CN113815901B - Satellite frame and satellite - Google Patents
Satellite frame and satellite Download PDFInfo
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- CN113815901B CN113815901B CN202111208801.3A CN202111208801A CN113815901B CN 113815901 B CN113815901 B CN 113815901B CN 202111208801 A CN202111208801 A CN 202111208801A CN 113815901 B CN113815901 B CN 113815901B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
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Abstract
The invention relates to the technical field of artificial satellites, in particular to a satellite frame and a satellite. The satellite frame, comprising: the box body, the middle plate and the two end plates; openings are formed in two ends of the box body, one end plate is connected to one end of the box body, and the other end plate is connected to the other end of the box body; the middle plate is arranged in the middle of the box body to divide an inner cabin of the box body into a plurality of sub-installation cabins; the shape of the cross section of the box body, the shape of the cross section of the end plate and the shape of the cross section of the middle plate are trapezoidal. The overall shapes of the satellites can be changed by placing the satellites, so that the overall shapes of the satellites can be adjusted according to the shapes of the cross sections of different cowlings, the satellites can adapt to the shapes of the cowlings, the space of the cowlings can be utilized more, and the utilization rate of the cowlings is improved.
Description
Technical Field
The invention relates to the technical field of artificial satellites, in particular to a satellite frame and a satellite.
Background
With the development of commercial satellites, microsatellites under the 100kg level become mainstream products, and the satellites usually participate in launching tasks in a piggyback mode, namely a rocket-multi-satellite launching mode is adopted. The cross section of the general satellite is square or rectangular, so that the space utilization rate of the fairing is low.
Disclosure of Invention
The invention aims to provide a satellite frame and a satellite so as to solve the technical problem of low utilization rate of a fairing due to satellite configuration to a certain extent.
The present invention provides a satellite frame comprising: the box body, the middle plate and the two end plates; openings are formed in two ends of the box body, one end plate is connected to one end of the box body, and the other end plate is connected to the other end of the box body; the middle plate is arranged in the middle of the box body to divide an inner cabin of the box body into a plurality of sub-installation cabins; the shape of the cross section of the box body, the shape of the cross section of the end plate and the shape of the cross section of the middle plate are trapezoidal.
The two end plates are respectively arranged at the openings at the two ends of the box body to cover the opening of the box body, the middle plate is arranged in the box body, and the middle plate can be connected with the inner wall of the box body; a mounting cavity is formed inside the box body, the middle plate divides the mounting cavity into a plurality of sub-mounting cavities, and the sub-mounting cavities can be used for mounting satellite equipment; the shape of the cross section of box, the shape of the cross section of end plate and the shape of the cross section of medium plate are trapezoidal, the shape of the cross section of the satellite frame is trapezoidal also, accomplish the installation back of satellite equipment, the satellite is trapezoidal, when adopting the one-arrow-more-star transmission mode, through the position of putting a plurality of satellites, can change the whole shape of a plurality of satellites, thereby can be according to the shape of the cross section of different cowlings, adjust the whole shape of a plurality of satellites, make a plurality of satellites can adapt to the shape of radome fairing, and then can utilize the space of radome fairing more, improve the utilization ratio to the radome fairing. In addition, the setting of medium plate not only can separate into a plurality of sub-installation chambeies with the installation chamber, can also improve box intensity to improve satellite frame's intensity.
Further, the shape of the cross section of the box body, the shape of the cross section of the end plate and the shape of the cross section of the middle plate are right-angled trapezoids.
Furthermore, the box body comprises a rear side plate, a left side plate, a front side plate and a right side plate which are sequentially connected end to end; the rear side plate and the left side plate are arranged at a right angle, and the left side plate and the front side plate are arranged at a right angle; and a transfer block is arranged between the right side plate and the front side plate and between the right side plate and the rear side plate.
Furthermore, one of the two end plates is a top plate, the other end plate is a bottom plate, the thickness of the top plate is 2.5mm-3.5mm, and the thickness of the bottom plate is 6.5mm-7.5 mm.
Furthermore, criss-cross end plate reinforcing ribs are arranged on the end plate, and the thickness of the end plate reinforcing ribs is 19mm-21 mm.
Further, the thickness of the left side plate, the thickness of the right side plate, the thickness of the front side plate and the thickness of the rear side plate are all 1.5mm-2.5 mm.
Furthermore, the right side plate, the front side plate and the rear side plate are all provided with first reinforcing ribs, and the thickness of each first reinforcing rib is 4-6 mm; and a second reinforcing rib is arranged on the left side plate, and the thickness of the second reinforcing rib is 9-11 mm.
Further, the satellite frame further comprises a body-mounted sailboard and an unfolded sailboard; the body-mounted sailboard is connected with one side plate of the box body, and the unfolding sailboards are arranged on two sides of the body-mounted sailboard in the width direction of the body-mounted sailboard; and the body-mounted sailboard and the unfolding sailboard are both provided with a heat control layer.
The invention provides a satellite, which comprises satellite equipment and the satellite frame, wherein the satellite equipment is arranged on the satellite frame.
Further, a ratio of an overall height of the satellite to a maximum length of a cross-section of the satellite is greater than 2: 1.
It is to be understood that both the foregoing general description and the following detailed description are for purposes of illustration and description and are not necessarily restrictive of the disclosure. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate the subject matter of the disclosure. Together, the description and drawings serve to explain the principles of the disclosure.
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, and it is obvious that the drawings in the following description are 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 structural diagram of a satellite frame according to an embodiment of the present invention;
FIG. 2 is a top view of the satellite frame shown in FIG. 1;
FIG. 3 is an exploded view of the satellite frame shown in FIG. 1;
FIG. 4 is a schematic diagram of a satellite-rocket structure according to an embodiment of the present invention;
fig. 5 is a schematic view of a satellite-rocket structure according to another embodiment of the present invention.
Icon: 01-rear side plate; 02-left side plate; 03-front side plate; 04-right side plate; 05-a top panel; 06-bottom panel; 07-middle plate; 09-a transfer block; 10-end plate reinforcing ribs; 11-a first reinforcing rib; 12-a second reinforcing rib; 13-bulk loading of sailboards; 14-unfolding the windsurfing board; 100-a fairing; 200-satellite.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention.
The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention.
All other embodiments, which can be 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 invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; 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 meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art. Furthermore, the terms "first," "second," "third," and "fourth" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
As shown in fig. 1 to 5, the present invention provides a satellite frame, including: the box body, the middle plate 07 and the two end plates; two ends of the box body are provided with openings, one end plate is connected to one end of the box body, and the other end plate is connected to the other end of the box body; the middle plate 07 is arranged in the middle of the box body to divide an inner cabin of the box body into a plurality of sub-installation cabins; the shape of the cross section of the box, the shape of the cross section of the end plate, and the shape of the cross section of the middle plate 07 are trapezoidal.
In this embodiment, the two end plates are respectively installed at the openings at the two ends of the box body to cover the openings of the box body, the middle plate 07 is installed in the box body, and the middle plate 07 can be connected with the inner wall of the box body; an installation cavity is formed inside the box body, the middle plate 07 divides the installation cavity into a plurality of sub-installation cavities, and the sub-installation cavities can be used for installing satellite equipment; the shape of the cross section of the box body, the shape of the cross section of the end plate and the shape of the cross section of the middle plate 07 are trapezoidal, that is, the shape of the cross section of the satellite frame is trapezoidal, after the installation of the satellite equipment is completed, the satellite 200 is trapezoidal, when a one-arrow-multi-satellite launching mode is adopted, the overall shapes of the satellites 200 can be changed by placing the positions of the satellites 200, so that the overall shapes of the satellites 200 can be adjusted according to the shapes of the cross sections of different fairings 100, the satellites 200 can adapt to the shapes of the fairings 100, the space of the fairings 100 can be utilized more, and the utilization rate of the fairings 100 is improved. In addition, the setting of medium plate 07 not only can separate into a plurality of sub-installation chambeies with the installation chamber, can also improve box intensity to improve satellite frame's intensity.
It will be appreciated that the end plates and the intermediate plate 07 have a shape which matches the shape of the cross-section of the tank.
The number of the middle boards 07 may be one, or may be multiple (e.g., two, three, or four).
Specifically, the box body comprises a rear side plate 01, a left side plate 02, a front side plate 03 and a right side plate 04 which are connected end to end in sequence.
As shown in fig. 1 to 3, on the basis of the above embodiments, further, the satellite frame further includes a body-mounted sailboard 13 and a deployed sailboard 14; the body-mounted sailboard 13 is connected with one side plate of the box body, and the two sides of the body-mounted sailboard 13 are provided with unfolded sailboards 14 in the width direction of the body-mounted sailboard 13; the body mounted sailboards 13 and the deployed sailboards 14 are each provided with a heat control layer (e.g., sprayed with a heat control paint), and specifically, the body mounted sailboards are connected to the rear side panel 01 (e.g., by screwing, etc.), one deployed sailboard is connected to the left side panel 02 (e.g., by screwing, etc.), and the other deployed sailboard is connected to the right side panel 04 (e.g., by screwing, etc.).
The trapezoid can be a common trapezoid or an isosceles trapezoid.
As an alternative, the shape of the cross section of the box, the shape of the cross section of the end plate, and the shape of the cross section of the middle plate 07 are right trapezoids, i.e., the satellite frame is a right trapezoid, and the satellite 200 is a right trapezoid. Specifically, be the right angle setting between posterior lateral plate 01 and the left side board 02, be the right angle setting between left side board 02 and the preceding curb plate 03, posterior lateral plate 01 and preceding curb plate 03 are right trapezoid's end, and left side board 02 and right side board 04 are right trapezoid's waist.
In the implementation, the satellite 200 is a right trapezoid, so that a single satellite can fully utilize the envelope of a quarter circle, and the inclined edge can avoid local projections such as cables, plugs and the like in the fairing 100; when a rocket-two-star launch is used, as shown in fig. 4, the left side plate 02 of one satellite frame and the rear side plate 01 of the other satellite frame are adjacently arranged face to face, so that the two satellites 200 can adapt to a semicircular envelope (that is, the cross section of the fairing 100 is semicircular in shape); as shown in fig. 5, the right side plate 04 of one satellite frame is disposed in face-to-face proximity to the right side plate 04 of the other satellite frame, and the two satellites 200 can accommodate a rectangular envelope (i.e., the cross-section of the fairing 100 is rectangular in shape); of course, when the fairing 100 is circular, two pairs of satellites 200 may be used, with the left side panel 02 of one satellite frame and the rear side panel 01 of the other satellite frame of each pair of satellites 200 being disposed adjacent to one another in a face-to-face relationship. The satellite 200 has greatly enhanced lateral spatial envelope adaptability and makes full use of the interior space of the fairing 100.
Preferably, the width of the rear side plate is equal to that of the left side plate, so that the overall structure of a plurality of satellites is regular, and the space utilization rate of the fairing is improved.
Wherein, the connection can be dismantled in proper order to posterior lateral plate 01, left side board 02, preceding curb plate 03 and right side board 04, for example: by means of a threaded connection. The angle between the right side board 04 and the posterior lateral plate 01 is the acute angle, and the angle between the right side board 04 and the preceding lateral plate 03 is the obtuse angle, can all set up the switching piece 09 between right side board 04 and the preceding lateral plate 03 and between right side board 04 and the posterior lateral plate 01, also realizes the connection of right side board 04 and preceding lateral plate 03 through switching piece 09, realizes the connection of right side board 04 and posterior lateral plate 01 through switching piece 09, makes things convenient for satellite frame's assembly.
Specifically, the switching block 09 between the right side plate 04 and the front side plate 03 is a right front switching block, a first connecting hole is formed in a first side wall of the right front switching block, a second connecting hole is formed in a second side wall of the right front switching block, which is adjacent to the first side wall, the first connecting hole of the right side plate 04 and the first connecting hole of the right front switching block are fixedly connected by a first fastener (such as a screw or a bolt), and the second connecting hole of the right side plate 04 and the second connecting hole of the right front switching block are fixedly connected by a second fastener; the transfer block 09 between the right side plate 04 and the front side plate 03 is a right rear transfer block, a first side wall of the right rear transfer block is provided with a third connecting hole, a second side wall of the right rear transfer block, which is adjacent to the first side wall, is provided with a fourth connecting hole, the third connecting hole of the right side plate 04 and the third connecting hole of the right rear transfer block are fixedly connected by a third fastener (for example, a screw or a bolt), and the fourth connecting hole of the right side plate 04 and the fourth connecting hole of the right rear transfer block are fixedly connected by a fourth fastener.
The thickness of the left side plate 02, the thickness of the right side plate 04, the thickness of the front side plate 03 and the thickness of the rear side plate 01 are all 1.5mm-2.5mm (for example, 1.5mm, 1.6mm, 1.7mm, 1.8mm, 2.0mm, 2.1mm, 2.2mm, 2.3mm or 2.5 mm), and the rear side plate 01, the left side plate 02, the front side plate 03 and the right side plate 04 may be made of aluminum alloy, but other materials may be used.
On the basis of the above embodiments, further, the right side plate 04, the front side plate 03 and the rear side plate 01 are all provided with the first reinforcing ribs 11, the thickness of the first reinforcing ribs 11 is 4mm to 6mm (for example, 4mm, 4.3mm, 4.5mm, 4.8mm, 5mm, 5.3mm, 5.6mm, 5.8mm or 6mm, etc.), the number of the first reinforcing ribs 11 can be multiple, the length direction of the first reinforcing ribs 11 can be set as required, the transverse first reinforcing ribs 11 and the longitudinal first reinforcing ribs 11 can be provided, the first reinforcing ribs 11 in a shape of Chinese character 'kou' can also be provided, etc., so as to improve the strength of the right side plate 04, the front side plate 03 and the rear side plate 01; the right side plate 04 is provided with a second reinforcing rib 12, the thickness of the second reinforcing rib 12 is 9mm-11mm (for example, 9mm, 9.3mm, 9.5mm, 9.8mm, 10mm, 10.3mm, 10.6mm, 10.8mm or 11mm and the like), the number of the second reinforcing ribs 12 can be multiple, the length direction of the second reinforcing ribs 12 can be set as required, the transverse second reinforcing ribs 12 and the longitudinal second reinforcing ribs 12 can be arranged, the square-shaped second reinforcing ribs 12 and the like can also be arranged, the left side plate 02 can provide an installation interface for sub-equipment in the cabin, and thermal control paint can be sprayed on the outer wall of the left side plate 02 to dissipate heat of the whole star.
In addition to the above embodiments, one of the two end plates is a top plate 05, the other is a bottom plate 06, the thickness of the top plate 05 is 2.5mm-3.5mm (for example: 2.5mm, 2.7mm, 2.8mm, 3.0mm, 3.3mm, or 3.5mm, etc.), the top plate 05 can be made of aluminum alloy, or of other materials, and the top plate 05 can be provided with an installation interface for installing onboard equipment; the thickness of the bottom panel 06 is 6.5mm-7.5mm (6.5mm, 6.4mm, 6.5mm, 6.7mm, 7.0mm, 7.2mm or 7.5mm, etc.), and an installation interface for installing partial onboard equipment and an installation interface for installing a satellite and rocket separation mechanism can be arranged on the bottom panel 06.
In addition to the above embodiments, the end plate is further provided with criss-cross end plate ribs 10, the thickness of the end plate ribs 10 is 19mm to 21mm (for example, 19mm, 19.5mm, 19.8mm, 20mm, 20.4mm, 20.6mm, 20.8mm, or 21 mm), and the end plate ribs 10 can improve the strength of the end plate.
The invention provides a satellite 200 which comprises satellite equipment and a satellite frame of any technical scheme, wherein the satellite equipment is arranged on the satellite frame, part of the satellite equipment can be arranged in a box body, and part of the satellite equipment is arranged outside an end plate. The satellite 200 provided in this embodiment includes the satellite frame according to any of the above technical solutions, and therefore, has all the beneficial technical effects of the satellite frame, and details are not described herein.
On the basis of the above embodiment, further, the ratio of the overall height of the satellite 200 to the maximum length of the cross section of the satellite 200 is greater than 2:1 (for example, 2:1, 3:1, or 4: 1), and in this embodiment, the ratio can ensure that the satellite 200 uses the internal space envelope of the fairing 100 as much as possible on the premise of meeting the requirements of the mechanical environment, which is beneficial to improving the adaptability of the satellite 200 to carry and transmit. For example: the maximum cross-sectional length of the satellite 200 is 400mm and the height is up to 1000 mm.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention. In the description provided herein, numerous specific details are set forth. It is understood, however, that embodiments of the invention may be practiced without these specific details. In some instances, well-known methods, structures and techniques have not been shown in detail in order not to obscure an understanding of this description. Furthermore, those skilled in the art will appreciate that while some embodiments herein include some features included in other embodiments, rather than other features, combinations of features of different embodiments are meant to be within the scope of the invention and form different embodiments.
Claims (9)
1. A satellite frame, comprising: the box body, the middle plate and the two end plates; openings are formed in two ends of the box body, one end plate is connected to one end of the box body, and the other end plate is connected to the other end of the box body; the middle plate is arranged in the middle of the box body to divide an inner cabin of the box body into a plurality of sub-installation cabins; the shape of the cross section of the box body, the shape of the cross section of the end plate and the shape of the cross section of the middle plate are trapezoidal; the shape of the cross section of the box body, the shape of the cross section of the end plate and the shape of the cross section of the middle plate are right trapezoid, and the box body comprises a rear side plate, a left side plate, a front side plate and a right side plate which are sequentially connected end to end; the rear side plate and the left side plate are arranged at a right angle, and the left side plate and the front side plate are arranged at a right angle;
when the rocket double-star launching is adopted, the left side plate of one satellite frame and the rear side plate of the other satellite frame are adjacently arranged face to adapt to semicircular envelope, or the right side plate of one satellite frame and the right side plate of the other satellite frame are adjacently arranged face to adapt to rectangular envelope;
when the fairing is circular, two pairs of satellites are used, the left side plate of one satellite frame and the rear side plate of the other satellite frame in each pair of satellites are adjacently arranged face to face.
2. The satellite frame as claimed in claim 1, wherein a transfer block is provided between the right side plate and the front side plate and between the right side plate and the rear side plate.
3. The satellite frame according to claim 1, wherein one of said end plates is a top plate and the other is a bottom plate, said top plate having a thickness of 2.5mm to 3.5mm and said bottom plate having a thickness of 6.5mm to 7.5 mm.
4. The satellite frame according to claim 3, wherein the end plates are provided with criss-cross end plate ribs having a thickness of 19mm to 21 mm.
5. The satellite frame of claim 2, wherein the thickness of the left side plate, the right side plate, the front side plate, and the rear side plate are each 1.5mm to 2.5mm thick.
6. The satellite frame according to claim 5, wherein the right side plate, the front side plate and the rear side plate are provided with first reinforcing ribs, and the thickness of the first reinforcing ribs is 4mm to 6 mm; and a second reinforcing rib is arranged on the left side plate, and the thickness of the second reinforcing rib is 9-11 mm.
7. The satellite frame according to any one of claims 1-6, further comprising a body mounted windsurfing board and a deployment windsurfing board; the body-mounted sailboard is connected with one side plate of the box body, and the unfolding sailboards are arranged on two sides of the body-mounted sailboard in the width direction of the body-mounted sailboard; and the body-mounted sailboard and the unfolding sailboard are both provided with a heat control layer.
8. A satellite comprising satellite equipment and a satellite frame according to any one of claims 1 to 7, the satellite equipment being mounted on the satellite frame.
9. The satellite of claim 8, wherein a ratio of an overall height of the satellite to a maximum length of a cross-section of the satellite is greater than 2: 1.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111208801.3A CN113815901B (en) | 2021-10-18 | 2021-10-18 | Satellite frame and satellite |
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| CN202111208801.3A CN113815901B (en) | 2021-10-18 | 2021-10-18 | Satellite frame and satellite |
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| CN113815901B true CN113815901B (en) | 2022-04-26 |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043741A (en) * | 2016-08-05 | 2016-10-26 | 深圳航天东方红海特卫星有限公司 | Satellite configuration design method adapting to one-rocket multi-satellite launching |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6776372B2 (en) * | 2002-09-26 | 2004-08-17 | The Boeing Company | Method of operating a satellite for end-of-life maneuvers |
| CN104443431B (en) * | 2014-10-23 | 2017-08-29 | 上海卫星工程研究所 | Triangle satellite configuration |
| CN105857640B (en) * | 2016-04-08 | 2018-10-16 | 上海微小卫星工程中心 | A kind of connection cornual plate and satellite for satellite modules |
| CN109080857B (en) * | 2018-07-27 | 2020-07-14 | 北京控制工程研究所 | Leg buffer mechanism for lunar flying robot |
| CN109229422A (en) * | 2018-11-14 | 2019-01-18 | 长光卫星技术有限公司 | A kind of deck board formula satellite configuration and its assembly method |
| CN109850186B (en) * | 2019-02-28 | 2021-02-09 | 中国空间技术研究院 | Plate frame type satellite structure for one-rocket multi-satellite parallel transmission and assembly method |
| CN110356592B (en) * | 2019-06-28 | 2021-06-11 | 中国空间技术研究院 | Full-electric-propulsion satellite platform configuration based on one-arrow two-satellite self-series-connection launching mode |
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Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043741A (en) * | 2016-08-05 | 2016-10-26 | 深圳航天东方红海特卫星有限公司 | Satellite configuration design method adapting to one-rocket multi-satellite launching |
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