CN115535298A - Cabin section shell structure - Google Patents
Cabin section shell structure Download PDFInfo
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- CN115535298A CN115535298A CN202211023947.5A CN202211023947A CN115535298A CN 115535298 A CN115535298 A CN 115535298A CN 202211023947 A CN202211023947 A CN 202211023947A CN 115535298 A CN115535298 A CN 115535298A
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- Prior art keywords
- end frame
- skin
- shell structure
- rear end
- separation
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- 238000000926 separation method Methods 0.000 claims abstract description 51
- 239000002360 explosive Substances 0.000 claims description 3
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 239000002775 capsule Substances 0.000 claims 1
- 238000003754 machining Methods 0.000 abstract description 7
- 230000000694 effects Effects 0.000 description 6
- 238000005266 casting Methods 0.000 description 5
- 238000005728 strengthening Methods 0.000 description 5
- 238000004880 explosion Methods 0.000 description 4
- 230000000149 penetrating effect Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 230000003139 buffering effect Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
Abstract
The utility model provides a cabin section shell structure, includes front end frame, rear end frame, covering and a plurality of separation cylinder, the opposite side of front end frame and rear end frame is equipped with preceding accepting portion and back accepting portion respectively, the both sides of covering are connected to preceding accepting portion and back accepting portion respectively, a plurality of separation cylinders are arranged between front end frame and rear end frame along circumference, the one end of separation cylinder is connected to front end frame and the other end is connected to the rear end frame, the side of separation cylinder is equipped with the supporting part that is connected to the inboard of covering. According to the scheme, the front bearing part and the rear bearing part are arranged, so that the skin is stably connected with the front end frame and the rear end frame, the integral structure is effectively simplified, and the processing cost is reduced; at the same time, the support of the skin is achieved by connecting the separating cylinder directly between the front and rear end bells and by bringing the side of the separating cylinder into abutment against the inside of the skin. The cabin shell structure of the scheme has the advantages of high machining and forming efficiency, good manufacturability and low machining cost of all components.
Description
Technical Field
The invention relates to the technical field of spacecraft structures, in particular to a cabin shell structure.
Background
The shell structure of the spacecraft is high in requirement, and in order to ensure the integral bearing strength of the shell structure, the shell structure usually adopts a form of integral molding of grid ribs or a form of bearing riveting of stringers. The integral forming mode of the grid ribs is that the raw materials are subjected to casting forming and then subjected to local finish machining, the wall thickness of a shell of the forming mode is not well controlled, if the shell is too thin, the processing difficulty is high, the rejection rate is high, if the shell is too thick, the total mass is large, the strength of a casting material is low compared with a forging material, and the difficulty of casting a large-diameter shell is large. The stringer bears the weight of the riveting form and has the riveting technology complicacy, and riveting stringer quantity is many, and stringer location and riveting need the type frame assistance-localization real-time, and skin specification is various and need design mould pressing frock shaping scheduling problem when not becoming the whole circle, and the cost input is great in the initial stage of developing, and later stage casing state slightly changes, and the type frame just need to be reformed or newly throw, and the waste is serious.
At present, the problem that the weight of a shell is uncontrollable and the strength of a casting material is low is generally solved by adopting the finish machining of all five-axis machining centers of a forged pipe in an integral forming mode of a grid rib, but the full machining cost is increased, the efficiency is reduced, the wall thickness of the shell cannot be too thin, and the rejection rate is high due to the fact that the shell is too thin and the machining difficulty is large.
The mode of riveting the stringer in a bearing mode is generally realized by reducing the types of the stringer and the skin, optimizing the structural layout, modifying the existing die fixture and other measures to improve the riveting efficiency and reduce the cost, but the mode has limited space for improving, and the problem of waste caused by slightly modifying the shell state and modifying or newly casting the fixture still exists.
Disclosure of Invention
The invention aims to provide a cabin shell structure which is stable in structure and convenient to machine and assemble.
In order to solve the problems, the invention provides a cabin shell structure which comprises a front end frame, a rear end frame, a skin and a plurality of separation cylinders, wherein a front bearing part and a rear bearing part are respectively arranged on the opposite sides of the front end frame and the rear end frame, the two sides of the skin are respectively connected to the front bearing part and the rear bearing part, the separation cylinders are circumferentially arranged between the front end frame and the rear end frame, one ends of the separation cylinders are connected to the front end frame, the other ends of the separation cylinders are connected to the rear end frame, and the side surfaces of the separation cylinders are provided with supporting parts connected to the inner side of the skin.
According to the scheme, the front bearing part and the rear bearing part are arranged, so that the skin is stably connected with the front end frame and the rear end frame, the integral structure is effectively simplified, and the processing cost is reduced; simultaneously, through with separating between cylinder lug connection front end frame and the rear end frame to make the side butt of separation cylinder connect to the inboard of covering in order to realize the support to the covering, make the separation cylinder can not only realize the cabin section separation function of basis, can also effectively improve the bearing strength and the bulk stiffness of whole casing. Compared with the prior art, the cabin shell structure has the advantages that the processing and forming efficiency of all the components is high, the manufacturability is good, the technology is mature, and the processing cost is low.
Preferably, the side face of the end, close to the skin, of the supporting portion is provided with a protruding receiving sheet, the receiving sheet is riveted to the skin, the other end of the supporting portion is provided with a groove, and the separating cylinder is welded to the groove, so that the supporting portion can play a better transition buffering role between the separating cylinder and the skin, and the overall structural strength is further improved.
Preferably, the support portions are distributed along the axial direction of the separation cylinder barrel, so that the support effect of the support portions on the separation cylinder barrel is further improved, and the support effect of the separation cylinder barrel and the support portions on the skin is improved.
Preferably, the front bearing portion is a front annular groove penetrating through the outer side wall of the front end frame, the rear bearing portion is a rear annular groove penetrating through the outer side wall of the rear end frame, and the groove depths of the front annular groove and the rear annular groove are equal to the thickness of the skin. The arrangement of the front annular groove and the rear annular groove enables the opposite sides of the front end frame and the rear end frame to form skirt-shaped structures, so that the skin can be conveniently positioned and assembled, and the outer side surfaces of the skin, the front end frame and the rear end frame after assembly are in a flat state.
As preferred, the inside wall of front end frame and rear end frame all is equipped with a plurality of strengthening ribs that distribute along circumference, the strengthening rib is used for supporting preceding accepting part and back accepting part to promote the structural strength of front end frame, rear end frame, guarantee that the connection between relative front end frame of covering and the rear end frame is more firm.
Preferably, the front bearing part is provided with a first positioning hole, the rear bearing part is provided with a second positioning hole, the front side and the rear side of the skin are respectively provided with a first positioning rivet used for being connected to the first positioning hole and a second positioning rivet used for being connected to the second positioning hole, and the front side and the rear side of the skin are respectively riveted to the front bearing part and the rear bearing part, so that the assembly is simple and convenient.
Preferably, the supporting frame further comprises supporting ribs, the butt seams of the skins are connected to the supporting ribs, so that the assembling difficulty of the skins relative to the front end frame and the rear end frame is further reduced, and the supporting ribs can play a certain strength improving role.
Preferably, the inner side of the front end frame is provided with a plurality of mounting frames distributed along the circumferential direction, the inner side of the rear end frame is provided with a plurality of bases distributed along the circumferential direction, the bottom end of the separation cylinder barrel is connected to the bases, the opening end of the separation cylinder barrel is connected to the mounting frames, and the mounting frames are provided with through holes for the inner rods of the separation cylinder barrel to penetrate through, so that the integral structure is stable, and subsequent assembly is facilitated.
Preferably, a plurality of explosion bolt boxes distributed along the circumferential direction are arranged on the outer side wall of the front end frame, and the explosion bolt boxes and the mounting frame are arranged at intervals; the lateral wall of rear end frame is equipped with a plurality of U type grooves along circumference distribution, U type groove with the base interval is arranged to make overall arrangement more reasonable.
Drawings
FIG. 1 is an axial schematic view of a nacelle shell structure;
FIG. 2 is a schematic view of a front end frame of a nacelle shell structure (the right side of FIG. 2 is the side of the front end frame facing the rear end frame);
FIG. 3 is a schematic illustration of the aft end frame of a deck section shell structure (the right side of FIG. 3 is the side of the aft end frame facing the forward end frame);
FIG. 4 is a schematic illustration of a skin of a nacelle section shell structure
FIG. 5 is a schematic illustration of a split cylinder and support portion of a deck section housing structure;
figure 6 is a schematic view of a support portion of a deck section shell structure.
The description of the reference numerals will be given,
1. a front end frame; 110. a front bearing part; 111. a first positioning hole; 120. mounting the frame; 121. a through hole; 130. an explosive bolt housing; 2. a rear end frame; 210. a rear receiving portion; 211. a second positioning hole; 220. a base; 230. a U-shaped groove; 3. covering a skin; 310. a first locating rivet; 320. a second set rivet; 330. butt seam welding; 4. separating the cylinder barrel; 410. a support portion; 411. a groove; 412. a receiving sheet; 5. reinforcing ribs; 6. and (7) supporting ribs.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. The technical solutions in the embodiments of the present invention will be 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 only a part of the embodiments of the present invention, and not all of the embodiments. 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. It should be noted that all directional indicators (such as up, down, left, right, front, back, inner and outer) in the embodiments of the present invention are only used for explaining the relative position relationship between the components, the motion situation, etc. in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indicator is changed accordingly.
Referring to fig. 1 to 6, a cabin shell structure according to an embodiment of the present invention includes a front end frame 1, a rear end frame 2, a skin 3, and a plurality of separation cylinders 4, where opposite sides of the front end frame 1 and the rear end frame 2 are respectively provided with a front receiving portion 110 and a rear receiving portion 210, two sides of the skin 3 are respectively connected to the front receiving portion 110 and the rear receiving portion 210, the plurality of separation cylinders 4 are circumferentially arranged between the front end frame 1 and the rear end frame 2, one end of each separation cylinder 4 is connected to the front end frame 1, the other end of each separation cylinder 4 is connected to the rear end frame 2, and a side surface of each separation cylinder 4 is provided with a support portion 410 connected to an inner side of the skin 3.
According to the scheme, the front bearing part 110 and the rear bearing part 210 are arranged, so that the skin 3 is stably connected with the front end frame 1 and the rear end frame 2, the integral structure is effectively simplified, and the processing cost is reduced; meanwhile, the separation cylinder barrel 4 is directly connected between the front end frame 1 and the rear end frame 2, and the side face of the separation cylinder barrel 4 abuts against the inner side of the skin 3 to support the skin 3, so that the separation cylinder barrel 4 can not only achieve the basic cabin separation function, but also effectively improve the bearing strength and the overall rigidity of the whole shell.
Compared with the prior art, the cabin shell structure has the advantages that the processing and forming efficiency of all the components is high, the manufacturability is good, the technology is mature, and the processing cost is low. Compared with the integral forming mode of the grid ribs, the scheme effectively improves the processing efficiency and greatly reduces the cost; compared with a stringer bearing riveting mode, the stringer bearing riveting device has the advantages that the relative connection of the skin 3, the front-end frame 1, the rear-end frame 2 and the separation cylinder barrel 4 is achieved by taking the skin 3 as a positioning reference, no complex mould pressing die is needed during skin 3 forming, no additional complex frame needs to be configured, the processing and assembling efficiency is high, the problem that the input frame cannot be used due to shell changing is solved, the input cost of an auxiliary tool is almost zero, and the quality of all components of the shell is controllable. It should be understood that the support portion 410 and the separation cylinder 4 may be integrated with each other or may be divided. For example, in some embodiments, the support portion 410 refers to an outer side wall of the separation cylinder 4, that is, the outer side wall of the separation cylinder 4 serves as the support portion 410 to abut and support the skin 3.
In other embodiments, the support part 410 is independent of the separating cylinder 4, the side of the support part 410 near the end of the skin 3 is provided with a raised receiving tab 412, and the receiving tab 412 is provided with a rivet connected to the skin 3. It should be understood that the support portion 410 and the skin 3 may be connected by other common methods such as screwing or welding, which is not limited by the present design. The one end that skin 3 was kept away from to supporting part 410 is equipped with recess 411, and separation cylinder 4 welds to recess 411 to make supporting part 410 can play transition cushioning effect between separation cylinder 4 and skin 3, promote holistic structural strength.
Furthermore, the number of the support portions 410 is three, and the support portions are uniformly distributed along the axial direction of the separation cylinder 4, and at least one support portion 410 is located in the middle of the separation cylinder 4, so that the support effect of the support portions 410 on the separation cylinder 4 is further improved, and the support effect of the separation cylinder 4 and the support portions 410 on the skin 3 is improved.
In the present embodiment, the front receiving portion 110 is a front annular groove penetrating through to the outer side wall of the front end frame 1, and the rear receiving portion 210 is a rear annular groove penetrating through to the outer side wall of the rear end frame 2, and the groove depths of the front annular groove and the rear annular groove are both equal to the thickness of the skin 3. The arrangement of the front annular groove and the rear annular groove enables the opposite sides of the front end frame 1 and the rear end frame 2 to form skirt-shaped structures, so that the skin 3 can be conveniently positioned and assembled, and the outer side faces of the skin 3, the front end frame 1 and the rear end frame 2 after assembly are guaranteed to be in a flat state.
Further, the inside wall of front end frame 1 and rear end frame 2 all is equipped with a plurality of strengthening ribs 5 that distribute along circumference, near position of the strengthening rib 5 extension preceding accepting portion 110 of front end frame 1 is in order to realize the reinforcement to preceding accepting portion 110, near position that strengthening rib 5 of rear end frame 2 extends to back accepting portion 210 is in order to realize the reinforcement to back accepting portion 210, thereby promote front end frame 1, the structural strength of rear end frame 2, it is more firm to guarantee the connection between relative front end frame 1 of covering 3 and the rear end frame 2.
In the present embodiment, the front socket 110 is provided with the first positioning hole 111, the rear socket 210 is provided with the second positioning hole 211, the front and rear sides of the skin 3 are respectively provided with the first positioning rivet 310 for connection to the first positioning hole 111 and the second positioning rivet 320 for connection to the second positioning hole 211, while the front and rear sides of the skin 3 are respectively riveted to the front socket 110 and the rear socket 210, thereby making assembly simple and convenient. It should be understood that the skin 3 may be connected to the front bolster 110 and the rear bolster 210 by other means commonly known in the art, such as bolting or welding, and the present design is not limited thereto.
As the optimization to above-mentioned embodiment, still include brace rod 6, the butt joint 330 of covering 3 is connected to brace rod 6 to further reduce the relative front end frame 1 of covering 3 and the assembly degree of difficulty of rear end frame 2, and brace rod 6 can play certain intensity and promote the effect.
As the optimization of the above embodiment, the inner side of the front end frame 1 is provided with a plurality of mounting frames 120 distributed along the circumferential direction, the inner side of the rear end frame 2 is provided with a plurality of bases 220 distributed along the circumferential direction, the cylinder bottom end of the separation cylinder 4 is connected to the bases 220, the cylinder opening end of the separation cylinder 4 is connected to the mounting frames 120, the mounting frames 120 are provided with through holes 121 through which the inner rod of the separation cylinder 4 passes, so that the overall structure is stable, the inner rod of the separation cylinder 4 can be loaded into the separation cylinder 4 through the through holes 121, and the assembly is simple and convenient.
Further, a plurality of explosion bolt boxes 130 distributed along the circumferential direction are arranged on the outer side wall of the front end frame 1, and the explosion bolt boxes 130 and the mounting frame 120 are arranged at intervals; the outer side wall of the rear end frame 2 is provided with a plurality of U-shaped grooves 230 distributed along the circumferential direction, the U-shaped grooves 230 are in a groove 411 shape and are arranged at intervals with the base 220, and therefore the overall layout is more reasonable.
Although the present disclosure has been described above, the scope of the present disclosure is not limited thereto. It will be apparent to those skilled in the art that various changes and modifications can be made without departing from the spirit and scope of the disclosure, and these changes and modifications will fall within the scope of the invention.
Claims (9)
1. The cabin shell structure is characterized by comprising a front end frame (1), a rear end frame (2), a skin (3) and a plurality of separation cylinders (4), wherein the opposite sides of the front end frame (1) and the rear end frame (2) are respectively provided with a front bearing part (110) and a rear bearing part (210), the two sides of the skin (3) are respectively connected to the front bearing part (110) and the rear bearing part (210), the separation cylinders (4) are circumferentially distributed between the front end frame (1) and the rear end frame (2), one ends of the separation cylinders (4) are connected to the front end frame (1) and the other ends of the separation cylinders are connected to the rear end frame (2), and the side faces of the separation cylinders (4) are provided with supporting parts (410) connected to the inner sides of the skin (3).
2. A cabin shell structure according to claim 1, characterized in that the side of the end of the support portion (410) close to the skin (3) is provided with a raised receiving tab (412), which receiving tab (412) is riveted to the skin (3), the other end of the support portion (410) is provided with a recess (411), and the split cylinder (4) is welded to the recess (411).
3. A cabin shell structure according to claim 2, characterized in that said supports (410) are plural and distributed along the axial direction of said separation cylinder (4).
4. A cabin segment shell structure according to claim 1, characterized in that the front socket (110) is a front annular groove running through to the outer side wall of the front end frame (1), and the rear socket (210) is a rear annular groove running through to the outer side wall of the rear end frame (2), the groove depth of both grooves being equal to the thickness of the skin (3).
5. A cabin segment shell structure according to claim 4, characterized in that the inner side walls of the front end frame (1) and the rear end frame (2) are provided with a plurality of reinforcing ribs (5) distributed along the circumferential direction, and the reinforcing ribs (5) are used for supporting the front bearing part (110) and the rear bearing part (210).
6. Cabin shell structure according to claim 4, characterized in that the front socket (110) is provided with a first positioning hole (111), the rear socket (210) is provided with a second positioning hole (211), the front and rear sides of the skin (3) are provided with a first positioning rivet (310) for connecting to the first positioning hole (111) and a second positioning rivet (320) for connecting to the second positioning hole (211), respectively, the front and rear sides of the skin (3) are riveted to the front socket (110) and the rear socket (210), respectively.
7. A capsule shell structure according to claim 1, characterized in that it further comprises support ribs (6), the butt seams (330) of the skin (3) being connected to said support ribs (6).
8. The cabin shell structure of claim 1, wherein a plurality of circumferentially distributed mounting frames (120) are arranged on the inner side of the front end frame (1), a plurality of circumferentially distributed bases (220) are arranged on the inner side of the rear end frame (2), the cylinder bottom end of the separation cylinder (4) is connected to the bases (220), the cylinder opening end of the separation cylinder (4) is connected to the mounting frames (120), and the mounting frames (120) are provided with through holes (121) for the inner rods of the separation cylinder (4) to pass through.
9. A cabin segment shell structure according to claim 8, characterized in that the outer side wall of the front end frame (1) is provided with a plurality of circumferentially distributed explosive bolt boxes (130), and the explosive bolt boxes (130) are arranged at intervals with the mounting frame (120); the outer side wall of the rear end frame (2) is provided with a plurality of U-shaped grooves (230) distributed along the circumferential direction, and the U-shaped grooves (230) and the base (220) are arranged at intervals.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211023947.5A CN115535298A (en) | 2022-08-24 | 2022-08-24 | Cabin section shell structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211023947.5A CN115535298A (en) | 2022-08-24 | 2022-08-24 | Cabin section shell structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115535298A true CN115535298A (en) | 2022-12-30 |
Family
ID=84725179
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211023947.5A Pending CN115535298A (en) | 2022-08-24 | 2022-08-24 | Cabin section shell structure |
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| Country | Link |
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| CN (1) | CN115535298A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107554818A (en) * | 2017-09-20 | 2018-01-09 | 上海微小卫星工程中心 | Satellite main force support structure |
| CN111674575A (en) * | 2020-05-26 | 2020-09-18 | 宁波天擎航天科技有限公司 | Cabin section connecting structure and aircraft |
| CN114322679A (en) * | 2021-12-31 | 2022-04-12 | 重庆零壹空间航天科技有限公司 | Solid rocket cold separation stage section suitable for automatic manufacturing |
-
2022
- 2022-08-24 CN CN202211023947.5A patent/CN115535298A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107554818A (en) * | 2017-09-20 | 2018-01-09 | 上海微小卫星工程中心 | Satellite main force support structure |
| CN111674575A (en) * | 2020-05-26 | 2020-09-18 | 宁波天擎航天科技有限公司 | Cabin section connecting structure and aircraft |
| CN114322679A (en) * | 2021-12-31 | 2022-04-12 | 重庆零壹空间航天科技有限公司 | Solid rocket cold separation stage section suitable for automatic manufacturing |
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