A lightweight umbrella hatch cover structure bearing double-point different step high impact ejection load

Abstract

The present application relates to a kind of lightweight umbrella hatch cover structure bearing double-point different step high impact ejection load, belong to high-performance landing buffer technical field;Including closed skin, well type structure and 2 ejection point place link beam;Wherein, well type structure is placed horizontally;Closed skin is completely covered in the outer wall of well type structure;Well type structure after being covered closed skin is as a whole disc structure;2 ejection point place link beam is symmetrically set in the two side walls of well type structure after being covered closed skin;Ejection point place link beam extends into the closed skin of butt joint;The present application is by clear load characteristics, interface constraint, load-bearing structure form, obtains the lightweight structure form bearing double-point different step high impact ejection load, can greatly reduce the iteration number of structure form, improves design and manufacturing efficiency, reduces structure weight.

Description

Technical Field

[0001] This invention belongs to the field of high-performance landing buffer technology and relates to a lightweight parachute canopy structure that can withstand high impact ejection loads from two asynchronous points. Background Technology

[0002] During spacecraft entry, deceleration, and landing, a parachute canopy structure is needed to enclose the parachute assembly housing. Simultaneously, the canopy is used to eject the parachute pack, enabling parachute deployment. For single-point ejection, ensuring the canopy's structural strength through structural design is sufficient. However, when structural layout is limited or a single ejector cannot meet ejection requirements, a dual- or multi-ejector scheme is necessary. Dual (or multi) ejection schemes require simultaneous ejection of the ejectors; otherwise, the rear ejection point will constrain the canopy, damaging it and failing to meet ejection requirements. This can lead to parachute failure, loss of deceleration function in the recovery subsystem, and even a hard landing of the spacecraft.

[0003] Currently, there are no relevant patents or documents in China that mention how to design a high-strength, lightweight parachute canopy structure that can withstand asynchronous impacts. Therefore, designing a parachute canopy structure that can withstand dual-point asynchronous high-impact ejection loads is of great significance for the development of spacecraft deceleration technology. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a lightweight parachute canopy structure that can withstand dual-point asynchronous high impact catapult loads. By clarifying the load characteristics, interface constraints, and load-bearing structural form, a lightweight structural form that can withstand dual-point asynchronous high impact catapult loads is obtained, which can significantly reduce the number of structural form iterations, improve design and manufacturing efficiency, and reduce structural weight.

[0005] The solution of the present invention is:

[0006] A lightweight parachute canopy structure capable of withstanding high-impact ejection loads at two asynchronous points includes a closed skin, a grid-like structure, and connecting beams at two ejection points. The grid-like structure is placed horizontally. The closed skin completely covers the outer wall of the grid-like structure. The grid-like structure after being covered with the closed skin has an overall disc-like structure. The connecting beams at the two ejection points are horizontally and symmetrically arranged on both sides of the grid-like structure after being covered with the closed skin. The connecting beams at the ejection points extend into the closed skin at the joint.

[0007] In the aforementioned lightweight parachute canopy structure designed to withstand dual-point asynchronous high-impact ejection loads, the diameter of the disc structure is 300 mm; the wall thickness of the closed skin is not less than 0.8 mm.

[0008] In the aforementioned lightweight parachute canopy structure designed to withstand dual-point asynchronous high-impact ejection loads, the surface of the disc structure is provided with four columnar grooves and four through holes; one columnar groove is located at the center of the upper surface of the disc structure; the other three columnar grooves are located on the upper surface of the disc structure and are evenly distributed along the circumference; the four through holes are located on the upper surface of the disc structure and are evenly distributed along the circumference; the diameter of the four through holes surrounding the ring is smaller than the diameter of the three columnar grooves surrounding the ring.

[0009] In the aforementioned lightweight parachute canopy structure designed to withstand dual-point asynchronous high-impact ejection loads, four columnar grooves allow for the avoidance of other external parts during parachute canopy assembly; four through holes serve as docking holes during parachute canopy assembly; and the positions of the three outer columnar grooves are customized according to actual needs.

[0010] In the aforementioned lightweight parachute canopy structure designed to withstand dual-point asynchronous high-impact ejection loads, the grid-shaped structure includes two horizontal stiffeners and two vertical stiffeners; the two horizontal stiffeners and two vertical stiffeners are staggered in a grid-like structure; the wall thickness of both the horizontal and vertical stiffeners is 1-3 mm; the vertical height of both the horizontal and vertical stiffeners is 10-15 mm; and the spacing L1 between the two horizontal stiffeners and between the two vertical stiffeners is 100-120 mm.

[0011] In the aforementioned lightweight parachute canopy structure designed to withstand high-impact ejection loads from two asynchronous points, four through holes are respectively located in the middle of two horizontal stiffeners and two vertical stiffeners in the grid-like structure.

[0012] In the aforementioned lightweight parachute canopy structure for withstanding dual-point asynchronous high-impact ejection loads, the connecting beam at the ejection point includes a portion exposed to the closed skin and a portion extending into the closed skin; wherein, the portion exposed to the closed skin is an isosceles triangular plate structure; the portion extending into the closed skin includes multiple uniformly placed cavity wall panels; a gap is left between two adjacent cavity wall panels to form a lightweight cavity.

[0013] In the aforementioned lightweight parachute canopy structure designed to withstand dual-point asynchronous high-impact ejection loads, the wall thickness of the cavity wall panel is 4-6 mm; the gap L2 between two adjacent cavity wall panels is 8-12 mm, meaning the width of the lightweight cavity is 8-12 mm.

[0014] In the aforementioned lightweight parachute canopy structure designed to withstand dual-point asynchronous high-impact ejection loads, the isosceles triangular plate structure is solid with no cavity, and the thickness of the isosceles triangular plate structure is not less than 9mm; the base of the isosceles triangular plate structure is connected to the disk structure, and the width of the base of the isosceles triangular plate structure covers the width of all lightweight cavities.

[0015] In the aforementioned lightweight parachute canopy structure designed to withstand high-impact ejection loads from two asynchronous points, the closed skin, the grid-shaped structure, and the connecting beams at the two ejection points are integrally formed using a 3D printing additive manufacturing method, and the entire structure is manufactured at a 45° angle.

[0016] The advantages of this invention compared to the prior art are:

[0017] (1) This invention, by clarifying load characteristics, interface constraints, and load-bearing structural forms, obtains a lightweight structural design form with optimized stress transfer, and provides an additive manufacturing method and an optimal manufacturing process method suitable for this structural form. Based on this method, it can be evolved and improved according to actual interface requirements, which can significantly reduce the number of structural form iterations, improve design and manufacturing efficiency, and reduce structural weight;

[0018] (2) The load-bearing structural forms of the present invention include a "well" type beam structure that minimizes mass while taking into account both interface and strength requirements; a thin skin structure and a closed connecting beam structure to increase structural stiffness; and a reinforced cavity structure at the ejection point that extends to intersect with the vertical continuous beam, which greatly improves the level of lightweighting.

[0019] (3) The additive manufacturing method of the present invention adopts the laser selective melting forming method, which focuses on ensuring that the raw materials and performance meet the technical requirements of laser selective melting forming materials; the optimal manufacturing process method is to control the structural forming direction—forming in a 45° tilt direction, which facilitates the forming of the inner cavity of the part and reduces the forming process support. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of the lightweight parachute canopy of the present invention;

[0021] Figure 2 This is a cross-sectional view of the lightweight parachute canopy structure of the present invention;

[0022] Figure 3 This is a schematic diagram showing the placement angle of the additively formed lightweight umbrella canopy structure of the present invention. Detailed Implementation

[0023] The present invention will be further described below with reference to the embodiments.

[0024] This invention provides a lightweight parachute canopy structure capable of withstanding dual-point asynchronous high-impact ejection loads. By clearly defining load characteristics, interface constraints, and load-bearing structural forms, a lightweight structural design with optimized stress transfer is obtained. An additive manufacturing method and an optimal manufacturing process method suitable for this structural form are also provided. Based on this method, it can be evolved and improved according to actual interface requirements, significantly reducing the number of structural iterations, improving design and manufacturing efficiency, and reducing structural weight.

[0025] The design process of this structure includes defining load characteristics, interface constraints, load-bearing structural form, and additive manufacturing methods adapted to this structural form as well as methods to improve manufacturability.

[0026] The load characteristics described are high-impact instantaneous loads of pyrotechnic devices. The load magnitude is generally in the range of several tons, the duration of action is generally ≤4ms, and the point of action is mirror-symmetrical along the central axis. Due to signal transmission and the response of the pyrotechnic device igniter, there is asynchrony, and the asynchrony time can currently be controlled to ≤1ms.

[0027] A lightweight parachute canopy structure capable of withstanding high-impact ejection loads from two asynchronous points, such as... Figure 1 , Figure 2 As shown, it specifically includes a closed skin 1, a grid-shaped structure 3, and two connecting beams 4 at the ejection points; wherein, the grid-shaped structure 3 is placed horizontally; the closed skin 1 completely covers the outer wall of the grid-shaped structure 3; the grid-shaped structure 3 after being covered with the closed skin 1 has an overall disc structure; the two connecting beams 4 at the ejection points are horizontally and symmetrically arranged on both sides of the grid-shaped structure 3 after being covered with the closed skin 1; the connecting beams 4 at the ejection points extend into the closed skin 1 at the joint.

[0028] The diameter of the disc structure is 300mm; the wall thickness of the closed skin 1 is not less than 0.8mm.

[0029] like Figure 1 As shown, the surface of the disk structure is provided with 4 columnar grooves and 4 through holes; one columnar groove is located at the center of the upper surface of the disk structure; the other 3 columnar grooves are located on the upper surface of the disk structure and are evenly distributed along the circumference; the 4 through holes are located on the upper surface of the disk structure and are evenly distributed along the circumference; the diameter of the 4 through holes surrounding the ring is smaller than the diameter of the 3 columnar grooves surrounding the ring.

[0030] Functionally, the four columnar grooves allow the parachute canopy structure to avoid other external parts during assembly; the four through holes serve as docking holes during assembly; and the positions of the three outer columnar grooves can be customized according to actual needs.

[0031] like Figure 2 As shown, the grid structure 3 includes two horizontal stiffeners and two vertical stiffeners; the two horizontal stiffeners and two vertical stiffeners are staggered in a grid pattern; the wall thickness of both the horizontal and vertical stiffeners is 1-3mm; the vertical height of both the horizontal and vertical stiffeners is 10-15mm; the spacing L1 between the two horizontal stiffeners and between the two vertical stiffeners is 100-120mm. Four through holes are respectively located in the middle of the two horizontal stiffeners and two vertical stiffeners in the central grid of the grid structure 3.

[0032] The connecting beam 4 at the ejection point includes a portion that exposes the closed skin 1 and a portion that extends into the closed skin 1; wherein, the portion that exposes the closed skin 1 is an isosceles triangular plate structure; the portion that extends into the closed skin 1 includes multiple uniformly placed cavity wall panels; a gap is left between two adjacent cavity wall panels to form a lightweight cavity 2.

[0033] To ensure the reliability of the overall structure, the wall thickness of the cavity wall panel is 4-6mm; the gap L2 between two adjacent cavity wall panels is 8-12mm, that is, the width of the lightweight cavity 2 is 8-12mm.

[0034] The isosceles triangular plate structure is solid with no cavity, and the thickness of the isosceles triangular plate structure is not less than 9mm; the base of the isosceles triangular plate structure is connected to the disk structure, and the width of the base of the isosceles triangular plate structure covers the width of all lightweight cavities 2.

[0035] The closed skin 1, the grid-shaped structure 3, and the connecting beams 4 at the two ejection points are integrally molded using 3D printing additive manufacturing method, and are manufactured at a 45° angle. Figure 3 As shown.

[0036] A lightweight parachute canopy structure capable of withstanding high-impact ejection loads from two asynchronous points is disclosed for use in the ejection parachute deployment phase during spacecraft deceleration, primarily in dual (multi)-point ejection parachute deployment schemes. The load characteristics involve high-impact instantaneous loads from pyrotechnic contaminants, typically on the order of several tons, caused by asynchronous signal transmission and pyrotechnic ignition responses. The interface constraints necessitate breaking the beam connection between the two points—the most basic structural form for high specific strength under bending loads. The load-bearing structural forms include a "well"-shaped beam structure that minimizes mass while balancing interface and strength requirements; a thin-skin structure; a closed connecting beam structure to increase structural stiffness; and reinforced cavity structures at the ejection points to enhance lightweighting. The additive manufacturing method employs selective laser melting (SLM). The optimal manufacturing process involves controlling the structural forming direction to ensure proper internal cavity forming and reduce the need for additional forming process support.

[0037] Example:

[0038] A lightweight parachute canopy structure capable of withstanding high-impact ejection loads from two asynchronous points, with the main structural form as follows: Figure 1 As shown. The load characteristics described are high-impact instantaneous loads of pyrotechnic devices. The load magnitude is generally in the range of several tons, and the action time is generally ≤4ms. The point of application is located on the outermost side of the parachute canopy structure, and the deceleration parachute is suspended in the middle area of ​​the parachute canopy. The applied load is mirror-symmetrical along the central axis. Due to signal transmission and the response of the pyrotechnic device igniter, there is asynchrony. The asynchrony time can currently be controlled to ≤1ms.

[0039] The overall layout of the structure is constrained by load characteristics and interfaces. The optimal force transmission path is a straight beam connecting the impact load application point, but it is interrupted in the middle due to interface constraints. The resulting intermediate radial stiffener structure has poor load-bearing capacity, and the vertical beams do not share the load and consume weight. By adopting the grid-shaped structure 3 of this invention, the interface can be avoided, and the load-bearing beams can be made continuous.

[0040] The use of lightweight cavity 2 can achieve effective connection between the load application point and the load-bearing beam, while also achieving lightweight design.

[0041] Using a closed skin 1 can improve the connection between beams in the grid structure 3, significantly enhancing the structural stiffness.

[0042] By using additive manufacturing methods to process products, we can adapt to structural forms that are hollow inside and closed outside, thereby improving the processability of the products.

[0043] The laser selective melting forming method is adopted, which takes into account both the raw materials and performance requirements of laser selective melting forming materials. Titanium alloy powder is used as the melting forming material, resulting in a lightweight structure with high specific strength and good temperature resistance, which can work normally at -120℃~200℃.

[0044] By placing it at a 45° angle, the weight increase caused by process support can be reduced, thus improving the level of lightweighting.

[0045] When using this embodiment to solve actual engineering needs, only load and interface constraints need to be considered. Rapid design can be completed by adjusting the dimensions of the cavity, skin, and "well" beam, and rapid processing can be completed through additive manufacturing methods and optimal manufacturing processes.

[0046] In addition to bearing two-point asynchronous loads, it can also be applied to tasks that bear multi-point asynchronous loads through an array "grid" structure.

[0047] This invention, by clearly defining load characteristics, interface constraints, and load-bearing structural forms, yields a lightweight structural design with optimized stress transfer. It also provides an additive manufacturing method and an optimal manufacturing process suitable for this structural form. Based on this method, it can be evolved and improved according to actual interface requirements, significantly reducing the number of structural iterations, improving design and manufacturing efficiency, and reducing structural weight.

[0048] The load-bearing structural forms of the present invention include a "well"-shaped beam structure that minimizes mass while balancing interface and strength requirements; a thin-skin structure and a closed connecting beam structure to increase structural stiffness; and a reinforced cavity structure at the ejection point that extends to intersect with the vertical continuous beam, greatly improving the level of lightweighting.

[0049] The additive manufacturing method of this invention adopts laser selective melting forming method, which focuses on ensuring that the raw materials and performance meet the technical requirements of laser selective melting forming materials; the optimal manufacturing process method is to control the structural forming direction - forming in a 45° tilt direction, which facilitates the forming of the internal cavity of the part and reduces the forming process support.

[0050] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A lightweight parachute canopy structure capable of withstanding high-impact ejection loads from two asynchronous points, characterized in that: It includes a closed skin (1), a grid structure (3), and two ejection point connecting beams (4); wherein, the grid structure (3) is placed horizontally; the closed skin (1) completely covers the outer wall of the grid structure (3); the grid structure (3) after being covered with the closed skin (1) is in the shape of a disc; the two ejection point connecting beams (4) are horizontally and symmetrically set on the two side walls of the grid structure (3) after being covered with the closed skin (1); the ejection point connecting beams (4) extend into the closed skin (1) at the joint.

2. The lightweight parachute canopy structure for withstanding dual-point asynchronous high-impact ejection loads according to claim 1, characterized in that: The diameter of the disc structure is 300 mm; the wall thickness of the closed skin (1) is not less than 0.8 mm.

3. The lightweight parachute canopy structure for withstanding dual-point asynchronous high-impact ejection loads according to claim 1, characterized in that: The surface of the disc structure is provided with 4 columnar grooves and 4 through holes; one columnar groove is located at the center of the upper surface of the disc structure; the other 3 columnar grooves are located on the upper surface of the disc structure and are evenly distributed along the circumference; the 4 through holes are located on the upper surface of the disc structure and are evenly distributed along the circumference; the diameter of the 4 through holes surrounding the ring is smaller than the diameter of the 3 columnar grooves surrounding the ring.

4. The lightweight parachute canopy structure for withstanding dual-point asynchronous high-impact ejection loads according to claim 3, characterized in that: Four columnar grooves allow the parachute canopy structure to avoid other external parts during assembly; four through holes serve as docking holes during parachute canopy structure assembly; and the positions of the three outer columnar grooves can be customized according to actual needs.

5. A lightweight parachute canopy structure for withstanding dual-point asynchronous high-impact ejection loads according to claim 4, characterized in that: The grid structure (3) includes two horizontal stiffeners and two vertical stiffeners; the two horizontal stiffeners and two vertical stiffeners are staggered to form a grid structure; the wall thickness of the horizontal stiffeners and the vertical stiffeners is 1-3mm; the vertical height of the horizontal stiffeners and the vertical stiffeners is 10-15mm; the spacing between the two horizontal stiffeners and the spacing L1 between the two vertical stiffeners are both 100-120mm.

6. A lightweight parachute canopy structure for withstanding dual-point asynchronous high-impact ejection loads according to claim 5, characterized in that: Four through holes are respectively set in the middle of the two horizontal stiffeners and two vertical stiffeners of the grid in the middle of the grid structure (3).

7. A lightweight parachute canopy structure for withstanding dual-point asynchronous high-impact ejection loads according to claim 1, characterized in that: The connecting beam (4) at the ejection point includes a portion that exposes the closed skin (1) and a portion that extends into the closed skin (1); wherein, the portion that exposes the closed skin (1) is an isosceles triangular plate structure; the portion that extends into the closed skin (1) includes multiple uniformly placed cavity wall panels; a gap is left between two adjacent cavity wall panels to form a lightweight cavity (2).

8. A lightweight parachute canopy structure for withstanding dual-point asynchronous high-impact ejection loads according to claim 7, characterized in that: The wall thickness of the cavity wall panel is 4-6mm; the gap L2 between two adjacent cavity wall panels is 8-12mm, that is, the width of the lightweight cavity (2) is 8-12mm.

9. A lightweight parachute canopy structure for withstanding dual-point asynchronous high-impact ejection loads according to claim 8, characterized in that: The isosceles triangular plate structure is solid without cavity, and the thickness of the isosceles triangular plate structure is not less than 9mm; the base of the isosceles triangular plate structure is connected to the disk structure, and the width of the base of the isosceles triangular plate structure covers the width of all lightweight cavities (2).

10. A lightweight parachute canopy structure for withstanding dual-point asynchronous high-impact ejection loads according to claim 1, characterized in that: The closed skin (1), the grid structure (3) and the connecting beams (4) at the two ejection points are integrally formed by 3D printing additive manufacturing method, and the whole is tilted at 45° during the manufacturing process.

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