CN115265293A - Rocket booster connection structure - Google Patents
Rocket booster connection structure Download PDFInfo
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- CN115265293A CN115265293A CN202210956941.7A CN202210956941A CN115265293A CN 115265293 A CN115265293 A CN 115265293A CN 202210956941 A CN202210956941 A CN 202210956941A CN 115265293 A CN115265293 A CN 115265293A
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- rocket
- booster
- core stage
- connecting piece
- connection
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- 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
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
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Abstract
The application discloses rocket booster connection structure includes: a rocket core stage; the booster is connected to the side wall of the rocket core stage through a connecting mechanism, when the rocket is in a static state, the axis of the booster is parallel to the axis of the rocket core stage, and the booster is used for providing boosting force for launching and flying of the rocket core stage; the connection mechanism comprises a first connection component; the first connecting assembly comprises a first connecting piece and a second connecting piece, the first connecting piece and the second connecting piece are both rod-shaped, one ends of the first connecting piece and the second connecting piece are respectively connected to the side wall of the rocket core stage, the distance between the two connecting points is a first set distance, the other end of the first connecting piece and the second connecting piece is respectively connected to the side wall of the middle part of the booster, the distance between the two connecting points is a second set distance, and the first set distance is larger than the second set distance. The rocket booster connecting structure can keep the track of the rocket during launching or flying.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to a rocket booster connecting structure.
Background
Rocket aircraft and the like generally comprise a core stage and a booster. The booster is connected with the core stage through a binding device, and the advantages and disadvantages of the binding scheme directly influence the reliability of launch and flight of the carrier rocket. The existing rocket binding mode mostly adopts a statically determinate binding scheme of two binding surfaces, namely two connecting pieces are adopted, one end of each connecting piece is respectively connected to different positions of a rocket core stage, and the other end of each connecting piece is respectively connected to the top and the bottom of the booster. On one hand, when the rocket is launched and flies, the acceleration between the booster and the core stage is different, the relative motion between the rocket core stage and the booster is easily caused by adopting the connection mode, and the flying track of the rocket is influenced; on the other hand, when the booster is long and large, the middle part of the booster is easy to twist in the rocket launching and flying processes, and the flying track of the rocket is also influenced.
Disclosure of Invention
In view of the above-identified deficiencies or inadequacies of the prior art, it would be desirable to provide a rocket booster attachment structure that maintains rocket flight path.
The specific technical scheme is as follows:
the application provides a rocket booster connection structure includes:
a rocket core stage;
the booster is connected to the side wall of the rocket core stage through a connecting mechanism, when the rocket is in an unactivated state, the axis of the booster is parallel to the axis of the rocket core stage, and the booster is used for providing boosting force for launching and flying of the rocket core stage;
the connection mechanism comprises a first connection assembly; the first connecting assembly comprises a first connecting piece and a second connecting piece, the first connecting piece and the second connecting piece are both rod-shaped, one ends of the first connecting piece and the second connecting piece are respectively connected to the side wall of the rocket core stage, the distance between the two connecting points is a first set distance, the other end of the first connecting piece and the second connecting piece is respectively connected to the side wall of the middle part of the booster, the distance between the two connecting points is a second set distance, the first set distance is larger than the second set distance, and the ratio of the second set distance to the length value of the booster is larger than
And is smaller than
。
Optionally, the connection mechanism further comprises a second connection assembly, the second connection assembly comprises a third connection member, the third connection member is connected between the rocket core stage and the booster, and the third connection member is used for keeping the rocket core stage and the booster axis parallel during rocket launching or flying.
Optionally, the first connecting assemblies are provided with two sets and located on two sides of a first plane respectively, and the first plane is a plane formed by the rocket core stage axis and the booster axis.
Optionally, the connection mechanism further includes:
an attachment ring looped over the rocket core stage sidewall, the first, second, and third connectors all connected to the rocket core stage through the attachment ring;
the separating piece is arranged on the connecting ring and used for cutting off the connecting ring when the separating piece is triggered.
Optionally, the first connecting piece and the second connecting piece are respectively hinged between the rocket core stage and the booster, the first connecting piece, the second connecting piece and the third connecting piece are dampers, the deformable directions of the first connecting piece and the second connecting piece are the respective extending directions, and the deformable direction of the third connecting piece is parallel to the axial directions of the rocket core stage and the booster.
Optionally, the first connecting piece, the second connecting piece, and the third connecting piece are all dampers with adjustable rigidity.
Optionally, the booster, the first connecting piece, the second connecting piece and the third connecting piece are combined into a plurality of sets and evenly arranged around the rocket core stage in the circumferential direction.
The beneficial effect of this application lies in:
the first connecting piece and the second connecting piece are arranged between the rocket core stage and the booster, the distance between the first connecting piece and the two connecting points on the rocket core stage is larger than the distance between the first connecting piece and the two connecting points on the booster, and the acceleration of the booster is generally larger than the acceleration of the rocket core stage during rocket launching and flying, so that the booster is used for providing boosting force for the rocket core stage. So that one of the first and second connecting members is located at the upper partOne of the two connecting pieces can support the rocket core stage and the booster, the other one of the two connecting pieces positioned below can pull the rocket core stage and the booster, and the two connecting pieces are matched for keeping the axes of the rocket core stage and the booster parallel. In addition, the connection points of the first connecting piece and the second connecting piece with the booster are positioned in the middle of the booster, and the distance between the two connection points occupies the whole length of the booster
To
And the middle part of the support can be effectively prevented from shaking by combining the acting force of the support and the pulling.
In conclusion, the arrangement can effectively avoid the change of the flight track caused by the structural change of the rocket with the booster with larger slenderness ratio in the launching or flying process.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings in which:
FIG. 1 is a schematic view of a rocket booster attachment configuration provided in an embodiment of the present application;
fig. 2 is a horizontal sectional view of the rocket booster attachment structure of fig. 1.
Reference numbers in the figures: 1, rocket core level; 2, a booster; 311, a first connecting piece; 312, a second connector; 321, a third connecting piece; 331, a connection ring; 332, a separating member.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not to be construed as limiting the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
Referring to fig. 1 and fig. 2, a rocket booster connecting structure capable of maintaining a rocket flight path provided in this embodiment includes:
a rocket core stage 1;
the booster 2 is connected to the side wall of the rocket core stage 1 through a connecting mechanism, when the rocket is in an unactivated state, the axis of the booster 2 is parallel to the axis of the rocket core stage 1, and the booster 2 is used for providing boosting force for launching and flying of the rocket core stage 1;
the connection mechanism comprises a first connection assembly; the first connecting component comprises a first connecting piece 311 and a second connecting piece 312, the first connecting piece 311 and the second connecting piece 312 are both rod-shaped, one ends of the first connecting piece 311 and the second connecting piece 312 are respectively connected to the side wall of the rocket core stage 1, the distance between the two connecting points is a first set distance, the other end of the two connecting pieces is respectively connected to the side wall of the middle part of the booster 2, the distance between the two connecting points is a second set distance, the first set distance is larger than the second set distance, and the ratio of the second set distance to the length value of the booster 2 is larger than the second set distance
And is less than
。
Due to the fact that the first connecting piece 311 and the second connecting piece 312 are arranged between the rocket core stage 1 and the booster 2, the distance between the first connecting piece 311 and the second connecting piece 312 and two connecting points on the rocket core stage 1 is larger than the distance between the first connecting piece 311 and two connecting points on the booster 2 and the acceleration of the booster 2 is generally larger than the acceleration of the rocket core stage 1 during rocket launching and flying, and the booster 2 is used for providing boosting force for the rocket core stage 1. The upper one of the first connector 311 and the second connector 312 would therefore be directed to the rocket core stage1 and the booster 2 play a supporting role, the lower one plays a pulling role on the rocket core stage 1 and the booster 2, and the two connecting pieces are matched for keeping the axes of the rocket core stage 1 and the booster 2 parallel. In addition, the connection points of the first connection piece 311 and the second connection piece 312 with the booster 2 are located in the middle of the booster 2, and the distance between the two connection points occupies the whole length of the booster 2
To is that
The middle part of the support can be effectively prevented from shaking by combining the acting force of the support and the pulling.
In conclusion, the arrangement can effectively avoid the change of the flight track caused by the structural change of the rocket with the booster with larger slenderness ratio in the launching or flying process.
In a preferred embodiment for further maintaining the rocket flight path, the connecting mechanism further comprises a second connecting assembly, the second connecting assembly comprises a third connecting member 321, the third connecting member 321 is connected between the rocket core stage 1 and the booster 2, and the third connecting member 321 is used for keeping the axes of the rocket core stage 1 and the booster 2 parallel during the rocket launching or flying process.
Since the third connecting element 321 is further arranged between the rocket core stage 1 and the booster 2, and the third connecting element 321 is used for keeping the axes of the rocket core stage 1 and the booster 2 parallel, the third connecting element 321 can further keep the axes of the rocket core stage 1 and the booster 2 parallel, so that the rocket flight trajectory is further kept.
In a preferred embodiment for further maintaining the flight path of the rocket, two sets of first connecting assemblies are provided and are respectively positioned at two sides of a first plane, and the first plane is a plane formed by the axis of the rocket core stage 1 and the axis of the booster 2.
Because the connecting assembly comprises two groups of the first connecting pieces 311 and the second connecting pieces 312 which are respectively arranged on two sides of the first plane, the connecting assembly can effectively resist relative movement between the booster 2 and the rocket core stage 1 along a plane perpendicular to the first direction, and further the rocket flight path is further maintained.
Wherein in a preferred embodiment for reducing the overall cost of the rocket, the linkage assembly further comprises:
a connection ring 331, wherein the connection ring 331 is sleeved on the sidewall of the rocket core stage 1, and the first connector 311, the second connector 312 and the third connector 321 are connected to the rocket core stage 1 through the connection ring 331;
a separating member 332, wherein the separating member 332 is disposed on the connection ring 331, and when the separating member 332 is activated, the connection ring 331 is cut off.
After the rocket is lifted and fuel in the booster 2 is exhausted, in order to reduce the load of the rocket, the booster 2 needs to be separated from the rocket core stage 1. Since the first connection part 311, the second connection part 312, and the third connection part 321 are connected to the rocket core stage 1 through the connection ring 331, the connection between the booster 2 and the rocket core stage 1 can be cut off by simply cutting off the connection ring 331. This is achieved by the triggering of the separating element 332. Preferably, the separating member 332 is an explosion bolt, and two explosion bolts are provided, respectively provided at both ends of the connecting ring 331 in the diameter direction. When both of the explosive bolts are activated, the connection ring 331 is cut into both ends and is naturally separated from the rocket core stage 1. This provides a further cost savings over providing an explosive bolt or other separate member on each of the first connector 311, the second connector 312 and the third connector 321.
In a preferred embodiment of reducing the rocket launching load, the first connecting element 311 and the second connecting element 312 are respectively hinged between the rocket core stage 1 and the booster 2, and the first connecting element 311, the second connecting element 312 and the third connecting element 321 are dampers, wherein the deformable directions of the first connecting element 311 and the second connecting element 312 are respectively the extending directions thereof, and the deformable direction of the third connecting element 321 is parallel to the axial direction of the rocket core stage 1 and the booster 2.
When the rocket core stage 1 and the booster 2 move relatively, the flight path of the rocket is affected. To prevent this, a strong and relatively stable connection between the two is required. And because the two have larger mass, if a rigid connection mode is adopted, the outer wall of the rocket core stage 1 needs to be additionally reinforced, so that the launching load of the rocket is increased. Therefore, by adopting the mode of connecting the dampers, small relative motion can be generated between the rocket core stage 1 and the booster 2, the middle part of the booster 2 can also be twisted within a certain range, the two conditions can not generate large influence on the flight path of the rocket, and the outer wall of the rocket core stage 1 does not need to be additionally reinforced. Thereby reducing the load of rocket launching.
Wherein the first connecting piece 311, the second connecting piece 312 and the third connecting piece 321 are all stiffness-adjustable dampers when the rocket flight path can be further maintained.
When the rigidity of the damper is too small, the middle part of the booster 2 can twist within a certain range due to lack of supporting force, so that the flight path of the rocket is influenced; when the damper is too rigid, the relative motion tendency between the rocket core stage 1 and the booster 2 may cause the damage of the outer walls of the two. Therefore, when the rigidity of the damper is adjustable, the relative movement tendency between the rocket core stage 1 and the booster 2 can be controlled within a proper range by adjusting the rigidity of the damper, and the additional reinforcement of the outer walls of the rocket core stage 1 and the booster 2 can be avoided, thereby not only further maintaining the flight path of the rocket, but also further reducing the rocket launching load.
In the preferred embodiment for further maintaining the rocket flight path, the combination of the thrusters 2, the first connecting members 311, the second connecting members 312 and the third connecting members 321 has a plurality of sets and are uniformly arranged around the circumference of the rocket core stage 1.
Because the booster 2, the first connecting member 311, the second connecting member 312 and the third connecting member 321 are combined into a plurality of sets and are uniformly arranged along the circumferential direction of the rocket core stage, the moving direction of the rocket core stage 1 can be kept in the first direction after receiving the thrust from each booster 2 in a plane perpendicular to the first direction in the rocket launching or flying process, and the rocket flying direction is further kept.
The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be appreciated by a person skilled in the art that the scope of the invention as referred to in the present application is not limited to the embodiments with a specific combination of the above-mentioned features, but also covers other embodiments with any combination of the above-mentioned features or their equivalents without departing from the inventive concept. For example, the above features may be replaced with (but not limited to) features having similar functions disclosed in the present application.
Claims (7)
1. A rocket booster connection structure, comprising:
a rocket core stage (1);
the booster (2) is connected to the side wall of the rocket core stage (1) through a connecting mechanism, when the rocket is in an unactivated state, the axis of the booster (2) is parallel to the axis of the rocket core stage (1), and the booster (2) is used for providing boosting force for launching and flying of the rocket core stage (1);
the connection mechanism comprises a first connection assembly; the first connecting component comprises a first connecting piece (311) and a second connecting piece (312), the first connecting piece (311) and the second connecting piece (312) are both rod-shaped, one ends of the first connecting piece and the second connecting piece are respectively connected to the side wall of the rocket core stage (1), the distance between the two connecting points is a first set distance, and the other ends of the two connecting points are respectively connected to the booster2) The distance between two connecting points of the side wall at the middle part is a second set distance, the first set distance is greater than the second set distance, and the ratio of the second set distance to the length value of the booster (2) is greater than
And is less than
。
2. A rocket booster attachment structure according to claim 1, wherein said attachment mechanism further comprises a second attachment assembly, said second attachment assembly comprising a third attachment member (321), said third attachment member (321) being attached between said rocket core stage (1) and said booster (2), said third attachment member (321) being adapted to maintain said rocket core stage (1) and said booster (2) axis parallel during rocket launch or flight.
3. A rocket booster connection structure according to claim 2, wherein there are two sets of said first connection assemblies, and said first connection assemblies are respectively located on both sides of a first plane, and said first plane is a plane formed by the axis of said rocket core stage (1) and the axis of said booster (2).
4. A rocket booster attachment structure according to claim 2, wherein said attachment mechanism further comprises:
a connecting ring (331), wherein the connecting ring (331) is sleeved on the side wall of the rocket core stage (1), and the first connector (311), the second connector (312) and the third connector (321) are all connected to the rocket core stage (1) through the connecting ring (331);
a separating member (332), wherein the separating member (332) is arranged on the connecting ring (331), and when the separating member (332) is triggered, the connecting ring (331) can be cut off.
5. Rocket motor connection according to claim 2, wherein said first connecting element (311) and said second connecting element (312) are hinged between said rocket core stage (1) and said motor (2), respectively, said first connecting element (311), said second connecting element (312) and said third connecting element (321) are dampers, wherein the direction of deformation of said first connecting element (311) and said second connecting element (312) is the respective direction of extension, and the direction of deformation of said third connecting element (321) is parallel to the axial direction of said rocket core stage (1) and said motor (2).
6. Rocket booster connection structure according to claim 5, characterized in that said first connection member (311), said second connection member (312) and said third connection member (321) are each a rigidly adjustable damper.
7. The rocket booster connection structure according to any one of claims 2-6, wherein the combination of the booster (2), the first connecting member (311), the second connecting member (312) and the third connecting member (321) has a plurality of sets and is uniformly arranged around the circumference of the rocket core stage (1).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210956941.7A CN115265293B (en) | 2022-08-10 | 2022-08-10 | Rocket booster connection structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210956941.7A CN115265293B (en) | 2022-08-10 | 2022-08-10 | Rocket booster connection structure |
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| CN115265293A true CN115265293A (en) | 2022-11-01 |
| CN115265293B CN115265293B (en) | 2023-10-20 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115790294A (en) * | 2023-01-30 | 2023-03-14 | 东方空间技术(北京)有限公司 | Binding connecting rod mechanism of rocket booster |
| US20230407819A1 (en) * | 2022-06-17 | 2023-12-21 | Blue Origin, Llc | Multi-volume acoustic resonator for rocket engine |
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| JP2018090160A (en) * | 2016-12-06 | 2018-06-14 | 株式会社Ｉｈｉエアロスペース | Aerial launching rocket and aerial launching method |
| CN109229429A (en) * | 2018-09-19 | 2019-01-18 | 北京理工大学 | A kind of boost motor expansion carrier rocket recyclable device |
| CN213481148U (en) * | 2021-05-13 | 2021-06-18 | 中国科学院力学研究所 | Three-boosting carrier based on modular fixed power system |
| CN114264199A (en) * | 2021-11-23 | 2022-04-01 | 上海宇航***工程研究所 | General core-grade-based rocket overall structure for recovering assembly |
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2022
- 2022-08-10 CN CN202210956941.7A patent/CN115265293B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2018090160A (en) * | 2016-12-06 | 2018-06-14 | 株式会社Ｉｈｉエアロスペース | Aerial launching rocket and aerial launching method |
| CN109229429A (en) * | 2018-09-19 | 2019-01-18 | 北京理工大学 | A kind of boost motor expansion carrier rocket recyclable device |
| CN213481148U (en) * | 2021-05-13 | 2021-06-18 | 中国科学院力学研究所 | Three-boosting carrier based on modular fixed power system |
| CN114264199A (en) * | 2021-11-23 | 2022-04-01 | 上海宇航***工程研究所 | General core-grade-based rocket overall structure for recovering assembly |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20230407819A1 (en) * | 2022-06-17 | 2023-12-21 | Blue Origin, Llc | Multi-volume acoustic resonator for rocket engine |
| US11867139B1 (en) * | 2022-06-17 | 2024-01-09 | Blue Origin, Llc | Multi-volume acoustic resonator for rocket engine |
| US20240191676A1 (en) * | 2022-06-17 | 2024-06-13 | Blue Origin, Llc | Multi-volume acoustic resonator for rocket engine |
| CN115790294A (en) * | 2023-01-30 | 2023-03-14 | 东方空间技术(北京)有限公司 | Binding connecting rod mechanism of rocket booster |
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| Publication number | Publication date |
|---|---|
| CN115265293B (en) | 2023-10-20 |
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