CN112046786B - Satellite and rocket separation structure for launching offshore satellite - Google Patents
Satellite and rocket separation structure for launching offshore satellite Download PDFInfo
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- CN112046786B CN112046786B CN202011033971.8A CN202011033971A CN112046786B CN 112046786 B CN112046786 B CN 112046786B CN 202011033971 A CN202011033971 A CN 202011033971A CN 112046786 B CN112046786 B CN 112046786B
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- 238000000926 separation method Methods 0.000 title claims abstract description 20
- 230000009471 action Effects 0.000 abstract description 3
- 230000004048 modification Effects 0.000 abstract description 2
- 238000012986 modification Methods 0.000 abstract description 2
- 238000004064 recycling Methods 0.000 abstract description 2
- 230000006872 improvement Effects 0.000 abstract 1
- 230000009467 reduction Effects 0.000 abstract 1
- 238000004880 explosion Methods 0.000 description 7
- 238000009434 installation Methods 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 3
- 230000009466 transformation Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
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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
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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Abstract
The invention discloses a satellite and arrow separation structure for launching an offshore satellite, which comprises a launcher body and a satellite body, wherein a fixed ring is arranged on the upper side of the launcher body, an arc-shaped groove is formed in the upper side of the fixed ring, a spring groove is formed in the upper side of the launcher body, a first spring is connected to the bottom of the spring groove, an arc-shaped bulge is formed in the lower part of the satellite body, a sliding piece is arranged on the outer ring side of the fixed ring in a sliding manner, an annular pipe is arranged on the outer side of the fixed ring, an arc-shaped sliding body is arranged in the annular pipe in a sliding manner, the sliding body is fixedly connected with the sliding piece through a connecting block, a baffle is fixedly arranged in the annular pipe, a second spring is connected between the baffle and the sliding body, an electric telescopic rod is fixedly arranged on the outer side of the annular pipe, and a limiting groove is formed in the outer side of the sliding body; the invention has compact structure, small space occupation, small modification on the satellite structure, stable connection structure, convenient operation, small action in the separation process, safety and reliability, recycling, effective improvement on the satellite emission efficiency and reduction on the emission cost.
Description
Technical Field
The invention belongs to the technical field of spacecraft launching equipment, in particular relates to a separating structure of a satellite and a rocket, and particularly relates to a satellite-rocket separating structure for launching an offshore satellite.
Background
At present, the mechanical interface between the satellite and the rocket has two connection modes of explosion bolt connection type or belting connection type. The separation mechanism of the explosion bolt connection type consists of a separation spring and an explosion bolt, and after the explosion bolt is unlocked, the satellite and the distributor are separated under the pushing of the separation spring. However, the explosion bolt and the separation spring of the separation mechanism are separately designed and installed on a satellite, have huge volume and complex installation, and cannot meet the requirement of quick installation. The strap connection type separating mechanism consists of elements such as straps, pollution-free explosion bolts, V-shaped clamping blocks and the like, is complex to install, occupies large space on the butting face of a satellite and an arrow, requires applying pretightening force to each strap at the same time when the strap locking device is installed, and uses a special strain gauge to measure the pretightening force, so that the installation process is complex and time-consuming. And the existing tape connecting type separating mechanism has larger specification of shaped products and can not meet the selection of microminiature satellites. Therefore, the satellite-rocket separating structure for launching the marine satellite has the advantages of compact structure, small volume, low cost, small transformation on the satellite structure, stable connection, small action in the separating process and safety and reliability.
Disclosure of Invention
The invention aims to provide a satellite and arrow separation structure for launching an offshore satellite, which solves the problems in the prior art, has a compact structure, reduces space occupation, has small modification on the satellite structure, has stable connection structure, is convenient to operate, has small action in the separation process, is safe and reliable, can be recycled, effectively improves the satellite launching efficiency and reduces the launching cost.
In order to achieve the above purpose, the present invention provides the following technical solutions: the satellite rocket separating structure for launching the offshore satellite comprises a launcher body and a satellite body, wherein a fixed ring is arranged on the upper side of the launcher body, the section of the fixed ring is of an inverted L-shaped structure, an annular groove is formed between the fixed ring and the launcher body, the notch of the annular groove faces the outer side of the fixed ring, an arc groove is formed on the upper side of the fixed ring, the arc groove penetrates through the inner ring side and the outer ring side of the fixed ring, the bottom of the satellite body is arranged in the fixed ring, a plurality of spring grooves are formed on the upper side of the launcher body in the fixed ring, a first spring is fixedly connected to the bottom of the spring grooves, the upper end of the first spring is abutted against the lower side of the satellite body, an arc protrusion matched with the arc groove is arranged in the arc groove, the upper side of the arc protrusion is flush with the upper side of the fixed ring, an arc slider is arranged on the outer side of the fixed ring, the section of the sliding member is U-shaped and slides along the outer side of the fixed ring, an annular pipe is arranged on the outer side of the fixed ring, a plurality of fixed blocks are connected between the annular pipe and the launcher body, an annular opening is formed on one side of the fixed ring, an annular pipe is arranged in the sliding manner, an arc slider is arranged between the annular pipe and the sliding body is fixedly connected with the outer side of the fixed block, and a telescopic link is arranged between the annular baffle, and the annular body is fixedly connected with the outer side, and the annular baffle, and the annular body is arranged; the telescopic end of the electric telescopic rod penetrates through the outer wall of the annular tube, stretches into the limiting groove, limits the sliding body, compresses the second spring and is positioned outside the arc-shaped bulge; the telescopic end of the electric telescopic rod is contracted, the telescopic end is separated from the limiting groove, the second spring pushes the sliding body to slide along the annular tube, the sliding body drives the sliding piece to slide to the outer side of the fixed ring which is not interfered with the arc-shaped bulge, and the first spring bounces up the satellite body in the state.
Further, the number of the arc grooves is two, the number of the arc protrusions is two, the arc grooves correspond to the arc protrusions one by one, the arc grooves are symmetrically arranged on the upper side of the fixing ring, and the arc protrusions are symmetrically arranged on two sides of the satellite body.
Further, the number of the spring grooves is the same as that of the first springs, and the number of the spring grooves is not less than three.
Further, the number of the sliding parts is two, the U-shaped openings of the sliding parts face the fixed ring, the upper wall and the lower wall of the inner side of the sliding parts are respectively provided with a ball groove, balls are arranged in the ball grooves, and the balls are respectively contacted with the upper side and the lower side of the outer ring part of the fixed ring; the sliding piece slides to the outer side of the arc-shaped bulge along the fixed ring, and the ball on the upper side of the sliding piece is contacted with the upper side of the arc-shaped bulge.
Further, the number of the sliding body, the connecting block, the second spring and the electric telescopic rod is two; the two sliding bodies are in one-to-one correspondence with the two sliding parts; the number of the baffles arranged in the annular pipe is two or four.
Further, the number of the baffles is two, the two baffles arranged in the annular tube are symmetrical, and the two baffles divide the annular tube into two semicircular tube cavities.
Further, the electric telescopic rod is symmetrically arranged on the outer side of the annular pipe.
Further, the slider has an arcuate length less than the arcuate projection; the length of the sliding body is smaller than that of the sliding piece; the height of the annular opening is larger than the thickness of the connecting block; the outer edge radius of the arc-shaped bulge is equal to the outer edge radius of the fixed ring; the height from the upper side surface of the arc-shaped bulge to the lower side surface of the satellite body is not greater than the height from the upper side surface of the fixed ring to the upper side surface of the emitter body.
The beneficial effects of the invention are as follows:
The invention adopts the double-spring structure to realize stable fixation and safe and effective separation of the satellite and the arrow, has small vibration in the separation process, has no explosion phenomenon, has high safety, small volume and reduces space occupation;
The invention has convenient installation and connection operation, is convenient for quick installation, only needs to arrange the bulge at the bottom of the satellite, and has small equipment transformation;
The invention can be recycled and fixedly connected with the launcher, is suitable for rocket recycling which is fast in development, saves cost and improves launching efficiency.
Drawings
Fig. 1 is a schematic cross-sectional view of a stationary satellite body according to the present invention.
FIG. 2 is a schematic cross-sectional view of the star arrow in a separated state according to the present invention.
FIG. 3 is a schematic cross-sectional view of the star arrow of the present invention after separation.
Fig. 4 is a schematic top view of the satellite body according to the present invention.
Fig. 5 is a schematic top view of the emitter body of the present invention.
Fig. 6 is a schematic view of the present invention in a state in which the slider is removed in fig. 5.
Fig. 7 is a schematic view of the inside of the second spring compressed state annular tube of the present invention.
Fig. 8 is a schematic view of the inside of the second spring-released state annular tube of the present invention.
In the figure: 1. the satellite transmitter comprises a transmitter body, 2, a satellite body, 101, a fixed ring, 102, arc grooves, 103, sliding parts, 104, an annular pipe, 105, a fixed block, 106, a sliding body, 107, a connecting block, 108, a ball groove, 109, a ball, 110, a spring groove, 111, a first spring, 112, a baffle, 113, a second spring, 114, an electric telescopic rod, 115, a limit groove, 21 and arc protrusions.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be understood that the terms "middle," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientation or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
Referring to fig. 1-8, the embodiment provides a satellite rocket separating structure for launching an offshore satellite, comprising a launcher body 1 and a satellite body 2, wherein the upper side of the launcher body 1 is provided with a fixed ring 101, the section of the fixed ring 101 is of an inverted-L structure, the fixed ring 101 and the launcher body 1 form an annular groove, the notch of the annular groove faces the outer ring side of the fixed ring 101, the upper side of the fixed ring 101 is provided with an arc-shaped groove 102, the arc-shaped groove 102 penetrates through the inner ring side and the outer ring side of the fixed ring 101, the bottom of the satellite body 2 is placed in the fixed ring 101, the upper side of the launcher body 1 in the fixed ring 101 is provided with a plurality of spring grooves 110, the bottom of the spring grooves 110 is fixedly connected with a first spring 111, the upper end of the first spring 111 is abutted against the lower side of the satellite body 2, the lower part of the satellite body 2 is provided with an arc-shaped protrusion 21 matched with the arc-shaped groove 102, the arc-shaped bulge 21 is arranged in the arc-shaped groove 102, the upper side surface of the arc-shaped bulge 21 is flush with the upper side surface of the fixed ring 101, the outer ring side of the fixed ring 101 is provided with an arc-shaped sliding part 103, the cross section of the sliding part 103 is U-shaped and slides along the outer side of the fixed ring 101, the outer side of the fixed ring 101 is provided with an annular pipe 104, a plurality of fixed blocks 102 are connected between the annular pipe 101 and the emitter body 1, one side of the annular pipe 104, which faces the fixed ring 101, is provided with an annular opening, an arc-shaped sliding body 106 is arranged in the annular pipe 104 in a sliding manner, the sliding body 106 is fixedly connected with the sliding part 103 through a connecting block 107, a baffle 112 is fixedly arranged in the annular pipe 104, a second spring 113 is connected between the baffle 112 and the sliding body 106, the outer side of the annular pipe 104 is fixedly provided with an electric telescopic rod 114, and the outer side of the sliding body 106 is provided with a limiting groove 115; the telescopic end of the electric telescopic rod 114 passes through the outer wall of the annular tube 104, stretches into the limiting groove 115, limits the sliding body 106, compresses the second spring 113 and ensures that the sliding piece 103 is positioned outside the arc-shaped bulge 21; the telescopic end of the electric telescopic rod 114 is contracted and separated from the limiting groove 115, the second spring 113 pushes the sliding body 106 to slide along the annular tube 104, the sliding body 106 drives the sliding piece 103 to slide to the outer side of the fixed ring 101 which is not interfered with the arc-shaped bulge 21, and the first spring 111 ejects the satellite body 2 in the state.
In this embodiment, the number of the arc-shaped grooves 102 is two, the number of the arc-shaped protrusions 21 is two, the arc-shaped grooves 102 and the arc-shaped protrusions 21 are in one-to-one correspondence, the arc-shaped grooves 102 are symmetrically arranged on the upper side of the fixing ring 101, and the arc-shaped protrusions 21 are symmetrically arranged on two sides of the satellite body 2.
In this embodiment, the number of the spring slots 110 and the number of the first springs 111 are the same, and the number of the spring slots is not less than three.
In this embodiment, the number of the sliding pieces 103 is two, the U-shaped openings of the sliding pieces 103 face the fixed ring 101, the upper and lower walls of the inner side of the sliding piece 103 are both provided with ball grooves 108, balls 109 are arranged in the ball grooves 108, and the balls 109 are respectively contacted with the upper and lower sides of the outer ring part of the fixed ring 101; the sliding member 103 slides along the fixing ring 101 to the outside of the arc-shaped protrusion 21, and the roller 109 on the upper side of the sliding member 103 contacts with the upper side of the arc-shaped protrusion 21. The provision of the balls 109 greatly reduces the resistance of the slider 103 to sliding along the stationary ring 101.
In this embodiment, the number of the sliding body 106, the connection block 107, the second spring 113 and the electric telescopic rod 114 is two; the two sliding bodies 106 are in one-to-one correspondence with the two sliding members 103.
In this embodiment, the number of the baffles 112 is two, the two baffles 112 disposed in the annular tube 104 are symmetrical, and the two baffles 112 divide the annular tube 104 into two semicircular cavities. The number of the baffles 112 arranged in the annular tube 104 can also be four, each two baffles 112 and the annular tube 104 form an arc cavity, the sizes of the sliding part 103 and the sliding body 106 can be correspondingly smaller during manufacturing, the size of the sliding part is reduced, and the cost is saved.
In this embodiment, the electric telescopic rods 114 are symmetrically disposed outside the annular tube 104.
In this embodiment, the arc length of the sliding member 103 is smaller than the arc protrusion 21; the length of the slider 106 is smaller than the slider 103; the height of the annular opening is greater than the thickness of the connection block 107; the outer edge radius of the arc-shaped bulge 21 is equal to the outer edge radius of the fixed ring 101; the height from the upper side of the arc-shaped protrusion 21 to the lower side of the satellite body 2 is not greater than the height from the upper side of the fixing ring 101 to the upper side of the transmitter body 1.
When the satellite is installed, the bottom of the satellite body 2 is placed on the upper side of the emitter body 1 in the fixed ring 101, so that the satellite body 2 compresses the first spring 111 into the spring groove 110; the arc-shaped bulge 21 on the outer side of the bottom of the satellite body 2 corresponds to the arc-shaped groove 102 on the upper side of the fixed ring 101, is placed in the arc-shaped groove 102 until the upper side surface of the arc-shaped bulge 21 is level with the upper side surface of the fixed ring 101; the sliding piece 103 is moved, the sliding piece 103 with the U-shaped section slides to the arc-shaped groove 102 of the fixed ring 101, and at the moment, the sliding piece 103 fixes the arc-shaped protrusion 21 in the arc-shaped groove 102, so that the satellite body 2 is fixed; the sliding piece 103 is fixedly connected with the sliding piece 106 through the connecting block 107, the sliding piece 106 slides along the annular tube 104 in the sliding process of the sliding piece 103, the second spring 113 is compressed, when the limiting groove 115 of the sliding piece 106 corresponds to the position of the electric telescopic rod 114 arranged on the annular tube 104, the electric telescopic rod 114 is started to enable the telescopic end to extend out and extend into the limiting groove 115, and the position of the sliding piece 106 in the annular tube 104 is fixed; the satellite body 2 and the emitter body 1 are connected and fixed, at the moment, the satellite body 2 compresses the first spring 111, the sliding body 106 compresses the second spring 113, the electric telescopic rod 114 and the limiting groove 115 are matched to fix the positions of the sliding body 106 and the sliding piece 103, and therefore the sliding piece 103 stably presses the arc-shaped protrusion 21 in the arc-shaped groove 102, and satellite and rocket connection and fixation are completed;
When the structure of the invention is separated, after the launcher sends the satellite to the preset position, the electric telescopic rod 114 is started by the instruction, the telescopic end of the electric telescopic rod 114 is contracted and separated from the limit groove 115 of the sliding body 106, the second spring 113 is released to push the sliding body 106 to slide in the annular tube 104, the sliding body 106 drives the sliding piece 103 to slide along the fixed ring 101, the sliding piece 103 slides from the outer side of the arc-shaped bulge 21 to the outer side of the fixed ring 101 which does not interfere with the arc-shaped bulge 21, the first spring 111 is released to push the satellite body 2 to separate from the emitter body 1, the arc-shaped protrusion 21 is smoothly separated from the arc-shaped groove 102, so that satellite and arrow separation is realized, the whole process only generates impact vibration from the sliding body 106 sliding to the tail end and the baffle 112, when the sliding body 106 impacts the baffle 112, the elastic potential energy of the second spring 113 is consumed, the impact is extremely small, the vibration is extremely small, the equipment cannot be influenced, and the satellite and arrow separation device is safe and reliable.
The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to assist in understanding the methods of the present invention and the core ideas thereof; meanwhile, as those skilled in the art will have variations in the specific embodiments and application scope in accordance with the ideas of the present invention, the present description should not be construed as limiting the present invention in view of the above.
Claims (5)
1. The utility model provides an offshore satellite launches with satellite rocket separation structure, includes transmitter body and satellite body, its characterized in that: the electric power transmitter comprises a transmitter body, and is characterized in that a fixing ring is arranged on the upper side of the transmitter body, the cross section of the fixing ring is of an inverted L-shaped structure, an annular groove is formed between the fixing ring and the transmitter body, the notch of the annular groove faces the outer ring side of the fixing ring, an arc-shaped groove is formed in the upper side of the fixing ring, the arc-shaped groove penetrates through the inner ring side and the outer ring side of the fixing ring, the bottom of the satellite body is arranged in the fixing ring, a plurality of spring grooves are formed in the upper side of the transmitter body in the fixing ring, a first spring is fixedly connected to the bottom of the spring grooves, the upper end of the first spring is abutted against the lower side of the satellite body, an arc-shaped bulge matched with the arc-shaped groove is formed in the lower side of the satellite body, the arc-shaped bulge is arranged in the arc-shaped groove, the upper side of the arc-shaped bulge is flush with the upper side of the fixing ring, an arc-shaped sliding piece is arranged on the outer ring side of the fixing ring, the cross section of the sliding piece is U-shaped and slides along the outer side of the fixing ring, an annular pipe is arranged on the outer side of the fixing ring, a plurality of fixing blocks are connected between the annular pipe and the transmitter body, an annular opening is formed on one side of the fixing ring, an arc-shaped sliding body is arranged in the fixing ring, an arc-shaped sliding body is arranged, a baffle is fixedly connected between the annular body and the annular pipe, and an electric connecting block is fixedly arranged, and an outer side, and a connecting block is arranged, and a limiting rod is fixedly, and the outer side, and a limiting rod is arranged; the telescopic end of the electric telescopic rod penetrates through the outer wall of the annular tube, stretches into the limiting groove, limits the sliding body, compresses the second spring and is positioned outside the arc-shaped bulge; the telescopic end of the electric telescopic rod is contracted and separated from the limiting groove, the second spring pushes the sliding body to slide along the annular tube, the sliding body drives the sliding piece to slide to the outer side of the fixed ring which is not interfered with the arc-shaped bulge, and the first spring bounces up the satellite body in the state;
The number of the arc-shaped grooves is two, the number of the arc-shaped protrusions is two, the arc-shaped grooves and the arc-shaped protrusions are in one-to-one correspondence, the arc-shaped grooves are symmetrically arranged on the upper side of the fixed ring, and the arc-shaped protrusions are symmetrically arranged on two sides of the satellite body;
The number of the sliding parts is two, the U-shaped openings of the sliding parts face the fixed ring, the upper wall and the lower wall of the inner side of the sliding parts are respectively provided with a ball groove, balls are arranged in the ball grooves, and the balls are respectively contacted with the upper side and the lower side of the outer ring part of the fixed ring; the sliding piece slides to the outer side of the arc-shaped bulge along the fixed ring, and the ball on the upper side of the sliding piece is contacted with the upper side of the arc-shaped bulge.
2. The marine satellite launching satellite separation structure according to claim 1, wherein: the number of the sliding body, the connecting block, the second spring and the electric telescopic rod is two; the two sliding bodies are in one-to-one correspondence with the two sliding parts; the number of the baffles arranged in the annular pipe is two or four.
3. The marine satellite launching satellite separation structure according to claim 2, wherein: the number of the baffles is two, the two baffles arranged in the annular tube are symmetrical, and the two baffles divide the annular tube into two semicircular tube cavities.
4. A satellite-rocket separating structure for launching an offshore satellite according to claim 3, wherein: the electric telescopic rod is symmetrically arranged on the outer side of the annular tube.
5. The marine satellite launching satellite separation structure according to claim 4, wherein: the arc length of the sliding piece is smaller than that of the arc-shaped bulge; the length of the sliding body is smaller than that of the sliding piece; the height of the annular opening is larger than the thickness of the connecting block; the outer edge radius of the arc-shaped bulge is equal to the outer edge radius of the fixed ring; the height from the upper side surface of the arc-shaped bulge to the lower side surface of the satellite body is not greater than the height from the upper side surface of the fixed ring to the upper side surface of the emitter body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011033971.8A CN112046786B (en) | 2020-09-27 | 2020-09-27 | Satellite and rocket separation structure for launching offshore satellite |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011033971.8A CN112046786B (en) | 2020-09-27 | 2020-09-27 | Satellite and rocket separation structure for launching offshore satellite |
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| Publication Number | Publication Date |
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| CN112046786A CN112046786A (en) | 2020-12-08 |
| CN112046786B true CN112046786B (en) | 2024-09-03 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN212354426U (en) * | 2020-09-27 | 2021-01-15 | 中国卫星海上测控部 | Satellite-rocket separation structure for marine satellite launching |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| SE518516C2 (en) * | 2001-04-19 | 2002-10-22 | Bofors Defence Ab | Methods and apparatus for improving the outer ballistics of an artillery grenade |
| CN104859870B (en) * | 2014-10-09 | 2017-02-08 | 航天东方红卫星有限公司 | An integrated star-arrow separation mechanism |
| CN106586031B (en) * | 2017-02-07 | 2017-12-15 | 哈尔滨工业大学 | A kind of expansion configuration satellite platform main structure |
| CN210000934U (en) * | 2019-03-05 | 2020-01-31 | 宁夏神瑞工贸有限责任公司 | chemical industry is with chemical industry holding vessel that can crashproof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN212354426U (en) * | 2020-09-27 | 2021-01-15 | 中国卫星海上测控部 | Satellite-rocket separation structure for marine satellite launching |
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