CN112964139A - Grid wing, novel rocket stage interval structure and application - Google Patents
Grid wing, novel rocket stage interval structure and application Download PDFInfo
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- CN112964139A CN112964139A CN202110256777.4A CN202110256777A CN112964139A CN 112964139 A CN112964139 A CN 112964139A CN 202110256777 A CN202110256777 A CN 202110256777A CN 112964139 A CN112964139 A CN 112964139A
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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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
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- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
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Abstract
The invention belongs to the technical field of rocket separation, and discloses a grid wing, a novel rocket stage interval structure and application. The grid wing/grid rudder is manufactured by adopting a titanium alloy SLM printing, casting or welding mode, and is arranged at the top of the first-stage rocket along the circumferential direction, and the upper-stage rocket and the lower-stage rocket are both provided with rocket engines. The invention is characterized in that a plurality of grid wings are arranged on the upper stage rocket close to the stage section along the circumferential direction, the grid wings are in a retracted state before the rocket is separated, and are connected with the upper stage rocket in a fixed connection and destructible or non-fixed connection and separable mode, and the grid wings transmit load to the upper stage rocket alone or together with other stage bearing structures. The invention reduces weight, reduces emission cost and improves emission efficiency.
Description
Technical Field
The invention belongs to the technical field of rocket separation, and particularly relates to a grid wing, a novel rocket stage interval structure and application.
Background
At present, in order to meet the rocket launching requirements, improve the rocket launching efficiency and reduce the launching cost, rocket sublevel recovery is vigorously carried out at home and abroad, and the recovery process is mostly controlled by grid wings.
The grid wings are used as lifting surfaces and control surfaces of an aerial aircraft and a water navigation device, so that the lift characteristic of the grid wings can be improved, the stability and the controllability of the grid wings are improved, and meanwhile, the grid wings are ensured to have sufficient specific strength and specific rigidity in each flight phase.
Before rocket stage section separation in the technical field of traditional rockets, the stage section is used as a main stage load bearing structure, and the grid wings are used as parts of a sub-stage rocket and tightly attached to the rocket, so that the aerodynamic appearance of the rocket is influenced, and no function is played in the launching and lifting process of the rocket; and unnecessary load is generated, thereby increasing part of the weight and reducing the emission efficiency.
Through the above analysis, the problems and defects of the prior art are as follows: the grid wing in the prior art not only influences the aerodynamic shape of the rocket, but also generates unnecessary load in the launching and lifting process of the rocket, increases part of weight and reduces launching efficiency. In order to meet the strength requirement of the interstage connection structure, the interstage structure is heavy, complex in structure and heavy, and the weight of the structure is further increased by adopting grid wings for recycling.
The difficulty in solving the above problems and defects is: in the past, the interstage structure and the recovery grid wing of the rocket are designed independently, and in order to ensure the structural strength, the interstage connecting section has heavy weight and complex structure; in order to effectively control the rocket attitude and aerodynamic force in the recovery process, a high-strength grid wing must be additionally designed, but before recovery, the grid wing is installed on the rocket as an attachment, and the weight of the grid wing is huge as redundant mass before launching and recovery, which cannot be avoided.
The significance of solving the problems and the defects is as follows: the invention relates to a brand-new rocket stage section structure design, and aims to improve the stage section structure design on the basis of the existing multi-stage rocket, reduce the weight of the rocket and improve the launching efficiency. Provides a good structural idea for the future rocket launching and recovery process.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a grid wing, a novel rocket stage interval structure, a control method and application. The invention optimizes the structure, reduces unnecessary weight and improves the strength-to-mass ratio under the condition of ensuring the complete rocket lifting and recovering functions. Meanwhile, the invention overcomes the defects of the prior art, and replaces part or all of the rocket interstage structures (skin and reinforcing rib structures) with the grid wings, thereby reducing the weight of the rocket and reducing the launching cost.
The invention is realized in this way, a novel rocket stage interval structure, including the upper stage rocket, the lower stage rocket, the novel rocket stage interval structure also has:
at least one grid wing or grid rudder;
the grid wings or the grid rudders are uniformly folded and arranged on the rocket at the lower stage along the circumferential direction;
the grid wings or grid rudders are connected with the rocket at the upper stage in a fixing, destructible or non-fixing and separable mode.
Further, the grid wings or grid rudders are in a retracted state before the upper stage rocket is separated from the lower stage rocket, and transmit load to the upper stage rocket alone or together with other inter-stage bearing structures.
Further, the grid wings or grid rudders replace the skin reinforcing rib structure between the upper stage rocket and the lower stage rocket wholly or partially before the upper stage rocket and the lower stage rocket are separated.
Further, when the upper stage rocket and the lower stage rocket are ready to be separated, the fixed connection structure is broken or the separable structure is separated, so that the grid wings or the grid rudders are disconnected from the upper stage rocket.
Further, the grid wings or grid rudders are in a deployed state when the upper stage rocket and the lower stage rocket are ready to be separated.
Further, the grid wings or grid rudders are unfolded after the upper stage rocket and the lower stage rocket are separated, and are used for regulating and controlling the falling posture of the lower stage rocket.
Another object of the present invention is to provide a grid fin, which is made of a titanium alloy or an aluminum alloy material.
Further, the grid wings are replaced by grid rudders; the shape radian of the grid wings or the grid rudders is the same as that of the rocket at the lower stage.
It is another object of the present invention to provide an airborne vehicle that carries the novel rocket stage bay structure for improving the lift characteristics of the airborne vehicle at the lifting and control surfaces.
It is another object of the present invention to provide a marine vessel that carries the novel rocket stage bay structure for improving the lift characteristics of an aerial vehicle at lifting and control surfaces.
By combining all the technical schemes, the invention has the advantages and positive effects that:
the invention installs a plurality of grid wings on the upper stage rocket near the stage section along the circumferential direction, the grid wings are in a retracting state before the rocket is separated, and are connected with the upper stage rocket in a fixed connection and destructible or non-fixed connection and separable mode, and the grid wings transmit load to the upper stage rocket alone or together with other inter-stage bearing structures, thereby replacing the structures such as the bearing structures (such as trusses, ribs, skins and the like) which are independently adopted among the stages of the original rocket. The grid wing has high aerodynamic load and large structural strength in the recovery process, and the load-bearing capacity and the load transfer capacity are strong when the grid wing is used as a part of a rocket interstage connecting structure in the invention, so that the structural strength requirement is met. Therefore, the invention adopts the integrated design of the separation grid rudder and the interstage structure, and takes the grid rudder as a part of the connection structure between the separation front stages of the rocket, thereby reducing the weight, reducing the launching cost and improving the launching efficiency. Meanwhile, in the rocket recovery process, the recovery process can be regulated, the ideal recovery speed is achieved, and the drop point is controlled.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments of the present application will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present application, and it is obvious for those skilled in the art that other drawings can be obtained from the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a grid wing in a novel rocket stage interval structure including a grid wing structure according to an embodiment of the present invention when the grid wing is deployed.
Fig. 2 is a schematic structural diagram of a closing of a grid wing in a novel rocket stage interval structure including a grid wing structure according to an embodiment of the present invention.
Fig. 3 is a schematic structural diagram of a post-separation recovery stage of an upper stage and a lower stage in a novel rocket stage interval structure including a grid wing structure according to an embodiment of the present invention.
Fig. 4 is a schematic structural diagram of an upper and lower connection stage provided in the embodiment of the present invention.
Fig. 5 is a schematic view of a connection unlocking structure of a stage section and an upper rocket according to an embodiment of the present invention.
Fig. 6 is a schematic diagram of a preliminary deployment structure of the grid wings provided by the embodiment of the invention.
Fig. 7 is a schematic structural diagram of upper and lower stage rocket separation and grid wing complete deployment provided by the embodiment of the invention.
In the figure: 1. a top stage rocket; 2. a lower stage rocket; 3. a grid rudder.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
In view of the problems in the prior art, the present invention provides a novel rocket stage slot structure including a grid wing structure and a control method thereof, and the present invention is described in detail below with reference to the accompanying drawings.
The invention provides a grid wing which is made of titanium alloy, aluminum alloy and other materials.
The part of the interstage connection bearing and load transferring structure is replaced by a grid wing or a grid rudder.
The invention also provides a novel rocket stage interval structure comprising the grid wings, and the novel rocket stage interval structure is provided with:
at least one grid wing or grid rudder;
the grid wings or the grid rudders are uniformly folded and arranged at the position, close to the stage section, of the lower stage rocket along the circumferential direction;
the grid wings or grid rudders are connected with the rocket at the upper stage in a fixing, destructible or non-fixing and separable mode. The shape radian of the grid wings or grid rudders is the same as that of the rocket of the lower stage.
When the upper stage rocket and the lower stage rocket are ready to be separated, the fixed connection structure is broken or the separable structure is separated, so that the grid wings or the grid rudders are disconnected with the upper stage rocket.
The grid wings or grid rudders are in a retracted state before rocket separation, and transmit load to the rocket in the upper stage independently or together with the rest inter-stage bearing structures.
Specifically, as a preferred embodiment, as shown in fig. 1 to fig. 3, the novel rocket-level block structure including the grid wing structure provided by the embodiment of the present invention includes: an upper stage rocket 1, a lower stage rocket 2, and a grid rudder (a plurality of grid wings) 3; the upper stage rocket 1 is connected with the lower stage rocket 2, and the lower stage rocket 2 is folded with grid wings/grid rudders 3; the grid wing/grid rudder 3 is manufactured by adopting titanium alloy SLM printing and is arranged at the top of the first-stage rocket along the circumferential direction.
Wherein, the upper stage rocket 1 and the lower stage rocket 2 are both provided with rocket engines. Before the upper stage rocket 1 and the lower stage rocket 2 are separated, the lower stage rocket 2 provides power; after the upper rocket stage and the lower rocket stage are separated, jet flow after the engine of the rocket 1 at the upper stage is ignited impacts the front end socket and the grid wings at the lower stage to generate separation power in the thermal separation process, and air mainly acts on the rocket at the lower stage and the grid wings to provide the separation power in the cold separation process.
The grid wing/grid rudder 3 is used as a part of a connection structure of a stage section for connecting an upper stage rocket 1 and a lower stage rocket 2 before the upper stage rocket 1 is separated from the lower stage rocket 2, and the grid wing/grid rudder 3 is unfolded to control the falling attitude of the lower stage rocket 2 after the upper stage rocket 1 is separated from the lower stage rocket 2.
One or more grid wings/grid rudders 3 are uniformly arranged on the lower rocket stage 2 along the circumferential direction; before the upper stage rocket 1 is separated from the lower stage rocket 2, the grid wing/grid rudder 3 is connected with the upper stage rocket 1 in a fixed connection and destructible or non-fixed connection separable mode. When the upper stage rocket 1 and the lower stage rocket 2 are ready to be separated, the fixed connection structure is broken or the separable structure is separated, so that the connection between the grid wing/grid rudder 3 and the upper stage rocket 1 is released.
According to the invention, before the upper stage rocket 1 is separated from the lower stage rocket 2, when the grid wings/grid rudders 3 are not connected with the upper stage rocket 1, the grid wings/grid rudders 3 and other inter-stage structures provide the bearing capacity of the lower stage rocket 2 for the upper stage rocket 1.
When the grid wings/grid rudders 3 are folded, the original partial skin reinforcing rib structure, truss structure or other connecting structures of the lower-level rocket 2 are replaced, and the weight of the rocket is reduced. After the upper stage rocket 1 and the lower stage rocket 2 are disconnected, the grid wings/grid rudders 3 are radially expanded to accelerate the separation speed of the upper stage rocket 1 and the lower stage rocket 2.
After the upper stage rocket 1 is separated from the lower stage rocket 2, the grid wings/grid rudders can control the falling track of the lower stage rocket 2.
The working principle of the invention is as follows: before the upper stage rocket 1 and the lower stage rocket 2 are separated: the grid wing/grid rudder 3 is folded onto the circumferential surface of the rocket and is connected with the tail parts of the upper and lower stages of rockets 2 together with the rest of the inter-stage structures in a mode of not being limited to mechanical locking or initiating explosive devices. In the launching process, the rocket plays a role in connecting the upper rocket and the lower rocket and transfers load.
When the upper stage rocket 1 is separated from the lower stage rocket 2: the connection between the grid wing/grid rudder 3 and other interstage structures and the lower-stage rocket 2 is released (mechanical unlocking or initiating of initiating explosive) and the grid wing/grid rudder 3 expands along the radial direction to increase the resistance of the lower-stage rocket 1 so as to separate the lower-stage rocket 1 from the upper-stage rocket 2, and the separation mode can adopt a cold separation mode or a hot separation mode to accelerate the separation of the upper-stage rocket 1 and the lower-stage rocket 2.
After the upper stage rocket 1 and the lower stage rocket 2 are separated: the grid wings/grid rudders 3 are unfolded and rotate under the action of a control steering engine arranged at the bottom to obtain different control moments and aerodynamic force, so that the falling track of the upper-stage rocket 1 is controlled. Helping the rocket 1 of the upper stage to recover.
Fig. 4 is a structure of an upper and lower connection stage according to an embodiment of the present invention. Fig. 5 is a connection unlocking structure of a stage section and an upper rocket provided in the embodiment of the present invention. Fig. 6 is a preliminary deployment structure of the grid wings provided by the embodiment of the present invention. Fig. 7 is a top and bottom rocket separation and grid wing complete deployment structure provided by an embodiment of the present invention.
In the conventional structure, the stage section and the grid wing/grid rudder are respectively different parts, but the grid wing/grid rudder is a part of the stage section, the stage section part replaced by the grid wing/grid rudder is a part with reduced weight, and the weight of the system for reducing the stage section and the grid wing/grid rudder can be calculated by adopting the following method because the driving device of the grid wing/grid rudder is not changed. The mass of the grid wing/grid rudder and its driving mechanism is m1, the weight of the stage section is m2, and the total mass of the above structure is m1+ m 2. Assuming that one-half of the section of the stage is replaced with a grid wing/grid rudder, the total weight of the new structure is m1+0.5m2, and therefore. The original interstage weight of a rocket structure is 300Kg (m 2), the weight of a grid rudder is 100Kg (m 1), the total weight of the original structure is 400Kg, and the total weight of the structure adopting the invention is only 250 Kg. The weight is reduced by 150Kg relative to the prototype structure, and therefore this part of the weight can be used to increase the rocket propellant weight or other payload. For different models, the quality of the grid wing/grid rudder is different in the above stages, and when the novel structure is adopted, the estimation can be carried out by adopting a similar method.
In the description of the present invention, "a plurality" means two or more unless otherwise specified; the terms "upper", "lower", "left", "right", "inner", "outer", "front", "rear", "head", "tail", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are only for convenience in describing and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, should not be construed as limiting the invention. Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
The above description is only for the purpose of illustrating the present invention and the appended claims are not to be construed as limiting the scope of the invention, which is intended to cover all modifications, equivalents and improvements that are within the spirit and scope of the invention as defined by the appended claims.
Claims (10)
1. The utility model provides a novel rocket level slot structure, includes last level rocket, following level rocket, its characterized in that, novel rocket level slot structure still is provided with:
at least one grid wing or grid rudder;
the grid wings or the grid rudders are uniformly folded and arranged on the rocket at the lower stage along the circumferential direction;
the grid wings or grid rudders are connected with the rocket at the upper stage in a fixing, destructible or non-fixing and separable mode.
2. A novel rocket stage slot structure as recited in claim 1, wherein said grid fins or grid rudders are in a stowed state prior to separation of the upper stage rocket from the lower stage rocket, and alone or in combination with the remaining stage load bearing structures transfer loads to the upper stage rocket.
3. A novel rocket-level bay structure as defined in claim 1, wherein said grid fins or grid vanes replace, in whole or in part, the skin stiffener structure between the upper rocket level and the lower rocket level before the upper rocket level is separated from the lower rocket level.
4. A novel rocket stage slot structure as defined in claim 1, wherein said attachment structure is broken or said detachable structure is detached to release the connection of the grid wings or grid rudder to the rocket of the upper stage when the rocket of the upper stage is ready to be detached from the rocket of the lower stage.
5. A novel rocket stage slot structure as recited in claim 4, wherein said lattice wings or lattice rudders are in a deployed state when said upper stage rocket is ready to be separated from said lower stage rocket.
6. A novel rocket-level bay structure as defined in claim 1, wherein said grid wings or grid rudders are deployed after separation of upper-level rockets from lower-level rockets for regulating the landing attitude of lower-level rockets.
7. The grid wing is characterized in that the grid wing is made of titanium alloy, aluminum alloy and other metal and nonmetal materials.
8. The grid fin of claim 7, wherein the grid fin is replaced with a grid rudder; the shape radian of the grid wings or the grid rudders is the same as that of the rocket at the lower stage.
9. An airborne vehicle carrying a novel rocket stage structure according to any one of claims 1 to 6 for improving the aerodynamic characteristics of the airborne vehicle at the lifting and control surfaces and reducing the weight of the stage structure.
10. A water craft carrying a novel rocket stage slot configuration as claimed in any one of claims 1 to 6 for improving the hydrodynamic properties of an aerial vehicle at lifting and control surfaces.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110256777.4A CN112964139A (en) | 2021-03-09 | 2021-03-09 | Grid wing, novel rocket stage interval structure and application |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110256777.4A CN112964139A (en) | 2021-03-09 | 2021-03-09 | Grid wing, novel rocket stage interval structure and application |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113465454A (en) * | 2021-07-28 | 2021-10-01 | 成都星源飞思科技有限公司 | Multi-group independent control surface and tail wing assembly device installed on same projectile body section |
| CN115406310A (en) * | 2022-09-14 | 2022-11-29 | 北京中科宇航技术有限公司 | Grid rudder device for rocket recovery |
| CN115406311A (en) * | 2022-09-14 | 2022-11-29 | 北京中科宇航技术有限公司 | Grid rudder device |
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| US20100219285A1 (en) * | 2006-11-30 | 2010-09-02 | Raytheon Company | Detachable aerodynamic missile stabilizing system |
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| CN109747860A (en) * | 2019-03-08 | 2019-05-14 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of grid rudder wing suitable for canister launch mixes aerodynamic arrangement and design method |
| EP3653516A1 (en) * | 2018-11-15 | 2020-05-20 | Orbital Express Lauch Limited | Recoverable rocket stage, rocket, and method for launching a multi-stage rocket and returning a recoverable rocket stage to earth |
| CN111189364A (en) * | 2020-03-13 | 2020-05-22 | 北京星际荣耀空间科技有限公司 | Rocket sublevel recovery method and system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US20100219285A1 (en) * | 2006-11-30 | 2010-09-02 | Raytheon Company | Detachable aerodynamic missile stabilizing system |
| CN108507422A (en) * | 2018-04-08 | 2018-09-07 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of lattice fin and the rocket core level-one remains based on lattice fin dissipate falling-point control method |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113465454A (en) * | 2021-07-28 | 2021-10-01 | 成都星源飞思科技有限公司 | Multi-group independent control surface and tail wing assembly device installed on same projectile body section |
| CN115406310A (en) * | 2022-09-14 | 2022-11-29 | 北京中科宇航技术有限公司 | Grid rudder device for rocket recovery |
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| CN115406311B (en) * | 2022-09-14 | 2023-09-29 | 北京中科宇航技术有限公司 | Grid rudder device |
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