CN117302550A - Multi-star serial transmitting system - Google Patents
Multi-star serial transmitting system Download PDFInfo
- Publication number
- CN117302550A CN117302550A CN202311445384.3A CN202311445384A CN117302550A CN 117302550 A CN117302550 A CN 117302550A CN 202311445384 A CN202311445384 A CN 202311445384A CN 117302550 A CN117302550 A CN 117302550A
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- Prior art keywords
- satellite
- cabin
- transition
- supporting
- fairing
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- 230000007704 transition Effects 0.000 claims abstract description 70
- 238000000926 separation method Methods 0.000 claims abstract description 35
- 239000002360 explosive Substances 0.000 claims abstract description 4
- 230000000977 initiatory effect Effects 0.000 claims abstract description 4
- 210000001503 joint Anatomy 0.000 claims abstract description 4
- 230000005540 biological transmission Effects 0.000 claims description 3
- 239000002775 capsule Substances 0.000 claims 1
- 238000005516 engineering process Methods 0.000 description 7
- 238000011161 development Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 108010066278 cabin-4 Proteins 0.000 description 2
- 101100438971 Caenorhabditis elegans mat-1 gene Proteins 0.000 description 1
- 101100491335 Caenorhabditis elegans mat-2 gene Proteins 0.000 description 1
- 101100495256 Caenorhabditis elegans mat-3 gene Proteins 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000006855 networking Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
- B64G1/005—Air launch
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radio Relay Systems (AREA)
Abstract
The invention provides a multi-star serial emission system, which comprises a satellite fairing, a point type separation device, a first supporting cabin, a first transition cabin, a second supporting cabin, a satellite adapter, a second transition cabin, a third transition cabin and a third supporting cabin, wherein the first supporting cabin is connected with the satellite fairing; the satellite fairing is used for protecting the payload inside the satellite fairing before the carrier rocket takes off and flies; the first transition cabin, the second transition cabin and the third transition cabin are used as structural supports of a satellite fairing and a satellite, and the payload in the rocket is protected before the carrier rocket takes off and in flight; the butt joint surface of the first transition cabin and the second supporting cabin is a separating surface of the first transition cabin and the rocket, the first transition cabin is connected with the rocket through a initiating explosive device, and separation is implemented by adopting a separating spring; compared with the prior art, the invention utilizes the inverted layout of the second supporting cabin, thereby fully utilizing the available space inside the second supporting cabin.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a multi-star serial transmitting system.
Background
The space access, space utilization and space control are the main tasks of aerospace power, and the quick and efficient space access is the basis of space utilization and space control. The multi-satellite launching technique refers to a technique of launching a plurality of satellites into a predetermined orbit at one time by using one carrier rocket. On the premise of rocket carrying capacity and in-cover envelope allowance, a multi-satellite launching technology is adopted to realize rapid networking after a plurality of satellites enter orbit, so that the requirements of rapid deployment of constellation tasks are met; meanwhile, a plurality of satellites are launched in one rocket launching period, so that the launching period of a single satellite can be shortened, the satellite launching cost is greatly reduced, and the method is an important way for improving the cost performance of the carrier rocket. Based on the advantages, the multi-star launching technology is highly paid attention to in large aerospace countries in the world, and a great deal of effort is put into research and development.
Currently, the main form of multi-satellite launching of domestic carrier rockets is serial or parallel configuration, but the satellite layout generally adopts central arrangement, and when a satellite with a special configuration is encountered, the available envelope in a satellite fairing is difficult to fully utilize. In addition, with the vigorous development of the multi-star launching technology, a certain development and development are carried out on the multi-star launching technology of the micro-nano satellites, but the multi-star launching technology of medium and small satellites, especially satellites with the weight of more than 100kg, is still one of key technologies of the development of the domestic aerospace technology.
Disclosure of Invention
The invention aims to provide a multi-star serial emission system which can realize rapid emission of one arrow and multiple stars and has higher reliability and safety.
The technical scheme of the invention is as follows: providing a multi-satellite serial emission system, comprising a satellite fairing, a point separation device, a first supporting cabin, a first transition cabin, a second supporting cabin, a satellite adapter, a second transition cabin, a third transition cabin and a third supporting cabin;
the satellite fairing is used for protecting the payload inside the satellite fairing before the carrier rocket takes off and flies; the first transition cabin, the second transition cabin and the third transition cabin are used as structural supports of a satellite fairing and a satellite, and the payload in the rocket is protected before the carrier rocket takes off and in flight; the butt joint surface of the first transition cabin and the second supporting cabin is a separating surface of the first transition cabin and the rocket, the first transition cabin is connected with the rocket through a initiating explosive device, and separation is implemented by adopting a separating spring;
the space occupied by the first supporting cabin and the point type separation device is subtracted from the space occupied by the satellite fairing, other spaces can be used for placing satellites, and the minimum gap between the satellite fairing and the satellites is not less than 150mm; the available space in the satellite fairing can meet the envelope space requirement of satellites with the weight of more than 100 kg;
the inner space formed by the first supporting cabin, the first transition cabin and the second supporting cabin can meet the outer envelope requirement of the satellite with the level of more than 100 kg; the minimum clearance between the satellite and the combination of the first supporting cabin and the first transition cabin is not less than 150mm;
the inner space formed by the second transition cabin, the third transition cabin, the second supporting cabin and the third supporting cabin can meet the outer envelope requirement of the satellite with the level of more than 100 kg; the minimum clearance between the satellite and the second support cabin, the second transition cabin and the third transition cabin is not less than 150mm.
Further, in the satellite fairing, a satellite is arranged on the first supporting cabin, and satellite-rocket connection is realized through the point type separation device; the second supporting cabin and the satellite adapter are arranged in the first transition cabin, a satellite is arranged on the second supporting cabin and the satellite adapter, and satellite-rocket connection is realized through a bag strap; the third supporting cabin is arranged in the second transition cabin and the third transition cabin, a satellite is arranged on the third supporting cabin, and satellite-rocket connection is achieved through the point type separation device.
Further, the satellite on the third bearing pod may be offset laterally by 200mm.
Further, the large diameter end of the second supporting cabin faces upwards, and the small diameter end of the second supporting cabin faces downwards.
Further, the direction of the satellite separation speed in the satellite fairing is parallel to the axis of the rocket body.
Further, the satellite separation speed direction in the first transition cabin is parallel to the axis of the rocket body.
Further, the satellite separation speed direction in the second transition cabin and the third transition cabin is parallel to the axis of the rocket body.
The multi-star serial transmitting system provided by the invention has the beneficial effects that:
compared with the prior art, the invention utilizes the inverted (large diameter end upwards and small diameter end downwards) layout of the second supporting cabin, thereby fully utilizing the available space inside the second supporting cabin.
Compared with the prior art, the invention designs the abutting surface of the first transition cabin and the second supporting cabin as the separating surface of the first transition cabin, reduces one transition cabin, and can effectively reduce the weight of the rocket body structure and improve the carrying capacity of the rocket.
In addition, the invention can meet the satellite bias layout requirement of more than 100kg through the improvement of the interface form of the upper end face of the third supporting cabin, and can be used for the satellite envelope layout requirement of special configuration.
Drawings
The invention is further described below with reference to the accompanying drawings:
FIG. 1 is a schematic diagram of a multi-star serial transmission system according to the present invention;
FIG. 2 is a side view of a third bearing cartridge and point separation device of the present invention;
FIG. 3 is a top view of a third bearing cartridge and point separation device of the present invention;
FIG. 4 is a side view of a second support pod and satellite adapter of the present invention;
fig. 5 is a top view of a second support pod and satellite adapter of the present invention.
Detailed Description
The multi-star serial transmitting system provided by the invention is further described in detail below with reference to the accompanying drawings and specific embodiments. Advantages and features of the invention will become more apparent from the following description and from the claims. It is noted that the drawings are in a very simplified form and utilize non-precise ratios, and are intended to facilitate a convenient, clear, description of the embodiments of the invention.
Example 1
The present embodiment provides a multi-star serial transmission system, as shown in fig. 1, including: satellite fairing 1, point separation device 2, first support pod 3, first transition pod 4, second support pod 5, satellite adapter 6, second transition pod 7, third transition pod 8, third support pod 9.
In the system, a satellite is arranged in a satellite fairing, and satellite-rocket connection is realized through a point type separation device, so that the minimum gap between the satellite and the satellite fairing is required to be ensured to be not less than 150mm in order to ensure the safety of the separation process of the satellite fairing.
In the system, a satellite is arranged in an inner space formed by a first supporting cabin 3, a first transition cabin 4 and a second supporting cabin 5, and flexible connection of the satellite and the arrow is realized through a belting, so that the minimum gap between the satellite and the first supporting cabin 3 and between the satellite and the first transition cabin 4 are required to be not less than 150mm in order to ensure that the satellite and the arrow do not collide in the separation process.
In the system, a satellite is arranged in an inner space formed by the second supporting cabin 5, the second transition cabin 7, the third transition cabin 8 and the third supporting cabin 9, and the satellite and arrow connection is realized through a point type separation device, so that the minimum gap between the satellite and the second transition cabin 7 and the third transition cabin 8 is required to be not less than 150mm in order to ensure that the satellite and the arrow do not collide in the separation process.
Example 2
In the embodiment, a satellite fairing with the diameter of 3.35m is adopted, a satellite is arranged in the satellite fairing and on the first supporting cabin, the satellite mass can reach more than 500kg, and the satellite arrow realizes connection, unlocking and spring separation through a point type separation device.
In the invention, a 600 kg-class satellite is arranged in a first transition cabin, as shown in fig. 1, satellite-rocket connection is realized through a bag strap, and satellite-rocket separation is realized through arranging a separation spring on a satellite adapter. The satellite is placed in an inner space formed by the first supporting cabin, the first transition cabin and the second supporting cabin.
In the invention, a 500 kg-class satellite is arranged in the third transition cabin and the second transition cabin, as shown in figure 1, and the satellite-rocket connection, unlocking and spring separation are realized through a point type separation device. Wherein a satellite offset 200mm placement on the third support pod is shown in fig. 3.
In the invention, the butt joint surface of the first transition cabin and the second supporting cabin is also designed as the separation surface of the first transition cabin and the rocket, the first transition cabin and the rocket are connected through a initiating explosive device, and separation is implemented by adopting a separation spring.
What is not described in detail in this specification is prior art known to those skilled in the art. It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.
Claims (7)
1. The multi-satellite serial emission system is characterized by comprising a satellite fairing, a point separation device, a first supporting cabin, a first transition cabin, a second supporting cabin, a satellite adapter, a second transition cabin, a third transition cabin and a third supporting cabin;
the satellite fairing is used for protecting the payload inside the satellite fairing before the carrier rocket takes off and flies; the first transition cabin, the second transition cabin and the third transition cabin are used as structural supports of a satellite fairing and a satellite, and the payload in the rocket is protected before the carrier rocket takes off and in flight; the butt joint surface of the first transition cabin and the second supporting cabin is a separating surface of the first transition cabin and the rocket, the first transition cabin is connected with the rocket through a initiating explosive device, and separation is implemented by adopting a separating spring;
the space occupied by the first supporting cabin and the point type separation device is subtracted from the space occupied by the satellite fairing, other spaces can be used for placing satellites, and the minimum gap between the satellite fairing and the satellites is not less than 150mm; the available space in the satellite fairing can meet the envelope space requirement of satellites with the weight of more than 100 kg;
the inner space formed by the first supporting cabin, the first transition cabin and the second supporting cabin can meet the outer envelope requirement of the satellite with the level of more than 100 kg; the minimum clearance between the satellite and the combination of the first supporting cabin and the first transition cabin is not less than 150mm;
the inner space formed by the second transition cabin, the third transition cabin, the second supporting cabin and the third supporting cabin can meet the outer envelope requirement of the satellite with the level of more than 100 kg; the minimum clearance between the satellite and the second support cabin, the second transition cabin and the third transition cabin is not less than 150mm.
2. The multi-satellite serial launching system according to claim 1, wherein a satellite is arranged on the first supporting cabin in the satellite fairing, and the satellite-rocket connection is realized through the point separation device; the second supporting cabin and the satellite adapter are arranged in the first transition cabin, a satellite is arranged on the second supporting cabin and the satellite adapter, and satellite-rocket connection is realized through a bag strap; the third supporting cabin is arranged in the second transition cabin and the third transition cabin, a satellite is arranged on the third supporting cabin, and satellite-rocket connection is achieved through the point type separation device.
3. The multi-satellite serial transmission system of claim 1, wherein the satellite on the third support pod is laterally offset by 200mm.
4. The multi-star serial launch system of claim 1 wherein said second support pod has a major diameter end facing upward and a minor diameter end facing downward.
5. The multi-star serial launch system of claim 1 wherein the satellite separation velocity direction within the satellite fairing is parallel to the arrow axis.
6. The multi-satellite serial launch system of claim 1, wherein the satellite separation velocity direction within the first transition capsule is parallel to the arrow axis.
7. The multi-satellite serial launch system of claim 1, wherein satellite separation velocity directions within the second transition pod and the third transition pod are parallel to an arrow axis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311445384.3A CN117302550A (en) | 2023-11-01 | 2023-11-01 | Multi-star serial transmitting system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311445384.3A CN117302550A (en) | 2023-11-01 | 2023-11-01 | Multi-star serial transmitting system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117302550A true CN117302550A (en) | 2023-12-29 |
Family
ID=89249942
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311445384.3A Pending CN117302550A (en) | 2023-11-01 | 2023-11-01 | Multi-star serial transmitting system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117302550A (en) |
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2023
- 2023-11-01 CN CN202311445384.3A patent/CN117302550A/en active Pending
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