CN111854542A - Active cruise return type liquid sounding rocket - Google Patents
Active cruise return type liquid sounding rocket Download PDFInfo
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- CN111854542A CN111854542A CN202010759201.5A CN202010759201A CN111854542A CN 111854542 A CN111854542 A CN 111854542A CN 202010759201 A CN202010759201 A CN 202010759201A CN 111854542 A CN111854542 A CN 111854542A
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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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Abstract
The application discloses return liquid sounding rocket initiatively cruises, includes: the device comprises a fairing, an instrument cabin, a kerosene storage box, an inter-box rod system, a liquid oxygen storage box, a rear transition section and a tail section which are arranged in sequence; the tail section is provided with a liquid oxygen kerosene engine; further comprising: a plurality of grid rudders and a plurality of return legs; the grid-deleting rudder is arranged on the instrument cabin; each return leg is disposed on the aft transition section in part and on the aft section in part. The method has the technical effects of being capable of being repeatedly used, carrying various effective loads, being controllable and being low in cost.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to an active cruise recoverable liquid sounding rocket.
Background
The sounding rocket is a near-earth space rocket. The device has the advantages of simple structure, low production cost, convenient emission and the like, and is widely applied to scientific experiments and releasing low-earth-level detectors. Therefore, the economy, stability and practicability of the sounding rocket become an important demand point for scientific application.
The commonly used sounding rocket generally uses a solid rocket as a matrix, and has the advantages of product curing, high response speed and the like. However, a commonly used sounding rocket has: the rocket has small diameter and limited effective load; the rocket has higher flying speed and great control difficulty; the rocket has the defects of disposable use, return to the ground by gravity, uncontrollable recovery state and the like.
Disclosure of Invention
The application aims to provide an active cruise return type liquid sounding rocket which has the technical effects of being capable of being repeatedly used, carrying various effective loads, being controllable and being low in cost.
To achieve the above object, the present application provides an active cruise return type liquid sounding rocket, comprising: the device comprises a fairing, an instrument cabin, a kerosene storage box, an inter-box rod system, a liquid oxygen storage box, a rear transition section and a tail section which are arranged in sequence; the tail section is provided with a liquid oxygen kerosene engine; further comprising: a plurality of grid rudders and a plurality of return legs; the grid-deleting rudder is arranged on the instrument cabin; each return leg is disposed on the aft transition section in part and on the aft section in part.
As above, wherein the fairing comprises: two half covers, a frame and a butt-joint frame; the two half covers are connected through a frame to form a streamline cover body, the size of the upper end of the cover body is smaller than that of the lower end of the cover body, and a butt-joint frame is arranged at the lower end of the cover body; the fairing is connected with the instrument cabin through the butt joint frame.
As above, wherein the instrument pod comprises: an upper end frame and a lower end frame; a covering is arranged between the upper end frame and the lower end frame so as to form a cylindrical structure; a plurality of stringers are arranged outside the skin; a middle frame is arranged inside the skin; a K-shaped beam is arranged on the middle frame; an instrument mounting plate and an inertial unit bracket are arranged on the K-shaped beam; the instrument cabin is connected with the fairing through the upper end frame.
The instrument shelter comprises a plurality of grid rudders, wherein the grid rudders are arranged on the outer part of the skin of the instrument shelter at uniform intervals in a circumferential shape.
As above, wherein the kerosene storage tank comprises: a front sole and a rear sole; the front bottom and the rear bottom form a box body, and a cylinder section is arranged outside the box body; one end of the cylinder section is provided with a front short shell, and the other end of the cylinder section is provided with a rear short shell; the kerosene storage box is connected with the instrument cabin through the front short shell and is connected with the rod system between the boxes through the rear short shell.
As above, wherein the liquid oxygen storage tank has the same structure as the kerosene storage tank, the liquid oxygen storage tank includes: a front sole and a rear sole; the front bottom and the rear bottom form a box body, and a cylinder section is arranged outside the box body; one end of the cylinder section is provided with a front short shell, and the other end of the cylinder section is provided with a rear short shell; the liquid oxygen storage tank is connected with the rod system between the tanks through the front short shell and is connected with the rear transition section through the rear short shell.
As above, wherein the inter-box linkage comprises: the pipe joint comprises an upper joint, a lower joint and a plurality of pipes, wherein one end of each pipe is connected with the upper joint, and the other end of each pipe is connected with the lower joint; the upper joint is connected with the rear short shell of the kerosene storage box; the lower joint is connected with the front short shell of the liquid oxygen storage tank; the adjacent pipes are connected in an angle through an upper joint or a lower joint and form a triangular space with the rear short shell or the front short shell.
As above, wherein the aft transition section comprises: an upper docking frame and a lower docking frame; a skin is arranged between the upper butt joint frame and the lower butt joint frame so as to form a cylindrical structure; a plurality of stringers are arranged outside the skin; a cross beam is arranged inside the skin; the rear transition section is connected with the liquid oxygen storage tank through an upper butt joint frame and is connected with the tail section through a lower butt joint frame.
As above, wherein the structure of the tail section is the same as the structure of the rear transition section, the tail section comprises: an upper docking frame and a lower docking frame; a skin is arranged between the upper butt joint frame and the lower butt joint frame so as to form a cylindrical structure; a plurality of stringers are arranged outside the skin; a cross beam is arranged inside the skin; the upper butt-joint frame of the tail section is connected with the lower butt-joint frame of the rear transition section; the tail section is provided with a liquid oxygen kerosene engine.
As above, wherein each return leg comprises: a main support bar and two auxiliary support bars; one end of the main supporting rod is rotatably connected with the rear transition section through the main supporting rod connecting piece, and the other end of the main supporting rod is connected with one end of the two auxiliary supporting rods through the buffer device; the other ends of the two auxiliary supporting rods are respectively connected with the tail section in a rotating way through an auxiliary supporting rod connecting piece.
The beneficial effect that this application realized is as follows:
(1) the active cruise recoverable liquid sounding rocket has the technical effects of reducing consumables, saving time and labor and reducing sounding test cost.
(2) The active cruise recoverable liquid sounding rocket has the advantages of achieving the purpose of scientific experiments and being rapid in response.
(3) The active cruise recoverable liquid sounding rocket disclosed by the invention applies a large amount of new materials, new structures and new technologies, realizes functions, and simultaneously can verify the reliability of the new technologies, so that more effective data information can be obtained for scientific research, and a better reference can be provided for the research and development of a novel carrier rocket.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments described in the present application, and other drawings can be obtained by those skilled in the art according to the drawings.
FIG. 1 is a schematic diagram of an embodiment of an active cruise return type liquid sounding rocket;
FIG. 2 is a schematic structural view of one embodiment of a fairing;
FIG. 3 is a schematic diagram of an embodiment of an instrument pod;
FIG. 4 is a schematic structural view of one embodiment of a kerosene storage tank;
FIG. 5 is a schematic view of an embodiment of an interbox linkage;
FIG. 6 is a schematic structural diagram of an embodiment of a rear transition section;
FIG. 7 is a schematic structural view of one embodiment of a return leg.
Detailed Description
The technical solutions in the embodiments of the present invention are clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1, the application provides an active cruise return type liquid sounding rocket, which comprises a fairing 1, an instrument cabin 2, a kerosene storage tank 3, an inter-tank rod system 4, a liquid oxygen storage tank 5, a rear transition section 6 and a tail section 7 which are arranged in sequence; the tail section 7 is provided with a liquid oxygen kerosene engine 8; the active cruise return type liquid sounding rocket further comprises: a plurality of grid rudders 9 and a plurality of return legs 10. The grid rudder 9 is provided on the instrument pod 2. Each return leg 10 is disposed in part at the aft transition section 6 and in part at the aft section 7.
As shown in fig. 2, the cowling 1 includes: two half-shells 11, a rim 12 and a docking rim 13. The two half-covers 11 are connected through a frame 12 to form a streamline cover body. The size of the upper end of the cover body is smaller than that of the lower end of the cover body, and the lower end of the cover body is provided with a butt joint frame 13; the fairing 1 is connected to the instrument pod 2 via a docking frame 13.
Specifically, the two half covers 11 are connected in a threaded manner, the cover body is connected with the butt-joint frame 13 in a threaded manner, and the butt-joint frame 13 is connected with the instrument chamber 2 in a threaded manner, but the connection method is not limited to the connection method and other connection methods can be used for connection. The cowling 1 is made of a brazed aluminum honeycomb material, but is not limited to the brazed aluminum honeycomb material, and the brazed aluminum honeycomb material is preferably used in the present application. The structure has the performances of high temperature resistance, weldability, light weight, high specific stiffness, heat insulation, sound insulation, flame retardance, vibration reduction, energy absorption, electromagnetic shielding and the like.
Further, a final stage correction device is arranged in the fairing 1, and a plurality of spray pipe holes 14 are formed in the fairing 1; the final stage correcting device is connected with the jet pipe, the jet pipe is exposed out of the jet pipe hole 14 of the fairing 1, and the final stage correcting device performs small-magnitude speed correction on the rocket by controlling airflow and the like so as to control the change of the rocket action.
Further, the nozzle hole 14 is opened in the cowl 1 at a position close to the butt frame 13.
Further, as shown in fig. 3, the instrument pod 2 includes: an upper end frame 21 and a lower end frame 22; a skin 23 is arranged between the upper end frame 21 and the lower end frame 22 so as to form a cylindrical structure; a plurality of stringers 24 are arranged outside the skin 23; a middle frame 25 is arranged inside the skin 23; the middle frame 25 is provided with a K-shaped beam 26; an instrument mounting plate 27 and an inertial measurement unit support 28 are arranged on the K-shaped beam 26; the instrument pod 2 is connected to the docking frame 13 of the fairing 1 via an upper end frame 21. The upper end frame 21 is connected with the butt-joint frame 13 by a screw connection, but not limited to this connection.
Specifically, the upper end frame 21 and the lower end frame 22 are circular ring frames having the same size. A plurality of stringers 24 are arranged on the outer surface of the skin 23 at regular intervals; the middle frame 25 is provided on the inner surface of the skin 23. Wherein, the instrument cabin 2 is an aluminum alloy skin stringer structure. The K-beam 26 is made of a composite material, but not limited to the composite material, and the cross section of the K-beam 26 has an i-shaped structure and an L-shaped structure. The instrument mounting plate 27 is of a carbon fiber honeycomb structure, and has the advantages of shock absorption, compression resistance, bending resistance, light weight and the like. The instrument mounting plate 27 and the inertial measurement unit support 28 are used for mounting instruments and the like.
Further, a plurality of grid rudders 9 are arranged outside the skin 23 of the instrument shelter 2 at uniform intervals in a circumferential shape.
Specifically, the specific number of the grid rudders 9 may be determined according to actual conditions, and is preferably four in the present application, and four grid rudders 9 are circumferentially and uniformly arranged outside the skin 23 at intervals. The grid rudder 9 is a rocket flight attitude control device, plays an important role in a rocket recovery accurate landing area, can control the attitude of the rocket during recovery through the grid rudder 9, and ensures that rocket debris can land in a set area.
As shown in fig. 4, the kerosene storage tank 3 includes: a front sole 31 and a rear sole 32; the front bottom 31 and the rear bottom 32 form a box body, and a cylinder section 33 is arranged outside the box body; one end of the cylinder section 33 is provided with a front short shell 34, and the other end is provided with a rear short shell 35; the kerosene storage tank 3 is connected with the instrument cabin 2 through a front short shell 34 and is connected with the inter-tank rod system 4 through a rear short shell 34.
Specifically, the front bottom 31 and the rear bottom 32 of the kerosene storage tank 3 are of an integrally formed integral structure. The kerosene storage tank 3 is connected with the lower end frame 22 of the instrument chamber 2 through a front short shell 34, and after the connection, the front bottom 31 of the kerosene storage tank 3 is positioned inside the instrument chamber 2. The rear short shell 35 of the kerosene storage tank 3 is connected to the upper joint 41 of the inter-tank linkage 4. The cylinder body is connected with the box body in a welding mode.
Further, the kerosene storage tank 3 is made of an aluminum alloy, but is not limited to an aluminum alloy, and an aluminum alloy is preferable in the present application.
Further, as shown in fig. 5, the inter-box linkage 4 includes: an upper joint 41, a lower joint 42, and a plurality of pipes 43, each pipe 43 having one end connected to the upper joint 41 and the other end connected to the lower joint 42; the upper joint 41 is connected with the rear short shell 35 of the kerosene storage tank 3; the lower joint 42 is connected with the front short shell of the liquid oxygen storage tank 5; the adjacent pipes 43 are connected at an angle by the upper joints 41 or the lower joints 42, and form a triangular space with the rear short shell or the front short shell.
Specifically, the number of the tubes 43 may be determined according to actual conditions. The specific angle between adjacent tubes 43 will depend on the application. The rear bottom 32 of the kerosene storage tank 3 and the front bottom of the liquid oxygen storage tank 4 are both located in the internal space formed by the inter-tank rod system 4. The triangular space may allow for the passage of pipes or lines of other equipment. The rod system 4 between boxes has the functions of bearing and transferring force besides the function of connection.
Furthermore, the rod system 4 between the boxes is connected by adopting a composite material rod system, so that the connection strength can be realized, the weight of a section is reduced, and the section is prevented from being opened.
Further, the liquid oxygen storage tank 5 has the same structure as the kerosene storage tank, and the liquid oxygen storage tank 5 includes: a front sole and a rear sole; the front bottom and the rear bottom form a box body, and a cylinder section is arranged outside the box body; one end of the cylinder section is provided with a front short shell, and the other end of the cylinder section is provided with a rear short shell; the liquid oxygen storage tank 5 is connected with the rod system between the tanks through the front short shell and is connected with the rear transition section through the rear short shell.
Specifically, the front bottom and the rear bottom of the liquid oxygen storage tank 5 are of an integrally formed integral structure. The liquid oxygen storage tank 5 is connected with the lower joint 42 of the inter-tank rod system 4 through the front short shell. The rear short shell of the liquid oxygen storage tank 5 is connected with a rear transition section 6.
Further, the liquid oxygen storage tank 5 is made of an aluminum alloy, but is not limited to an aluminum alloy, and an aluminum alloy is preferable in the present application.
Further, as shown in fig. 6, the rear transition section 6 includes: an upper docking frame 61 and a lower docking frame 62; a skin 23 is arranged between the upper butt joint frame 61 and the lower butt joint frame 62 so as to form a cylindrical structure; a plurality of stringers 24 are provided on the exterior of the skin 23; the skin 23 is internally provided with a cross beam 63, and the rear transition section 6 is connected with the liquid oxygen storage tank 5 through an upper butt joint frame 61 and is connected with the tail section 7 through a lower butt joint frame 62.
Specifically, the upper docking frame 61 and the lower docking frame 62 are circular ring frames having the same size. A plurality of stringers 24 are provided on the outer surface of the skin 23 at regular intervals.
Further, the structure of the tail section 7 is the same as that of the rear transition section 6, and the tail section 7 comprises: an upper docking frame and a lower docking frame; a skin is arranged between the upper butt joint frame and the lower butt joint frame so as to form a cylindrical structure; a plurality of stringers are arranged outside the skin; a cross beam is arranged inside the skin; the upper butt-joint frame of the tail section 7 is connected with the lower butt-joint frame 62 of the rear transition section 6; the tail section 7 is provided with a liquid oxygen kerosene engine 8.
Specifically, the rear transition section 6 and the tail section 7 are made of aluminum alloy skin stringer structures. The height of the tail section 7 is greater than the height of the rear transition section.
As shown in fig. 7, the return legs 10 are arranged in a four-leg configuration, and each return leg includes: one main support bar 71 and two sub support bars 72; one end of the main supporting rod 71 is rotatably connected with the rear transition section 6 through a main supporting rod connecting piece 74, and the other end of the main supporting rod is connected with one end of two auxiliary supporting rods 72 through a buffer device 73; the other ends of the two auxiliary support rods 72 are rotatably connected with the tail section 7 through an auxiliary support rod connecting piece 75.
Specifically, the number of the return legs 10 is determined according to actual conditions, and four return legs are preferred in the present application. The main support bar coupler 74 includes: main tributary vaulting pole hinge and main tributary vaulting pole, main tributary vaulting pole 71 rotates through main tributary vaulting pole hinge and main tributary vaulting pole to be connected, main tributary vaulting pole and back changeover portion 6 fixed connection.
The auxiliary support rod connector 75 includes: an auxiliary support rod hinge and an auxiliary support seat; the auxiliary supporting rod is rotatably connected with the auxiliary supporting seat through an auxiliary supporting rod hinge.
Furthermore, each auxiliary supporting seat is provided with two hinge connecting pieces, and one auxiliary supporting rod of the previous returning supporting leg and one auxiliary supporting rod of the next returning supporting leg are arranged on the same auxiliary supporting seat.
Furthermore, an unlocking device 64 is further arranged on the rear transition section 6, the unlocking device 64 is connected with the supporting leg cover, and after the unlocking device receives an unlocking instruction, the supporting leg cover is opened, the supporting leg is returned to be unfolded, and a supporting effect is achieved.
Specifically, the inside of the whole active cruise return type liquid sounding rocket further comprises: a pressurized delivery system and a control measurement system.
The pressurization conveying system adopts a gas cylinder pressurization structure, and a conveying pipeline layout structure on the outer wall of the box mainly comprises a conveying pipe, a pressurization gas cylinder, a pipeline, a safe overflow system, an exhaust system, a filling system, a control gas circuit system, a measurement gas circuit system and the like. The control and measurement system instrument and equipment are respectively arranged in an instrument cabin and a fairing and comprise an instrument cable, a grid air rudder, a final-stage correction device and the like.
Specifically, the rocket returns to the landing device, and functions of providing stable support, reducing impact and the like after the rocket returns are achieved. And the return control system realizes navigation control, rocket body attitude adjustment control, landing place control, propulsion system start and stop control, landing auxiliary system control and the like when the rocket returns. And the return control device realizes attitude adjustment and drop point control when the rocket returns. The liquid pressurizing and conveying system provides a stable, simple and safe power system for the rocket. The composite material rod system is applied to realize the connecting strength and the function of the rocket section, and simultaneously, the weight of the section is reduced, and the light weight is achieved. The application of the novel brazing aluminum honeycomb material in rockets. Liquid fuel, and the whole arrow is recovered and reused.
The beneficial effect that this application realized is as follows:
(2) the active cruise recoverable liquid sounding rocket has the technical effects of reducing consumables, saving time and labor and reducing sounding test cost.
(2) The active cruise recoverable liquid sounding rocket has the advantages of achieving the purpose of scientific experiments and being rapid in response.
(3) The active cruise recoverable liquid sounding rocket disclosed by the invention applies a large amount of new materials, new structures and new technologies, realizes functions, and simultaneously can verify the reliability of the new technologies, so that more effective data information can be obtained for scientific research, and a better reference can be provided for the research and development of a novel carrier rocket.
While the preferred embodiments of the present application have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, the scope of protection of the present application is intended to be interpreted to include the preferred embodiments and all variations and modifications that fall within the scope of the present application. It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (10)
1. An active cruise return type liquid sounding rocket, comprising: the device comprises a fairing, an instrument cabin, a kerosene storage box, an inter-box rod system, a liquid oxygen storage box, a rear transition section and a tail section which are arranged in sequence; the tail section is provided with a liquid oxygen kerosene engine;
further comprising: a plurality of grid rudders and a plurality of return legs; the grid-deleting rudder is arranged on the instrument cabin; each of the return legs is disposed on the aft transition section in part and on the aft section in part.
2. The active cruise return liquid sounding rocket of claim 1, wherein the fairing comprises: two half covers, a frame and a butt-joint frame; the two half covers are connected through a frame to form a streamline cover body, the size of the upper end of the cover body is smaller than that of the lower end of the cover body, and a butt-joint frame is arranged at the lower end of the cover body; the fairing is connected with the instrument cabin through the butt joint frame.
3. The active cruise return liquid sounding rocket of claim 1, wherein the instrument pod comprises: an upper end frame and a lower end frame; a skin is arranged between the upper end frame and the lower end frame so as to form a cylindrical structure; a plurality of stringers are arranged outside the skin; a middle frame is arranged inside the skin; the middle frame is provided with a K-shaped beam; the K-shaped beam is provided with an instrument mounting plate and an inertial measurement unit bracket; the instrument cabin is connected with the fairing through the upper end frame.
4. The active cruise return liquid sounding rocket of claim 3, wherein a plurality of grid rudders are circumferentially and evenly spaced outside of an instrument pod skin.
5. The active cruise return liquid sounding rocket of claim 1, wherein the kerosene tank comprises: a front sole and a rear sole; the front bottom and the rear bottom form a box body, and a cylinder section is arranged outside the box body; one end of the cylinder section is provided with a front short shell, and the other end of the cylinder section is provided with a rear short shell; the kerosene storage box is connected with the instrument cabin through the front short shell and is connected with the inter-box rod system through the rear short shell.
6. The active cruise return liquid sounding rocket of claim 5, wherein the liquid oxygen tank is structurally identical to the kerosene tank, the liquid oxygen tank comprising: a front sole and a rear sole; the front bottom and the rear bottom form a box body, and a cylinder section is arranged outside the box body; one end of the cylinder section is provided with a front short shell, and the other end of the cylinder section is provided with a rear short shell; the liquid oxygen storage tank is connected with the inter-tank rod system through a front short shell and is connected with the rear transition section through a rear short shell.
7. The active cruise return liquid sounding rocket of claim 6, wherein the inter-tank linkage comprises: the pipe joint comprises an upper joint, a lower joint and a plurality of pipes, wherein one end of each pipe is connected with the upper joint, and the other end of each pipe is connected with the lower joint; the upper joint is connected with the rear short shell of the kerosene storage box; the lower joint is connected with the front short shell of the liquid oxygen storage tank; the adjacent pipes are connected in an angle through the upper joint or the lower joint and form a triangular space with the rear short shell or the front short shell.
8. The active cruise return liquid sounding rocket of claim 1, wherein the aft transition section comprises: an upper docking frame and a lower docking frame; a skin is arranged between the upper butt joint frame and the lower butt joint frame so as to form a cylindrical structure; a plurality of stringers are arranged outside the skin; a cross beam is arranged inside the skin; the rear transition section is connected with the liquid oxygen storage tank through the upper butt joint frame and is connected with the tail section through the lower butt joint frame.
9. An active cruise return liquid sounding rocket according to claim 1 or 8, wherein the structure of the tail section is the same as the structure of the rear transition section, the tail section comprising: an upper docking frame and a lower docking frame; a skin is arranged between the upper butt joint frame and the lower butt joint frame so as to form a cylindrical structure; a plurality of stringers are arranged outside the skin; a cross beam is arranged inside the skin; the upper butt-joint frame of the tail section is connected with the lower butt-joint frame of the rear transition section; the tail section is provided with a liquid oxygen kerosene engine.
10. The active cruise return liquid sounding rocket of claim 1, wherein each of the return legs comprises: a main support bar and two auxiliary support bars; one end of the main supporting rod is rotatably connected with the rear transition section through a main supporting rod connecting piece, and the other end of the main supporting rod is connected with one end of each of the two auxiliary supporting rods through a buffer device; the other ends of the two auxiliary supporting rods are respectively connected with the tail section in a rotating way through an auxiliary supporting rod connecting piece.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010759201.5A CN111854542A (en) | 2020-07-31 | 2020-07-31 | Active cruise return type liquid sounding rocket |
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| CN202010759201.5A CN111854542A (en) | 2020-07-31 | 2020-07-31 | Active cruise return type liquid sounding rocket |
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| CN114061379A (en) * | 2021-11-16 | 2022-02-18 | 天津爱思达新材料科技有限公司 | Front cabin T-shaped frame reinforcing structure |
| 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 |
| CN114560105A (en) * | 2022-03-24 | 2022-05-31 | 青岛泰泓轨道装备有限公司 | Carrier rocket welding aluminum honeycomb fairing and preparation method thereof |
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| CN114264199B (en) * | 2021-11-23 | 2024-02-09 | 上海宇航系统工程研究所 | General core-level-based combined body recovery rocket overall configuration |
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