CN115596573B - Spherical-bottom rocket storage box with simple structure - Google Patents
Spherical-bottom rocket storage box with simple structure Download PDFInfo
- Publication number
- CN115596573B CN115596573B CN202211492084.6A CN202211492084A CN115596573B CN 115596573 B CN115596573 B CN 115596573B CN 202211492084 A CN202211492084 A CN 202211492084A CN 115596573 B CN115596573 B CN 115596573B
- Authority
- CN
- China
- Prior art keywords
- shaped ring
- tank
- storage box
- box
- storage tank
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/605—Reservoirs
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention provides a spherical-bottom rocket storage tank with a simplified structure, which belongs to the technical field of rockets, and comprises a cylindrical storage tank shell, wherein the end part of the storage tank shell is connected with the bottom of the storage tank through an r-shaped ring; and one end of the r-shaped ring, which is far away from the tank shell, is connected with a connecting section. The connecting section is connected with the r-shaped ring of the storage box by bolts, riveting or welding. The storage box has simplified structural design, eliminates a storage box transition section and an end frame, reduces the matching of storage box structural members, saves tooling equipment for storage box production or welding assembly, reduces the process difficulty of storage box production and manufacturing, and can effectively reduce the manufacturing cost of the storage box.
Description
Technical Field
The invention belongs to the technical field of rockets, and particularly relates to a spherical-bottom rocket storage box with a simplified structure.
Background
At present, the world aerospace industry has entered the commercialization era, and the core feature of the world aerospace industry is low-cost rocket launching and satellite operation services. The carrier rocket mainly comprises a structure, power, an electrical control system and the like, and the rocket structure is an important component of the carrier rocket and also an important component of the rocket cost.
The existing general liquid rocket structure mainly comprises a primary rocket body structure A, a secondary rocket body structure B, a fairing C and the like as shown in fig. 1a and fig. 1B, wherein the primary rocket body structure A mainly comprises a primary power cabin A5, a storage tank, a stage section A4 and the like. The storage tank is the most important part of the rocket structure, and not only needs to fill oxidant and combustion agent fuel, bear pressure and ensure sealing, but also needs to bear internal pressure or axial pressure, aerodynamic force and thermal load, and the storage tank is more necessary to be used as a rocket type aircraft product and needs to be lighter.
The first-stage arrow body structure A generally comprises two storage tanks which are respectively filled with an oxidant and a combustion agent and can be called a first-stage front tank A1 and a first-stage rear tank A2 according to the positions of the two storage tanks, and the two storage tanks are separated by a first-stage tank interval section A3. The front box A1 mainly comprises a front box front end frame A11, a front box front transition section A12, a front box front bottom A13, a front box front Y-shaped ring A14, a front box shell A15 (formed by multiple sections of shells), a front box rear Y-shaped ring A16, a front box rear bottom A17, a front box rear transition section A18 and a front box rear end frame A19 which are connected. Similarly, the rear box A2 mainly includes a rear box front end frame a21, a rear box front transition section a22, a rear box front bottom a23, a rear box front Y-ring a24, a rear box casing a25 (made up of multiple sections of casing), a rear box rear Y-ring a26, a rear box rear bottom a27, a rear box rear transition section a28, and a rear box rear end frame a29, which are connected.
As shown in fig. 1c, taking the front side of the first-stage front box A1 as an example, the front box front Y-shaped ring a14 is used as a structural member and is respectively fixedly connected (e.g., welded) with the front box front bottom a13, the front box front transition section a12 and the front box shell a 15; the front transition section A12 of the front box is connected (such as welded or riveted) with the front end frame A11 of the front box; the front box front end frame A11 is used as a connecting frame of the storage box and is connected with the stage section A4. The rear side of the front case A1 and the rear case A2 are structured in the same manner.
The existing storage box has a complex structure, is difficult to produce and process, and still needs to further reduce the cost and the total weight.
Disclosure of Invention
Based on the technical problems existing in the prior art. The invention provides a spherical-bottom rocket storage box with a simplified structure, which solves the problems of complex structure, higher processing difficulty, higher cost and heavier weight of the storage box, thereby realizing the effect of further reducing the launching cost of a commercial carrier rocket.
According to the technical scheme, the invention provides the spherical-bottom rocket storage tank with the simplified structure, the spherical-bottom rocket storage tank with the simplified structure is the spherical-bottom rocket storage tank with the simplified structure, the spherical-bottom rocket storage tank with the simplified structure comprises a cylindrical storage tank shell, and the end part of the storage tank shell is connected with the bottom of the storage tank through an r-shaped ring; one end of the r-shaped ring, which is far away from the storage box shell, is connected with a connecting section.
According to some embodiments, the r-shaped ring has a first butt frame, the connection section has a second butt frame, and the first butt frame and the second butt frame are connected by a bolt.
According to some embodiments, the r-shaped ring is provided with an outer groove from the outer side to the inner side, or provided with an inner groove from the inner side to the outer side.
According to some embodiments, the r-ring is attached to the connector segment by a first circumferential groove and connected by a rivet or a lock-bottom weld.
According to some embodiments, the r-ring is attached to the tank shell by a butt weld or by a second ring groove that is fitted to the tank shell and attached by a lock bottom weld.
According to some embodiments, the r-ring is attached to the tank bottom by a butt weld or by a third ring groove that engages and is attached to the tank bottom by a lockseam weld.
Preferably, a thinning groove is formed in one side wall, close to the bottom of the storage box, of the r-shaped ring.
Further, the storage box comprises a front box and a rear box, and the connecting section is a stage section, a box section or a power cabin.
Preferably, it is made of 2A14 aluminum alloy material and welded by friction stir welding process.
Compared with the prior art, the spherical-bottom rocket storage box with the simplified structure has the beneficial technical effects that:
1. compared with the existing storage tank, the invention simplifies the structural design, removes the transition section and the end frame, adopts the r-shaped ring structure to integrate the transition section, the end frame and the Y-shaped ring, reduces the matching of the storage tank structural member, saves the tooling equipment for production or welding assembly of the storage tank transition section and the end frame, reduces the process difficulty of production and manufacture of the storage tank, and can effectively reduce the manufacturing cost of the storage tank.
2. The r-shaped ring structure and the connection form of the r-shaped ring structure are welded with the bottom of the storage tank and a storage tank shell by butt welding seams or lock bottom welding seams, mechanically connected with a connection section (a stage section, a tank section or a power cabin) by a bolt, or connected by riveting and welding according to the requirements of materials, structures, connection functions and working conditions. The r-shaped ring structure is designed with bolts or inner and outer grooves, which is beneficial to connection and structure weight reduction.
3. The invention is provided with the arc-shaped thinning groove, thereby realizing the release and the reduction of the concentrated stress effect generated on the welding seam when the bottom of the storage tank is pressed.
4. The storage tank adopts 2A14 aluminum alloy material and a friction stir welding process. As a low-temperature storage tank structural material of a liquid oxygen and methane rocket, the 2A14 aluminum alloy has better low-temperature strength, is favorable for reducing or controlling the structural weight and improves the load efficiency of the rocket. The solid-phase welding process of friction stir welding can effectively improve the strength coefficient of a welding line and reduce the quality defects of welding pores, inclusions, cracks and the like. The optimization of materials and processes can ensure that the rocket storage tank has better comprehensive performance and higher cost performance.
Drawings
Fig. 1a and 1b are schematic structural views of conventional rockets.
FIG. 1c is a schematic cross-sectional view of section D of FIG. 1 a.
Fig. 2a and 2b are schematic structural views of rockets according to an embodiment of the present invention.
Fig. 2c is a schematic cross-sectional view of section E of fig. 2 a.
Fig. 3 to 6 are schematic cross-sectional views of corresponding part E in other embodiments of the present invention.
Description of reference numerals in the drawings:
A. a first-order arrow body structure; B. a secondary arrow structure; C. a cowling; a1, a front box; a2, a rear box; a3, a tank interval section; a4, a stage section; a5, a power cabin; a11, a front box front end frame; a12, a front box front transition section; a13, the front bottom of the front box; a14, a front Y-shaped ring of the front box; a15, a front box shell; a16, a front box rear Y-shaped ring; a17, the rear bottom of the front box; a18, a front box rear transition section; a19, a front box rear end frame; a21, a front end frame of the rear box; a22, a rear box front transition section; a23, the front bottom of the rear box; a24, a Y-shaped ring in front of a rear box; a25, a rear box shell; a26, a Y-shaped ring behind the rear box; a27, the rear bottom of the rear box; a28, a rear box rear transition section; a29, a rear box rear end frame; 1. a tank housing; 2. the bottom of the storage box; 3. a connecting section; 4. an r-shaped ring; 401. a front r-shaped ring of the front box; 402. a r-shaped ring behind the front box; 403. a r-shaped ring in front of the rear box; 404. a rear r-shaped ring of the rear box; 5. a first docking frame; 6. a second docking frame; 7. an outer groove; 8. an inner groove; 9. a first ring groove; 10. a second ring groove; 11. a third ring groove; 12. butt welding; 13. a lock bottom weld; 14. riveting; 15. and thinning the groove.
Detailed description of the preferred embodiments
In order to make the objects, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is obvious that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
It should be noted that, for convenience of description, only the portions related to the related invention are shown in the drawings. The embodiments and features of the embodiments of the invention may be combined with each other without conflict.
It should be noted that the terms "first", "second", and the like in the present invention are only used for distinguishing different devices, modules or units, and are not used for limiting the order or interdependence relationship of the functions performed by the devices, modules or units.
It is noted that references to "a", "an", and "the" modifications in the present invention are intended to be illustrative rather than limiting, and that those skilled in the art will recognize that reference to "one or more" unless the context clearly dictates otherwise.
The invention discloses a spherical-bottom rocket storage tank with a simplified structure, which belongs to the technical field of rockets, and comprises a cylindrical storage tank shell, wherein the end part of the storage tank shell is connected with the bottom of the storage tank through an r-shaped ring; and one end of the r-shaped ring, which is far away from the tank shell, is connected with a connecting section. The connecting section is connected with the r-shaped ring of the storage box by bolts, riveting or welding. The storage box structure of the invention has simplified design, eliminates the transition section and the end frame of the storage box, reduces the matching of the structural parts of the storage box, saves the tooling equipment for the production or welding assembly of the storage box, reduces the process difficulty of the production and the manufacture of the storage box, and can effectively reduce the manufacturing cost of the storage box.
Referring to fig. 1a to 1c, it is a structure of a conventional liquid rocket, a tank-shaped storage tank is provided with a storage tank shell outside, two ends of the storage tank are provided with protruding storage tank bottoms, and the storage tank bottoms at the two ends of the storage tank are provided with a plurality of sections of connected annular connecting structures outside. Therefore, in addition to the bottom of the tank and the outer casing constituting the tank, the first-stage rocket body structure includes 12 connecting parts, namely a front tank front end frame a11, a front tank front transition section a12, a front tank front Y-shaped ring a14, a front tank rear Y-shaped ring a16, a front tank rear transition section a18, a front tank rear end frame a19, a rear tank front end frame a21, a rear tank front transition section a22, a rear tank front Y-shaped ring a24, a rear tank rear Y-shaped ring a26, a rear tank rear transition section a28 and a rear tank rear end frame a29. Furthermore, the parts need to be manufactured, assembled and connected respectively, the process is complex, the processing difficulty is high, the cost is high, the total weight is also high, and the development of a commercial carrier rocket which is required to reduce the cost is hindered.
Therefore, the invention provides a spherical-bottom rocket storage tank with a simplified structure, which is a spherical-bottom rocket storage tank with a simplified structure, please refer to fig. 2a to fig. 2b, the improvement focus is that a transition section, an end frame and a Y-shaped ring split type structure of the storage tank are eliminated, the three structures and functions are fused and optimized to form an r-shaped ring, and therefore 4 parts of a front r-shaped ring 401 of a front box, a rear r-shaped ring 402 of the front box, a front r-shaped ring 403 of a rear box and a rear r-shaped ring 404 of the rear box replace 12 parts in the prior art, the structure is simplified, and the weight is also reduced.
Specifically, referring to fig. 2c, the compact spherical-bottom rocket tank includes a cylindrical tank housing 1, and the end of the tank housing 1 is connected (generally welded) to a spherical tank bottom 2 by an r-ring 4, thereby forming a sealed tank. A cylindrical or conical connecting section 3 is connected to the end of the r-shaped ring 4 remote from the tank housing 1. The outer sides of the tank housing 1, the r-ring 4 and the connecting section 3 are aligned, thereby facilitating assembly and reducing aerodynamic drag.
For the first-stage rocket body structure, the spherical bottom rocket storage tank with a simplified structure comprises a front tank A1 and a rear tank A2, and correspondingly, the connecting section 3 is a stage section A4, a tank section A3 or a power cabin A5 adjacent to the upper part or the lower part of the storage tank. It is contemplated that aspects of the present invention may also be employed with two-level arrow configurations and the like. The r-shaped ring 4 of the invention is an annular structure with an r-shaped section, and three end parts of the r shape are respectively connected with the connecting section 3, the storage box shell 1 and the storage box bottom 2, thereby forming a stable integrally fixed arrow body structure.
In the embodiment shown in fig. 2c, the r-ring 4 has a first butt frame 5, the connection section 3 has a second butt frame 6, and the first butt frame 5 and the second butt frame 6 each have a plurality of through holes for bolt connection so as to be connected by bolts. Furthermore, the r-shaped ring 4 is provided with an outer groove 7 from the outside to the inside, the outer groove 7 is communicated with the through hole of the first butt-joint frame 5, and the volume is as large as possible on the premise of meeting the structural strength, so that the installation of the outer through-nail butt-joint bolt is facilitated, and the weight reducing effect is achieved. The outer grooves 7 are intermittent, i.e. only provided at the through hole locations, thereby ensuring structural strength. The r-shaped ring 4 is connected with the connecting section 3 through bolts, and the r-shaped ring 4 is directly butted with the storage tank shell 1 and the storage tank bottom 2 and is welded through a butt welding seam 12.
In another embodiment shown in fig. 3, the r-shaped ring 4 and the connecting section 3 are bolted together by a butt-joint frame, but an inner groove 8 is formed in the r-shaped ring 4 from the inside to the outside, and the volume is as large as possible while satisfying the structural strength, thereby achieving the weight reduction effect. At the position where the r-shaped ring 4 is connected with the tank shell 1, the r-shaped ring 4 is provided with a second annular groove 10 which is an annular groove recessed inwards to accommodate the tail end of the tank shell 1, or it can be understood that an annular baffle is additionally arranged on the inner side on the basis of the structure shown in fig. 2c, in short, the area of the fit between the r-shaped ring 4 and the tank shell 1 is increased through the structure, and the r-shaped ring can be welded through a lock bottom welding seam 13 to ensure the sealing of the welding seam. Similarly, at the position where the r-shaped ring 4 is connected with the tank bottom 2, the r-shaped ring 4 is provided with a third annular groove 11, the area of the r-shaped ring 4 attached with the tank bottom 2 is increased, and the r-shaped ring is welded through a lock bottom welding line 13.
In another embodiment as shown in fig. 4, the r-shaped ring 4 has a first ring groove 9 at the position where the r-shaped ring 4 is connected to the connecting section 3, and the connecting section 3 has through holes, such as two rows of holes distributed uniformly in the circumferential direction, at the end and the first ring groove 9, and the through holes are fixed by rivets 14. The r-shaped ring 4 is welded with the storage tank shell 1 and the storage tank bottom 2 through butt-joint welding seams 12.
It can be understood that the connection mode of the three ends of the r-shape of the r-shaped ring 4 and whether the outer groove 7 or the inner groove 8 is provided can be selected and combined according to the requirement, for example, in another embodiment shown in fig. 5, the r-shaped ring 4 has the outer groove 7, is connected with the connecting section 3 through a bolt, and is welded with the tank shell 1 and the tank bottom 2 through the lock bottom welding seam 13. Naturally, the r-shaped ring 4 may be connected to the tank case 1 and the tank bottom 2 by bolts or rivets, or may be welded to the connecting section 3, and in consideration of convenience in assembling the entire structure and the need for subsequent use, it is preferable that the r-shaped ring 4 is directly welded to the tank case 1 and the tank bottom 2 to form a sealing structure integrally connected to the tank main body, and the r-shaped ring 4 is detachably connected to the connecting section 3 by bolts, so that maintenance and the like can be facilitated.
In a preferred embodiment, as shown in fig. 6, an arc-shaped thinning groove 15 is formed on one side wall of the r-shaped ring 4 close to the bottom 2 of the storage tank. By adopting the design of 'weld joint stress release thinning arc-shaped groove under the compression action of the tank bottom', the concentrated stress generated on the weld joint under the compression action of the tank bottom 2 of the storage tank can be reduced, and the stress condition of the structure is improved.
In addition, the general rocket tank materials mainly adopt aluminum alloys 5A06, 2A14, 2219 and the like in terms of materials, so that the items currently adopt 2195 aluminum alloy materials with higher strength, tanks adopting composite materials or composite structures are also available, and tank structures adopting stainless steel materials are also available for ultra-large rockets.
The rocket storage tank disclosed by the invention preferably adopts 2A14 aluminum alloy materials with better comprehensive performance and cost performance, and is welded by adopting a friction stir welding process. As a storage tank of a liquid oxygen and methane rocket, the low-temperature strength of the 2A14 aluminum alloy is close to 500MPa, and the low-temperature property is better. And a solid-phase welding process of friction stir welding is adopted, so that the strength coefficient of a welding seam can be effectively improved, and quality defects such as welding pores, impurities, cracks and the like are reduced.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (4)
1. The spherical-bottom rocket storage box with the simplified structure is characterized by comprising a cylindrical storage box shell (1), wherein the end part of the storage box shell (1) is connected with a storage box bottom (2) through an r-shaped ring (4); one end of the r-shaped ring (4) far away from the tank shell (1) is connected with a connecting section (3);
the r-shaped ring (4) is provided with a first butt joint frame (5), the connecting section (3) is provided with a second butt joint frame (6), and the first butt joint frame (5) and the second butt joint frame (6) are both provided with through holes and connected through bolts; an outer groove (7) is formed in the r-shaped ring (4) from the outer side to the inner side, and the outer groove (7) is communicated with the through hole of the first butt-joint frame (5);
the r-shaped ring (4) is connected with the storage tank shell (1) through a butt weld, or is attached to the storage tank shell (1) through a second annular groove (10) and is connected through a lock bottom weld;
the r-shaped ring (4) is attached to the bottom (2) of the storage box through a third annular groove (11) and connected through a lock bottom welding line;
the storage box comprises a front box (A1) and a rear box (A2), and the connecting section (3) is a stage section (A4), a box section (A3) or a power cabin (A5).
2. The reduced-structure spherical-bottom rocket tank according to claim 1, wherein the r-shaped ring (4) is provided with an inner groove (8) from the inside to the outside.
3. The reduced-structure spherical-bottom rocket storage tank according to claim 1, wherein a thinning groove (15) is formed in one side wall of the r-shaped ring (4) close to the tank bottom (2).
4. The reduced-structure spherical-bottom rocket tank according to any one of claims 1-3, wherein the tank is made of 2A14 aluminum alloy material and is welded by friction stir welding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211492084.6A CN115596573B (en) | 2022-11-25 | 2022-11-25 | Spherical-bottom rocket storage box with simple structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211492084.6A CN115596573B (en) | 2022-11-25 | 2022-11-25 | Spherical-bottom rocket storage box with simple structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115596573A CN115596573A (en) | 2023-01-13 |
| CN115596573B true CN115596573B (en) | 2023-04-14 |
Family
ID=84852654
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211492084.6A Active CN115596573B (en) | 2022-11-25 | 2022-11-25 | Spherical-bottom rocket storage box with simple structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115596573B (en) |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5085343A (en) * | 1989-10-23 | 1992-02-04 | Martin Marietta Corporation | Nested tank construction |
| RU2333869C2 (en) * | 2003-03-28 | 2008-09-20 | Моуджейв Аэроспейс Венчерз, Ллс | Unified combined rocket system |
| CN104439686B (en) * | 2014-11-13 | 2016-06-29 | 首都航天机械公司 | A kind of friction stir welding method locking base ring seam for carrier rocket tank |
| CN109736973B (en) * | 2019-01-30 | 2022-04-29 | 北京星际荣耀空间科技股份有限公司 | Storage tank transition ring and propellant storage tank |
| CN215984225U (en) * | 2021-08-27 | 2022-03-08 | 火箭派(北京)航天科技有限公司 | Liquid rocket for bioburden launching |
-
2022
- 2022-11-25 CN CN202211492084.6A patent/CN115596573B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN115596573A (en) | 2023-01-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107416183B (en) | Spar connection structure of aircraft wing | |
| CN101472794B (en) | Aerial vehicle airframe segment, aerial vehicle airframe and method for producing aerial vehicle airframe | |
| CN204223194U (en) | A kind of light thin-wall goalpost shape suspension type tank structure | |
| CN213481148U (en) | Three-boosting carrier based on modular fixed power system | |
| CN112298617B (en) | On-orbit separable satellite propulsion service cabin main structure | |
| US20140217233A1 (en) | Aircraft propulsion assembly | |
| CN114718763B (en) | Liquid carrier rocket and propellant storage tank thereof | |
| CN115596573B (en) | Spherical-bottom rocket storage box with simple structure | |
| CN109050989B (en) | Double-star point type adapter | |
| CN109736973B (en) | Storage tank transition ring and propellant storage tank | |
| CN103963955B (en) | Aircraft frame, aircraft fuselage and the method being used for being installed together two aircraft fuselage section | |
| CN218624445U (en) | Cone-shaped bottom rocket storage box with simple structure | |
| CN115628155B (en) | Common-bottom storage tank and rocket structure thereof | |
| CN218545466U (en) | Spherical common-bottom rocket storage tank with simplified structure | |
| CN112611269A (en) | Carrier rocket | |
| CN115539252B (en) | Tapered common-base rocket storage tank with simplified structure | |
| CN205221111U (en) | Modularization aircraft | |
| CN105129087A (en) | Aircraft modularization solution method and modularized aircraft | |
| CN210116656U (en) | Rocket and propellant storage tank thereof | |
| CN216270000U (en) | Multi-satellite series satellite launching device | |
| CN110979630B (en) | Composite vertical-fin main box section wing spar root joint considering damage safety and design method | |
| CN209838557U (en) | Assembly structure, rocket engine and liquid rocket | |
| CN112407229A (en) | Unmanned helicopter fuselage force transmission structure assembly | |
| CN108657559B (en) | Battery tray and vehicle | |
| CN114408160B (en) | Tail support pipe and unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |