CN218097425U - Solid carrier rocket capable of continuously boosting in atmosphere - Google Patents
Solid carrier rocket capable of continuously boosting in atmosphere Download PDFInfo
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- CN218097425U CN218097425U CN202221447974.0U CN202221447974U CN218097425U CN 218097425 U CN218097425 U CN 218097425U CN 202221447974 U CN202221447974 U CN 202221447974U CN 218097425 U CN218097425 U CN 218097425U
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Abstract
The utility model discloses a solid carrier rocket for continuous boosting in the atmosphere, which belongs to the technical field of spaceflight and comprises a boosting system, a multistage solid power system, a final posture correction control system, an instrument cabin and a fairing; the multistage solid power system, the instrument cabin and the fairing are connected along the length direction of the solid carrier rocket; the multistage solid power system comprises a plurality of subsystems which are sequentially connected along the length direction of the solid carrier rocket; the boosting system is arranged on the outer circumferential direction of the multistage solid power system and is connected with a designated subsystem in the multistage solid power system. The utility model discloses but full play solid carrier rocket's quick response advantage reduces the transmission guarantee requirement to realize low cost of launch and big carrying capacity, effectively satisfy growing satellite and launch the demand fast in batches.
Description
Technical Field
The utility model relates to a space flight technical field, in particular to solid carrier rocket of continuous boosting 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 the carrier rocket, and the solid carrier rocket has obvious technical advantages for meeting the requirement of satellite batch rapid launching due to the characteristics of long-term storage, short launch preparation time, low guarantee requirement, high response speed and the like.
In daily practice, the inventors found that the prior art solutions have the following problems:
the existing solid carrier rockets at home and abroad adopt a core-level serial general configuration, and an all-solid carrier rocket with a binding booster configuration is not available, so that the carrying capacity of the rocket is limited, and the launching cost is difficult to effectively reduce.
Therefore, how to provide a novel solid rocket which can not only fully exert the technical advantages of the solid rocket, but also 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 the solid carrier rocket capable of continuously boosting in the atmosphere, which can fully exert the advantage of quick response of the solid carrier rocket, reduce the requirement of launch guarantee, realize low launch cost and large carrying capacity, and effectively meet the increasing requirement of satellite batch quick launch.
A solid carrier rocket for continuous boosting in an atmosphere comprises a boosting system, a multi-stage solid power system, an end posture correction control system, an instrument cabin and a fairing; the multistage solid power system, the instrument cabin and the fairing are connected along the length direction of the solid carrier rocket; the multistage solid power system comprises a plurality of subsystems which are sequentially connected along the length direction of the solid carrier rocket; the boosting system is arranged on the outer circumferential direction of the multistage solid power system and is connected with a designated subsystem in the multistage solid power system.
Preferably, the multistage solid power system comprises a core primary power system, a core secondary power system and a core tertiary power system which are sequentially connected along the length direction of the solid launch vehicle; the diameter of the core primary power system is the same as that of the core secondary power system; the diameter of the core tertiary power system is not larger than that of the core secondary power system.
Preferably, the boosting system is arranged at the outer periphery of the core primary power system and is connected with the core primary power system in a binding manner; and the core three-stage power system is connected with the instrument cabin.
Preferably, the core primary power system comprises a core primary stage section, a core primary solid rocket engine and a core primary tail section which are sequentially connected.
Preferably, the core secondary power system comprises a core secondary stage section, a core secondary solid rocket engine and a core secondary tail section which are sequentially connected.
Preferably, the core three stage power system comprises a core three stage solid rocket engine; the rear end face of the core three-stage solid rocket engine is fixedly connected with the core two-stage section; the front end face of the core three-stage solid rocket engine is fixedly connected with the instrument cabin.
Preferably, the core three-stage power system comprises a core three-stage solid rocket engine and a core three-stage tail section; the rear end face of the core three-stage solid rocket engine is fixedly connected with the core three-stage tail section; the front end face of the core three-stage solid rocket engine is fixedly connected with the instrument cabin.
Preferably, the boosting system comprises four identical boosting subsystems which are connected in parallel; each boosting subsystem 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 interstage 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 carrier rocket capable of continuously boosting in the atmosphere, all stages of power adopt solid rocket engines, long-term storage of the rocket can be achieved, the rocket launching preparation work content is less, the guarantee requirement is low, and the rapid launching response capability can be achieved.
2) The solid carrier rocket capable of continuously boosting in the atmosphere can effectively improve the carrying capacity of the rocket by using a binding booster method, and can improve the carrying capacity by 3-10 times compared with the existing solid carrier rocket without a binding booster structure.
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 structural diagram of the boosting subsystem.
Wherein the figures include the following reference numerals:
10. a boosting system, 20, a multi-stage solid power system, 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 primary power system, 22, a core secondary power system and 23, a core tertiary power system.
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 launch vehicle for continuous boosting in the atmosphere comprises a boosting system 10, a multistage solid power system 20, a final attitude control system 30, an instrument cabin 40 and a fairing 50, wherein the multistage solid power system 20, the instrument cabin 40 and the fairing 50 are connected along the length direction of the solid launch vehicle. The multistage solid power system 20 comprises a plurality of subsystems which are sequentially connected along the length direction of the solid carrier rocket, and the boosting system 10 is arranged on the outer circumferential direction of the multistage solid power system 20 and is connected with a designated subsystem in the multistage solid power system 20.
Specifically, the multistage solid power system 20 includes a core primary power system 21, a core secondary power system 22 and a core tertiary power system 23 which are sequentially connected along the length direction of the solid launch vehicle. The core tertiary power system 23 is connected to the instrument pod 40. The core primary power system 21 comprises a core primary stage section, a core primary solid rocket engine and a core primary tail section which are sequentially connected. The core secondary power system 21 comprises a core secondary stage section, a core secondary solid rocket engine and a core secondary tail section which are sequentially connected. The core three-stage power system 23 comprises a core three-stage solid rocket engine, the rear end face of the core three-stage solid rocket engine is fixedly connected with the core two-stage section, and the front end face of the core three-stage solid rocket engine is fixedly connected with the instrument cabin 40.
In other embodiments of the present invention, the core three-stage power system 21 includes a core three-stage solid rocket engine and a core three-stage tail section, the rear end face of the core three-stage solid rocket engine is fixedly connected with the core three-stage tail section, and the front end face of the core three-stage solid rocket engine is fixedly connected with the instrument chamber 40.
Preferably, the diameters of the core primary power system 21, the core secondary power system 22 and the core tertiary power system 23 are the same.
In other embodiments of the present invention, the diameter of the core primary power system 21 is the same as the diameter of the core secondary power system 22, and the diameter of the core tertiary power system 21 is smaller than the diameter of the core secondary power system 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 4.2m, and the length of the column section 53 is 5m, so that the requirement of batch loading of various types of satellites can be met.
Preferably, the instrumentation pod 40 is comprised of an inverted cone section and a column section, wherein the inverted cone angle of the inverted cone section of the instrumentation pod 40 is the same as the inverted cone angle of the inverted cone section 54 of the fairing 50.
The boosting system 10 includes four identical boosting sub-systems connected in parallel. The four same boosting subsystems are arranged on the outer periphery of the core primary power system 21 and are connected with the core primary power system 21 in a binding mode through a binding mechanism. Each boosting sub system comprises a boosting stage nose cone 11, a boosting solid rocket engine 12 and a boosting stage tail section 13 which are sequentially connected.
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 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 of the boosting system 10, the core primary power system 21, the core secondary power system 22 and the core tertiary power system 23. The boosting connection and separation mechanism is arranged between the boosting subsystem and the core primary power system 21 in the boosting system 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 and separation mechanism comprises a core-to-secondary connection and separation mechanism arranged between the core primary power system 21 and the core secondary power system 22 and a core-to-secondary connection and separation mechanism arranged between the core secondary power system 22 and the core tertiary power system 23. The core-to-core connection and separation mechanism adopts an explosive bolt and a separation spring. In addition, the core interstage connection and separation mechanism can also adopt a cutting rope and a separation spring.
Further, the core primary power system 21, the core secondary power system 22, the core tertiary power system 23 and the solid rocket engine used for propelling the solid rocket engine 12 all include swinging nozzles.
When the rocket takes off, the four boosting subsystems in the boosting system 10 are ignited to work first, and the core primary power system 21 is ignited to work a period of time before the boosting system 10 finishes working, so that the continuous boosting of the rocket is realized. In the working stage of the boosting system 10, the swing nozzles of the four boosting solid rocket engines 12 are used for carrying out all-rocket three-channel control. Starting from the operation of the core first-stage power system 21, carrying out full-rocket pitching and yawing channel control by the swinging spray pipes of all stages of solid power systems, and carrying out full-rocket rolling channel control by the final posture correction control system 30.
For ease of description, spatially relative terms, such as "on," "over," "on top of," "above," and the like, may be used herein to describe one device or feature's spatial relationship to another device 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 other sequences 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 (10)
1. A solid carrier rocket for continuous boosting in the atmosphere is characterized by comprising a boosting system, a multi-stage solid power system, a final posture correction control system, an instrument cabin and a fairing; the multistage solid power system, the instrument cabin and the fairing are connected along the length direction of the solid carrier rocket; the multistage solid power system comprises a plurality of subsystems which are sequentially connected along the length direction of the solid carrier rocket; the boosting system is arranged on the outer circumferential direction of the multistage solid power system and is connected with a designated subsystem in the multistage solid power system.
2. The solid launch vehicle of claim 1 wherein the multi-stage solid power system comprises a core primary power system, a core secondary power system and a core tertiary power system connected in series along the length of the solid launch vehicle; the diameter of the core primary power system is the same as that of the core secondary power system; the diameter of the core tertiary power system is not larger than that of the core secondary power system.
3. The solid launch vehicle of claim 2, wherein the propulsion system is disposed circumferentially about the core primary power system and is in bundled connection with the core primary power system; and the core three-stage power system is connected with the instrument cabin.
4. The solid launch vehicle of claim 2 wherein said core primary power system comprises a core primary stage section, a core primary solid rocket motor, and a core primary tail section connected in series.
5. The solid launch vehicle of claim 2, wherein said core secondary power system comprises a core secondary stage section, a core secondary solid rocket motor, and a core secondary tail section connected in series.
6. The solid launch vehicle of claim 2 wherein said core three stage power system comprises a core three stage solid rocket engine; the rear end face of the core three-stage solid rocket engine is fixedly connected with the core two-stage section; the front end face of the core three-stage solid rocket engine is fixedly connected with the instrument cabin.
7. The solid launch vehicle of claim 2 wherein said core tertiary power system comprises a core tertiary solid rocket engine and a core tertiary tail section; the rear end face of the core three-stage solid rocket engine is fixedly connected with the core three-stage tail section; the front end face of the core three-stage solid rocket engine is fixedly connected with the instrument cabin.
8. The solid launch vehicle of claim 1 wherein said booster system comprises four identical booster subsystems in parallel with each other; each boosting subsystem comprises a boosting stage nose cone, a boosting solid rocket engine and a boosting stage tail section which are sequentially connected.
9. A solid launch vehicle according to claim 8, characterised in that the booster stage nose cone is in the form of a positive cone with a cone angle of 30 °.
10. A solid launch vehicle according to any one of claims 1-9 and further comprising a thrust coupling and decoupling mechanism and a core interstage coupling and decoupling 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 |
|---|---|---|---|
| CN202221447974.0U CN218097425U (en) | 2022-06-10 | 2022-06-10 | Solid carrier rocket capable of continuously boosting in atmosphere |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221447974.0U CN218097425U (en) | 2022-06-10 | 2022-06-10 | Solid carrier rocket capable of continuously boosting in atmosphere |
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| Publication Number | Publication Date |
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| CN218097425U true CN218097425U (en) | 2022-12-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221447974.0U Active CN218097425U (en) | 2022-06-10 | 2022-06-10 | Solid carrier rocket capable of continuously boosting in atmosphere |
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| CN (1) | CN218097425U (en) |
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- 2022-06-10 CN CN202221447974.0U patent/CN218097425U/en active Active
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