CN218329572U - Solid-liquid mixed carrier rocket for continuously boosting in atmosphere - Google Patents
Solid-liquid mixed carrier rocket for continuously boosting in atmosphere Download PDFInfo
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- CN218329572U CN218329572U CN202223042348.6U CN202223042348U CN218329572U CN 218329572 U CN218329572 U CN 218329572U CN 202223042348 U CN202223042348 U CN 202223042348U CN 218329572 U CN218329572 U CN 218329572U
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- 239000007788 liquid Substances 0.000 title claims abstract description 45
- 239000007787 solid Substances 0.000 claims abstract description 40
- 238000012937 correction Methods 0.000 claims abstract description 5
- 230000007246 mechanism Effects 0.000 claims description 22
- 238000000926 separation method Methods 0.000 claims description 20
- 238000003860 storage Methods 0.000 claims description 10
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 7
- 239000003350 kerosene Substances 0.000 claims description 7
- 238000004880 explosion Methods 0.000 claims description 5
- 238000005520 cutting process Methods 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims 2
- 238000010168 coupling process Methods 0.000 claims 2
- 238000005859 coupling reaction Methods 0.000 claims 2
- 239000002775 capsule Substances 0.000 description 4
- 235000015842 Hesperis Nutrition 0.000 description 3
- 235000012633 Iberis amara Nutrition 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008275 binding mechanism Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000006855 networking Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
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Abstract
The utility model discloses a solid-liquid mixed carrier rocket for continuous boosting in the atmosphere, belonging to the technical field of spaceflight, comprising a solid boosting sub-stage, a multi-stage liquid power core stage, a final posture correction control system, an instrument cabin and a fairing; the multi-stage hydrodynamic core stage, the instrument cabin and the fairing are sequentially connected along the length direction of the carrier rocket; the multi-stage hydrodynamic core stage comprises a plurality of sub-stages which are sequentially connected along the length direction of the carrier rocket; the solid boosting sub-stage is arranged on the outer circumferential direction of the multi-stage hydrodynamic core stage and is connected with a designated sub-stage in the multi-stage hydrodynamic core stage. The utility model discloses can full play liquid rocket engine performance high, operating time is long to and solid rocket engine thrust is big, reliable operation, use and maintain simple comprehensive advantage, and realize big carrying capacity, effectively satisfy growing satellite and launch the demand fast in batches.
Description
Technical Field
The utility model relates to an aerospace technical field, in particular to solid-liquid mixed carrier rocket of boosting in succession in atmosphere.
Background
The rapid development of the low-orbit internet constellation puts an urgent need on the one-rocket multi-satellite rapid networking launching capability of a carrier rocket, and in daily practice, the inventor finds that the prior technical scheme has the following problems:
the solid-liquid hybrid power scheme can comprehensively exert the technical advantages of solid power and liquid power, and becomes an important development direction of medium and large-sized carrier rockets in the world, such as the United states 'universe' carrier rocket, a space shuttle launching system and a 'space launching system' to be used in the 'Elite' project, the 'Aliran' series carrier rockets in Europe and the 'H' series carrier rockets in Japan, wherein the solid-liquid hybrid power scheme is adopted.
At present, china only changes 'long-standing six-number' type solid-liquid hybrid rocket with the carrying capacity of about 4 tons (700 km SSO), and how to provide a novel carrier rocket which can give full play to the technical advantages of solid-liquid hybrid power and realize large carrying capacity is a problem which needs to be solved urgently at present in the field.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problems, the application provides a solid-liquid mixed carrier rocket for continuously boosting in the atmosphere, which can fully exert the comprehensive advantages of high performance and long working time of a liquid rocket engine, large thrust, reliable work and simple use and maintenance of a solid rocket engine, realize large carrying capacity and effectively meet the increasing requirement of rapid satellite batch launching.
A solid-liquid mixed carrier rocket for continuously boosting in the atmosphere comprises a solid boosting sub-stage, a multi-stage liquid power core stage, a final attitude correction control system, an instrument cabin and a fairing; the multi-stage hydrodynamic core stage, the instrument cabin and the fairing are sequentially connected along the length direction of the carrier rocket; the multi-stage hydrodynamic core stage comprises a plurality of sub-stages which are sequentially connected along the length direction of the carrier rocket; the solid boosting sub-stage is arranged on the outer circumferential direction of the multi-stage hydrodynamic core stage and is connected with a designated sub-stage in the multi-stage hydrodynamic core stage.
Preferably, the multi-stage hydrodynamic core stage comprises a core first sub-stage and a core second sub-stage which are sequentially connected along the length direction of the launch vehicle; the first core sub-stage and the second core sub-stage have the same diameter.
Preferably, the solid booster stage has 2 pieces; 2 solid boosting sub-stages are symmetrically arranged on the outer periphery of the core first sub-stage and are connected with the core first sub-stage in a binding manner; the second core sub-stage is connected with the instrument cabin.
Preferably, the core first-level sub-level comprises a core first-level interval section, a core first-level liquid oxygen storage tank, a core first-level tank interval section, a core first-level kerosene storage tank, a core first-level liquid rocket engine and a core first-level tail section which are sequentially connected.
Preferably, the core secondary sub-stage comprises a core secondary stage section, a core secondary liquid oxygen storage tank, a core secondary tank section, a core secondary kerosene storage tank, a core secondary liquid rocket engine and a core secondary tail section which are sequentially connected.
Preferably, the solid booster sub-stage comprises a boosting stage nose cone, a boosting solid rocket engine and a boosting stage tail section which are sequentially connected.
Preferably, the booster-stage nose cone is in the form of a positive cone, and the cone angle is 30 degrees.
Preferably, the device also comprises a boosting connection and separation mechanism and a core interstage connection and separation mechanism; the boosting connecting and separating mechanism comprises a main binding connecting mechanism and an auxiliary binding connecting mechanism and an explosion bolt; the core-to-core connection and separation mechanism comprises an explosion bolt and a separation spring, or a cutting rope and a separation spring.
Compared with the prior art, the application has at least the following beneficial effects:
1) According to the solid-liquid mixed carrier rocket for continuously boosting in the atmosphere, the solid boosting sub-stage adopts the solid rocket engine capable of being stored for a long time, so that the content of rocket launching preparation work can be effectively reduced, the guarantee requirement is lowered, and the quick launching response capability is realized; the multi-stage liquid power core stage adopts a liquid oxygen kerosene liquid rocket engine, so that the specific impulse of the upper stage can be effectively improved, the working time of a single stage can be prolonged, the stage number of the rocket can be reduced, and the complexity of the overall design can be reduced. The advantages of the solid and liquid power schemes are complemented, so that the balance between the rocket performance and the cost is realized, and the excellent comprehensive performance is achieved.
2) The solid-liquid mixed carrier rocket capable of continuously boosting in the atmosphere can effectively improve the carrying capacity of the rocket by utilizing the method of binding the solid booster, and the carrying capacity can be doubled compared with the unique solid-liquid mixed rocket in China.
3) The application provides a solid-liquid hybrid carrier rocket of continuous boosting in atmosphere through adopting the configuration design of binding, can realize modularization, unitization, the serialization design of carrier rocket, and the adjustment of follow-up accessible solid boosting sublevel forms multiple configuration, makes the carrier rocket series that carrying capacity coverage is wide, the gradient is reasonable, the price/performance ratio is high, satisfies the diversified intensive launch demand of future satellite.
Drawings
Some specific embodiments of the present invention will be described in detail hereinafter, by way of illustration and not by way of limitation, with reference to the accompanying drawings. The same reference numbers in the drawings identify the same or similar elements or components. Those skilled in the art will appreciate that the drawings are not necessarily to scale.
In the drawings:
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a view taken along line A of FIG. 1;
fig. 3 is a schematic diagram of the structure of a solid booster stage.
Wherein the figures include the following reference numerals:
10. a solid booster stage, 20, a multi-stage liquid power core stage, 30, a final posture correction control system, 40, an instrument cabin, 50 and a fairing;
11. a boosting stage nose cone 12, a boosting solid rocket engine 13 and a boosting stage tail section;
21. a core one sub-stage, 22, a core two sub-stage;
51. end cap 52, front cone section 53, column section 54 and back cone section.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the technical solutions of the present application will be described in detail and completely with reference to the following specific embodiments of the present application and the accompanying drawings. It should be apparent that the described embodiments are only a few embodiments of the present application, and 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.
As shown in fig. 1 to 3, a solid-liquid hybrid launch vehicle for continuously propelling in the atmosphere comprises a solid propelling propellant sub-stage 10, a multi-stage hydrodynamic core stage 20, a final attitude correction control system 30, an instrument capsule 40 and a fairing 50, wherein the multi-stage hydrodynamic core stage 20, the instrument capsule 40 and the fairing 50 are sequentially connected along the length direction of the launch vehicle. The multi-stage liquid power core stage 20 comprises a plurality of sub-stages which are sequentially connected along the length direction of the carrier rocket, and the solid boosting sub-stage 10 is arranged on the outer circumference of the multi-stage liquid power core stage 20 and is connected with a designated sub-stage in the multi-stage liquid power core stage 20.
Specifically, the multi-stage hydrodynamic core stage 20 includes a core first sub-stage 21 and a core second sub-stage 22 connected in series along the length of the launch vehicle. The diameter of the core first substage 21 is the same as the diameter of the core second substage 22. An instrument pod 40 is connected to the core two substage 22. The core first-level sub-level 21 comprises a core first-level interval section, a core first-level liquid oxygen storage tank, a core first-level tank interval section, a core first-level kerosene storage tank, a core first-level liquid rocket engine and a core first-level tail section which are sequentially connected. The core secondary sub-stage 22 comprises a core secondary stage section, a core secondary liquid oxygen storage tank, a core secondary tank section, a core secondary kerosene storage tank, a core secondary liquid rocket engine and a core secondary tail section which are sequentially connected. The core secondary tail section is connected with the core primary section.
The final attitude control system 30 is mounted on an instrument capsule 40, and the diameter of the instrument capsule 40 is the same as that of the second core substage 22.
The fairing consists of an end cap 51, a front cone section 52, a column section 53 and an inverted cone section 54, and the inverted cone section 54 is fixedly connected with the instrument chamber 40.
Preferably, the diameter of the column section 53 is 5m, and the length of the column section 53 is 5.5m, so that the requirement of batch loading of various types of satellites can be met.
The solid booster stage 10 has 2 pieces and is the same size. The two solid booster sub-stages 10 are arranged on the outer periphery of the core first sub-stage 21 and are bound and connected with the core first sub-stage 21 through a binding mechanism. The solid booster sub-stage 10 comprises a booster stage nose cone 11, a booster solid rocket engine 12 and a booster stage tail section 13 which are connected in sequence.
Preferably, to achieve better aerodynamic characteristics and simplify the machining process, the booster nose cone 11 takes the form of a positive cone with a cone angle of 30 °.
Preferably, the solid-liquid hybrid launch vehicle for continuous boosting in the atmosphere further comprises a boosting connection and separation mechanism and a core interstage connection and separation mechanism for realizing connection and separation between the solid boosting sub-stage 10 and the core first sub-stage 21 and between the core first sub-stage 21 and the core second sub-stage 22. The boost connection and separation mechanism is arranged between the solid boost sub-stage and the core first sub-stage 21 in the solid boost sub-stage 10. The boosting connecting and separating mechanism comprises a main binding connecting mechanism and an auxiliary binding connecting mechanism and an explosion bolt. The core to core connection separation mechanism includes a core to core connection separation mechanism disposed between the core first substage 21 and the core second substage 22. The core-to-core connection and separation mechanism adopts an explosive bolt and a separation spring. In addition, the core interstage connection separation mechanism can also adopt a cutting rope and a separation spring.
Further, the liquid rocket engines employed in the core-one substage 21, the core-two substage 22, and the solid rocket engines employed in the boost solid rocket engine 12 all include oscillating nozzles.
When the rocket takes off, the two boosting subsystems in the solid boosting sub-stage 10 are ignited to work first, and the core-sub-stage 21 is ignited to work a period of time before the solid boosting sub-stage 10 finishes working, so that the continuous boosting of the rocket is realized. In the working stage of the solid boosting sub-stage 10, the swing spray pipes of 2 boosting solid rocket engines 10 are used for carrying out all-rocket three-channel control. Starting from the operation of the core first sub-stage 21, the swinging spray pipes of all stages of the liquid power system control the whole arrow pitching and yawing channels, and the tail-repair attitude control system 30 controls the whole arrow rolling channel.
For ease of description, spatially relative terms, such as "over", "above", "on", "upper surface", "over", and the like, may be used herein to describe one element or feature's spatial relationship to another element or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above" may encompass both an orientation of "above" and "below. The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular is intended to include the plural unless the context clearly dictates otherwise, and it should be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of features, steps, operations, devices, components, and/or combinations thereof.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the application described herein are capable of operation in sequences other than those illustrated or described herein.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A solid-liquid mixed carrier rocket for continuously boosting in the atmosphere is characterized by comprising a solid booster stage, a multi-stage liquid power core stage, a final posture correction control system, an instrument cabin and a fairing; the multi-stage hydrodynamic core stage, the instrument cabin and the fairing are sequentially connected along the length direction of the carrier rocket; the multi-stage hydrodynamic core stage comprises a plurality of sub-stages which are sequentially connected along the length direction of the carrier rocket; the solid boosting sub-stage is arranged on the outer circumferential direction of the multi-stage hydrodynamic core stage and is connected with a designated sub-stage in the multi-stage hydrodynamic core stage.
2. The solid-liquid hybrid launch vehicle of claim 1 wherein the multi-stage hydrodynamic core stage comprises a core first sub-stage and a core second sub-stage connected in series along the length of the launch vehicle; the first core sub-stage and the second core sub-stage have the same diameter.
3. The solid-liquid hybrid launch vehicle of claim 2, wherein the solid booster stage has 2 pieces; 2 solid boosting sub-stages are symmetrically arranged on the outer periphery of the core first sub-stage and are connected with the core first sub-stage in a binding manner; the second core sub-stage is connected with the instrument cabin.
4. The solid-liquid hybrid launch vehicle of claim 2 wherein the core-first substage comprises, in series, a core-first stage bay section, a core-first liquid oxygen tank, a core-first tank bay section, a core-first kerosene tank, a core-first liquid rocket engine, and a core-first tail section.
5. The hybrid solid-liquid launch vehicle of claim 2 wherein the core secondary sub-stage comprises a core secondary stage bay section, a core secondary liquid oxygen storage tank, a core secondary tank bay section, a core secondary kerosene storage tank, a core secondary liquid rocket motor, and a core secondary tail section connected in series.
6. The solid-liquid hybrid launch vehicle of claim 1 wherein the solid booster stage comprises a booster stage nose cone, a booster solid rocket motor, and a booster stage tail section connected in series.
7. The hybrid solid-liquid launch vehicle of claim 6 wherein the booster nose cone is in the form of a forward cone having a cone angle of 30 °.
8. The solid-liquid hybrid launch vehicle of any of claims 1-7 further comprising a thrust coupling and separation mechanism and a core interstage coupling and separation mechanism; the boosting connecting and separating mechanism comprises a main binding connecting mechanism and an auxiliary binding connecting mechanism and an explosion bolt; the core-to-core connection and separation mechanism comprises an explosion bolt and a separation spring, or a cutting rope and a separation spring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223042348.6U CN218329572U (en) | 2022-11-16 | 2022-11-16 | Solid-liquid mixed carrier rocket for continuously boosting in atmosphere |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202223042348.6U CN218329572U (en) | 2022-11-16 | 2022-11-16 | Solid-liquid mixed carrier rocket for continuously boosting in atmosphere |
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| CN218329572U true CN218329572U (en) | 2023-01-17 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116486673A (en) * | 2023-06-21 | 2023-07-25 | 中国人民解放军国防科技大学 | Solid rocket and water rocket integrated two-stage model rocket |
| CN116929159A (en) * | 2023-09-18 | 2023-10-24 | 北京星河动力装备科技有限公司 | Carrier rocket with solid-liquid hybrid power and launching method thereof |
| CN117932792A (en) * | 2024-03-18 | 2024-04-26 | 东方空间(江苏)航天动力有限公司 | Method for reducing thrust imbalance of binding boosting solid rocket engine |
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2022
- 2022-11-16 CN CN202223042348.6U patent/CN218329572U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116486673A (en) * | 2023-06-21 | 2023-07-25 | 中国人民解放军国防科技大学 | Solid rocket and water rocket integrated two-stage model rocket |
| CN116486673B (en) * | 2023-06-21 | 2023-08-29 | 中国人民解放军国防科技大学 | Solid rocket and water rocket integrated two-stage model rocket |
| CN116929159A (en) * | 2023-09-18 | 2023-10-24 | 北京星河动力装备科技有限公司 | Carrier rocket with solid-liquid hybrid power and launching method thereof |
| CN116929159B (en) * | 2023-09-18 | 2024-01-09 | 北京星河动力装备科技有限公司 | Carrier rocket with solid-liquid hybrid power and launching method thereof |
| CN117932792A (en) * | 2024-03-18 | 2024-04-26 | 东方空间(江苏)航天动力有限公司 | Method for reducing thrust imbalance of binding boosting solid rocket engine |
| CN117932792B (en) * | 2024-03-18 | 2024-05-28 | 东方空间(江苏)航天动力有限公司 | Method for reducing thrust imbalance of binding boosting solid rocket engine |
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Address after: No. 30, Nanjing Street, Economic Development Zone, Haiyang City, Yantai City, Shandong Province, 265118 Patentee after: Dongfang space technology (Shandong) Co.,Ltd. Country or region after: China Patentee after: Dongfang Space (Jiangsu) Aerospace Power Co.,Ltd. Patentee after: Oriental space technology (Beijing) Co.,Ltd. Patentee after: Orient Space (Hainan) Technology Co.,Ltd. Address before: No. 30, Nanjing Street, Economic Development Zone, Haiyang City, Yantai City, Shandong Province, 265118 Patentee before: Dongfang space technology (Shandong) Co.,Ltd. Country or region before: China Patentee before: Oriental space technology (Beijing) Co.,Ltd. Patentee before: Dongfang Space (Jiangsu) Aerospace Power Co.,Ltd. Patentee before: Orient Space (Hainan) Technology Co.,Ltd. Address after: No. 30, Nanjing Street, Economic Development Zone, Haiyang City, Yantai City, Shandong Province, 265118 Patentee after: Dongfang space technology (Shandong) Co.,Ltd. Country or region after: China Patentee after: Oriental space technology (Beijing) Co.,Ltd. Patentee after: Dongfang Space (Jiangsu) Aerospace Power Co.,Ltd. Patentee after: Orient Space (Hainan) Technology Co.,Ltd. Address before: No. 30, Nanjing Street, Economic Development Zone, Haiyang City, Yantai City, Shandong Province, 265118 Patentee before: Dongfang space technology (Shandong) Co.,Ltd. Country or region before: China Patentee before: Oriental space technology (Beijing) Co.,Ltd. Patentee before: Oriental space (Xi'an) Aerospace Technology Co.,Ltd. Patentee before: Orient Space (Hainan) Technology Co.,Ltd. |