CN210027982U

CN210027982U - Magnesium alloy spaceflight cabin casting shell

Info

Publication number: CN210027982U
Application number: CN201920732568.0U
Authority: CN
Inventors: 李小龙; 张欢德
Original assignee: Nanjing Nanchao Mould Equipment Co Ltd
Current assignee: Nanjing Nanchao Mould Equipment Co Ltd
Priority date: 2019-05-21
Filing date: 2019-05-21
Publication date: 2020-02-07
Anticipated expiration: 2029-05-21

Abstract

The utility model discloses a magnesium alloy space capsule section foundry goods casing, including the covering, the covering is the tube-shape, the equipartition has multiunit support bar, every group in the covering the support bar includes the support bar that two symmetries set up, support bar and covering fixed connection, every group the equipartition has a plurality of arc baffles between the support bar, arc baffle's arc lateral wall and covering inner wall fixed connection, arc baffle's both ends respectively with the support bar fixed connection of both sides, adjacent the equipartition has a plurality of reinforcement strip, and is a plurality of between the arc baffle reinforcement strip both ends respectively with two adjacent arc baffle fixed connection, reinforcement strip and covering fixed connection. The utility model discloses to make the casting mode that adopts the integration with the covering except that the skeleton component of roof beam, bulk strength and rigidity are higher, strengthen simultaneously the processing to the roof beam alone to accept the effort between a plurality of baffles and the roof beam through the support bar, reduce the fracture probability.

Description

Magnesium alloy spaceflight cabin casting shell

Technical Field

The utility model relates to an aerospace equipment facility technical field especially relates to a magnesium alloy aerospace cabin section foundry goods casing.

Background

At present, a casting shell of a aerospace flight segment has an integral structure, and a skin and a skeleton element are processed into an integral structure. The structure type has the advantages of a semi-hard shell structure, high strength and rigidity, good structural integrity, less assembly amount, high appearance quality and the like. However, this type of shell is limited by the processing conditions and is not suitable for aerospace sections with larger diameters.

However, in this structural style, the beam and the bulkheads are integrated, when the beam bears axial force and bending moment, the contact parts of the bulkheads and the beam have large bearing force and are easy to break, the strength requirement of the beam is greatly different from that of the skin, and the strength and toughness of the beam cannot be increased under the condition of integrated casting.

To this end, we propose a magnesium alloy aerospace cabin casting shell to solve the above problems.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving the defects existing in the prior art and providing a magnesium alloy spaceflight cabin casting shell.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

the utility model provides a magnesium alloy space capsule section foundry goods casing, includes the covering, the covering is the tube-shape, the equipartition has the multiunit support bar in the covering, every group the support bar includes the support bar that two symmetries set up, support bar and covering fixed connection, every group the equipartition has a plurality of arc baffles between the support bar, the arc lateral wall and the covering inner wall fixed connection of arc baffle, arc baffle's both ends respectively with the support bar fixed connection of both sides, adjacent the equipartition has a plurality of reinforcing bars, and is a plurality of reinforcing bar both ends respectively with two adjacent arc baffles fixed connection, reinforcing bar and covering fixed connection.

Preferably, the end surfaces of the two support bars, which face away from each other, are both in an arc shape bending outwards.

Preferably, the end face of the reinforcing strip, which is far away from the skin, is in an inward-bending arc shape.

Preferably, a slot for mounting the beam is formed between the two support bars, and a plurality of transverse mounting holes for assisting in reinforcing the beam are uniformly distributed on the support bars.

Preferably, a plurality of positioning holes are uniformly distributed in one end of the skin, a plurality of positioning short columns are uniformly and fixedly connected to the other end of the skin, and the plurality of positioning short columns correspond to the plurality of positioning holes respectively.

Preferably, the cross-sectional width of the reinforcing strip is smaller than that of the arc-shaped partition plate.

Preferably, the cross-sectional width of the support bar is greater than that of the arc-shaped partition plate.

Compared with the prior art, the beneficial effects of the utility model are that:

1. the framework elements except the beam are integrally cast with the skin, so that the integral strength and rigidity are increased, the integral loading quantity is reduced, the operation steps are reduced in the manufacturing process, the framework elements can be used for automatic production, excessive grinding operation is not needed after the casting is finished, and meanwhile, the production efficiency and the production precision can be ensured.

2. The beam and the skin are not integrally cast, the strength and the toughness of the beam can be increased independently, so that the supporting function and the resisting function of the beam are guaranteed, the supporting bars arranged can uniformly transmit the acting force of the partition plate to the beam, the stress area is increased, the stress effect is guaranteed, the axial bearing force and the bending moment of the beam are increased, and the overall strength is higher.

Drawings

Fig. 1 is a schematic structural diagram of a magnesium alloy spaceflight cabin casting shell provided by the utility model;

fig. 2 is a schematic end face structure view of a magnesium alloy spaceflight cabin casting shell provided by the utility model;

fig. 3 is a schematic structural view of a support bar in a magnesium alloy spaceflight cabin casting shell provided by the utility model;

FIG. 4 is the schematic structural diagram of the reinforcing bar in the casting shell of the magnesium alloy spaceflight cabin section provided by the utility model

In the figure: the structure comprises a skin 1, support bars 2, an arc-shaped clapboard 3, a reinforcing bar 4, a positioning short column 5 and a positioning hole 6.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.

Referring to fig. 1-4, a magnesium alloy aerospace cabin casting casing, including covering 1, covering 1 is the tube-shape, and covering means to surround outside the skeleton structure and with adhesive or fix with rivet on the skeleton, forms the dimension shape component of aircraft appearance, in the aerospace field, covering 1 of the general commonly used barrel-type, covering 1 serves the equipartition and has a plurality of locating holes 6, and the even fixedly connected with a plurality of locating stubs 5 of covering 1 other end, a plurality of locating stubs 5 correspond with a plurality of locating holes 6 position respectively, can play the positioning action when multistage cabin is spliced, conveniently splice.

Wherein, the equipartition has multiunit support bar 2 in covering 1, every group support bar 2 includes the support bar 2 that two symmetries set up, the terminal surface that two root support bars 2 deviate from each other all is the arc of outside bending, increase the bearing capacity, support bar 2 and covering 1 fixed connection, form the fluting that is used for installing the roof beam between two root support bars 2, can arrange the roof beam in and install between two support bars 2, thereby support bar 2 can play the effect of consolidating and supplementary bearing capacity to the roof beam, the equipartition has a plurality of horizontal mounting holes that are used for supplementary reinforcement roof beam on support bar 2, a support bar 2 is fixed with the roof beam.

Wherein, a plurality of arc-shaped clapboards 3 are uniformly distributed between each group of supporting bars 2, which play the role of a clapboard and are skeleton elements, the section width of each supporting bar 2 is larger than that of the arc-shaped clapboard 3, the structure is rationalized, the effect of the supporting bars 2 on a beam is ensured, the arc-shaped side wall of each arc-shaped clapboard 3 is fixedly connected with the inner wall of the skin 1, two ends of each arc-shaped clapboard 3 are respectively fixedly connected with the supporting bars 2 at two sides, which can bear the acting force from the skin 1 and the supporting bars 2 at two sides, a plurality of reinforcing bars 4 are uniformly distributed between the adjacent arc-shaped clapboards 3, which play a reinforcing role and can bear the axial force, the section width of each reinforcing bar 4 is smaller than that of each arc-shaped clapboard 3, the structure is rationalized, the end surfaces of the reinforcing bars 4 far away from the skin 1 are in an inward-bent arc shape, the reinforcing strip 4 is fixedly connected with the skin 1, can bear the axial force from the arc-shaped clapboard 3, and plays a role in reinforcing.

The utility model discloses in, when carrying out the monolithic fabrication, support bar 2 except the roof beam, arc baffle 3, it makes through the mode of casting together to consolidate strip 4 and locator post 5 and covering 1, through simple operation of polishing after the casting is accomplished, then in arranging the fluting between two spinal branch brace 2 with the roof beam that additionally made in, the roof beam can increase intensity and toughness through extra process, it is fixed with roof beam and covering 1 through bonding agent or fix with rivet, a plurality of horizontal mounting holes through equipartition on the support bar 2 are fixed with roof beam support bar 2 simultaneously, when bearing the axial force, it can play supplementary reinforced effect to consolidate strip 4, when bearing the tangential force, arc baffle 3 can play the effect that the load was resisted.

The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.

Claims

1. A magnesium alloy spaceflight cabin casting shell comprises a skin (1) and is characterized in that, the skin (1) is in a cylindrical shape, a plurality of groups of supporting bars (2) are uniformly distributed in the skin (1), each group of supporting bars (2) comprises two symmetrically arranged supporting bars (2), the supporting bars (2) are fixedly connected with the skin (1), a plurality of arc-shaped clapboards (3) are uniformly distributed among the supporting bars (2) of each group, the arc-shaped side wall of the arc-shaped clapboard (3) is fixedly connected with the inner wall of the skin (1), the both ends of arc baffle (3) respectively with support bar (2) fixed connection of both sides, it is adjacent the equipartition has a plurality of reinforcing strip (4) between arc baffle (3), and is a plurality of reinforcing strip (4) both ends respectively with two adjacent arc baffle (3) fixed connection, reinforcing strip (4) and covering (1) fixed connection.

2. The magnesium alloy spaceflight cabin segment casting shell as claimed in claim 1, wherein the end surfaces of the two support bars (2) which face away from each other are in an outward curved arc shape.

3. A magnesium alloy aerospace capsule section casting shell according to claim 1, wherein the end face of the reinforcing strip (4) remote from the skin (1) is in the shape of an inwardly curved arc.

4. The magnesium alloy spaceflight cabin section casting shell as claimed in claim 1, wherein a slot for mounting the beam is formed between the two support bars (2), and a plurality of transverse mounting holes for auxiliary reinforcing beams are uniformly distributed on the support bars (2).

5. The magnesium alloy aerospace cabin casting shell according to claim 1, wherein a plurality of positioning holes (6) are uniformly distributed on one end of the skin (1), a plurality of positioning short columns (5) are uniformly and fixedly connected to the other end of the skin (1), and the plurality of positioning short columns (5) correspond to the plurality of positioning holes (6) respectively.

6. A magnesium alloy aerospace capsule section casting shell according to claim 1, wherein the reinforcing strips (4) have a cross-sectional width smaller than the cross-sectional width of the segmental baffles (3).

7. A magnesium alloy aerospace capsule section casting shell according to claim 1, wherein the support bars (2) have a cross-sectional width greater than the cross-sectional width of the segmental baffles (3).