A satellite deployable high-speed collision interception type protective superstructure

Abstract

The present application discloses a satellite deployable high-speed collision blocking type protection superstructure, which relates to the field of satellite protection structures. A bracket is connected to the satellite body, and a guide rail is arranged on the bracket; a protection screen, one end of which is slidably connected to the guide rail and the other end is rotatably connected to the bracket through a winding shaft; a driving deployment structure is connected to the bracket and is used to drive one end of the protection screen to move, so that the protection screen rotates around the winding shaft and unfolds. The in-orbit safety ability of the spacecraft itself is improved.

Description

Technical Field

[0001] The present invention relates to a satellite deployable high-speed collision interception type superstructure and method, in particular to a protective superstructure capable of effectively intercepting non-cooperative targets such as high-speed collision space debris during the in-orbit service of a satellite. Background Art

[0002] With the continuous increase of human space activities, the state of the space environment is deteriorating day by day. A large number of debris existing in space has the characteristics of uncontrollable direction, extremely high speed, irregular volume and large quantity, posing an increasing safety threat to on-orbit spacecraft. It is necessary to use an efficient, deployable and retractable protective structure to improve the space debris impact protection ability of spacecraft to ensure the in-orbit safety of satellites.

[0003] At present, the space debris protection structures mainly include non-deployable or mechanically deployable rigid structures such as single screen, double screen, and multi-screen. The installation position and space of spacecraft are limited. The non-deployable protection structure affects the payload layout and increases the implementation difficulty of thermal control, optical coating, etc. It is not suitable for large-area adoption and is still mainly based on deployable structures. The Whipple protection scheme has a simple structure and a small installation space, but its protection ability is relatively low; the filled Whipple protection scheme captures the debris cloud through the filling layer, and based on protective materials such as metal honeycomb and foam, the protection ability is limited; other multi-layer protection structures have further enhanced protection ability, but the installation space increases and the structure is complex. At the same time, in terms of the reliability of deployment and retraction control and protection application, etc., the semi-rigid structure has certain advantages.

[0004] Based on the three-dimensional variable density superstructure of additive manufacturing, the macroscopic Young's modulus and Poisson's ratio can be adjusted through the design of microscopic cells, and the bearing capacity can be improved on the basis of light weight and high strength, achieving a strong impact resistance ability that traditional honeycomb and foam materials do not have.

[0005] In summary, the traditional space protection structure design cannot take into account high reliability, high performance and light miniaturization. The integrated design of materials and structures based on additive manufacturing and the semi-rigid structure form are effective technical ways to further improve the performance of the protection structure. Summary of the Invention

[0006] The technical problem solved by the present invention is: overcoming the deficiencies of the prior art, providing a satellite deployable high-speed collision interception type protective superstructure to improve the in-orbit safety ability of the spacecraft itself.

[0007] The technical solution of the present invention is:

[0008] A satellite deployable high-speed collision interception type protective superstructure includes:

[0009] A bracket, connected to the satellite body, and a guide rail is arranged on the bracket;

[0010] A protective screen, one end of which is slidably connected to a guide rail and the other end is rotatably connected to a bracket through a winding shaft;

[0011] A driving and unfolding structure, connected to the bracket, for driving one end of the protective screen to move, so that the protective screen rotates around the winding shaft and unfolds.

[0012] The winding shaft is connected with a driving member for driving its own rotation, and the driving member is used to drive the winding shaft to rotate to realize winding the protective screen outside the winding shaft; the driving member is a motor.

[0013] The driving and unfolding structure includes an opening rope and a rope control component for tightening and releasing the opening rope. One end of the opening rope is connected to one end of the protective screen, and is used to drive the end of the protective screen to move along the guide rail to unfold or retract.

[0014] The protective screen includes a fiber mesh and a plurality of protective units uniformly fixed to the fiber mesh. <F

[0015] The protective unit includes a first flexible layer, a capture bottom layer, an energy absorption inner layer, a high-strength surface layer, and a second flexible layer connected in sequence. The first flexible layer is connected to the fiber mesh. When the protective screen unfolds, the second flexible layer is located on the side of the fiber mesh away from the satellite body.

[0016] The energy absorption inner layer is formed by arranging a plurality of superstructure units in sequence.

[0017] The energy absorption inner layer is set with a variable density gradient. Along the direction away from the fiber mesh, the density of the energy absorption inner layer increases; the sizes and distribution densities of the superstructure units included in the energy absorption inner layer with different densities are different.

[0018] The superstructure unit includes a plurality of rod bodies connected, and one or more types of metamaterial units can be used. The arrangement method is designed according to the impact variable of the protection load. The superstructure unit can be selected as body-centered cubic, face-centered cubic, or concave sixteen-sided body, etc. and their deformed structures.

[0019] The flexible layer is a woven Kevlar composite screen; the high-strength surface layer and the capture bottom layer are high-modulus carbon fiber composite materials formed by composite materials; the energy absorption inner layer is an additively manufactured aluminum alloy superstructure unit.

[0020] The distribution spacing of the protective units on the fiber mesh satisfies that there is no ballistic gap between two adjacent protective units.

[0021] In summary, the present application at least includes the following beneficial technical effects:

[0022] (1) The design structure has a lower relative density, meeting the lightweight requirements of the satellite. (2) The deployable structure can be repeatedly deployed and reused, saving costs. (3) Considering the practicality of the process and variable-density adaptive growth, it is beneficial for processing and obtaining high-quality components. Description of the Drawings

[0023] Figure 1 It is a schematic diagram of a deployable and retractable active protection structure.

[0024] Figure 2 It is a schematic diagram of the deployment of a deployable and retractable active protection structure.

[0025] Figure 3 It is a schematic diagram of a semi-rigid deployable protection screen.

[0026] Figure 4 It is a schematic diagram of a protection unit.

[0027] Description of the reference numerals: 1, satellite body; 2, bracket; 3, guide rail; 4, drive deployment structure; 5, protection screen; 6, protection unit; 7, fiber mesh; 8, second flexible layer; 9, high-strength surface layer; 10, energy-absorbing inner layer; 11, capture bottom layer; 12, first flexible layer. Detailed Description of the Embodiment

[0028] The following further describes the present application in detail with reference to the drawings and specific embodiments:

[0029] The embodiment of the present application discloses a deployable high-speed collision interception type protection superstructure for a satellite, as Figures 1-4 shown, including a satellite body 1, a bracket 2, a guide rail 3, a drive deployment structure 4, and a protection screen 5.

[0030] The bracket 2 is connected to the satellite body 1. A guide rail 3 is provided on the bracket 2. One end of the protection screen 5 is slidably connected to the guide rail 3, and the other end is rotatably connected to the bracket 2 through a winding shaft; the drive deployment structure 4 is connected to the bracket 2 and is used to drive one end of the protection screen 5 slidably connected to the bracket 2 to move, so that the protection screen 5 rotates around the winding shaft and unfolds.

[0031] The winding shaft is connected with a driving member for driving its own rotation. The driving member is used to drive the winding shaft to rotate to realize winding the protection screen 5 outside the winding shaft. In this embodiment, the driving member is a motor.

[0032] The drive deployment structure 4 includes an opening rope and a rope control assembly for tensioning and releasing the opening rope. The end of the opening rope is connected to one end of the protective screen 5 which is slidably connected to the guide rail 3, and is used to drive the end of the protective screen 5 to move along the guide rail 3 to be deployed or retracted. In this embodiment, the rope control assembly may include a motor and a winding wheel. The winding wheel is connected to the output shaft of the motor, and the opening rope is wound around the winding wheel. The motor drives the winding wheel to rotate forward or backward to realize the winding and releasing of the opening rope, so that the opening rope can pull the protective screen to open.

[0033] The driving member, the winding shaft and the drive deployment structure 4 cooperate to realize the winding and deployment of the protective screen 5. When the satellite body 1 detects space debris, the drive deployment structure 4 drives the protective screen 5 to deploy. When the satellite body 1 detects that there is no space debris in the current space, the driving member drives the winding shaft to rotate and at the same time the drive deployment structure 4 releases the protective screen 5, and the protective screen 5 is wound up, realizing the winding and deployment of the protective screen 5 based on the kinetic energy distribution of space debris.

[0034] The protective screen 5 includes a fiber mesh 7 and a plurality of protection units 6. The plurality of protection units 6 are uniformly fixed to the fiber mesh 7, and the distribution spacing of the protection units 6 on the fiber mesh 7 satisfies that there is no ballistic gap between two adjacent protection units 6.

[0035] The protection unit 6 includes a first flexible layer 12, a capture bottom layer 11, an energy absorption inner layer 10, a high-strength surface layer 9, and a second flexible layer 8 arranged in sequence. The first flexible layer 12 is adhesively connected to the fiber mesh 7. When the protective screen 5 is deployed, the second flexible layer 8 is located on the side of the fiber mesh 7 away from the satellite body 1. The energy absorption inner layer 10 is formed by arranging a plurality of superstructural units in sequence. The energy absorption inner layer 10 is set with a variable density gradient. Along the direction away from the fiber mesh 7, the density of the energy absorption inner layer 10 increases; the sizes and distribution densities of the superstructural units included in the energy absorption inner layer 10 with different densities are different.

[0036] The superstructural unit includes a connection of a plurality of rod bodies, and one or more types of metamaterial units can be adopted. The arrangement method is designed according to the impact variable of the protection load. The superstructural unit can be selected as a body-centered cubic, a face-centered cubic, or an inwardly concave hexahedron and its deformed structure.

[0037] In this embodiment, the flexible layer is a woven Kevlar composite screen; the high-strength surface layer 9 and the capture bottom layer 11 are high-modulus carbon fiber composites formed by composite materials; the energy absorption inner layer 10 is an additively manufactured aluminum alloy superstructural unit. The structure of the aluminum alloy superstructural unit in this embodiment is: a body-centered cubic unit with a unit size of 7.5 mm, which is integrally formed by two parts of variable density units, and the size of the high-density unit is 3.75 mm.

[0038] An additive design and implementation method for a satellite deployable high-speed collision interception type protection superstructure includes:

[0039] Step 1: Carry out the macro-micro integrated additive manufacturing superstructure design with high energy absorption ratio by integrating multiple disciplines such as structural mechanics, dynamics, and composite materials.

[0040] Step 2: Use the finite element analysis method to optimize the three-dimensional variable density buffer energy absorption protection layer, conduct the optimization design of the high-speed collision crushing layer of various composite materials, design the structure of the high-speed anti-collision protection unit 6, and design the connection combination method without ballistic gaps.

[0041] Step 3: Carry out the scheme design and optimization of the repeatable deployment and retraction mechanism of the semi-rigid protection screen 5.

[0042] Step 4: According to the different protection requirements of the flexible layer, high-strength surface, energy absorption inner layer 10, and capture bottom layer 11 of the high-speed collision protection structure, select the woven Kevlar composite screen for the flexible layer, select the high-modulus carbon fiber composite material formed by composite materials for the high-strength surface layer 9 and the capture bottom layer 11, and use the additive manufacturing aluminum alloy superstructure filling unit for the energy absorption inner layer 10 to conduct the integrated protection structure design of the semi-rigid and multi-material body composite materials.

[0043] Step 5: Use the ground high-speed impact test device to conduct the high-speed impact test of the protection structure unit and the protection structure panel, and evaluate the reliability of the protection structure unit and the protection panel against high-speed particle impact in space.

[0044] The content not described in detail in the specification of the present invention belongs to the well-known technology of those skilled in the art.

[0045] Although the present invention is disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, the protection scope of the present invention should be determined by the scope defined by the claims of the present invention.

Claims

1. A satellite deployable high-speed collision arrest type protection superstructure, characterized in that, Comprising: A bracket (2), connected to the satellite body (1), and a guide rail (3) is provided on the bracket (2); A protective screen (5), one end of which is slidably connected to the guide rail (3) and the other end of which is rotatably connected to the bracket (2) through a winding shaft; A driving and deploying structure (4), connected to the bracket (2), for driving one end of the protective screen (5) to move, so that the protective screen (5) rotates around the winding shaft and unfolds; The protective screen (5) includes a fiber mesh (7) and a plurality of protective units (6) uniformly fixed to the fiber mesh (7); The protective unit (6) includes a first flexible layer (12), a capture bottom layer (11), an energy absorption inner layer (10), a high-strength surface layer (9), and a second flexible layer (8) connected in sequence. The first flexible layer (12) is connected to the fiber mesh (7). When the protective screen (5) unfolds, the second flexible layer (8) is located on the side of the fiber mesh (7) away from the satellite body (1); The energy absorption inner layer (10) includes a plurality of superstructure units arranged in sequence; The energy absorption inner layer (10) is provided with a variable density gradient. Along the direction away from the fiber mesh (7), the density of the energy absorption inner layer (10) increases; the sizes and distribution densities of the superstructure units included in the energy absorption inner layer (10) with different densities are different.

2. The deployable high-speed impact arresting protection superstructure for a satellite according to claim 1, wherein: The winding shaft is connected with a driving member for driving its own rotation, and the driving member is used for driving the winding shaft to rotate to wind the protective screen (5) outside the winding shaft.

3. The deployable high-speed impact arresting and protecting superstructure for a satellite according to claim 1, characterized in that: The driving and deploying structure (4) includes an opening rope and a rope control assembly for tensioning and releasing the opening rope. One end of the opening rope is connected to one end of the protective screen (5) for driving the end of the protective screen (5) to move along the guide rail (3) to unfold or retract.

4. The deployable high-speed impact arresting protection superstructure for a satellite according to claim 1, characterized in that: The superstructure unit includes a connection of a plurality of rod bodies, adopts one or more types of metamaterial units, and the arrangement mode is designed according to the impact variable of the protection load. The superstructure unit is a body-centered cubic, face-centered cubic, or concave sixteen-sided body and its deformed structure.

5. A deployable high-speed collision arrest protection superstructure for a satellite according to claim 1, characterized in that: The first flexible layer (12) and the second flexible layer (8) are woven and formed Kevlar composite screens; the high-strength surface layer (9) and the capture bottom layer (11) are high-modulus carbon fiber composite materials formed by composite materials; the energy absorption inner layer (10) is an additively manufactured aluminum alloy superstructure unit.

6. The satellite deployable high-speed collision arrest type protection superstructure according to claim 1, characterized in that: The distribution spacing of the protective units (6) on the fiber mesh (7) satisfies that there is no ballistic gap between two adjacent protective units (6).

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