CN111762338A - Folding flat satellite structure - Google Patents
Folding flat satellite structure Download PDFInfo
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- CN111762338A CN111762338A CN202010447697.2A CN202010447697A CN111762338A CN 111762338 A CN111762338 A CN 111762338A CN 202010447697 A CN202010447697 A CN 202010447697A CN 111762338 A CN111762338 A CN 111762338A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
Abstract
The invention provides a folding flat satellite configuration, which is characterized in that through the design of the folding flat satellite configuration, a folding flat satellite body comprises a first satellite cabin body and a second satellite cabin body, and a connector for connecting the first satellite cabin body and the second satellite cabin body is arranged, so that the angle between the skyward surface of each of the first satellite cabin body and the second satellite cabin body can be adjusted, and then the two cabin bodies of a satellite can be folded or unfolded, so that the folding flat satellite can be placed in a stacking mode in a fairing, can adapt to different fairing sizes, achieves extremely high fairing space utilization rate, realizes the 'rocket multi-star' launching with high numerical value proportion, ensures the rapid and low-cost deployment of a satellite constellation, and solves two problems of satellite launching period requirement and cost control requirement. The satellite has the characteristics of large ground surface and multiple heat dissipation surfaces, and is more friendly to the satellite design mainly aiming at microwave application such as space-based radar remote sensing and high-capacity satellite communication.
Description
Technical Field
The invention relates to the technical field of satellites, in particular to a folding flat satellite structure.
Background
The current aerospace industry faces explosive growth opportunities and challenges, commercial aerospace is driven by market, technology, capital and other forces, a batch of large-scale internet satellite constellations and remote sensing satellite constellations appear, and the requirement of launching nearly thousands of micro satellites is met in five years in the future, and the 'one rocket multi-satellite' launching is a necessary requirement for rapid deployment of large-scale satellite constellations.
Facing the requirement of satellite transmission of large-batch and rapid deployment, the satellite transmission faces two major problems at present. Firstly, the rocket launching capability in China is weak, and a single type rocket is difficult to meet the requirement of large-scale constellation rapid deployment. Secondly, the price of the domestic rocket is high, and the competitive environment is difficult to build by selecting a single type rocket. Therefore, large-scale constellation deployment requires that a satellite is adapted to the constraint of multiple rockets, and when different rockets are adopted, high space utilization rate is required to be achieved, and the multiple rockets can be selected to share the launching task. The traditional satellite configuration during one-rocket-multi-satellite launching has the defects that the space of a fairing cannot be fully utilized, or the space utilization rate of a single rocket can be higher.
Disclosure of Invention
To address at least one of the above issues, the present invention provides a folding flat panel satellite configuration comprising:
the satellite comprises a folding flat-plate satellite body, a first satellite cabin and a second satellite cabin, wherein the satellite body comprises the first satellite cabin and the second satellite cabin;
and the connector is used for connecting the first satellite cabin and the second satellite cabin and enabling the angle between the opposite skyways of the first satellite cabin and the second satellite cabin to be adjustable.
In a preferred embodiment, the first satellite pod and the second satellite pod are provided with mutually cooperating fixing structures for assisting at least the relative fixing of the first satellite pod and the second satellite pod when an angle between the opposite surfaces of the first satellite pod and the second satellite pod is lower than a set angle.
In a preferred embodiment, the fixing structure comprises:
a first disconnect coupling on the first satellite pod and a second disconnect coupling on the second satellite pod; when the angle between the opposite surfaces of the first satellite cabin and the second satellite cabin is lower than a set angle, the first separation connecting cylinder and the second separation connecting cylinder are abutted, and the cylinder bodies of the first separation connecting cylinder and the second separation connecting cylinder are communicated;
the barrel of first separation connecting cylinder with the second separation connecting cylinder can run through the compression rope, and then makes the compression rope is connected fixedly first separation connecting cylinder with the second separation connecting cylinder.
In a preferred embodiment, a first disconnect connector barrel located on the first satellite pod and a second disconnect connector barrel located on the second satellite pod; when the angle between the opposite skywards of the first satellite pod and the second satellite pod is lower than a set angle, at least part of the second separation connecting cylinder is inserted into the cylinder body of the first separation connecting cylinder.
In a preferred embodiment, the first separation connector projects from the ground-to-ground of the first satellite pod, the second separation connector extends through the ground-to-ground of the second satellite pod, and an aperture of an end of the first separation connector adjacent to the ground-to-ground is smaller than an aperture of an end of the second separation connector adjacent to the ground-to-ground, such that when two folding flat-panel satellite configurations are stacked, the first separation connector of a previous folding flat-panel satellite configuration is inserted into the second separation connector of a next folding flat-panel satellite configuration.
In a preferred embodiment, each separation connector comprises a first portion located inside the space defined by the satellite pod facing the sky and facing the ground, and a second portion located outside said defined space, said second portion having a diameter smaller than the diameter of said first portion.
In a preferred embodiment, the first part of each separation connector is fixed to the outer side wall of the corresponding nacelle or the first part of each separation connector is sunk into the interior of the corresponding nacelle.
In a preferred embodiment, a protrusion on the zenith-facing surface of the first satellite pod and a depression on the zenith-facing surface of the second satellite pod; the protrusion can be inserted into the recess to form the fixing structure in a matching manner.
In a preferred embodiment, two solar wings are laid on the opposite skywards of the first satellite hull and the second satellite hull; and the connector is connected with the solar wing and the corresponding satellite cabin body, and enables the angle between the solar wing and the opposite-to-sky surface of the corresponding satellite cabin body to be adjustable.
In a preferred embodiment, each satellite cabin is provided with a ground antenna on the ground; and/or
And a sensor or an antenna is arranged on the opposite-to-sky surface of each satellite cabin.
The invention has the advantages of
The invention provides a folding flat satellite configuration, through the design of the folding flat satellite configuration, a satellite body comprises a first satellite cabin body and a second satellite cabin body, and through arranging a connector for connecting the first satellite cabin body and the second satellite cabin body, the respective angles between the skyward surfaces of the first satellite cabin body and the second satellite cabin body can be adjusted, so that the two cabin bodies of the folding flat satellite configuration can be folded or unfolded, and the satellite can be placed in a fairing in a stacking mode in a folding state and an unfolding state during launching, so that the folding flat satellite configuration can adapt to different fairing sizes, and the extremely high fairing space utilization rate can be achieved, and thus various rockets can be adopted for competitive launching; the structure meets various requirements of structural design of other satellites, has the characteristics of large ground and multiple radiating surfaces, is more friendly to the design of satellites taking microwave application such as space-based radar remote sensing and high-capacity satellite communication as main directions, realizes one-rocket multi-satellite emission with high numerical proportion, and ensures the rapid and low-cost deployment of satellite constellations, thereby solving two problems of requirement on satellite emission period and requirement on cost control.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic view showing a folded state of a folding flat-panel satellite according to an embodiment of the present invention.
Fig. 2 shows a front view of a breakaway connector in the form of a through-nacelle structure in an embodiment of the present invention.
Fig. 3 shows a top view of a separation joint in an embodiment of the invention in a structural form through the nacelle.
Fig. 4 shows a front view of a breakaway connector in the form of an extra-cabin structural form in an embodiment of the present invention.
Fig. 5 shows a top view of a separation connector in the form of an extra-cabin structural form in an embodiment of the invention.
Fig. 6 is a schematic diagram illustrating an unfolded state of a foldable flat-panel satellite according to an embodiment of the present invention.
Fig. 7 is a schematic view showing a satellite stacking state in a case of a small-sized cowling according to an embodiment of the present invention.
Fig. 8 shows a schematic view of the satellite in a folded state and a unfolded state fixed by a pressing rope in the embodiment of the invention.
Fig. 9 is a schematic diagram illustrating an in-orbit operation state of a folding flat-plate satellite according to an embodiment of the invention.
FIG. 10 is a schematic view of a satellite stack in an embodiment of the invention for a large fairing size.
FIG. 11 is a second schematic view of the satellite stack state of the small-sized fairing according to the embodiment of the invention.
FIG. 12 is a second schematic view of the satellite stack state of the fairing of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. 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.
Fig. 1 shows a schematic configuration diagram of a folding flat-plate satellite in an embodiment of the present application, as shown in fig. 1, which specifically includes: the satellite comprises a satellite body, a first satellite cabin body 01 and a second satellite cabin body 02; and the connector 05 is used for connecting the first satellite cabin 01 and the second satellite cabin 02 and enabling the angle between the respective opposite skyways of the first satellite cabin 01 and the second satellite cabin 02 to be adjustable.
The solar wing is attached to the opposite-to-sky surface when the satellite is launched to a set orbit, and the sun wing is unfolded to form a certain angle with the opposite-to-sky surface, wherein the angle can be 0-180 degrees, and the angle is preferably 90 degrees, namely the sun wing is perpendicular to the opposite-to-sky surface.
The present invention has two specific states, one is a folded state, that is, the angle between the opposite skyways of the two cabins is lower than a set angle, the set angle can be set between 0 and 10, for example, 5 degrees, 10 degrees, etc., the present invention is not limited, and preferably 0 degrees, that is, when folded, the folded satellite is rectangular as a whole, as shown in fig. 1. The second is the unfolding state, that is, the angle between the opposite surfaces of the two cabins is higher than the set angle, and the set angle can be set between 170 and 180, for example, 170 °, 175 °, etc., but the invention is not limited thereto, and preferably 180 °, as shown in fig. 6.
In an embodiment of the invention, in order to make the two pods relatively fixed when folded, a fixing structure may be provided for relatively fixing the first and second satellite pods when the angle between the skyward surfaces of the first and second satellite pods is below a set angle.
Specifically, as shown in fig. 6, the fixing structure includes: a first disconnect coupling cylinder 06 on the first satellite pod 01 and a second disconnect coupling cylinder 07 on the second satellite pod 02; when the angle between the opposite-to-sky surfaces 08 of the first satellite pod 01 and the second satellite pod 02 is lower than a set angle, the first separation connecting cylinder 06 and the second separation connecting cylinder 07 are abutted, and the cylinder bodies of the first separation connecting cylinder 06 and the second separation connecting cylinder 07 are communicated with each other. As shown in fig. 7, the cylinders of the first separation connecting cylinder 06 and the second separation connecting cylinder 07 can penetrate through the pressing rope 10, so as to facilitate the overlapping and fixing of a plurality of satellites. And the compression rope is connected and fixed with the first separation connecting cylinder and the second separation connecting cylinder, and in the embodiment, the separation connecting cylinders can play a role in separation and connection.
It can be understood that the sky 08 and the ground 09 are planes or curved surfaces in the invention, that is, the specific structure of the satellite capsule of the invention is not limited too much, for example, the sky of the satellite capsule may be rectangular, rhombic, circular or irregular, and may also be curved surfaces that can be matched as much as possible when folded.
In some embodiments, the first separation connecting cylinder 06 and the second separation connecting cylinder 07 may not be disposed in an abutting manner, and in order to reduce the space waste caused when the first separation connecting cylinder 06 and the second separation connecting cylinder 07 are mutually matched, which leads to the reduction of the loading capacity of the fairing, in this embodiment, the fixing structure includes: a first disconnect coupling on the first satellite pod and a second disconnect coupling on the second satellite pod; when the angle between the opposite planes of the first satellite cabin and the second satellite cabin is lower than a set angle, at least part of the second separation connecting cylinder is inserted into the cylinder body of the first separation connecting cylinder; the barrel of first separation connecting cylinder with the second separation connecting cylinder can run through the compression rope, and then makes the compression rope is connected fixedly first separation connecting cylinder with the second separation connecting cylinder.
In this embodiment, in order to realize that a plurality of folding flat satellites can be relatively fixed without using an external fixing device when stacked on each other, the first separation connecting cylinder protrudes out of the ground facing surface of the first satellite cabin, the second separation connecting cylinder penetrates through the ground facing surface of the second satellite cabin, and the aperture of one end, close to the ground facing surface, of the first separation connecting cylinder is smaller than the aperture of one end, close to the ground facing surface, of the second separation connecting cylinder, so that at least part of the first separation connecting cylinder of the upper folding flat satellite configuration is inserted into the second separation connecting cylinder of the lower folding flat satellite configuration when the folding flat satellites are stacked, and then the first separation connecting cylinder and the second separation connecting cylinder are relatively fixed.
Further, in order to mass-produce the separation connecting cylinders, ensure that the specifications of the first separation connecting cylinder and the second separation connecting cylinder are consistent, and save production process steps, in this embodiment, each separation connecting cylinder may be configured into two parts, please continue to combine with fig. 6, each separation connecting cylinder includes a first part located in a space limited by the satellite capsule body facing the sky and the ground, and a second part located outside the limited space, and the diameter of the second part is smaller than that of the first part, so that the first separation connecting cylinder and the second separation connecting cylinder may be produced by using the same production process, and process costs are greatly saved.
In addition, the location of the breakaway connector in the present invention may include a variety of locations, for example, each breakaway connector may alternatively be configured throughout the nacelle body, as shown in fig. 2 and 3, or outside the nacelle body, as shown in fig. 4 and 5. In addition, the number of the connecting cylinders can also be 8, and can also be less than 8 or more than 8, and the invention is not limited.
In an embodiment of the invention not shown in the drawings, the fixing structure comprises: a protrusion on the skyward surface of the first satellite pod and a depression on the skyward surface of the second satellite pod; the protrusion can be inserted into the recess to form the fixing structure in a matching manner. In the embodiment, the compression rope is not adopted for fixing, the relative limit is carried out only by adopting the bulge and the recess, the structure of the fairing is further required to be utilized for further limit in specific application, and the collision caused in the rocket flying process is avoided.
It is understood that the first satellite cabin and the second satellite cabin are level with the sky, but may be level with or not level with the ground, and the invention is not limited thereto, as shown in fig. 6 to 10, and may be not level with the ground, that is, the heights of the two satellite cabins may be different (the direction of the arrow in fig. 1 is the height direction, and the height in this embodiment is the length along the direction of the arrow in fig. 1).
As shown in fig. 8, after the satellites are stacked, the cylinders of the first separation connecting cylinder 06 and the second separation connecting cylinder 07 can penetrate through the pressing rope 10 to press the satellites, so that the folded flat satellite configuration is stacked, and then the stacked folded flat satellite configuration is integrally loaded into the carrying fairing. As shown in fig. 9, when the satellite and the rocket are separated, the whole train of satellites in the fairing is separated from the last stage of the carrier rocket, the pre-tightening force device is opened after separation, the satellites are slowly dispersed under the action of the pressing rope, the satellites are unfolded from the folded state to the flat state after being dispersed to a safe distance, and then the solar wing is unfolded to achieve the on-orbit flying state.
It can be appreciated that to prevent slippage when the satellites are stacked, compression ropes are required to adjust, maintain the tension that should be present, reduce slippage, and compress and release the folded flat satellite configurations that are sequentially stacked.
In some embodiments, the fairing may take on a large or small size, and the invention is not limited thereto, and it is understood that the large and small sizes in this embodiment are relative to the size of the folded flat panel satellite configuration, for example, the large size may be defined as the size that can accommodate the folded flat panel satellite configuration in the unfolded state, and the small size may be defined as the size that can accommodate the folded flat panel satellite configuration in the folded state. It will further be appreciated that the folded flat panel satellite configuration of the present invention may be stacked in a variety of configurations depending on the size of the cowling, as described below.
When small-sized cowlings are used to carry the launch, as shown in fig. 7, the "satellite folded state + stacking" approach can be used to take full advantage of the limited space inside the carrying cowlings.
When a large-size fairing is used for carrying and launching, as shown in fig. 10, a mode of 'satellite unfolding state + stacking' can be adopted, and the satellite is in the unfolding state during launching, so that the first satellite cabin 01 and the second satellite cabin 02 can be designed into a fixed connection mode, and the structural form of the satellite can be further simplified. When the satellite piles up, two satellites are a set of, and upset about its below satellite was done earlier, horizontal rotation again, and horizontal rotation is preferred 180, because separation connecting cylinder position is designed for 180 rotational symmetry, and the high and low complementation of size on two satellites direction of height, consequently the separation connecting cylinder of two satellites from top to bottom just can inlay each other together, becomes a satellite, uses the compressing rope to pass the separation connecting cylinder and fixes. When the satellites adopt the large-size fairing, two rows of satellites can be arranged side by side. The star-arrow separation process is similar to the use of small size fairings.
More specifically, in practical application, two carrier rockets are needed for satellite launching, the inner diameters of the rocket fairings are 1.9 meters and 3.8 meters respectively, and at the moment, one satellite configuration and structure need to be designed to meet launching requirements of the two carrier rockets. As shown in fig. 11, a folding flat satellite configuration and a structure form are adopted, the first satellite cabin and the second satellite cabin are designed to be a square structure with the enveloping size of 1.3m × 1.3m, the height is not limited, and when a carrier rocket with the fairing inner diameter of 1.9 m is used for launching, the satellite is in a folded state; as shown in fig. 12, when a launch vehicle with a fairing internal diameter of 3.8 meters is used for launching, the satellite is in an unfolded state, and each layer can be placed side by side in a configuration of 2 folded flat satellites.
In addition, a communication and measurement and control ground antenna (or other load equipment with ground requirements) is arranged on the outer surface of the ground deck, a sensor and a measurement and control antenna are arranged on the outer surface of the ceiling deck, and various load equipment and platform equipment are arranged on the inner surface of the deck. The equipment is placed in the first satellite cabin or the second satellite cabin without specific requirements, and can be selected according to actual conditions, but for convenience of satellite modularization and mass production, the number of cabin penetrating soft cables (including low-frequency lines and high-frequency lines) between the first satellite cabin and the second satellite cabin is reduced as much as possible, and hard connection between the first satellite cabin equipment and the second satellite cabin equipment, such as cabin penetrating waveguides, is avoided. The flexible cable connection between the first satellite pod and the second satellite pod may be in the following manner: holes are respectively formed in the cabin plates where the two cabin connecting devices are located to serve as flexible wire cable wiring holes between the two cabin bodies, the flexible wire cables penetrate through the wiring holes of the two cabin plates to achieve connection of two cabin devices, the flexible wire cables are protected, and damage to the flexible wire cables when the satellite is folded and unfolded is avoided.
According to the solution, the folding flat satellite structure can meet the launching requirements of various carrier rockets at the same time, and each launching mode can realize 'one rocket with multiple stars' with high numerical value proportion, so that the launching efficiency is improved, and the urgent launching period requirements and cost control requirements are met. The sizes of the first satellite cabin body and the second satellite cabin body in the height direction can be flexibly distributed and flexibly adjusted according to the satellite equipment components, and the two cabin bodies can be assembled in parallel and then simply spliced finally, so that the requirements of modularization and batch production are met. The structure meets various requirements of structural design of other satellites, has the characteristics of large ground and multiple radiating surfaces, is more friendly to the design of satellites taking microwave application such as space-based radar remote sensing and high-capacity satellite communication as main directions, realizes one-rocket multi-satellite emission with high numerical proportion, and ensures the rapid and low-cost deployment of satellite constellations, thereby solving two problems of requirement on satellite emission period and requirement on cost control.
The embodiments in the present specification are described in a progressive manner, and the same and similar parts among the embodiments can be referred to each other, and each embodiment focuses on the differences from the other embodiments. In particular, as for the system embodiment, since it is substantially similar to the method embodiment, the description is simple, and for the relevant points, reference may be made to part of the description of the method embodiment.
In the description of the present specification, reference to the description of the terms "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the embodiments of the present specification. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example.
Furthermore, the various embodiments or examples and features of the various embodiments or examples described in this specification can be combined and combined by those skilled in the art without contradiction. The above description is only an embodiment of the present disclosure, and is not intended to limit the present disclosure. Various modifications and changes may occur to those skilled in the art to which the embodiments of the present disclosure pertain. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the embodiments of the present specification should be included in the scope of the claims of the embodiments of the present specification.
Claims (10)
1. A folded flat panel satellite configuration, comprising:
the foldable flat-plate satellite body comprises a first satellite cabin and a second satellite cabin;
and the connector is used for connecting the first satellite cabin and the second satellite cabin and enabling the angle between the opposite skyways of the first satellite cabin and the second satellite cabin to be adjustable.
2. The folding flat panel satellite configuration of claim 1, wherein the first and second satellite pods have cooperating securing structures configured to at least assist in securing the first and second satellite pods relative to each other when an angle between the skyward surfaces of the first and second satellite pods is below a predetermined angle.
3. A foldable flat panel satellite configuration according to claim 2, characterized in that said fixed structure comprises:
a first disconnect coupling on the first satellite pod and a second disconnect coupling on the second satellite pod; when the angle between the opposite surfaces of the first satellite cabin and the second satellite cabin is lower than a set angle, the first separation connecting cylinder and the second separation connecting cylinder are abutted, and the cylinder bodies of the first separation connecting cylinder and the second separation connecting cylinder are communicated;
the barrel of first separation connecting cylinder with the second separation connecting cylinder can run through the compression rope, and then makes the compression rope is connected fixedly first separation connecting cylinder with the second separation connecting cylinder.
4. A foldable flat panel satellite configuration according to claim 2, characterized in that said fixed structure comprises:
a first disconnect coupling on the first satellite pod and a second disconnect coupling on the second satellite pod; when the angle between the opposite skywards of the first satellite pod and the second satellite pod is lower than a set angle, at least part of the second separation connecting cylinder is inserted into the cylinder body of the first separation connecting cylinder.
5. The folding flat panel satellite configuration of claim 4, wherein the first breakaway connector protrudes from an opposite ground of the first satellite pod, the second breakaway connector extends through an opposite ground of the second satellite pod, and an aperture of an end of the first breakaway connector proximate the opposite ground is smaller than an aperture of an end of the second breakaway connector proximate the opposite ground, such that the first breakaway connector of a previous satellite is inserted into the second breakaway connector of a next satellite when two satellites are stacked.
6. The folding flat panel satellite configuration of claim 4 or 5, wherein each breakaway connector includes a first portion within a satellite pod skyward and skyward confined space and a second portion outside of the confined space, the second portion having a diameter less than a diameter of the first portion.
7. The folding flat panel satellite configuration of claim 6, wherein the first portion of each breakaway connector is secured to an exterior side wall of the corresponding hull or the first portion of each breakaway connector is recessed within the interior of the corresponding hull.
8. A foldable flat panel satellite configuration according to claim 2, characterized in that said fixed structure comprises:
a protrusion on the skyward surface of the first satellite pod and a depression on the skyward surface of the second satellite pod; the protrusion can be inserted into the recess to form the fixing structure in a matching manner.
9. The folding flat panel satellite configuration of claim 7, further comprising:
the two solar wings are laid on the opposite skyways of the first satellite cabin and the second satellite cabin; and
and the connector is connected with the solar wing and the corresponding satellite cabin body and enables the angle between the solar wing and the opposite-to-sky surface of the corresponding satellite cabin body to be adjustable.
10. The folding flat panel satellite configuration of claim 7, wherein each satellite pod has a ground antenna disposed on a ground facing surface; and/or
And a sensor or an antenna is arranged on the opposite-to-sky surface of each satellite cabin.
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| CN202010447697.2A CN111762338A (en) | 2020-05-25 | 2020-05-25 | Folding flat satellite structure |
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| CN202010447697.2A CN111762338A (en) | 2020-05-25 | 2020-05-25 | Folding flat satellite structure |
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| CN112693638A (en) * | 2021-01-07 | 2021-04-23 | 航天行云科技有限公司 | Multi-satellite series stacked structure and fixing and separating control device |
| CN112693627A (en) * | 2021-01-05 | 2021-04-23 | 航天行云科技有限公司 | One-rocket multi-satellite stacked launching method |
| CN112849432A (en) * | 2021-01-25 | 2021-05-28 | 航天科工空间工程发展有限公司 | Folding flat satellite structure |
| CN113232892A (en) * | 2021-04-30 | 2021-08-10 | 中国空间技术研究院 | One-rocket-multi-satellite-launching foldable and expandable modular stacked satellite configuration |
| CN113581493A (en) * | 2021-07-30 | 2021-11-02 | 北京微焓科技有限公司 | Plate-shaped satellite main frame and plate-shaped satellite |
| CN113650807A (en) * | 2021-03-26 | 2021-11-16 | 中国空间技术研究院 | Open satellite configuration suitable for multilayer stacking |
| CN114148546A (en) * | 2021-11-17 | 2022-03-08 | 北京九天微星科技发展有限公司 | Satellite configuration |
| CN114171882A (en) * | 2021-10-11 | 2022-03-11 | 北京理工大学 | One-rocket multi-satellite SAR satellite flat antenna lamination device |
| WO2022146279A1 (en) * | 2020-12-28 | 2022-07-07 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | A satellite system |
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