsion system includes a spherical tank, wherein:
the first multilayer assembly wrapping the storage tank comprises two single-side serrated assembly sheets and two petal-shaped assembly sheets;
the two unilateral sawtooth-shaped component pieces are butted at one side back to the sawtooth and fixed on the spherical storage box by silicon rubber, and the two petal-shaped component pieces are respectively fixed by the silicon rubber so as to cover the gap of the two unilateral sawtooth-shaped component pieces.
Optionally, in the multilayer assembly of the satellite propulsion system, the satellite propulsion system further includes a pipeline, wherein:
the second multilayer assembly wrapping the pipeline is a strip-shaped assembly sheet, is obliquely wound on the pipeline at a certain angle and is sequentially wound along the center line of the upper layer, the outermost layer is coated with a layer of single-sided aluminum-plated polyester film with an aluminum-plated surface facing outwards after fixation, and the tail end of the single-sided aluminum-plated polyester film is fixed by aluminum-plated pressure-sensitive adhesive.
Optionally, in the multi-layer assembly of the satellite propulsion system, a first grounding end portion is further included, the first grounding end portion includes an accordion-shaped aluminum foil, a rivet, and a grounding lug, wherein:
the second material layer is removed at the first ground end, exposing the first material layer;
the number of layers of the organ-shaped aluminum foil is consistent with that of the first material layer, each layer of the organ-shaped aluminum foil is embedded between each layer of the first material layer, and the grounding soldering lug is pressed on the top layer of the organ-shaped aluminum foil;
the rivet rivets the grounding welding sheet, the organ-shaped aluminum foil and the first material layer into a whole.
Optionally, in the multi-layer assembly of the satellite propulsion system, the landing end includes a first landing assembly and a second landing assembly, wherein:
removing the second material layer of the first lap joint component to expose the first material layer of the first lap joint component;
removing the second material layer of the second lap joint component to expose the first material layer of the second lap joint component;
the first material layer of the first lap joint component is in a step shape and is folded along the direction of contacting with the second lap joint component;
the first material layer of the second lap joint component is in an inverted step shape;
each layer of the first material layer of the first lap joint component is in direct contact with each layer of the first material layer of the second lap joint component in sequence, and the first material layer and the second material layer are firmly adhered by a polyimide adhesive tape.
Optionally, in the multi-layer assembly of the satellite propulsion system, a second ground end is further included, wherein:
the second material layer is removed at the second ground end, exposing the first material layer;
the first material layer of the second grounding end part is in a step shape and is folded along the direction of contacting with the conductive surface;
the first material layer of the second grounding end is in direct contact with the conductive surface and is fixed by aluminized pressure-sensitive adhesive.
Optionally, in the multi-layer assembly of the satellite propulsion system, the first ground end is located on all but the second multi-layer assembly, the second ground end is located on the second multi-layer assembly, and the lap end is located on the second multi-layer assembly.
Optionally, in the multilayer assembly of the satellite propulsion system, the first material layer is a double-sided aluminum-plated polyester film, the second material layer is a nylon net towel, one first material layer covers one second material layer to form an assembly unit, and the innermost layer of the plurality of assembly units covers one polyimide film;
the satellite propulsion system further comprises a pressure sensor, a self-locking valve and a charging and discharging valve, wherein the pressure sensor, the self-locking valve and the charging and discharging valve are externally wrapped by 15 component units;
the first multilayer assembly comprises 10 assembly units and the second multilayer assembly comprises 3 assembly units.
The utility model provides an among the multilayer assembly of satellite propulsion system, the ground connection tip and the overlap joint tip department of multilayer assembly are removed through the second material layer, expose first material layer, first material layer is in multilayer assembly's ground connection tip and overlap joint tip department direct contact, and/or connect through conductive parts, has realized the simple ground structure of the thermal-insulated subassembly of multilayer between the first material layer, has simplified multilayer preparation and assembly process.
The utility model relates to a satellite propulsion system multilayer subassembly design and ground connection scheme, satellite propulsion system include storage tank, pipeline, pressure sensor, self-locking valve, add row valve and solenoid valve etc. in order to satisfy the control by temperature change requirement, all need the thermal-insulated subassembly of cladding multilayer.
The utility model designs a four-piece type storage tank multilayer heat insulation component which can adapt to the spherical characteristics of the storage tank, closely fit the appearance of the storage tank and simplify the process flow; multilayer heat insulation assemblies of square components such as a pressure sensor, a self-locking valve and the like are designed; the long-strip-shaped multilayer heat insulation assembly for the pipeline and the lap joint mode thereof are designed: when the length of the multilayer strip is insufficient and needs to be spliced, the first material layer is trimmed to be in a step shape in the length direction and is folded along the direction of the contact surface of the spliced multilayer, and the spliced multilayer first material layer is also trimmed to be in the step shape and is sequentially contacted with the spliced multilayer first material layer, so that the double-sided contact of each first material layer of the two multilayer strips is ensured; the grounding structure of the multilayer heat insulation assembly is designed: the first material layers are trimmed in a step shape in the length direction and folded along the direction of contact with the conductive surface, and then are directly contacted and fixed on the conductive surface, so that the double-sided grounding of each first material layer of the plurality of layers is ensured. The multilayer manufacturing and assembling process can be simplified, the problem that the grounding sheet is not easy to rivet due to the shape of the multilayer heat insulation assembly of the long-strip pipeline is solved, the multilayer grounding flow of the pipeline is simplified, and the full and effective grounding of the multilayer heat insulation assembly of the pipeline is ensured, so that the charging and discharging risks of a satellite propulsion system are effectively reduced.
Drawings
Fig. 1 is a schematic view of a first multi-layer assembly according to an embodiment of the present invention;
FIG. 2 is a schematic view of a first multi-layer assembly and tank installation according to an embodiment of the present invention;
fig. 3 is a schematic view of a first grounding end according to an embodiment of the present invention;
FIG. 4 is a schematic view of the overlapping end of an embodiment of the present invention;
fig. 5 is a schematic view of a second ground end of an embodiment of the present invention;
fig. 6 is a schematic view of a second grounding end of an embodiment of the present invention;
fig. 7 is a schematic view of a satellite propulsion system according to an embodiment of the present invention;
shown in the figure:
100-a first multilayer assembly;
110-a ground location;
200-a storage tank;
210-single-sided serrated component pieces;
220-petal-shaped component pieces;
300-a first ground end;
310-double-sided aluminum-plated polyester film;
320-a ground plate;
330-ground line;
340-blind rivets;
350-silver-plated soldering lugs;
360-aluminum foil strips;
400-overlapping the ends;
410-pipeline multilayer 1;
420-pipeline multilayer 2;
430-double-sided aluminum-plated polyester film;
500-a second ground end;
510-double-sided aluminum plated polyester film;
600-a satellite propulsion system;
610-a solenoid valve;
620-line to solenoid valve connection;
630-a propel circuit;
700-a second ground end;
710-a second multi-layer assembly;
720-pipeline and solenoid valve connection.
Detailed Description
The multi-layer assembly of the satellite propulsion system of the present invention is described in further detail below with reference to the accompanying drawings and specific embodiments. The advantages and features of the present invention will become more fully apparent from the following description and appended claims. It should be noted that the drawings are in simplified form and are not to precise scale, and are provided for convenience and clarity in order to facilitate the description of the embodiments of the present invention.
Furthermore, features in different embodiments of the invention may be combined with each other, unless otherwise specified. 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.
The utility model discloses a core thought lies in providing a satellite propulsion system's multilayer assembly to the multilayer assembly structure of solving current satellite propulsion system is complicated, the big problem of the assembly degree of difficulty.
In order to realize the above idea, the utility model provides a satellite propulsion system's multilayer subassembly, first material layer and second material layer including the interval is laid, wherein: the second material layer is removed at a ground end and a lap end of the multilayer assembly, exposing the first material layer; and the first material layers are in direct contact at the ground end and the lap end of the multilayer assembly and/or are connected by a conductive member.
The utility model provides a pair of satellite propulsion system multilayer subassembly design and ground connection scheme, including the multilayer thermal-insulated subassembly design of parts such as storage tank, pipeline and pressure sensor, the multilayer thermal-insulated subassembly overlap joint structure of pipeline and the multilayer thermal-insulated subassembly ground structure of pipeline etc.. The structure can simplify the multilayer manufacturing, assembling and grounding processes, solve the problem that the multilayer heat insulation assembly of the long-strip pipeline is not easy to rivet the grounding sheet due to the shape, simplify the multilayer grounding flow of the pipeline and ensure the full and effective grounding.
As shown in fig. 2, in one embodiment of the present invention, the multi-layer thermal insulation assembly of the storage box 200 is a four-piece design, with two pieces of upper and lower hemispheres each having a similar shape, one piece being in the shape of a cluster (single-sided serrated assembly pieces 210) and one piece being in the shape of a petal (petal assembly pieces 220). When the multilayer heat insulation assembly of the storage box is assembled, the two grass-shaped multilayer bodies are assembled firstly, the two grass-shaped multilayer bodies are adhered firmly by silicon rubber, then the two petal-shaped multilayer bodies are covered on gaps of the grass-shaped multilayer bodies, and the adhesive is firmly dispensed.
As shown in fig. 4, when the pipeline multi-layer 1(410) and the pipeline multi-layer 2(420) are overlapped, two multi-layer nylon net towels (second material layers) are cut short to expose the double-sided aluminum-plated mylar 430 (first material layer), and both the double-sided aluminum-plated mylar 430 are trimmed to be step-shaped. When the pipeline multiple layers 410 and 420 are overlapped, the double-sided aluminum-plated polyester film 430 of one of the multiple layers 410 is folded along the contact surface direction, the folding length is 5mm, and when the two multiple layers are continuously connected, each double-sided aluminum-plated polyester film 430 is sequentially contacted, so that the double-sided contact of each double-sided aluminum-plated polyester film 430 is ensured. When the pipelines are lapped in multiple layers, two layers with two contacted surfaces are firmly adhered by using polyimide adhesive tapes with two surfaces and one surface.
When the propelling pipeline is wrapped in multiple layers, the propelling pipeline is obliquely wound on the propelling pipeline in a 45-degree direction, the propelling pipeline is sequentially wound by pressing the central lines of the multiple layers of strips, and a layer of single-sided aluminum-plated polyester film (the aluminum-plated surface faces outwards) with the thickness of 16 microns is further coated on the outermost layer after the pushing pipeline is fixed. As shown in fig. 5, when the propulsion pipeline is grounded in multiple layers, the nylon mesh towel is cut short to expose the double-sided aluminum-plated polyester film 510, and the double-sided aluminum-plated polyester film 510 is trimmed to form a step shape. When the propulsion pipeline multilayer is grounded, the multilayer on each pipeline is completely contacted and conductive when spliced, and only one grounding is needed.
The multi-layer heat insulation component of the utility model lays the double-sided aluminized polyester film and the net towel according to the proportion of 1:1 at intervals, the innermost layer is covered with a layer of polyimide film, and the outermost layer is the surface of the double-sided aluminized polyester film. The multilayer heat insulation assembly of the storage tank, the pressure sensor, the self-locking valve and the discharge valve is 10 units, the multilayer heat insulation assembly of the electromagnetic valve is 15 units, and the multilayer heat insulation assembly of the pipeline is 3 units. The multiple layers of the propelling pipeline are cut into multiple layers of strips with the width of 20 mm. Except for the multiple layers of the pipeline, each other multi-layer heat insulation assembly needs to be riveted with a grounding sheet, and the length of the grounding wire is designed according to the principle of nearby grounding. Except for the multiple layers of the pipeline, the structures of the riveting grounding piece of other multilayer heat insulation assemblies are all consistent, and the size of the grounding piece is M4.
Fig. 1 shows a design diagram of a four-piece multi-layer heat insulation assembly of a storage tank, wherein a first multi-layer assembly 100 comprises two multi-layers of an upper hemisphere and a lower hemisphere, the two multi-layers on the right side are assembled on the upper hemisphere and the lower hemisphere of the storage tank firstly during assembly, and are fixed by silicone rubber, and then the two multi-layers on the left side are covered on a gap of the two multi-layers on the right side tightly and are fixed firmly by the silicone rubber, so that a structure shown in fig. 2 is formed. The multilayer of the pipeline is a multilayer strip with the width of 20mm, the head end of the strip-shaped multilayer assembly is grounded when the pipeline is bound, the strip-shaped multilayer assembly is obliquely wound on the propulsion pipeline in the direction of 45 degrees and is sequentially wound along the central line of the multilayer strip, a layer of single-side aluminized polyester film with the thickness of 16 mu m (the aluminized surface faces outwards) is coated on the outermost layer after the fixation, and the tail end of the strip-shaped multilayer assembly is fixed by aluminized pressure sensitive adhesive. And the other parts are square, so that the manufacture and assembly of multiple layers are processed conventionally.
Fig. 3 is a grounding structure of the first grounding end 300 of the other components except the propulsion line. The aluminum foil is cut into a strip-shaped aluminum foil strip 360 with the width of 20mm, the aluminum foil strip is folded into an organ shape, the number of layers of the organ is consistent with that of the multi-layer assembly units, each organ sheet is embedded between the double-sided aluminum-plated polyester films 310 after the aluminum foil strip is folded, the double-sided contact of the organ sheets is guaranteed, and then the silver-plated soldering sheets 350 and the organ sheets are riveted into a whole by hollow rivets 340. The pop rivet 340 is connected to the ground plate 320 via the ground wire 330. In the case of fig. 1, the first ground end 300 is arranged at the ground location 110.
Fig. 4 is a schematic view of a multi-layered overlapping end 400 of a pusher line. When the length of the multiple layers (pipeline multiple layers 1410) is not enough and needs to be spliced, the nylon net towel is cut short to expose the double-sided aluminum-plated polyester film 430, the double-sided aluminum-plated polyester film 430 is trimmed to be in a step shape and is folded for 5mm along the direction of the contact surface of the multiple layers to be spliced, the multiple layers (pipeline multiple layers 2420) of the nylon net towel to be spliced are also cut short, the double-sided aluminum-plated polyester film 430 is trimmed to be in the step shape and sequentially contacted according to the structure shown in the figure, and double-sided and single-sided polyimide tapes are used for adhering firmly, so that the double-sided contact of each layer of the.
Fig. 5 is a schematic diagram of a stepped head end of a second grounded end 500 of a propulsion pipeline, where a double-sided aluminum-plated polyester film 510 is trimmed to be stepped and folded for 5mm in a direction of contacting with a conductive surface, and fig. 6 is a partial schematic diagram of a pipeline of a satellite propulsion system 600, which includes a solenoid valve 610 and a pipeline and solenoid valve connector 620; fig. 7 is a schematic diagram of a second ground end portion 700 of a head end of a second multi-layer assembly 710 of a pipeline. With a similar structure, the nylon net towel is cut short to expose the double-sided aluminum plated polyester film 510, and then the nylon net towel is directly contacted and fixed on the conductive surface of the pipeline and solenoid valve connecting piece 720 by the aluminum plated pressure sensitive adhesive and is firmly dotted by the silicon rubber, so that the double-sided grounding of each layer of double-sided aluminum plated polyester film of the multilayer assembly is ensured.
In summary, the above embodiments have been described in detail with respect to different configurations of the multi-layer assembly of the satellite propulsion system, and it is understood that the present invention includes, but is not limited to, the configurations listed in the above embodiments, and any modifications based on the configurations provided by the above embodiments are within the scope of the present invention. One skilled in the art can take the contents of the above embodiments to take a counter-measure.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the structure disclosed by the embodiment, and the relevant points can be referred to the structural part for description.
The above description is only for the preferred embodiment of the present invention and is not intended to limit the scope of the present invention, and any modification and modification made by those skilled in the art according to the above disclosure are all within the scope of the claims.
Claims (8)
1. A multi-layer assembly of a satellite propulsion system, comprising first and second spaced apart layers of material, wherein:
the second material layer is removed at a ground end and a lap end of the multilayer assembly, exposing the first material layer; and
the first material layers are in direct contact at the ground and lap ends of the multilayer assembly and/or are connected by a conductive member.
2. The multi-layer assembly of a satellite propulsion system as claimed in claim 1, wherein the satellite propulsion system includes a spherical tank, wherein:
the first multilayer assembly wrapping the storage tank comprises two single-side serrated assembly sheets and two petal-shaped assembly sheets;
the two unilateral sawtooth-shaped component pieces are butted at one side back to the sawtooth and fixed on the spherical storage box by silicon rubber, and the two petal-shaped component pieces are respectively fixed by the silicon rubber so as to cover the gap of the two unilateral sawtooth-shaped component pieces.
3. The multi-layer assembly of a satellite propulsion system as claimed in claim 2, wherein the satellite propulsion system further comprises a pipeline, wherein:
the second multilayer assembly wrapping the pipeline is a strip-shaped assembly sheet, is obliquely wound on the pipeline at a certain angle and is sequentially wound along the center line of the upper layer, the outermost layer is coated with a layer of single-sided aluminum-plated polyester film with an aluminum-plated surface facing outwards after fixation, and the tail end of the single-sided aluminum-plated polyester film is fixed by aluminum-plated pressure-sensitive adhesive.
4. The multi-layer assembly of a satellite propulsion system as claimed in claim 3 further comprising a first ground end portion comprising a concertina aluminum foil, rivets and ground lugs, wherein:
the second material layer is removed at the first ground end, exposing the first material layer;
the number of layers of the organ-shaped aluminum foil is consistent with that of the first material layer, each layer of the organ-shaped aluminum foil is embedded between each layer of the first material layer, and the grounding soldering lug is pressed on the top layer of the organ-shaped aluminum foil;
the rivet rivets the grounding welding sheet, the organ-shaped aluminum foil and the first material layer into a whole.
5. The multi-layer assembly of a satellite propulsion system of claim 4, wherein the landing end includes a first landing assembly and a second landing assembly, wherein:
removing the second material layer of the first lap joint component to expose the first material layer of the first lap joint component;
removing the second material layer of the second lap joint component to expose the first material layer of the second lap joint component;
the first material layer of the first lap joint component is in a step shape and is folded along the direction of contacting with the second lap joint component;
the first material layer of the second lap joint component is in an inverted step shape;
each layer of the first material layer of the first lap joint component is in direct contact with each layer of the first material layer of the second lap joint component in sequence, and the first material layer and the second material layer are firmly adhered by a polyimide adhesive tape.
6. The multi-layer assembly of a satellite propulsion system as claimed in claim 5, further comprising a second ground end, wherein:
the second material layer is removed at the second ground end, exposing the first material layer;
the first material layer of the second grounding end part is in a step shape and is folded along the direction of contacting with the conductive surface;
the first material layer of the second grounding end is in direct contact with the conductive surface and is fixed by aluminized pressure-sensitive adhesive.
7. The multi-layer assembly of a satellite propulsion system as claimed in claim 6 wherein the first ground end is located on all but the second multi-layer assembly, the second ground end is located on the second multi-layer assembly, and the landing end is located on the second multi-layer assembly.
8. A multi-layer assembly as claimed in claim 3 wherein said first layer of material is a double-sided aluminized polyester film and said second layer of material is a nylon scrim, a first layer of material overlying a second layer of material to form an assembly unit, and an innermost layer of the plurality of assembly units overlying a polyimide film;
the satellite propulsion system further comprises a pressure sensor, a self-locking valve and a charging and discharging valve, wherein the pressure sensor, the self-locking valve and the charging and discharging valve are externally wrapped by 15 component units;
the first multilayer assembly comprises 10 assembly units and the second multilayer assembly comprises 3 assembly units.
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| CN202021779101.0U CN212605900U (en) | 2020-08-24 | 2020-08-24 | Multi-layer assembly of satellite propulsion system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111824460A (en) * | 2020-08-24 | 2020-10-27 | 中国科学院微小卫星创新研究院 | Multi-layer assembly of satellite propulsion system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111824460A (en) * | 2020-08-24 | 2020-10-27 | 中国科学院微小卫星创新研究院 | Multi-layer assembly of satellite propulsion system |
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