CN115265293B - Rocket booster connection structure - Google Patents
Rocket booster connection structure Download PDFInfo
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- CN115265293B CN115265293B CN202210956941.7A CN202210956941A CN115265293B CN 115265293 B CN115265293 B CN 115265293B CN 202210956941 A CN202210956941 A CN 202210956941A CN 115265293 B CN115265293 B CN 115265293B
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- rocket
- booster
- connecting piece
- core stage
- piece
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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)
- Mechanical Control Devices (AREA)
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Abstract
The application discloses a rocket booster connecting structure, which comprises: rocket core stage; the booster is connected to the side wall of the rocket core stage through a connecting mechanism, the axial line of the booster is parallel to the axial line of the rocket core stage when the rocket is in a static state, and the booster is used for providing boosting force for the launching and flying of the rocket core stage; the connecting mechanism comprises a first connecting 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 rod-shaped, one ends of the first connecting piece and the second connecting piece are connected to the rocket core-level side wall respectively, the distance between the two connecting points is a first set distance, the other ends of the two connecting points are connected to the side wall of the middle part of the booster respectively, 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 in 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-like aircraft typically have a core stage and a booster. Wherein the booster is connected with the core stage by a binding device, and the advantages and disadvantages of the binding scheme directly affect the reliability of launch and flight of the carrier rocket. The existing rocket binding mode mostly adopts a statically determined binding scheme of two binding surfaces, namely two connecting pieces are adopted, one ends of the connecting pieces are respectively connected to different positions of a rocket core stage, and the other ends of the connecting pieces are respectively connected to the top and the bottom of a booster. On one hand, when the acceleration between the booster and the core stage is different in the rocket launching and flying process, the adoption of the connecting mode easily causes the relative movement between the rocket core stage and the booster, so that the flying track of the rocket is influenced; on the other hand, when the booster is relatively long and thin, the middle part of the booster is easy to twist in the rocket launching and flying process, and the flying track of the rocket can be influenced.
Disclosure of Invention
In view of the foregoing drawbacks or shortcomings in the prior art, it is desirable to provide a rocket booster connection structure that maintains the trajectory of a rocket.
The specific technical scheme is as follows:
the application provides a rocket booster connecting structure, comprising:
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 unactuated state, the axial line of the booster is parallel to the axial line of the rocket core stage, and the booster is used for providing boosting force for the launching and flight of the rocket core stage;
the connecting mechanism comprises a first connecting component; the first connecting component comprises a first connecting piece and a second connecting piece, the first connecting piece and the second connecting piece are rod-shaped, one ends of the first connecting piece and the second connecting piece are respectively connected to the rocket core-level side wall, the distance between the two connecting points is a first set distance, the other ends of the first connecting piece and the second connecting piece are 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 thanAnd is less than->。
Optionally, the connection mechanism further comprises a second connection assembly, the second connection assembly comprises a third connection piece, the third connection piece is connected between the rocket core stage and the booster, and the third connection piece is used for keeping the axes of the rocket core stage and the booster parallel when the rocket is launched or flown.
Optionally, the first connecting assembly is provided with two sets, and is respectively located two sides of a first plane, and the first plane is a plane formed by the rocket core level axis and the booster axis.
Optionally, the connection mechanism further includes:
the connecting ring is sleeved on the side wall of the rocket core stage, and the first connecting piece, the second connecting piece and the third connecting piece are all connected to the rocket core stage through the connecting ring;
the separating piece is arranged on the connecting ring, and is 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 all dampers, wherein the deformable directions of the first connecting piece and the second connecting piece are respective extending directions, and the deformable directions of the third connecting piece are parallel to the axis 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 rigidity-adjustable dampers.
Optionally, the booster, the first connecting piece, the second connecting piece and the third connecting piece are combined into a plurality of sets, and are uniformly arranged around the circumference of the rocket core stage.
The application has the beneficial effects that:
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 second connecting piece and the distance between the first connecting piece and the second connecting piece are larger than the distance between the second connecting piece and the second connecting point on the booster, and the acceleration of the booster is generally larger than the acceleration of the rocket core stage in the rocket launching and flying process, so that the booster is used for providing boosting force for the rocket core stage. Therefore, one of the first connecting piece and the second connecting piece, which is positioned above, can play a supporting role on the rocket core stage and the booster, and the other of the first connecting piece and the second connecting piece, which is positioned below, can play a pulling role on the rocket core stage and the booster, and the two connecting pieces are matched, so that the axis of the rocket core stage and the axis of the booster are kept parallel. In addition, as the connection points of the first connecting piece, the second connecting piece and the booster are positioned in the middle of the booster, and the distance between the two connection points occupies the whole length of the boosterTo->The supporting and pulling acting forces are combined, so that the middle part of the support can be effectively prevented from shaking.
In summary, the arrangement can effectively avoid changing the flight track due to the structural change of the rocket with the booster with a larger slender ratio in the launching or flight process.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the detailed description of non-limiting embodiments, made with reference to the accompanying drawings in which:
FIG. 1 is a schematic view of a rocket booster connection structure provided by an embodiment of the present application;
fig. 2 is a horizontal cross-sectional view of the rocket booster connection structure of fig. 1.
Reference numerals in the drawings: 1, rocket core stage; 2, a booster; 311, a first connector; 312, a second connector; 321, a third connector; 331, a connecting ring; 332, separate pieces.
Detailed Description
The application is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the application are shown in the drawings.
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The application will be described in detail below with reference to the drawings in connection with embodiments.
Referring to fig. 1 and fig. 2, a rocket booster connection structure capable of maintaining a rocket flight path according to the present embodiment includes:
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 unactuated 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 the launching and flight of the rocket core stage 1;
the connecting mechanism comprises a first connecting component; the first connecting component comprises a first connecting piece 311 and a second connecting piece 312, wherein the first connecting piece 311 and the second connecting piece 312 are in a rod shape, and the second connecting pieceOne end of the two connecting points 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 points are 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 thanAnd is less than->。
Since the first connecting piece 311 and the second connecting piece 312 are disposed between the rocket core stage 1 and the booster 2, the distance between the first connecting piece 311 and the second connecting piece and the two connecting points on the rocket core stage 1 is greater than the distance between the second connecting piece and the two connecting points on the booster 2, and since the acceleration of the booster 2 is generally greater than the acceleration of the rocket core stage 1 during the rocket launching and flying process, the booster is used for providing boosting force for the rocket core stage 1. Therefore, one of the first connector 311 and the second connector 312 located above will support the rocket core stage 1 and the booster 2, and the other one located below will pull the rocket core stage 1 and the booster 2, and the two connectors cooperate to keep the axes of the rocket core stage 1 and the booster 2 parallel. In addition, since 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, the distance between the two connection points occupies the whole length of the booster 2To->The supporting and pulling acting forces are combined, so that the middle part of the support can be effectively prevented from shaking.
In summary, the arrangement can effectively avoid changing the flight track due to the structural change of the rocket with the booster with a larger slender ratio in the launching or flight process.
Wherein in a preferred embodiment for further maintaining the trajectory of the rocket, the connection mechanism further comprises a second connection assembly, the second connection assembly comprising a third connection 321, the third connection 321 being connected between the rocket core stage 1 and the booster 2, the third connection 321 being adapted to maintain the rocket core stage 1 and the booster 2 axis parallel during the launch or flight of the rocket.
Because the third connecting piece 321 is further arranged between the rocket core stage 1 and the booster 2, and the third connecting piece 321 is used for keeping the axes of the rocket core stage 1 and the booster 2 parallel, the axes of the rocket core stage 1 and the booster 2 can be further kept parallel through the third connecting piece 321, so that the rocket flight track is further kept.
In a preferred embodiment for further maintaining the rocket flight path, the first connecting assemblies are provided with two sets and are respectively positioned at two sides of a first plane, wherein 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, and the two groups of the first connecting pieces and the second connecting pieces are respectively arranged at two sides of the first plane, the connecting assembly can effectively resist the relative movement between the booster 2 and the rocket core stage 1 in the plane vertical to the first direction, and further maintain the rocket flight path.
Wherein in a preferred embodiment for reducing the overall cost of the rocket, the connection assembly further comprises:
the connecting ring 331 is sleeved on the side wall of the rocket core stage 1, and the first connecting piece 311, the second connecting piece 312 and the third connecting piece 321 are all connected to the rocket core stage 1 through the connecting ring 331;
a separating member 332, the separating member 332 is disposed on the connection ring 331, and the connection ring 331 can be cut off when the separating member 332 is triggered.
After the rocket is lifted, when the fuel in the booster 2 is exhausted, the booster 2 needs to be separated from the rocket core stage 1 in order to reduce the load of the rocket. Since 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, the connection between the booster 2 and the rocket core stage 1 can be cut by cutting the connection ring 331. This is achieved by triggering of the release member 332. Preferably, the separating member 332 is an explosion bolt, and the explosion bolts are provided at two ends of the connecting ring 331 in the diameter direction. When both of the explosive bolts are activated, the connection ring 331 is cut off to both ends and naturally separated from the rocket core stage 1. This is more cost effective than providing explosive bolts or other separate pieces on each of the first, second and third connectors 311, 312 and 321.
In a preferred embodiment for reducing the load of rocket launching, the first connecting piece 311 and the second connecting piece 312 are respectively hinged between the rocket core stage 1 and the booster 2, and the first connecting piece 311, the second connecting piece 312 and the third connecting piece 321 are all dampers, wherein the deformable directions of the first connecting piece 311 and the second connecting piece 312 are respectively extending directions, and the deformable direction of the third connecting piece 321 is parallel to the axial directions of the rocket core stage 1 and the booster 2.
When the relative movement of the rocket core stage 1 and the booster 2 occurs, the flight path of the rocket will be affected. To prevent this, a firm and relatively stable connection of the two is required. And because the two are relatively large in 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 rocket launching load is increased. Therefore, by adopting the damper connection mode, small relative movement can be generated between the rocket core stage 1 and the booster 2, torsion in a certain range can also be generated in the middle of the booster 2, the rocket flight trajectory cannot be greatly influenced under the two conditions, and the outer wall of the rocket core stage 1 is not required to be additionally reinforced. And further reduces the load of rocket launching.
Wherein the first connecting piece 311, the second connecting piece 312 and the third connecting piece 321 are all dampers with adjustable rigidity, so that the rocket flight trajectory can be further maintained.
When the rigidity of the damper is too low, the middle part of the booster 2 may twist within a certain range due to lack of supporting force, thereby affecting the rocket flight path; when the damper is too rigid, the relative movement trend between the rocket core stage 1 and the booster 2 may cause damage to the outer walls of the rocket core stage and the booster. Therefore, when the rigidity of the damper is adjustable, the relative movement trend between the rocket core stage 1 and the booster 2 can be controlled in a proper range by adjusting the rigidity of the damper, and the outer walls of the rocket core stage 1 and the booster 2 can be prevented from being additionally reinforced, so that the rocket flight track is further maintained, and the rocket launching load is further reduced.
Wherein in a preferred embodiment for further maintaining the rocket flight trajectory, the combination of the booster 2, the first connector 311, the second connector 312 and the third connector 321 has a plurality of sets, and is uniformly disposed around the circumference of the rocket core stage 1.
Because the booster 2, the first connecting piece 311, the second connecting piece 312 and the third connecting piece 321 are combined in multiple sets and are uniformly arranged along the circumferential direction of the rocket core stage, during the rocket launching or flying process, the movement direction of the rocket core stage 1 can be kept in the first direction after receiving the thrust from each booster 2 in the plane perpendicular to the first direction, and the flying direction of the rocket is further kept.
The above description is only illustrative of the preferred embodiments of the present application and of the principles of the technology employed. It will be appreciated by persons skilled in the art that the scope of the application referred to in the present application is not limited to the specific combinations of the technical features described above, but also covers other technical features formed by any combination of the technical features described above or their equivalents without departing from the inventive concept. Such as the above-mentioned features and the technical features disclosed in the present application (but not limited to) having similar functions are replaced with each other.
Claims (5)
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 unactuated 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 the launching and flight of the rocket core stage (1);
the connecting mechanism comprises a first connecting component; 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 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 ends of the two connecting points are 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 thanAnd is less than->
The connecting mechanism further comprises a second connecting assembly, the second connecting assembly comprises a third connecting piece (321), the third connecting piece (321) is connected between the rocket core stage (1) and the booster (2), and the third connecting piece (321) is used for keeping the axes of the rocket core stage (1) and the booster (2) parallel when the rocket is launched or flown;
the first connecting piece (311) and the second connecting piece (312) are respectively hinged between the rocket core stage (1) and the booster (2), the first connecting piece (311), the second connecting piece (312) and the third connecting piece (321) are all dampers, wherein the deformable directions of the first connecting piece (311) and the second connecting piece (312) are respectively the respective extending directions, and the deformable directions of the third connecting piece (321) are parallel to the axial directions of the rocket core stage (1) and the booster (2).
2. A rocket booster connection structure according to claim 1, wherein the first connection assembly is provided with two sets and is respectively located 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).
3. A rocket booster connection structure as recited in claim 1, wherein said connection mechanism further comprises:
the connecting ring (331), the connecting ring (331) is sleeved on the side wall of the rocket core stage (1), and the first connecting piece (311), the second connecting piece (312) and the third connecting piece (321) are all connected to the rocket core stage (1) through the connecting ring (331);
and the separating piece (332) is arranged on the connecting ring (331), and when the separating piece (332) is triggered, the connecting ring (331) can be cut off.
4. A rocket booster connection structure according to claim 1, wherein the first (311), second (312) and third (321) connectors are all rigidly adjustable dampers.
5. A rocket booster connection structure according to any one of claims 2-4, wherein the booster (2), the first connector (311), the second connector (312) and the third connector (321) are combined in a plurality of sets and are uniformly arranged around the circumference of the rocket core stage (1).
Priority Applications (1)
| 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 CN115265293A (en) | 2022-11-01 |
| CN115265293B true CN115265293B (en) | 2023-10-20 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US11867139B1 (en) * | 2022-06-17 | 2024-01-09 | 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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| 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 | 上海宇航系统工程研究所 | General core-grade-based rocket overall structure for recovering assembly |
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- 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 | 上海宇航系统工程研究所 | General core-grade-based rocket overall structure for recovering assembly |
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