CN115246494A - Satellite layout scheme and adapter structure for multi-satellite transmission - Google Patents
Satellite layout scheme and adapter structure for multi-satellite transmission Download PDFInfo
- Publication number
- CN115246494A CN115246494A CN202110488666.6A CN202110488666A CN115246494A CN 115246494 A CN115246494 A CN 115246494A CN 202110488666 A CN202110488666 A CN 202110488666A CN 115246494 A CN115246494 A CN 115246494A
- Authority
- CN
- China
- Prior art keywords
- satellite
- mounting plate
- adapter
- satellites
- mounting
- 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
Links
- 230000005540 biological transmission Effects 0.000 title claims description 20
- 238000000926 separation method Methods 0.000 claims abstract description 19
- 238000000034 method Methods 0.000 claims abstract description 16
- 230000002452 interceptive effect Effects 0.000 claims description 4
- 238000009434 installation Methods 0.000 abstract description 10
- 230000003014 reinforcing effect Effects 0.000 description 6
- 230000009471 action Effects 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 101100110009 Caenorhabditis elegans asd-2 gene Proteins 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 108091092878 Microsatellite Proteins 0.000 description 1
- 239000000969 carrier Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
Images
Classifications
-
- 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
Landscapes
- 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 discloses a multi-satellite launching satellite layout scheme and an adapter, relates to the technical field of space flight and aviation, and particularly relates to a multi-satellite launching satellite layout scheme. The scheme of the invention carries out separation by arranging the non-interference launching directions in the separation stage by installing a plurality of satellites on the adapter in a layered mode. The method obviously improves the satellite release efficiency and the safety. Meanwhile, the scheme also provides an adapter structure to realize multilayer installation and separation of satellites, so that the carrying quantity of the satellites is increased, and the requirements of various satellite launching tasks can be met. Compared with the related art, the technical scheme provided by the invention obviously improves the satellite release efficiency and safety.
Description
Technical Field
The invention relates to the technical field of space flight and aviation, in particular to a satellite layout scheme for multi-satellite transmission and an adapter structure.
Background
In recent years, with the rapid development of microsatellites and the increasing popularization of large-scale constellation projects, the number of small satellites to be transmitted and the occupation ratio of the small satellites to be transmitted are remarkably increased, so that resources are saved. The one-rocket multi-satellite launching not only improves the launching efficiency of the carrier rocket, but also meets the requirement of a small satellite for mass launching. So one-rocket-multi-satellite transmission is becoming a common means for satellite transmission.
As the number of satellites to be launched is increased, there is a need for efficiency of satellite launching. In the satellite adapter and the launching scheme in the prior art, satellites are launched one by one, so that the efficiency is low. A new problem arises when simultaneous transmission is desired: the launching direction of the launched satellite is required by the installation position of the adapter and the orbit of the satellite target, and the satellites have collision safety risks.
Therefore, it is an urgent problem for practitioners to separate satellites efficiently and ensure the safety of satellite separation.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a multi-satellite launching satellite layout scheme and an adapter, and solves the problem of improving the separation efficiency and safety simultaneously in multi-satellite launching.
In order to achieve the above purposes, the technical scheme adopted by the invention is as follows:
satellites arranged in layers on the adapter are separated by configuring the non-interfering transmitting direction.
In some embodiments, satellites disposed on both the top and bottom of the satellite mounting plate of the adapter are separated in a direction perpendicular to the satellite mounting plate and in a direction parallel to the satellite mounting plate.
In some embodiments, a satellite mounting box for mounting the main task star is arranged on the satellite mounting plate, and the main task star is separated along the direction vertical to the satellite mounting plate;
separating the carrying star on the satellite mounting plate along the direction parallel to the satellite mounting plate;
the carrying star under the satellite mounting plate is separated along the direction parallel to the satellite mounting plate.
In some embodiments, two piggy-backs are disposed both above and below the satellite mounting plate, four of which are separated in different orthogonal directions in a direction parallel to the satellite mounting plate.
In some embodiments, the height of the satellite mounting box is configured to be higher than the carrier star on the upper surface of the satellite mounting plate, and the carrier star on the upper surface of the satellite mounting plate is arranged at a distance from the satellite mounting box.
In some embodiments, the adapter includes at least two connected satellite mounting plates, the satellites arranged on the upper and lower surfaces of the uppermost satellite mounting plate are separated in a direction perpendicular to the satellite mounting plate and in a direction parallel to the satellite mounting plate, and the satellites arranged on the upper and lower surfaces of the remaining satellite mounting plates are separated in a direction parallel to the satellite mounting plate.
In some embodiments, there is provided an adapter comprising:
and the upper surface and the lower surface of the at least one satellite mounting plate are respectively provided with a satellite emitter for separating satellites according to mutually non-interfering emission directions.
In some embodiments, satellite launchers on the upper and lower surfaces of the satellite mounting plate are used to separate satellites in a direction perpendicular to the satellite mounting plate and in a direction parallel to the satellite mounting plate.
In some embodiments, the number of the satellite mounting plates is one, and the upper surface of the satellite mounting plate is provided with two satellite mounting boxes and two satellite emitters for enabling satellites to be relatively separated on a horizontal plane parallel to the mounting plates; the lower surface of the satellite mounting plate is provided with two satellite launchers for relatively separating satellites in a horizontal plane parallel to the mounting plate.
In some embodiments, the satellite mounting plate is two connected pieces;
the upper surface of the satellite mounting plate above is provided with four satellite emitters;
the upper surface and the lower surface of the satellite mounting plate below are respectively provided with four satellite emitters.
Compared with the prior art, the satellite layout scheme provided by the invention improves the carrying capacity of the satellite and improves the efficiency and safety of satellite release and separation by changing the installation mode and the separation direction of the satellite. Similarly, the technical scheme of the invention provides an adapter structure matched with the component layout scheme, the adapter structure can be simply modified according to the requirement of a satellite launching task, and the adapter structure has strong applicability.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the description below are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 is a schematic view of a satellite layout standard view of six-star transmission.
Fig. 2 is a bottom view of a satellite layout for a six-star launch.
Fig. 3 is a schematic diagram of a six-star separation process.
Fig. 4 is a schematic view of a satellite layout standard view of twelve-star transmission.
The main mission star 1, the main mission star 2, the carrier star 3, the carrier star 4, the carrier star 5, the carrier star 6, the satellite mounting box 7, the satellite mounting box 8, the satellite mounting plate 9, the reinforcing ribs 10, and the bottom plate 11.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
Embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.
The embodiment of the application provides a satellite layout scheme for multi-satellite transmission, which can improve the satellite release efficiency and safety and improve the adaptability to different satellite transmission tasks.
The embodiment of the application provides a satellite layout scheme for multi-satellite transmission, which comprises the following steps:
after the satellite launching task is obtained, the number of satellites and the scale of each satellite are firstly confirmed, and in order to increase the number of satellites carried by each launching, a plurality of satellites are installed on the adapter in a layered mode. Meanwhile, the layered installation also provides convenience for the subsequent multi-satellite release process. In the installation stage, the installation position of the satellite is determined according to the integral mass center of the satellite and the adapter, and the mass center of the satellite is positioned on the integral geometric center of the satellite. This is done to balance the reactive force applied to the adapter after the satellite is released, which causes the adapter to be affected by excessive external force and the direction of travel of the adapter to be uncontrolled after the satellite is launched. And finally, the satellite is transmitted in a direction which does not interfere with each other.
In some embodiments, the technical solution of the present application can also be applied to a plurality of satellite launching tasks of equivalent size.
In some embodiments, a plurality of satellites are launched in a direction parallel to the mounting plate and perpendicular to the mounting plate.
Preferably, the plurality of satellites, when separated, are separated towards different orthogonal transmission directions.
Referring to fig. 1 and 2, in one embodiment provided by the present application, the mission satellites are two large-scale main mission satellites (1, 2) and four small-scale piggy-backs satellites (3, 4, 5, 6). Two satellite mounting boxes (7, 8) are mounted on the upper surface of a first satellite mounting plate 9, and a main task star 1 and a main task star 2 are respectively mounted on the satellite mounting boxes 7 and 8 to form a first layer; the carrying star 3 and the carrying star 4 are arranged on the upper surface of the first satellite mounting plate 9 to form a second layer; the carrying star 5 and the carrying star 6 are mounted on the lower surface of the first satellite mounting plate 9, forming a third layer. Thus, the six-satellite launching task is arranged on the adapter structure in three layers. The four carrying stars are connected to the upper and lower surfaces of the satellite mounting plate 9 through satellite transmitters. The two satellite mounting boxes (7, 8) launch two main mission satellites vertically upwards on a vertical plane perpendicular to the satellite mounting plate 9. And two carrying stars (3, 4) positioned on the upper surface of the satellite mounting plate 9 leave the adapter in the north and south directions on the horizontal plane respectively under the action of the satellite transmitter. Two carrying stars (5, 6) located on the lower surface of the satellite mounting plate 9 leave the adapter towards the east and west respectively on the horizontal plane under the action of the satellite launcher. Of course, the transmitting directions of the satellites only need to be directions that do not interfere with each other, and the goal is not limited to the directions mentioned above.
Preferably, the satellites leave the adapter in different orthogonal directions.
Further, in order to meet the requirement of the launching task on the satellite orbit, the application takes the six-satellite launching task as an example to provide two satellite launching schemes:
emission scheme 1: sending a first separation instruction, and separating the main task satellite 1 and the main task satellite 2 along the vertical upward direction; after the main task star is separated by a certain safety distance, a second separation instruction is sent, and the carrying star 3, the carrying star 4, the carrying star 5 and the carrying star 6 are separated along four different orthogonal directions respectively.
Transmission scheme 2: after the separation instruction is sent out, the main task satellite 1 and the main task satellite 2 are separated along the vertical upward direction at the same time, the carrying satellite 3, the carrying satellite 4, the carrying satellite 5 and the carrying satellite 6 are separated along four different orthogonal directions respectively, and six satellites leave the adapter at the same time.
Therefore, the satellite layout scheme can freely adjust the time for separating the satellites so as to meet the requirements of different orbit tasks. Wherein the main task star separates in advance to pull open certain safe distance and can ensure that main task star can not bump with other carriers in the separation process, further improve the security. The distance is determined according to the size of the satellite, and collision is avoided.
In summary, in the satellite layout scheme of multi-satellite transmission, multi-layer installation is adopted during satellite installation, and satellites are separated along the non-interfering direction in the satellite separation stage. Therefore, the satellites can emit a plurality of satellites at the same time, the satellite release efficiency is greatly improved compared with the prior art, and meanwhile, the probability of collision of the satellites after the satellites are released is reduced by installing the satellites in such a way, and the safety is improved. The satellites are installed on the adapter in multiple layers, so that the number of portable satellites is increased, the applicability is improved, and convenience is brought to planning of the satellite separation direction in the subsequent separation stage. The satellite makes its whole barycenter be located its geometry at the installation stage, has improved the adapter and has received the influence of satellite reaction force, has further improved the security. In the separation stage, multiple particles can be selectively separated simultaneously or in batches, so that the satellite release is more accurate and effective.
The present application further provides an adapter structure capable of implementing the satellite layout scheme according to the embodiment of the present application, including: the satellite separation device comprises at least one satellite mounting plate, wherein satellite emitters for satellite separation are arranged on the upper surface and the lower surface of the satellite mounting plate; and a bottom plate 11 connected to the lower surface of the lowermost satellite mounting plate by reinforcing ribs 10.
The satellite launcher can be used for installing and launching satellites with smaller scales, and a satellite installing box can be additionally arranged on the upper surface of the satellite installing plate on the uppermost layer of the adapter in order to deal with the satellites with larger scales. Satellite transmitters may be used to separate satellites in transmission directions that do not interfere with each other. The adapter with the satellite mounting box has the following cautions during satellite mounting: the height of the satellite mounting box mounted on the upper surface of the satellite mounting plate is greater than that of other satellites mounted on the upper surface of the satellite mounting plate on the uppermost layer; gaps need to be reserved between the satellite mounting box and other satellites carried on the upper surface of the satellite mounting plate on the uppermost layer.
The present application further provides a specific embodiment of an adapter:
the satellite mounting plate 9 is provided with two mounting boxes on the upper surface of the satellite mounting plate 9, the mounting boxes are arranged for mounting and transmitting a main task satellite with large scale, and the main task satellite can be transmitted in a direction perpendicular to the first satellite mounting plate; the lower surface of the satellite mounting plate 9 is connected with a bottom plate 11 through a reinforcing rib 10; the upper and lower surfaces of the first satellite mounting plate are each provided with two satellite launchers which can launch satellites in a direction parallel to the first satellite mounting plate 9.
Preferably, in the adapter structure, the mounting plate and the bottom plate can be arranged in a central symmetrical shape, so that the centroid and the geometric center can be more conveniently determined in the satellite mounting process. Also, the adapter structure maintains a center point in the plane, and is an improvement for this purpose.
Preferably, the bottom plate 11 is circular, and the first satellite mounting plate 9 has a cross shape with a central symmetry. The bottom plate 11 is connected with the lower surface of the first satellite mounting plate 9 through a plurality of reinforcing ribs 10, the satellite mounting plate 9 and the fixing plate 11 have the same center on the plane, and the lower surface of the first satellite mounting plate 9, the bottom plate 11 and the reinforcing ribs 10 enclose two launching cavities. Of course, the shape of the adapter part described above may be varied reasonably according to the requirements of the launch task and is not limited to the embodiments described.
And when only need launch the less satellite of scale, can need not install the satellite mounting box on the adapter, this application embodiment provides another kind of concrete adapter structure to this kind of condition:
referring to fig. 4, the adapter structure comprises two centrosymmetric satellite mounting plates (9, 12), and a base plate 10. The lower surface of the lower satellite mounting plate 9 is connected with the bottom plate 11 through the reinforcing ribs 10, and the upper surface of the lower satellite mounting plate 9 is connected with the lower surface of the upper satellite mounting plate 9.
The adapter can be used for carrying 10 to 12 satellites with relatively small scale. When 12 satellites are loaded, 4 satellites are installed on each floor. Four satellites are arranged on the upper surface of the second satellite mounting plate 12, and 4 satellites are respectively arranged on the upper surface and the lower surface of the first satellite mounting plate 9. Also, each satellite mounting location on the satellite mounting plate is configured with a satellite launcher that allows satellites to be launched in a manner parallel and perpendicular to the satellite mounting plate.
Preferably, the satellite transmitters of each layer in the adapter structure transmit satellites in different orthogonal directions that do not interfere with each other.
Preferably, the satellite mounting plate 9 can be continuously added to the existing uppermost satellite mounting plate 9. Thereby facing more satellite launching tasks,
In summary, the adapter structure can deal with the launching tasks under different conditions by adjusting the number and the positions of the satellite mounting boxes on the adapter structure. Simple modification can be made to meet the launching requirement of one rocket with multiple stars. The adapter structure of the invention can divide the satellite into a plurality of layers for installation, and the satellites or the launching devices in the same plane are provided with proper intervals, so that the safety of satellite release is further improved. Meanwhile, the satellites in the adapter structure are arranged in a multi-layer open mode, the constraint of the satellite transmitter on the selection of the transmitting direction by the adapter structure is small, the directions which do not interfere with each other can be selected, and therefore the risk of mutual collision after the satellites are transmitted is reduced.
In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are only for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present application. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
It is noted that, in the present application, relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrases "comprising one of 8230; \8230;" 8230; "does not exclude the presence of additional like elements in a process, method, article, or apparatus that comprises the element.
The above description is merely exemplary of the present application and is presented to enable those skilled in the art to understand and practice the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A method for satellite multi-satellite transmission, the method comprising the steps of:
satellites arranged in layers on the adapter are separated by configuring the transmission directions without interference.
2. The method for satellite multi-satellite launching according to claim 1, wherein the separating satellites arranged in layers on an adapter by configuring the launching directions without interference comprises:
satellites arranged on the upper and lower surfaces of a satellite mounting plate of the adapter are separated in a direction perpendicular to the satellite mounting plate and in a direction parallel to the satellite mounting plate (9).
3. Method for satellite multi-satellite launching according to claim 2, characterised in that said separation of the satellites arranged on the upper and lower faces of the satellite plate of the adapter according to a direction perpendicular to the satellite plate and a direction parallel to the satellite plate (9) comprises:
arranging a mounting box for mounting a main task star on the upper surface of the satellite mounting plate (9), and separating the main task star along the direction vertical to the satellite mounting plate (9);
separating the carrying star on the satellite mounting plate (9) along the direction parallel to the satellite mounting plate (9);
the carrying star under the satellite mounting plate (9) is separated along the direction parallel to the satellite mounting plate (9).
4. A method of satellite multi-satellite transmission according to claim 3, characterized in that: two carrying stars, four, are arranged on the upper surface and the lower surface of the satellite mounting plate (9) and are separated along different orthogonal directions in the direction parallel to the satellite mounting plate (9).
5. A method of satellite multi-satellite transmission as claimed in claim 3, wherein: the height of the mounting box is configured to be higher than the carrying star on the upper surface of the satellite mounting plate (9), and the carrying star on the upper surface of the satellite mounting plate (9) is arranged at a distance from the mounting box.
6. The method of satellite multi-satellite transmission of claim 1, wherein:
the adapter includes two piece at least continuous satellite mounting panels (9), separates the satellite of arranging on satellite mounting panel (9) upper surface and the lower surface of the top according to the direction of perpendicular to satellite mounting panel (9) and the direction that is on a parallel with satellite mounting panel (9), separates the satellite of arranging on the upper and lower surface two sides of all the other satellite mounting panels (9) according to the direction that is on a parallel with satellite mounting panel (9).
7. An adapter, comprising:
at least one satellite mounting plate (9), the upper surface and the lower surface of which are provided with satellite emitters for separating satellites according to the non-interfering emission directions.
8. The adapter of claim 7, wherein: the satellite launcher on the upper surface and the lower surface of the satellite mounting plate (9) is used for separating the satellite according to the direction vertical to the satellite mounting plate (9) and the direction parallel to the satellite mounting plate (9).
9. The adapter of claim 7, wherein:
the number of the satellite mounting plates (9) is one, and the upper surface of each satellite mounting plate (9) is provided with two satellite mounting boxes (7 and 8) and two satellite emitters for enabling the carrying satellites (3 and 4) to be relatively separated on a horizontal plane parallel to the mounting plates;
the lower surface of the satellite mounting plate (9) is provided with two satellite emitters which are used for enabling the carrying stars (5 and 6) to be relatively separated on a horizontal plane parallel to the mounting plate.
10. The adapter of claim 7, wherein:
the satellite mounting plates (9) are two connected blocks;
the upper surface of the satellite mounting plate (9) above is provided with four satellite emitters;
the upper surface and the lower surface of the satellite mounting plate (9) below are respectively provided with four satellite emitters.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110488666.6A CN115246494A (en) | 2021-04-27 | 2021-04-27 | Satellite layout scheme and adapter structure for multi-satellite transmission |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110488666.6A CN115246494A (en) | 2021-04-27 | 2021-04-27 | Satellite layout scheme and adapter structure for multi-satellite transmission |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115246494A true CN115246494A (en) | 2022-10-28 |
Family
ID=83696964
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110488666.6A Pending CN115246494A (en) | 2021-04-27 | 2021-04-27 | Satellite layout scheme and adapter structure for multi-satellite transmission |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115246494A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005075209A (en) * | 2003-09-02 | 2005-03-24 | Kawasaki Heavy Ind Ltd | Satellite separation structure and rocket |
| US20140131521A1 (en) * | 2012-05-07 | 2014-05-15 | The Johns Hopkins University | Adaptor System for Deploying Small Satellites |
| US20200299004A1 (en) * | 2017-12-01 | 2020-09-24 | D-ORBIT S.p.A. | Method of releasing artificial satellites in earth's orbit |
| CN212300133U (en) * | 2020-11-04 | 2021-01-05 | 中国长征火箭有限公司 | Satellite support, last stage structure and carrier rocket of carrier rocket |
-
2021
- 2021-04-27 CN CN202110488666.6A patent/CN115246494A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005075209A (en) * | 2003-09-02 | 2005-03-24 | Kawasaki Heavy Ind Ltd | Satellite separation structure and rocket |
| US20140131521A1 (en) * | 2012-05-07 | 2014-05-15 | The Johns Hopkins University | Adaptor System for Deploying Small Satellites |
| US20200299004A1 (en) * | 2017-12-01 | 2020-09-24 | D-ORBIT S.p.A. | Method of releasing artificial satellites in earth's orbit |
| CN212300133U (en) * | 2020-11-04 | 2021-01-05 | 中国长征火箭有限公司 | Satellite support, last stage structure and carrier rocket of carrier rocket |
Non-Patent Citations (1)
| Title |
|---|
| 吴胜宝;胡冬生;: "国外"一箭多星"发射现状及关键技术分析", 国际太空, no. 10, 25 October 2015 (2015-10-25), pages 18 - 22 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR102422173B1 (en) | Modular architecture optimized for making microsatellites | |
| US11827384B2 (en) | Efficient satellite structure concept for single or stacking multiple launches | |
| US10181894B2 (en) | Process and apparatus for communicating with user antenna phased arrays | |
| CN107532923A (en) | System and method for assembling and disposing satellite | |
| US9730339B2 (en) | Common bus structure for avionics and satellites (CBSAS) | |
| CN105775164A (en) | Multiple space vehicle launch system | |
| CN103847982A (en) | Methods and apparatus for performing propulsion operations using electric propulsion systems | |
| CN115246494A (en) | Satellite layout scheme and adapter structure for multi-satellite transmission | |
| CN102717901B (en) | Separation type many device combinations Mars probes structure and forming method thereof | |
| WO2023149132A1 (en) | Launch method, launch device, acceleration method, mass driver, and transport system | |
| CN116151590B (en) | Modularized unmanned aerial vehicle airport planning method for urban air traffic | |
| EP3717356B1 (en) | Method of releasing artificial satellites in earth's orbit | |
| Khartov et al. | Conceptual design of “Exomars-2018” descent module developed by federal enterprise “Lavochkin Association” | |
| CN114008938A (en) | High-altitude platform fleet comprising antennas and positioning method thereof | |
| CN110411276A (en) | A kind of carrier rocket emission system based on magnetic suspension electromagnetic booster | |
| RU2581274C2 (en) | Modular spacecraft | |
| King-Hele et al. | Table of the earth satellites launched in 1965 | |
| Bérend et al. | ALTAIR-An innovative air-launch system for small satellites | |
| RU2208296C2 (en) | Cluster telecommunication system | |
| CN116873221A (en) | Satellite batch transmitting system and method based on stacking mode | |
| CN113955151A (en) | Stacked satellite assembly | |
| Bouhia et al. | Implementation of a large multi-beam mission on Eurostar E3000 | |
| Tewell et al. | Shuttle Derived Space Transportation The Next Step Beyond STS | |
| MAGNUSON | Skepticism, inter-service rivalry surrounds joint heavy lift aircraft program | |
| RU2001103260A (en) | CLUSTER TELECOMMUNICATION SYSTEM |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |