CN117516292A - Pin-shaped carrier rocket - Google Patents
Pin-shaped carrier rocket Download PDFInfo
- Publication number
- CN117516292A CN117516292A CN202311770595.4A CN202311770595A CN117516292A CN 117516292 A CN117516292 A CN 117516292A CN 202311770595 A CN202311770595 A CN 202311770595A CN 117516292 A CN117516292 A CN 117516292A
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- Prior art keywords
- rocket
- secondary core
- boosting
- booster
- stage
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- 235000015842 Hesperis Nutrition 0.000 claims abstract description 36
- 235000012633 Iberis amara Nutrition 0.000 claims abstract description 36
- 210000001503 joint Anatomy 0.000 claims abstract description 18
- 238000000926 separation method Methods 0.000 claims abstract description 16
- 239000007800 oxidant agent Substances 0.000 claims description 21
- 239000000446 fuel Substances 0.000 claims description 14
- 230000001590 oxidative effect Effects 0.000 claims description 14
- 239000002828 fuel tank Substances 0.000 claims description 10
- 238000004891 communication Methods 0.000 claims description 6
- 239000007921 spray Substances 0.000 claims description 5
- 238000013461 design Methods 0.000 abstract description 7
- 238000011161 development Methods 0.000 abstract description 6
- 241000967522 Eruca pinnatifida Species 0.000 description 33
- 239000007788 liquid Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The application relates to the technical field of aerospace, in particular to a delta carrier rocket, which comprises: a boosting rocket combination system without a primary core stage, a secondary core stage system, a control cabin and a fairing; the booster rocket combination system without the primary core stage comprises: the plurality of boosting rockets are uniformly distributed around a central shaft, the size of a space surrounded by the plurality of boosting rockets is not smaller than the diameter of the lower section of the secondary core system, the secondary core system is coaxial with the central shaft, the lower section of the secondary core system stretches into the space, and the side surface of the lower section of the secondary core system is fixedly connected with the side surface of the upper section of the boosting rocket; the lower end of the control cabin is in butt joint and fixation with the upper end of the secondary core system, and the lower end of the fairing is in butt joint and fixation with the upper end of the control cabin. The carrier rocket design can be simplified, the development period is shortened, the cost is reduced, the inter-stage separation interference is reduced, the bottom thermal environment is optimized, and the reliability of the carrier rocket is improved as a whole.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to a delta carrier rocket.
Background
The connection mode of the multistage carrier rocket mainly comprises three modes of serial connection, parallel connection and mixed connection, and in order to improve the carrying capacity of the multistage carrier rocket, the current large multistage carrier rocket mostly adopts a mixed connection mode of connecting a primary core stage with a secondary core stage in parallel and connecting more than three core stages in series. The method can utilize the ready-made rockets to form the large-sized carrier rockets in a parallel mode, can simplify and accelerate the development progress of the large-sized rockets, has the advantages of low cost, short period and high reliability, and also enables the carrier rockets to have larger carrying capacity. In addition, hybrid-coupled launch vehicles combine many of the advantages of serial and parallel rockets. For example, rockets are short in length and relatively compact in construction.
However, hybrid-coupled launch vehicles inherit some of the disadvantages of both serial and parallel rockets. For example, each core stage requires a separate design, increasing lead time and cost; the primary core stage and the boosting rocket are still in a parallel connection mode, the radial size of the boosting rocket is still larger, and when more engines are arranged, the distance between the engines of the primary core stage and the jet pipe of the boosting rocket is relatively short, and the thermal environment at the bottom of the rocket body caused by jet interference or radiation of the engines is relatively poor; in addition, the interstage connection mechanism is still more complex and complex to assemble, so that the overall structure of the carrier rocket has low efficiency and larger take-off quality; in addition, cold separation or heat separation is generally adopted when the primary core stage and the secondary core stage are separated, if cold separation is adopted, the runaway time of the carrier rocket is longer, if heat separation is adopted, the engine jet flow forms a more complex high-pressure high-heat environment between stages, the inter-stage separation interference is large, and the safe flight of the carrier rocket is not facilitated.
Therefore, how to simplify the design of the carrier rocket, shorten the development period, reduce the cost, reduce the inter-stage separation interference, optimize the bottom thermal environment, and integrally improve the reliability of the carrier rocket is a technical problem which is urgently needed to be solved by the person skilled in the art at present.
Disclosure of Invention
The carrier rocket in a delta shape is provided to simplify the design of the carrier rocket, shorten the development period, reduce the cost, reduce the inter-stage separation interference, optimize the bottom thermal environment and improve the reliability of the carrier rocket as a whole.
In order to solve the technical problems, the application provides the following technical scheme:
a chevron shaped launch vehicle comprising: a boosting rocket combination system without a primary core stage, a secondary core stage system, a control cabin and a fairing; wherein, the boost rocket combination system of no one-stage core level includes: the plurality of boosting rockets are uniformly distributed around a central shaft, the size of a space surrounded by the plurality of boosting rockets is not smaller than the diameter of the lower section of the secondary core system, the secondary core system is coaxial with the central shaft, the lower section of the secondary core system stretches into the space, and the side surface of the lower section of the secondary core system is fixedly connected with the side surface of the upper section of the boosting rocket; the lower end of the control cabin is in butt joint and fixation with the upper end of the secondary core system, and the lower end of the fairing is in butt joint and fixation with the upper end of the control cabin.
A delta carrier rocket as described above wherein, preferably, the booster rocket combination system without a primary core stage comprises: three boosting rockets are distributed in a delta shape.
A delta carrier rocket as described above wherein the separation between the secondary core system and the booster rocket combination system without the primary core is preferably thermal.
A delta launch vehicle as described above, wherein the booster rocket preferably comprises: a universal rocket module and a booster nose cone; the lower end of the booster nose cone is in butt joint and fixed with the upper end of the general rocket module; the secondary core system adopts a general rocket module.
A delta carrier rocket as described above, wherein preferably the universal rocket module comprises: the device comprises an engine, a fuel storage tank, an oxidant storage tank, a tank compartment and a tail section; the engine is arranged below the fuel storage tank，The spray pipe of the engine extends to the outside of the shell from the lower end of the tail section; the fuel tank and the oxidizer tank are in communication with the engine.
The delta carrier rocket as described above, wherein preferably one or more advanced core systems are sequentially butt-jointed and fixed between the upper end of the secondary core system and the lower end of the control cabin.
A chevron shaped launch vehicle comprising: a boosting rocket combination system without a primary core stage, a secondary core stage system, a control cabin and a fairing; wherein, the boost rocket combination system of no one-stage core level includes: the plurality of boosting rockets are uniformly distributed around a central shaft, the size of a space surrounded by the plurality of boosting rockets is smaller than the diameter of the lower section of the secondary core system, the lower end of the secondary core system is fixedly connected with the upper ends of the plurality of boosting rockets, and the secondary core system is coaxial with the central shaft; the lower end of the control cabin is in butt joint and fixation with the upper end of the secondary core system, and the lower end of the fairing is in butt joint and fixation with the upper end of the control cabin.
A delta carrier rocket as described above wherein, preferably, the booster rocket combination system without a primary core stage comprises: three boosting rockets are distributed in a delta shape.
A delta launch vehicle as described above, wherein the booster rocket preferably comprises: a universal rocket module and a booster nose cone; the lower end of the booster nose cone is in butt joint and fixed with the upper end of the general rocket module; the secondary core system adopts a general rocket module.
A delta carrier rocket as described above, wherein preferably the universal rocket module comprises: the device comprises an engine, a fuel storage tank, an oxidant storage tank, a tank compartment and a tail section; the engine is arranged below the fuel storage tank，The spray pipe of the engine extends to the outside of the shell from the lower end of the tail section; the fuel tank and the oxidizer tank are in communication with the engine.
Compared with the background technology, the design of the carrier rocket in the shape of the Chinese character 'pin' can be simplified, the development period is shortened, the cost is reduced, the inter-stage separation interference is reduced, the bottom thermal environment is optimized, and the reliability of the carrier rocket is improved as a whole.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present invention, and other drawings may be obtained according to these drawings for a person having ordinary skill in the art.
FIG. 1 is a front view of a first configuration of a chevron shaped launch vehicle provided by an embodiment of the present application;
FIG. 2 is a front view of a second configuration of a chevron shaped launch vehicle provided by an embodiment of the present application;
FIG. 3 is a flight attitude diagram of a chevron shaped launch vehicle provided by an embodiment of the present application;
FIG. 4 is a layout view of a first configuration of a booster rocket combination system provided by an embodiment of the present application;
FIG. 5 is a layout of a second configuration of a booster rocket combination system provided by an embodiment of the present application;
fig. 6 is a schematic diagram of a generic rocket module of a delta carrier rocket provided in an embodiment of the present application.
Detailed Description
Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the invention.
As shown in fig. 1 to 3, the present application provides a delta carrier rocket, including: a booster rocket combination system 100 without a primary core stage, a secondary core stage system 200, a control cabin 300 and a fairing 400; wherein, booster rocket combination system 100 without a primary core stage comprises: a plurality of booster rockets 110, the plurality of booster rockets 110 being evenly distributed about the central axis.
The size of the space surrounded by the plurality of booster rockets 110 is not smaller than the diameter of the lower section of the secondary core system 200, the secondary core system 200 is coaxial with the central shaft, the lower section of the secondary core system 200 extends into the space, and the side surface of the secondary core system 200 is fixedly connected with the side surface of the upper section of the booster rockets 110. Alternatively, the space surrounded by the plurality of booster rockets 110 is smaller in size than the diameter of the lower section of the secondary core system 200, the lower end of the secondary core system 200 cannot extend into the space, but the lower end of the secondary core system 200 is fixedly connected to the upper ends of the booster rockets 110, and the secondary core system 200 is coaxial with the central shaft. For the connection mode of the two-stage core system 200 and the booster rocket combination system 100 without a one-stage core, the adjustment can be performed according to the actual task requirement, that is, one of the relative positions of the two-stage core systems 200 can be selected according to the actual task requirement, and the design is more flexible.
The booster rocket combination system 100 without a primary core stage is adopted, and the booster rocket combination system is mainly used as power for the carrier rocket to fly at low altitude; and the booster rocket 110 and the secondary core system 200 are completely separated at one time by adopting the booster rocket combination system 100 with the primary core stage, so that the secondary core stage separation is not needed, the launching flow is reduced, the influence of the separation between the primary core stage and the secondary core system 200 is avoided, the inter-stage separation interference is reduced, the bottom thermal environment is optimized, and the reliability of the carrier rocket is improved as a whole. Because there is no primary core stage, there is sufficient space between the multiple booster rockets 110 to optimize the aerodynamic thermal environment, and the radial envelope size of the booster rocket combination system 100 without a primary core stage can be further reduced, so that the structure is more compact.
Optionally, the booster rocket combination system 100 without a primary core stage includes: three booster rockets 110, the three booster rockets 110 are distributed in a delta shape, that is, the three booster rockets 110 are distributed to three vertexes of an equilateral triangle. The number of the booster rockets 110 can be adjusted according to the task requirements, and is not limited to three. Alternatively, as shown in fig. 1 and 4, the space surrounded by the three booster rockets 110 is not smaller than the lower section of the secondary core system 200, so that the lower section of the secondary core system 200 can extend into the space. When the booster rocket combination system 100 without a primary core stage adopts this configuration, the separation between the secondary core stage system 200 and the booster rocket combination system 100 without a primary core stage can adopt thermal separation to reduce the runaway time and the possibility of collision with the booster rocket 110; in addition, the engine jet is not affected by the following stages, and a high-pressure high-heat environment is not generated. Alternatively, as shown in fig. 2 and 5, three booster rockets 110 enclose a space smaller than the lower section of the secondary core system 200, such that the lower section of the secondary core system 200 cannot extend into the space.
As shown in fig. 1, the booster rocket 110 includes: a universal rocket module 500 and a booster nose cone 111; the lower end of booster nose cone 111 is butt-fixed with the upper end of universal rocket module 500, thereby forming booster rocket 110. In addition, the two-stage core system 200 employs the universal rocket module 500, that is, the two-stage core system 200 and the main body of the booster rocket 110 have the same structure, and all the two-stage core system and the booster rocket 110 employ the identical universal rocket module 500.
By adopting the identical general rocket module 500 for the booster rocket 110 and the secondary core system 200, each core is prevented from being designed independently, so that the modularization and universalization targets of the carrier rocket are realized, the development period is shortened, and the research and development cost and the production cost are reduced. Moreover, the universal rocket modules 500 in the present application are all recyclable rocket modules, thereby further reducing the cost.
On the above basis, as shown in fig. 6, the universal rocket module 500 includes: tank compartment 510, engine 520, fuel tank 530, oxidant tank 540, and tail section 550; the engine 520 is located below the fuel tank 530, and the nozzle of the engine 520 extends from the lower end of the tail section 550 to the outside of the tail section 550 to spray tail flame to the outside, and the maneuverability of the carrier rocket can be improved by swinging the nozzle to perform gesture control; the fuel tank 530 and the oxidant tank 540 are in communication with the engine 520, specifically, may be in communication with the engine 520 through a propellant system, valves and regulators, engine assembly components, etc., to provide fuel and oxidant to the engine 520; tank compartment 510 is located in fuel tank 530 and oxidant tank 540. When the booster rocket 110 adopts the universal rocket module 500, the lower end of the booster nose cone 111 is in butt joint and fixed with the upper end of the oxidant storage tank 540; when the universal rocket module 500 is adopted by the secondary core stage 200, the lower end of the control cabin 300 is in butt joint and fixed with the upper end of the oxidant storage tank 540.
Optionally, the fuel reservoir 530 is located proximate to the engine 520 and the oxidant reservoir 540 is located remotely from the engine 520. Still alternatively, the oxidizer reservoir 540 is located near the engine 520 and the fuel reservoir 530 is located far from the engine 520. The order of the fuel tank 530 and the oxidizer tank 540 may be adjusted accordingly based on the design of the center of gravity of the launch vehicle and the mission requirements. Alternatively, the common rocket module 500 of the booster rocket 110 and the common rocket module 500 of the secondary core system 200 use the same liquid propellant, namely the same liquid fuel is stored in the fuel storage tank 530 of the common rocket module 500 of the booster rocket 110 and the fuel storage tank 530 of the common rocket module 500 of the secondary core system 200, and the same liquid oxidant is stored in the oxidant storage tank 540 of the common rocket module 500 of the booster rocket 110 and the oxidant storage tank 540 of the common rocket module 500 of the secondary core system 200. Of course, the powertrain modules may also be replaced according to mission requirements, including engine type, number of engines, fuel tank type, and oxidizer tank type.
With continued reference to fig. 1 and 2, the lower end of the control cabin 300 is butt-fixed with the upper end of the secondary core system 200, and the lower end of the fairing 400 is butt-fixed with the upper end of the control cabin 300. Wherein, a control system of the carrier rocket is arranged in the control cabin 300 and is used for controlling the carrier rocket; mounted within the fairing 400 is a payload such as: satellites to transmit payloads to predetermined orbits. The control pod 300 and fairing 400 herein are consistent with conventional launch vehicle structures and system functions.
On the basis of the above, one or more advanced core stage systems may be further sequentially butt-jointed and fixed between the upper end of the secondary core stage system 200 and the lower end of the control cabin 300, for example: the three-level core level system is fixedly connected between the upper end of the two-level core level system 200 and the lower end of the control cabin 300 in a butt joint mode, or the three-level core level system and the four-level core level system are sequentially connected between the upper end of the two-level core level system 200 and the lower end of the control cabin 300 in a butt joint mode so as to adapt to different load or track emission requirements. In addition, these advanced core systems all employ a generic rocket module 500.
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. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.
Claims (10)
1. A chevron shaped launch vehicle, comprising: a boosting rocket combination system without a primary core stage, a secondary core stage system, a control cabin and a fairing;
wherein, the boost rocket combination system of no one-stage core level includes: the plurality of boosting rockets are uniformly distributed around a central shaft, the size of a space surrounded by the plurality of boosting rockets is not smaller than the diameter of the lower section of the secondary core system, the secondary core system is coaxial with the central shaft, the lower section of the secondary core system stretches into the space, and the side surface of the lower section of the secondary core system is fixedly connected with the side surface of the upper section of the boosting rocket;
the lower end of the control cabin is in butt joint and fixation with the upper end of the secondary core system, and the lower end of the fairing is in butt joint and fixation with the upper end of the control cabin.
2. A delta carrier rocket as recited in claim 1, wherein the booster rocket combination system without a primary core stage comprises: three boosting rockets are distributed in a delta shape.
3. A delta carrier rocket according to claim 1 or 2, wherein the separation between the secondary core system and the booster rocket combination system without a primary core is thermal.
4. A delta launch vehicle according to claim 1 or claim 2, wherein the booster rocket comprises: a universal rocket module and a booster nose cone; the lower end of the booster nose cone is in butt joint and fixed with the upper end of the general rocket module;
the secondary core system adopts a general rocket module.
5. The delta carrier rocket of claim 4, wherein the universal rocket module comprises: the device comprises an engine, a fuel storage tank, an oxidant storage tank, a tank compartment and a tail section; the engine is positioned below the fuel storage tank, and the spray pipe of the engine extends to the outside of the tail section from the lower end of the tail section;
the fuel tank and the oxidizer tank are in communication with the engine.
6. A delta carrier rocket according to claim 1 or 2, wherein one or more advanced core systems are sequentially butt-jointed and fixed between the upper end of the secondary core system and the lower end of the control cabin.
7. A chevron shaped launch vehicle, comprising: a boosting rocket combination system without a primary core stage, a secondary core stage system, a control cabin and a fairing;
wherein, the boost rocket combination system of no one-stage core level includes: the plurality of boosting rockets are uniformly distributed around a central shaft, the size of a space surrounded by the plurality of boosting rockets is smaller than the diameter of the lower section of the secondary core system, the lower end of the secondary core system is fixedly connected with the upper ends of the plurality of boosting rockets, and the secondary core system is coaxial with the central shaft;
the lower end of the control cabin is in butt joint and fixation with the upper end of the secondary core system, and the lower end of the fairing is in butt joint and fixation with the upper end of the control cabin.
8. A delta carrier rocket as recited in claim 7, wherein the booster rocket combination system without a primary core stage comprises: three boosting rockets are distributed in a delta shape.
9. A delta launch vehicle according to claim 6 or claim 7, wherein the booster rocket comprises: a universal rocket module and a booster nose cone; the lower end of the booster nose cone is in butt joint and fixed with the upper end of the general rocket module;
the secondary core system adopts a general rocket module.
10. A delta carrier rocket as recited in claim 9, wherein the universal rocket module comprises: the device comprises an engine, a fuel storage tank, an oxidant storage tank, a tank compartment and a tail section;
the engine is positioned below the fuel storage tank, and the spray pipe of the engine extends to the outside of the shell from the lower end of the tail section;
the fuel tank and the oxidizer tank are in communication with the engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311770595.4A CN117516292A (en) | 2023-12-20 | 2023-12-20 | Pin-shaped carrier rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311770595.4A CN117516292A (en) | 2023-12-20 | 2023-12-20 | Pin-shaped carrier rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117516292A true CN117516292A (en) | 2024-02-06 |
Family
ID=89744076
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311770595.4A Pending CN117516292A (en) | 2023-12-20 | 2023-12-20 | Pin-shaped carrier rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117516292A (en) |
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2023
- 2023-12-20 CN CN202311770595.4A patent/CN117516292A/en active Pending
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