A large, lightweight, deformable protective shield for on-orbit spacecraft

Abstract

This application belongs to the field of on-orbit spacecraft technology and relates to a large, lightweight deformable protective shield for on-orbit spacecraft. It consists of a push rod base, a deployment push rod, a base, a deployment arm, a telescopic push rod, a protective fabric, a telescopic arm, a crank, and a drive pin. The deployment arm and telescopic arm adopt a frame structure and have weight-reduction holes. The protective shield has a simple and compact structure, few transmission paths, and high overall reliability. It is controlled by a servo motor, providing high control precision and enabling remote or remote sensing control. When the protective shield is deployed, it can effectively protect the on-orbit spacecraft, avoiding or mitigating impacts from space debris.

Description

Technical Field

[0001] This application belongs to the field of on-orbit spacecraft technology and relates to a large, lightweight deformable protective shield for on-orbit spacecraft. Background Technology

[0002] The space environment in which spacecraft operate is deteriorating with the increasing frequency of space activities. Space debris impacts spacecraft at speeds of kilometers per second, posing a huge threat to the reliability and safety of spacecraft. However, there is no effective way to block space debris in the current technology. Utility Model Content

[0003] According to one aspect of this application, a large, lightweight, deformable protective shield for an on-orbit spacecraft is provided, comprising a push rod seat, a deployable push rod, a base, a deployable arm, a telescopic push rod, a protective cloth, a telescopic arm, a crank, and a drive pin.

[0004] The deployable arm and telescopic arm adopt a frame structure and have weight-reducing holes.

[0005] Optionally, the deployable arm and telescopic arm are made of aluminum alloy.

[0006] Optionally, the push rod seat is equipped with a plurality of deployable push rods;

[0007] The base is installed above the push rod seat;

[0008] The base is equipped with multiple deployable arms;

[0009] The fixed end of the telescopic push rod is installed inside the unfolding arm, and the movable lead screw is installed on the telescopic arm;

[0010] The protective fabric is installed on the deploying arm and telescopic arm via hooks.

[0011] Optionally, the movable lead screw of the deployment push rod is connected to the crank, and the crank, base, and deployment arm are connected by a drive pin. The deformable protective shield of the on-orbit spacecraft is configured such that: the movable lead screw of the deployment push rod extends and drives the deployment arm to rotate around the pin through the crank, thereby realizing the deployment action of the deployment arm; conversely, the movable lead screw of the deployment push rod retracts and drives the deployment arm to rotate around the pin through the crank, thereby realizing the retraction action of the deployment arm.

[0012] The extension and retraction of the movable lead screw of the unfolding push rod are achieved by its own servo motor. After it is extended or retracted into place, it is braked by the brake of the unfolding push rod and kept in the current position.

[0013] The fixed end of the telescopic push rod is installed inside the extended arm. The movable screw of the telescopic push rod is connected to the telescopic arm through a pin. Rollers are installed on the upper, lower, left, and right sides of the telescopic arm. When the movable screw of the telescopic push rod extends, it drives the telescopic arm to extend. When the movable screw of the telescopic push rod retracts, it drives the telescopic arm to retract.

[0014] The extension and retraction of the movable lead screw of the telescopic push rod are achieved by its own servo motor. After the extension or retraction is completed, the brake of the telescopic push rod is used to brake and maintain the current position.

[0015] Optionally, the deploying push rod has three or more components;

[0016] The deployable arm has three or more.

[0017] The advantages of this application are:

[0018] The protective shield boasts a simple and compact structure with minimal transmission paths, resulting in high overall reliability. It employs servo motor control, ensuring high precision and enabling remote or telesensor control. When deployed, the shield effectively protects spacecraft in orbit, preventing or mitigating impacts from space debris. Attached Figure Description

[0019] Figure 1 Schematic diagram of a deformable protective shield structure for an in-orbit spacecraft.

[0020] Figure 2 Schematic diagram of the deployable arm and telescopic arm structure.

[0021] Figure 3 A schematic diagram of the deployment of a deformable protective shield on an in-orbit spacecraft.

[0022] Among them, 1-push rod seat; 2-expanding push rod; 3-base; 4-expanding arm; 5-telescopic push rod; 6-protective cloth; 7-telescopic arm; 8-crank; 9-drive pin; 21-first motor; 22-first movable lead screw; 51-second motor. Detailed Implementation

[0023] The present application is described in detail below with reference to the embodiments, but the present application is not limited to these embodiments.

[0024] Example 1

[0025] A large, lightweight, deformable protective shield for on-orbit spacecraft mainly consists of a push rod seat 1, a deployable push rod 2, a base 3, a deployable arm 4, a telescopic push rod 5, a protective cloth 6, a telescopic arm 7, a crank 8, and a drive pin 9.

[0026] The protective shield has an extended length greater than 5m and an extended area greater than 15m², classifying it as an ultra-large protective device. Simultaneously, the shield needs to be lightweight; therefore, the main load-bearing structures, the deployable arm 4 and the telescopic arm 7, adopt a frame structure. Both feature weight-reduction holes. The structural form after topology optimization is shown in [see attached image]. Figure 2 Both the deployable arm 4 and the telescopic arm 7 employ triangular weight-reduction holes, with alternating equilateral and inverted triangles, to minimize the weight of the protective shield while ensuring the load-bearing capacity of the main structure. The materials used for the deployable arm 4 and the telescopic arm 7 follow the principle of "high strength + low density," employing high-strength aluminum alloy to further reduce the weight of the protective shield.

[0027] The deployable arm 4 and telescopic arm 7 are made of high-strength aluminum alloy.

[0028] The push rod seat 1 serves as the mounting base for the unfolding push rod 2, and multiple unfolding push rods 2 are mounted on it. Taking four unfolding push rods 2 as an example.

[0029] The push rod seat 1 is also the mounting base of the base 3, and the base 3 is installed above the push rod seat 1;

[0030] The base 3 serves as the mounting base for the deployable arms 4, and multiple deployable arms 4 are mounted on it. Taking four deployable arms 4 as an example.

[0031] The unfolding arm 4 serves as the mounting base for the telescopic push rod 5. The fixed end of the telescopic push rod 5 is installed inside the unfolding arm 4, and the movable end of the telescopic push rod 5 is installed on the telescopic arm 7. Specifically, the telescopic push rod 5 includes a motor and a nut (not shown in the figure) connected to the motor for transmission. The nut is threadedly connected to a movable lead screw, the end of which is installed on the telescopic arm 7. The nut cannot move axially, only rotate, while the movable lead screw cannot rotate, only move axially. Thus, when the motor output shaft rotates, it synchronously drives the nut to rotate, and the movable lead screw rotates relative to the nut, thereby causing the movable lead screw to move axially, achieving extension and retraction, and driving the telescopic arm to unfold or retract. In this embodiment, the transmission connection between the motor output shaft and the nut can be gear meshing, belt drive, or chain drive, etc., as long as it can achieve the rotational drive of the nut; no limitation is made here. Figure 3 As shown, the motor is named the second motor 51, and the movable lead screw is named the second movable lead screw (not shown in the figure).

[0032] The protective cloth 6 is installed by hooks on the deploying arm 4 and the telescopic arm 7. That is, hooks are provided on both the deploying arm 4 and the telescopic arm 7, and the protective cloth 6 is installed on the deploying arm 4 and the telescopic arm 7 by the hooks.

[0033] The large, lightweight, deformable protective shield of the spacecraft in orbit is capable of both deployment and extension.

[0034] The unfolding action is achieved by the unfolding push rod 2. The unfolding push rod 2 can adopt the same structural features as the telescopic push rod 5. That is, the unfolding push rod 2 includes a motor and a nut (not shown in the figure) connected to the motor. The nut is threadedly connected to a movable lead screw, the end of which is mounted on the crank 8. The nut cannot move axially, only rotate, and the movable lead screw cannot rotate, only move axially. Thus, when the motor output shaft rotates, it synchronously drives the nut to rotate, and the movable lead screw rotates relative to the nut, thereby causing the movable lead screw to move axially, achieving extension and retraction, and driving the crank to move (oscillate). In this embodiment, the transmission connection between the motor output shaft and the nut can be gear meshing, belt drive, or chain drive, etc., as long as it can achieve the rotational drive of the nut; no limitation is made here. This motor is named the first motor 21, and the movable lead screw is named the first movable lead screw 22.

[0035] In this embodiment, the movable lead screw of the unfolding push rod 2 is connected to the crank 8. The crank 8, the base 3, and the unfolding arm 4 are connected by a drive pin 9. Specifically, one end of the crank 8 is rotatably connected to the end of the movable lead screw, and the other end is rotatably connected to the base 3 by the pin 9. The pin 9 is rotatably connected to the base 3 and is fixedly connected to the unfolding arm 4 and the other end of the crank 8, thereby achieving a relatively fixed connection between the crank 8 and the unfolding arm 4. The two rotate synchronously, that is, the crank 8 drives the unfolding arm 4 to rotate relative to the base 3, thereby realizing the opening and closing of the unfolding arm.

[0036] When the movable lead screw of the unfolding push rod 2 extends, it drives the unfolding arm 4 to rotate axially around the pin 9 via the crank 8, thereby realizing the unfolding action of the unfolding arm 4. Conversely, when the movable lead screw of the unfolding push rod 2 retracts, it drives the unfolding arm 4 to rotate axially around the pin 9 via the crank 8, thereby realizing the retraction action of the unfolding arm 4.

[0037] The extension and retraction of the movable lead screw of the unfolding push rod 2 are achieved by its own servo motor. After it is extended or retracted into place, the brake of the unfolding push rod 2 is used to brake and maintain the current position. It should be noted that the brake here can adopt a mature setting method in the existing technology, and is not limited here.

[0038] As the deploying arm 4 unfolds and the telescopic arm 7 extends, the protective cloth 6 is stretched open, and the protective shield is in the open state to protect the spacecraft in orbit.

[0039] The extension action is achieved by telescopic push rod 5. The fixed end of telescopic push rod 5 is installed inside the unfolding arm 4. The movable screw of telescopic push rod 5 is connected to the telescopic arm 7 by a pin. A certain number of rollers are installed on the upper, lower, left, and right sides of the telescopic arm 7. When the movable screw of telescopic push rod 5 extends, it drives the telescopic arm 7 to extend. When the movable screw of telescopic push rod 5 retracts, it drives the telescopic arm 7 to retract. The rollers installed on the four sides of the telescopic arm 7 roll inside the unfolding arm 4, resulting in low friction and reducing the work done by telescopic push rod 5, which is beneficial for installation inside the unfolding arm 4.

[0040] The extension and retraction of the movable lead screw of the telescopic push rod 5 are achieved by its built-in servo motor. After being extended or retracted to the correct position, the telescopic push rod 5 is braked by its built-in brake to maintain the current position. It should be noted that the brake here can adopt a mature setting method of existing technology, and is not limited here.

[0041] As the above analysis shows, deformable protective shields for on-orbit spacecraft can block or mitigate space debris, preventing structural damage and critical component failure caused by impacts. These shields are an active space debris protection mechanism that can replace traditional external passive protection mechanisms or serve as a supplement to them. Applying deformable shields can significantly enhance the operational safety of on-orbit spacecraft, thereby extending their lifespan. The deformable protective shield mechanism must be lightweight, minimizing its own weight to reduce launch costs and increase the effective payload ratio while ensuring structural safety, functional compliance, and adaptability to the extreme space environment.

[0042] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any modifications or substitutions made by those skilled in the art within the scope of the technology disclosed in this application should be covered within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A large, lightweight, deformable protective shield for on-orbit spacecraft, characterized in that, It consists of a push rod seat (1), an unfolding push rod (2), a base (3), an unfolding arm (4), a telescopic push rod (5), a protective cloth (6), a telescopic arm (7), a crank (8), and a drive pin (9); The deployable arm (4) and telescopic arm (7) adopt a frame structure and have weight reduction holes.

2. The large, lightweight, deformable protective shield for on-orbit spacecraft according to claim 1, characterized in that, The deployable arm (4) and telescopic arm (7) are made of high-strength aluminum alloy.

3. The large, lightweight, deformable protective shield for on-orbit spacecraft according to claim 1, characterized in that, The push rod seat (1) is equipped with multiple unfolding push rods (2); The base (3) is installed above the push rod seat (1); The base (3) is equipped with multiple deployable arms (4); The fixed end of the telescopic push rod (5) is installed inside the unfolding arm (4), and the movable screw is installed on the telescopic arm (7); The protective cloth (6) is installed on the unfolding arm (4) and the telescopic arm (7) by hooks.

4. The large, lightweight, deformable protective shield for on-orbit spacecraft according to claim 3, characterized in that, The movable lead screw of the deployment push rod (2) is connected to the crank (8), and the crank (8), the base (3), and the deployment arm (4) are connected by the drive pin (9). The deformable protective shield of the on-orbit spacecraft is configured such that the movable lead screw of the deployment push rod (2) extends and drives the deployment arm (4) to rotate around the pin through the crank (8), thereby realizing the deployment action of the deployment arm (4). Conversely, the movable lead screw of the deployment push rod (2) retracts. The extension and retraction of the movable screw of the unfolding push rod (2) are achieved by its own servo motor. After it is extended or retracted into place, it is braked by the brake of the unfolding push rod (2) and kept in the current position. The fixed end of the telescopic push rod (5) is installed inside the unfolding arm (4). The movable screw of the telescopic push rod (5) is connected to the telescopic arm (7) through a pin. Rollers are installed on the upper, lower, left and right sides of the telescopic arm (7). When the movable screw of the telescopic push rod (5) extends, it drives the telescopic arm (7) to extend. When the movable screw of the telescopic push rod (5) retracts, it drives the telescopic arm (7) to retract. The extension and retraction of the movable screw of the telescopic push rod (5) is achieved by its own servo motor. After it is extended or retracted into place, it is braked by the brake of the telescopic push rod (5) and kept in the current position.

5. The deformable protective shield for on-orbit spacecraft according to claim 3, characterized in that, The deploying push rod (2) has three or more; The deployable arm (4) has more than three.

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