CN112902769A - Grid wing, novel rocket stage interval structure, control method and application - Google Patents
Grid wing, novel rocket stage interval structure, control method and application Download PDFInfo
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- CN112902769A CN112902769A CN202110257817.7A CN202110257817A CN112902769A CN 112902769 A CN112902769 A CN 112902769A CN 202110257817 A CN202110257817 A CN 202110257817A CN 112902769 A CN112902769 A CN 112902769A
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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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- 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
- F42B10/143—Lattice or grid fins
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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
- F42B15/01—Arrangements thereon for guidance or control
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- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention belongs to the technical field of rocket separation, and discloses a novel rocket stage section structure, a control method and application. The grid wing/grid rudder is manufactured by adopting the modes of SLM printing, welding, casting and the like of metals such as titanium alloy and the like, and is installed 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, a control method 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.
The difficulty in solving the above problems and defects is: in the prior art, the rocket grid wings and the rocket interstage connecting section are designed independently, the grid wings are required to be installed on a rocket as accessories, the weight of the grid wings is large, and the grid wings are huge in redundant mass before launching and recovering, so that the situation 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 new separation control method of rocket stage interval structure is applied to the new rocket stage interval structure, the separation control method of the new rocket stage interval structure includes:
controlling before separating the upper stage rocket and the lower stage rocket: the grid wings/grid rudders are folded onto the circumferential surface of the next-stage rocket and are connected with the next-stage rocket together with the rest of the interstage structures;
controlling when the upper stage rocket and the lower stage rocket are separated: the grid wings/grid rudders and other interstage structures are disconnected with the next-stage rocket, and the grid wings/grid rudders are expanded along the radial direction;
separating the upper stage rocket and the lower stage rocket, and then controlling: the grid wings/grid rudders are unfolded, and the angular postures and angular speed changes along three directions are controlled by the steering engine, so that the aerodynamic characteristics of the rocket are influenced, and the falling track of the rocket at the next stage is controlled.
Further, before the upper stage rocket and the lower stage rocket are separated, the grid wings or the grid rudders are in a retracted state, and the load is transmitted to the upper stage rocket independently or together with other interstage bearing structures.
Further, the grid wings or the grid rudders completely or partially replace connecting structures such as skin reinforcing ribs, trusses and the like between the upper-stage rocket and the lower-stage rocket before the upper-stage rocket is separated from the lower-stage rocket.
Further, when the upper stage rocket is separated from the lower stage rocket, the lower stage rocket is separated from the upper stage rocket in a cold separation or hot separation mode.
Further, when the upper stage rocket is separated from the lower stage rocket, the connection releasing mode is as follows: mechanical unlocking or initiating explosive device ignition.
Further, after the upper stage rocket and the lower stage rocket are separated, the angles and angular velocities of the grid wings or the grid rudders in three directions are controlled by mechanisms such as a steering engine in the unfolding state.
Further, after the upper-stage rocket and the lower-stage rocket are separated, the bottom of the grid wing or the grid rudder is provided with a control steering engine, and the grid wing or the grid rudder is controlled to rotate in three directions to control the falling track of the lower-stage rocket.
Another objective of the present invention is to provide a novel rocket stage interval structure, which includes a previous stage rocket and a next stage rocket, and the novel rocket stage interval structure is further provided with:
at least one grid wing or grid rudder;
the grid wings or the grid rudders are uniformly folded and installed on the next stage rocket along the circumferential direction;
the grid wings or the grid rudders are connected with the upper-stage rocket in a fixed connection and destructible or non-fixed connection separable mode;
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 independently or together with other inter-stage bearing structures;
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.
The grid wings or the grid rudders are made of titanium alloy or aluminum alloy materials; the shape radian of the grid wings or the grid rudders is the same as that of the next stage rocket.
Another object of the present invention is to provide an air vehicle and a water craft which implement the separate control method of the novel rocket-stage bay structure.
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 stage bearing structures, thereby replacing the structures such as bearing structures (such as trusses, ribs, skins and the like) which are independently adopted among the stages of the original rocket. The invention reduces weight, reduces emission cost and improves emission 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 flowchart of a separation control method of a novel rocket stage interval structure according to an embodiment of the present invention.
Fig. 2 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.
In fig. 2: 1. a rocket at the upper stage; 2. a next stage rocket; 3. a grid rudder.
Fig. 3 is a schematic structural diagram of a closing of a grid wing in a novel rocket stage block section structure including a grid wing structure according to an embodiment of the present invention.
Fig. 4 is a schematic structural diagram of a post-separation recovery stage of an upper stage and a lower stage in a novel rocket stage block structure including a grid wing structure according to an embodiment of the present invention.
Fig. 5 is a schematic structural diagram of an upper and lower connection stage provided in the embodiment of the present invention.
Fig. 6 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. 7 is a schematic diagram of a preliminary deployment structure of the grid wings provided by the embodiment of the invention.
Fig. 8 is a schematic structural diagram of upper and lower stage rocket separation and grid wing complete deployment provided by the embodiment of the invention.
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.
As shown in fig. 1, the present invention provides a separation control method for a novel rocket stage interval structure, which is applied to a novel rocket stage interval structure, and the separation control method for the novel rocket stage interval structure includes:
s101, controlling a previous rocket and a next rocket before separation: the grid wings/grid rudders are folded onto the circumferential surface of the next-stage rocket and are connected with the next-stage rocket together with the rest of the interstage structures;
s102, controlling when the upper stage rocket and the lower stage rocket are separated: the grid wings/grid rudders and other interstage structures are disconnected with the next-stage rocket, and the grid wings/grid rudders are expanded along the radial direction;
s103, separating the upper stage rocket and the lower stage rocket, and controlling: and the grid wings/grid rudders are unfolded, and after being unlocked, the angles and the angular velocities of the unfolded grid wings/grid rudders are controlled by the steering engine to control the falling track of the next-stage rocket.
As shown in fig. 2 to 4, the novel rocket-level slot structure including the grid wing structure provided by the embodiment of the present invention includes: a first-stage rocket 1, a second-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, welding, casting and other modes, and is arranged on 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 is separated from the lower stage rocket 2, the lower stage rocket 2 provides power; after the upper rocket stage and the lower rocket stage are separated, the engine of the upper rocket stage 1 is ignited to provide power, and the power for unfolding the grid wings at the moment can comprise one or a combination of more of engine jet flow acting force, incoming flow pneumatic force and steering engine control force.
The grid wing/grid rudder 3 is used as a part of a stage section connecting structure before a previous stage rocket 1 is separated from a next stage rocket 2, and is used for connecting the previous stage rocket 1 and the next stage rocket 2, and the grid wing/grid rudder 3 is unfolded after the previous stage rocket 1 is separated from the next stage rocket 2 to control the falling attitude of the next stage rocket 2.
One or more grid wings/grid rudders 3 are uniformly arranged on the next stage rocket 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.
Before the upper-stage rocket 1 is separated from the lower-stage rocket 2, when the grid wing/grid rudder 3 is not connected with the upper-stage rocket 1, the grid wing/grid rudder 3 and other interstage 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, partial skin reinforcing rib structures or quilting frames and other structures of the original next-stage rocket 2 can be omitted, and the weight of the rocket is reduced. After the connection between the upper stage rocket 1 and the lower stage rocket 2 is released, the grid wings/grid rudders 3 are unfolded along the radial direction, so that the separation speed of the upper stage rocket 1 and the lower stage rocket 2 is accelerated.
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 to the tail part of the upper-level rocket 2 and the lower-level rocket 2 together with the rest of the inter-level structure, and the connection mode is not limited to mechanical locking or initiating explosive devices and the like. 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 next-stage rocket 2 is released (mechanical unlocking or ignition of initiating explosive devices), the grid wing/grid rudder 3 is expanded along the radial direction, so that the resistance of the previous-stage rocket 1 is increased, and the next-stage rocket 2 can adopt a cold separation or hot separation mode to accelerate the separation of the previous-stage rocket 1 and the next-stage rocket 2.
After the upper stage rocket 1 and the lower stage rocket 2 are separated: the grid wings/grid rudders 3 reach an unfolded state, and then the angles and the oil bottoms of the angles are matched with control steering engines for controlling, so that the grid wings can rotate in three degrees of freedom to control the falling track of the upper-stage rocket 1. Helping the rocket 1 of the upper stage to recover.
Fig. 5 is a structure of an upper and lower connection stage according to an embodiment of the present invention. Fig. 6 is a structure for unlocking the connection between the stage section and the upper rocket according to the embodiment of the present invention. Fig. 7 is a preliminary deployment structure of the grid wings provided in the embodiment of the present invention. Fig. 8 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 different parts, so that the grid wing/grid rudder can be 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 weight of original interstage of a certain rocket structure is 200Kg, the weight of the grid rudder is 80Kg, the total weight of the original structure is 280Kg, and the total weight of the structure adopting the invention is only 180 Kg. The weight is reduced by 100Kg 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. A novel separation control method of a rocket stage interval structure is characterized by being applied to the novel rocket stage interval structure, and comprises the following steps:
controlling before separating the upper stage rocket and the lower stage rocket: the grid wings/grid rudders are folded onto the circumferential surface of the next-stage rocket and are connected with the next-stage rocket together with the rest of the interstage structures;
controlling when the upper stage rocket and the lower stage rocket are separated: the grid wings/grid rudders and other interstage structures are disconnected with the next-stage rocket, and the grid wings/grid rudders are expanded along the radial direction;
separating the upper stage rocket and the lower stage rocket, and then controlling: and the grid wings/grid rudders are in a fully unfolded state and are kept locked, and the falling track of the next stage of rocket is controlled.
2. A novel rocket stage interval structure separation control method as recited in claim 1, wherein said grid wings or grid rudders are in a retracted state before said upper stage rocket and said lower stage rocket are separated, and alone or together with the rest of the stage load-bearing structures, transfer the load to the upper stage rocket.
3. A novel rocket-level slot structure separation control method as defined in claim 1,
the grid wings or the grid rudders completely or partially replace skin reinforcing ribs, trusses and other types of connecting structures between the upper-stage rocket and the lower-stage rocket before the upper-stage rocket is separated from the lower-stage rocket.
4. A novel rocket stage interval structure separation control method as defined in claim 1, wherein when said upper stage rocket and lower stage rocket are separated, the lower stage rocket is separated from the upper stage rocket by means of cold separation or hot separation.
5. A novel rocket-level interval structure separation control method as recited in claim 1, wherein said connection releasing manner is: mechanical unlocking or initiating explosive devices.
6. A novel rocket stage interval structure separation control method as claimed in claim 1, wherein after the rocket at the upper stage and the rocket at the lower stage are separated, the unfolding state of the grid wings or grid rudders, such as 90 degrees or the unfolding angle, can be adjusted by a steering engine or other mechanisms according to the control requirements.
7. A novel separation control method for a rocket-stage interval structure as in claim 1, wherein after the previous stage rocket and the next stage rocket are separated, the bottom of the grid wing or grid rudder is equipped with a control steering engine to control the three-degree-of-freedom rotation of the grid wing or grid rudder and control the falling trajectory of the next stage rocket.
8. The utility model provides a novel rocket level slot structure, includes last one-level rocket, next stage 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 installed on the next stage rocket along the circumferential direction;
the grid wings or the grid rudders are connected with the upper-stage rocket in a fixed connection and destructible or non-fixed connection separable mode;
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 independently or together with other inter-stage bearing structures;
the grid wings or the grid rudders completely or partially replace skin reinforcing ribs or other forms of connecting structures between the upper-stage rocket and the lower-stage rocket before the upper-stage rocket is separated from the lower-stage rocket.
9. A novel rocket-grade slot structure as recited in claim 8, wherein said lattice wings or lattice vanes are fabricated from titanium alloy or aluminum alloy material; the shape radian of the grid wings or the grid rudders is the same as that of the next-stage rocket or the independent aerodynamic shape and structure design is carried out according to the control requirement.
10. An air vehicle and water craft, characterized in that they implement the method of separate control of the new rocket stage bay structure according to any one of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202110257817.7A CN112902769A (en) | 2021-03-09 | 2021-03-09 | Grid wing, novel rocket stage interval structure, control method and application |
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| CN202110257817.7A CN112902769A (en) | 2021-03-09 | 2021-03-09 | Grid wing, novel rocket stage interval structure, control method and application |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113551565A (en) * | 2021-09-18 | 2021-10-26 | 中国科学院力学研究所 | Stage section pneumatic shape-preserving solid rocket and separation method |
| CN115325889A (en) * | 2022-09-01 | 2022-11-11 | 北京中科宇航技术有限公司 | Control system for leaf surface rotating grid rudder |
| 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 |
| CN117961221A (en) * | 2024-03-29 | 2024-05-03 | 苏州融速智造科技有限公司 | Integrated additive manufacturing method of grid wing/rudder |
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| 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 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113551565A (en) * | 2021-09-18 | 2021-10-26 | 中国科学院力学研究所 | Stage section pneumatic shape-preserving solid rocket and separation method |
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| CN115325889A (en) * | 2022-09-01 | 2022-11-11 | 北京中科宇航技术有限公司 | Control system for leaf surface rotating grid rudder |
| CN115325889B (en) * | 2022-09-01 | 2023-09-29 | 北京中科宇航技术有限公司 | Leaf surface rotating grid rudder control system |
| 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 |
| CN115406311B (en) * | 2022-09-14 | 2023-09-29 | 北京中科宇航技术有限公司 | Grid rudder device |
| CN115406310B (en) * | 2022-09-14 | 2023-09-29 | 北京中科宇航技术有限公司 | Grid rudder device for rocket recovery |
| CN117961221A (en) * | 2024-03-29 | 2024-05-03 | 苏州融速智造科技有限公司 | Integrated additive manufacturing method of grid wing/rudder |
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